Mars Society International StudentDesign Competition

Team Russia

2014

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Contents

1 Introduction 2

2 Onboard systems 32.1 Construction and composition of the spacecraft . . . . . . . . . . . . . . . . 32.2 Motion and navigation control system . . . . . . . . . . . . . . . . . . . . . . 42.3 Communication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82.4 Life support system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92.5 Thermal regulation system . . . . . . . . . . . . . . . . . . . . . . . . . . . . 132.6 Onboard computer system . . . . . . . . . . . . . . . . . . . . . . . . . . . . 162.7 The power system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 182.8 Protection against radiation . . . . . . . . . . . . . . . . . . . . . . . . . . . 192.9 Medical training and medical briefing . . . . . . . . . . . . . . . . . . . . . . 202.10 Materials for the crew . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

3 Mass analysis 25

4 Leading out process and Ballistics 264.1 Leading out process . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 264.2 Ballistics and flight path . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

5 Scientific experiments 355.1 Medical and biological experiments . . . . . . . . . . . . . . . . . . . . . . . 355.2 Other experiments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

6 Quick start guide 41

7 Mission control center 42

8 The cost of the mission 44

9 Conclusion 45

10 Sources: 46

11 Team 47

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1 Introduction

The beginning of 2013 was marked with a bright event. First space tourist and multimillion-aire Dennis Tito established Inspiration Mars Foundation to send a spaceship to Mars witha crew of two people in 2018. Despite the fact that only a flyby mission without landingon surface of The Red Planet is planned, such a brave initiative could not have passed byunnoticed. Pioneers of cosmonautics in Russia, (USSR back then), such as Friedrich Zanderand Sergei Korolev, used to dream of flights to Mars. Works on engineering an interplane-tary Martian spaceship were already held in 60’s of the last century. Forseeing the problemsawaiting humans on their way to Mars, Korolev initiated development of closed ecosystems(which later turned into a successful experiment BIOS-3), and researches in long-time isola-tion of people in a confined space in the Institute of Biomedical Problems (IBMP).

In today’s Russia there is no project of manned mission to Mars. Unfortunately, since endof 80’s Russia didn’t even have any successful automatic missions to The Red Planet. Stillsome standalone experiments are carried out, primarily associated with accommodation andwork of a crew of future expeditions. So in 2011-2012 in IBMP an experiment Mars-500 washeld, modelling a 520-day expedition to Mars with crew of 6 people. Experiments on testingcosmonauts operability after a long flight in weightlessness were held in Gagarin Research &Test Cosmonaut Training Centre, in cooperation with Korolev Rocket & Space Corporation”Energia”. Cosmonauts who returned after a half-year flight to ISS simulated both workingin space suite on a surface of a planet and operating a descending space ship in a centrifugeright after flight from Kazakhstan to Moscow. These experiments proved thatcosmonautsare capable of working during the landing and after it in spite of a long stay in weightlessness.

Nowadays Russian enthusiasts of cosmonautics are looking forward to some serious re-search on behalf of future expedition to Mars. That is why Dennis Tito’s initiative attractseveryone’s keen attention. What seems to be of even greater interest is the opportunity toparticipate in initial design of flyby mission provided by Mars Society International StudentDesign Competition.A significant number of Russian students decided to take part in the competition, me andmy teammates among them. It took quite a time to gather our team as we have students andgraduates from six Russian universities and three different cities - Moscow, St-Petersburgand Voronezh - as well as one Russian student from Austrian university. The one thing thatunites us is the space dream of humans flying further than a low-earth orbit, and we believefirmly that a manned mission planned by Tito will play a big part in future humanity’s spaceexpansion.

The flight to Mars will help us to overcome the fear of perils that await us on the wayof long-distance expeditions between planets. It will demonstrate us effectiveness of existingand developing ways of preventing harmful effect of weightlessness and space radiation. Andabove all, as a result of such a flyby, the humanity will obtain almost all technologies that arenecessary for a full Martian mission with landing on the planet. A heavy-lift launch system,living module and atmospheric entry from an interplanetary trajectory will be developedduring the project.

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Our goal in this work is to show what existing Russian sources could be used for a fullflight. It is useful to keep in mind that since 2011 Russian Federation is the only countryexecuting regular delivery of international crews to the ISS. The results of our workare rep-resented in this report.

2 Onboard systems

2.1 Construction and composition of the spacecraft

Interplanetary manned spacecraft that we suggest to use for the flyby mission Mars 2018may be created on the basis of previously proved and worked-out solutions.

We take modified European cargo spaceship ATV as the main living and working module.The engineers of ATV have left the groundwork for modifications considering the possibilityof using it for manned missions. There are control, power and life support systems etc. in-side ATV while heat exchangers and coolers of thermal regulation system are outside. Alsowe have chosen Russian descent capsule used with Soyuz -TMA for crew delivery to Earth.Surely, we couldn’t choose the descent capsule which is now in use for crew delivery from ISSbecause it demands set of modifications. The possibility of modification of descent capsulewe choose for the tourist flyby Moon mission was worked-out in ”RSC Energia” before. Alsothere was suggested to use a modified heat shield for the passing through the atmosphere onthe escape velocity on the way back that will allow reducing the speed safely. Besides space-craft Soyuz has been already used in XX century for the Moon flyby missions in unmannedmode and with living beings onboard.

During our mission the descent capsule will be also used as the radiation hideout. Forthis reason it is surrounded with the flue and water tanks. This construction is equippedwith pyrotechnic devices for undocking before the entrance to the atmosphere. There aresolar panels outside the toroidal protection with tanks. The propulsion system (used onATV in standard mode) is situated on the butt of the descent capsule. The docking andobserve compartment with active and passive docking adapters and observe dome with anopening lid is used for delivery the crew onboard, docking with space tugs and for the Spaceand Mars visual observation during the mission.

The general construction and composition of the IMS is shown on the picture below.

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1. Inhabited compartment2. Descent capsule3. Docking and observe compartment4. External flue and water tanks5. The propulsion system6. Solar panels7. Heat shield8. Active docking adapter9. Passive docking adapter10. Observe dome

Continuation of the text in Annex

2.2 Motion and navigation control system

Motion and navigation control system (MNCS) of the ship interacts with the system of theequipment control onboard (SECO) which receives information from the sensor equipmentand transmits commands to the executive members. In addition, MNCS communicates withthe onboard computer system (OCS) to make decisions on the motion of the ship. OCS alsoreceives signals from themissioncontrol center (MCC). MNCS, OCS and SECOall togetherform the control system onboard (CSO).OCS is a computer with real-time operating system (OS), coupled witha terminal by thebus, in which the crew can input commands. Job of OS is based on ”modal” approach: the

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ship during the flight goes from one mode to another, thus changing algorithms of OCS anda controlled equipment set. Each mode provides a set of functions. Each function exists tomanage certain set of parameters that need to take prescribed values within the margin oferror. In all modes, the first priority is to maintain the function of the required parametersof LSS. Furthermore, each mode has its own specific function.

Basic modes:

1. Standard mode - passive flight and maintenance of orientation. Key features:- Determination of the direction of the Sun (solar cells) and the Earth (for antenna connec-tion) and maintain triaxial orientation;- If necessary - gyrodines unloading;- Conducting scientific experiments;- Conducting the test instruments and systems checks.

2. Acceleration and orbit correction - giving impulse in the right direction. Key features:- The orientation of the ship in the right direction;- Issuing corrective impulse desired value;- A return to the standard orientation to the Sun and the Earth.

3. Docking, undocking, redocking. Key features:- Docking with boosters;- Docking with the transport ship ”Union”;- Decoupling the return module.

4. Rescue the crew. Key features:- Go to the quickest path back to Earth;- Decoupling the recovery module.

In stage of the leading out process switching between the modes goes by applying signalsfrom the MCC in real time. In later stages, modes 2 and 3 are included in the certainmoments of time specified program of MCC or manually from the terminal. The rest ofthetime the ship is in Mode 1. Mode 4 is turned on automatically when it is impossible toperform critical functions, or manually from the terminal. When you manually switch toanother mode orat the command of the team from MCC,OCS checks readiness to transitionin different mode, and in case all of the systems are ready, asks for confirmation. If theconfirmation comes in one minute, theregime changes.

System condition monitoringis carried out on three levels:1. Instrument level.2. Functional level.3. Modes level.

On the instrument level it retrieves information from devices and control equipment. Ifa device fails, it isreplaced with a duplicate. If all duplicate devices fail, an error message

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istransmitted to the functional level. At the functional level, the OCSmust execute the func-tions to be performed in this mode. If the function cannot be executed, an error messageis transmitted to the modes level where this function either is replaced to perform otherfunctions, or the ship enters the rescue the crew mode.

While calculating coordinates and orientation the following coordinate system is used:1. Associated with the vehicle coordinate system.2. Reference coordinate system associated with the celestial bodies:- Geocentric equatorial coordinate system: the origin - in the center of the Earth axis di-rected to the vernal equinox and the north pole of the Earth;- Geocentric ecliptic coordinate system: the origin - in the center of the Earth axis directedto the vernal equinox and the north pole of the ecliptic;- Heliocentric ecliptic coordinate system: the origin - in the center of the Sun, axes areoriented the same way;- Areocentric ecliptic coordinate system: the origin - in the center of Mars, the axes areoriented the same way.

The transition from one coordinate system to another is performed by rotating and shift-ing. Rotation can be described in several ways:- With an orthogonal rotation matrix (9 component coordinate transformation - linear);- Using normalized quaternion (4 components, coordinate transformation - square);- Using Euler angles or Krylov corners (3 angles , coordinate transformation - for complextrigonometric formulas).

Representation turns with the aid of a quaternion is quite simple and computationallystable, so they are usually used to describe the rotation in an arbitrary coordinate system.Two successive rotation quaternions are describedby the productof them,a turn in the op-posite direction -by the inverse quaternion. Coordinates of the Sun, Earth and Mars andquaternions linking reference coordinate systems are calculated by the model DE405/LE405for epoch J2000.Thus, to determine coordinates and orientation of the ship in any coordinate system is suf-ficient to determine the position and orientation of the ship in one of the systems, and thenperform the rotation and shift of the coordinates. To impart a predetermined orientationLto the ship in a predetermined coordinate system, one need to define the ship’sorientationL0 0 in the system and define the quaternion of transition to the required of orientation W= L0 - 1L. Quaternion W defines the axis around which it is necessary to turn the ship, andthe rotation angle.Knowing the axis, the rotation angle and the approximate ship inertia tensor (the exact iner-tia tensor cannot be determined because the objects and the crew can move inside the ship),OCS counts the pulses for theorientationengines, direction and speed of rotationofgyrodinescorrecting calculations as the orientation changes.If the known ship position is x0, its speed is v0 and the rotation quaternion L0 at time t0, itis possible, knowing the acceleration a(t) and the angular velocity w(t) at each time point,to determine the coordinates x(t), velocity v(t ) and a quaternion rotation L(t) at any time.Acceleration and angular velocity determines the inertial navigation system, consisting of

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accelerometers and angular rate sensors respectively.To determine the x(t) and v(t)it is necessary to integrate a simple linear system of differentialequations. This system is stable, so an uncertaintyofthe position, velocity and rotation isproportional to the measurement inaccuracy of the initial parameters x0, v0, L0. But at thesame time, it increases with the error caused by inaccurate determination of a(t) and w(t).For velocity and rotation this error is proportional to elapsed time (t - t0), coordinates - thesquare of the time (t – t0)2.So you need to periodically adjust readings of inertial navigation system using other meansof navigation. Orientation can beidentified by the stars quite accurate. If the star sensoris out of action, one can use a solar sensor to determine at least the direction toward theSun for the correct orientation of the solar panels. To determine the coordinates of the shipin the geocentric system onecan use radionavigation or an optical sensor of Earth’s horizon,but their accuracy decreases in sync with the distance from the Earth, so that they areunsuitablefor correction near Mars. To determine the coordinates in areocentric systemonecan use the optical sensorof horizon of Mars. Finally, for sufficiently rough positioning ina heliocentric system, onecan use the same stellar sensor, determining the direction towardthe planets - 2 planets are enough to determine the coordinates.Thus, MNCSis required to have:

1. Board control:- Central computer OCS - bus-modular system, similar to those used on the ISS: 5.85 kgweight, power consumption 40W, standard bus-modular system (4U) has dimensions of ap-proximately 50x30x20 cm. For reliability you need 3 identical computer: ”the main” -working; backup - backup, in the ”hot” reserve, and replacement - in the ”cold” provision,i.e. off. Possible to improve the reliability and efficiency need to add the computers thatcontrol subsystems: Coolant, Ships , etc.- MIL 1553B bus standard for connecting peripherals with the UA;- OCS interfaces with hardware, one coupling device has a mass of 6.45 kg and consumes 24watts, the ISS has 23 interfaces , but we probably need less.- Terminal - the usual Laptop (notebook) with the operating system Linux. Dimensions -approx 30x20x5 cm, weight - about 3 kg.

2. Strapdown inertial system (SINS), consisting of:- Accelerometers: developed devices to within 0.000001g, the size of about 5 cm and weighingnot more than 200 g- Gyro meter angular velocity ( GIVUS ) Accuracy 3.6”/h, power 75 W, diameter 30 cm,weight 12 kg.

3. Automatic optical sensors:- Solar sensor (SD) 251K2: Accuracy 3 ’, 6.5 W power consumption, weight 3 kg;- Block positioning stars (BOKZ) for AMC ”Phobos-Grunt ”designed device with an accu-racy of 0.5”, 2 kg, power consumption 8 W; BOKZ dimensions - about 20x10x20 cm- Optical horizonSensors: AMC for ”Phobos-Grunt” developed wide television camera (TCS)with a field of view of 23 degrees, weighing 1.6 kg, power consumption 8W and narrow-angletelevision camera (UTC) with a field of view of 0.85 degrees, up 3” weight 2.8 kg. Thus,

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the first TCS finds the sky Mars or Earth, then UGC directed to that part of the sky anddetermines the direction of the planet and its angular size more accurately. Resolution ofUGC allows to ”aim” at Mars accurate to 8 km from a distance of 500 km away (radius ofthe sphere of action of Mars) and to ”aim” at the Earth accurate to 13 km from a distanceof 900 km away (radius of the sphere of action of the Earth).

4. Onboard equipment for navigation. To determine the position and velocity, knowingthe orientation, a single antenna is enough: the distance from the Earth is determined by thedelay of the signal, relative velocity -bythe Doppler Effect. For backup we use 2 antennas.It is possible to use the same antennas whichare used for communication. If they take theirsignals from the Deep Space Network, it can be navigation signals. Thedistance from Earthwas ensured accurate within about 3 km speed and within about 2 m/s for the Mars ScienceLaboratory mission in the same way.

5. Engines orientation (DO) - 24 pieces (3 axes of rotation, 2 pairs of engines on eachaxle, each engine is duplicated).

6. Gyrodine - 4 pieces (3 support orientation 3 perpendicular axes, one in reserve). Theirsize and weight can be determined on the basis of similarity to the ISS. Martian ship issimilar to the ISS in terms of the requirements for orientation and change of orientation (italso makes one revolution around the Sun per year). At the same time the ISS weighs 400tons, and the ship - 16 tons, that is 25 times smaller. 4 gyrodine ISS weigh about 1 ton,then 4 gyrodine the ship should weigh about 40 kg. Each gyrodine ISS takes 95x74x71 cmand consumes a maximum of 470 W, thenevery gyrodine will take about 32x25x25 cm onthe ship and consume about 20 watts. In the absence of gyrodines ISS orientation spends12 kg of fuel per day. It means, a ship without gyrodines in 500 days will spend 240 kg offuel on the orientation flight. Consequently, gyrodines can save 200 kg.

7. Automatic docking system “Course MM”: measures the relative motion in the conicalsector with an angle of 15 degrees at a distance of 1 km before docking. Power consumptionis 30W, weight 14.8 kg.

2.3 Communication

A communication system need for exchanging information between spaceship and terrestrialpoints of communication.

The system provides:- transmission of telemetric information about the status of all spaceships’s systems- receive commands to control onboard systems from Earth- receive/transmission telephone information- receive/transmission photo/video - information

The communication system operates in the following modes:

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- standby (receive work)- session - mode (work on to receiver/transmitter of information)

The structure of the communication system includes:- Antenna-feeder device- transmitter’s module- receiver’s module- decoders- information exchanging device- onboard cable network.

Antenna-feeder device includes two antennas:a) 2 omnidirectional antennas as like as antennas Service Module of the ISS. 1 kg weight.These antenna will operate when the spaceship will be on Earth’s orbit and on near withEarth zone of passage trackb) high gain antenna with a diameter of 2 m. Data will be transmitted with a speed of 550kbit/s. Antenna weight 20 kg. Selected from the foreign analogue AFS used on interplane-tary spacecraft MAVEN.

This antenna will operate at the far part of the orbit flight.To improve the accuracy and reliability of information transmitting, t must be directed sothat the major axis was oriented determinably on Earth induring a session mode.If the antenna will be included in the work on near the Earth, there will be considerablewaste of fuel for constant orientation of the complex.In case of failure of the main sets of transmitters and receivers, the second and third set oftransmitters and receivers always will be in cold mode reserve.

Continuation of the text in Annex

2.4 Life support system

Manned Mars circling flight is unthinkable without life support systems (LSS), which is oneof the most important systems onboard the spaceship, as it affects the lives of the crew. Todate we have accumulated a rich experience in the creation of the Earth environment in aconfined space suitable for human life. Including the time exceeding the years of continuousflight, for example, as on the International Space Station (ISS) and the orbital station ”Mir”.As the basis of our mission to circle overflight Mars we decided to take the basic system usedon the Russian segment of the ISS. These advantages include: the use of long-term mannedstations, maintainability and low price with respect to the existing analogue.Selected LSS must meet the requirements to maintain minimum conditions, without whichlife is not conceivable for the astronauts aboard: provide oxygen, water and nutrients, removecarbon dioxide and other products and slag separation of a person in liquid, solid or gaseousform, as well as to maintain the temperature in the environment habitat.Life support systems are designed on the basis of balance of nutrients and energy consumptionof a healthy person. Space missions have produced a range of necessary data on the dynamics

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of human metabolic processes and its adaptation to the flight spacecraft and working in outerspace.To calculate the LSS we use the following averages for the needs of one person (Table 1)

Table 1: The means of mass-energy components flows for 1 person per dayMass-energy components flows Unit ValueProducts of metabolism:Heat generation W 95-100

kJ 8160-13000Water generation(respiratory and skin surface)1. kg 1.2-2.5Diuresis kg 1.3-1.5Carbon dioxide gas kg 1.0-1.5Excrement kg 0.16-0.20

Consumed waste products:Food kg 0.6-1.7Water(driking) kg 1.7-3.6Water(hygienic) kg 2.2-5.5Oxygen kg 0.9-1.2

Selected life support complex solves a wide range of tasks to establish, maintain andcontrol comfortable conditions of human existence and technical equipment operability.

Depending on the task, LSS equipment is combined in groups:1. means to ensure the gas composition;2. water supply facilities;3. means of providing nutrition;4. sanitary facilities;5. means of fire detection and firefighting.

In normal human activity can take place in a fairly narrow range of environmental param-eters. Therefore, designing an integrated system of life, we must form a ship microclimaticconditions close to perfect, including: pressure - 660...860mm Hg, temperature - 20...25C,relative humidity - 40 ... 70%, air velocity - 0.1...0.4 m/s, the partial pressure of oxygen -140...200mm Hg, partial pressure of carbon dioxide - not more than 10mm Hg.Due to the limited scope of our spaceship, we cannot use the most reliable LSS on stockswhen all necessary means are taken along for all the 500 days of the planned flight.Unfortunately, the use of biological closed system is also impossible today. The first ex-periments in this area during the experiment BIOS-3 in Krasnoyarsk (Russia) showed quiteimpressive results.Three people lived inside at almost 100% closure of the water and air and 50% on the foodcircuit for 6 months. BIOS-3 was the first and, to date, the only system in the world whereall the human needs for water, air and plant foods were completely covered by maintaininga closed ecological cycle of matter in the system.

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But the disadvantages of this system include its operation only in terrestrial conditions. Inorbit weightless conditions only small greenhouses (root modules) were fulfilled.Currently the use of actual physical and chemical methods of regeneration and air condi-tioning is on the cards. Collection and treatment of water allow an almost complete circuitof oxygen and water. Unfortunately, limitations in terms of power supply for our spaceshipdid not allow us to use the full range of systems for the complete isolation of gas and waterinside. For example, we had to abandon the thought of Sabatier Reactor, which would allowthe crew to use the allocated carbon dioxide and hydrogen released by the ”electronic”.Now, let’s consider all the life support systems for our ship. (Picture 1)

Picture 1. Life support systems onboard.

1. Means of gas composition

Means of gas composition are intended for:• oxygen for the crew from the average daily consumption of one person to 25 l/h;• removal of carbon dioxide from the atmosphere at the rate of average daily discharge oneperson to 20 l/h;• removal of atmospheric trace gases;• control of the gas composition in the parameters of microclimate Robsch, PO2, PCO2,RN2O, RSO, PH2;• alarm on exceeding PCO2, RSO, PH2 above normal and below normal PO2 decreases;• signaling leakage module;

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• signaling Robsch fall below the set value adjustment;

To solve these problems is to ensure that the gas composition would be further dividedinto subgroups:1.1 Funds of oxygen support system;1.2 Cleaning and atmosphere;1.3 Means of gas analysis;1.4 Controls ship watertight compartments;1.5 Means of control tightness of joints.

1.1 Funds of oxygen support system

Oxygen support system of our ship includse the installation of ”Electron”, one solid oxygengenerator (THC) and oxygen fuel module ATV.

1.1.1 System of oxygen support ”Elektron-VM”

Installment ”Electron” works on the principle of electrochemical decomposition of water.Installment ”Electron” includes: liquid circuit with a 30% solution of potassium hydroxide(KOH), gas pipelines with a pressure regulator, solenoid valves (TBE). Liquid circuit islocated (enclosed) in a sealed enclosure which charges with nitrogen (to enhance security).From the outside the fluid circuit is connected to periodically replace a water tank (EDV).Oxygen is generated in the electrolysis unit by electrolysis of water contained in the solutionof potassium hydroxide. Water contains 89% of oxygen. By the reaction water is decomposedinto oxygen and hydrogen. Oxygen is supplied directly to the atmosphere of the ship, andthe hydrogen is discharged at a vacuum. Electrolysis unit consists of 12 electrolysis cells,prisoners of a flameproof enclosure. Elements cool trailers (CTP). The decomposition of 1kg of water at a rate of 25 l release of oxygen per hour at a pressure of 760 mm Hg is enoughto provide one person breathing during the day. To ensure the daily oxygen requirements ofthe crew of 2 persons, there must be expanded 2 kg of water per day. Power consumptionin this case is 0.5 kW.Thus, to provide oxygen for crew mission (500 days) spending one ton of water is required.Installment ”Elektron” is a controlled onboard computer system. In the operation of control:status valves, the pressure of oxygen and hydrogen in the presence of hydrogen and oxygenbackbone presence of oxygen in the hydrogen lin.In case of deviation from the norm setting parameters ”Electron” is automatically disabled.Guaranteed lifetime of ”Electron” is a year, so on the ship it will go through the full spareset. In the experience of the International Space Station operating time units for water (BZ)of the ”Elektron” reached more than 600 days.

1.1.2 Solid oxygen generator

SOG consists of replaceable cartridge (cassette) with an igniting device impactor, filter, Dustfilter and fan placed in the same housing. It is intended for the thermal decomposition ofoxygen-containing substance pressed into a cylindrical casing. The effluent from the oxygen

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generator is cooled by the air flow. Generator is operated by turning the handle (handwheel)until it clicks. This means that the hammer broke the capsule and chemical reaction started.The amount of oxygen released by a single cassette is 600 L, the decomposition of thecassette product takes 5 - 20 minutes with the reaction temperature of 450 - 500 ◦ C. Surfacetemperature is SOG can reach 50 ◦C. Generator cooling process continues for about 3 hourswhile the fan is running.Solid oxygen generator serves as a reserve in case of failure of the primary system ”Electron”while it’s being repaired.Two crew members oxygen recycling should go 2 rounds per day. If we used only SOD forthe oxygen support system it would require 2x500 = 1000 rounds.To save storage capacity, we take 40 rounds, providing 20 days of reserve for the possiblerepairs of ”Electron”.

1.1.3 Compressed gas cylinders ATV

As an additional reserve of oxygen onboard stands compressed gas cylinders ATV.In considering oxygen support system it is important to remember about the toxicity ofoxygen.

Therefore, if the oxygen concentration in the compartment for any reason would be setabove 24,1%, we will face:1. stop of the flow of oxygen;2. possible performing of a partial collapse.

It should be taken in knowledge that the toxic effect of oxygen is proportional to thepartial pressure and not the percentage of gas. Therefore, inhalation of gas with high oxygencontent (including 100% oxygen in individual masks PBA) is necessary to alternate breathingair or pressure reduction.

1.2 Cleaning and atmosphere

Cleaning tools designed to remove atmospheric carbon dioxide and gaseous harmful tracefrom the atmosphere onboard.The composition of the atmosphere of cleaning agents include:• system of cleaning carbon dioxide from the atmosphere ”Vozduh”;• chemical absorbers of carbon dioxide;• purification unit from harmful atmospheric trace (BMP);

Continuation of the text in Annex

2.5 Thermal regulation system

Thermal control system (TCS) MPK based on similar system has been used and spent onSoviet and Russian space stations (”Mir”, the RS ISS) and is designed to perform the fol-lowing functions:- provide comfortable atmosphere parameters habitable compartments Interplanetary manned

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spacecraft (IPC ) for 2 people manning;- ensure temperature conditions for the functioning of the structural elements, onboard sys-tems and equipment located both outside and inside the sealed compartment of the IPC;- provide the desired humidity of the gas medium sealed compartment of the IPC;- ensure uniform gas composition in the joint IPC Containment;- provide the required air velocity in the habitable zone of the instrument and the IPC;

Providing thermal regime

External heat sources are:* Direct sunlight

Internal heat sources are:* Operating units and equipment;* Regenerative substance of a system to ensure the gas composition;* Crew members (metabolic heat).

TCS MPK was established in accordance with the following principles:* Maximum insulation from the external surfaces of the IPC has to minimize unregulatedexternal heat transfer and heat transfer from the heated blocks and structural elements tocold;* Radiation way to reset into the environment of excess heat generated in the atmosphereof the IPC;* Maximum utilization of heat generated crew and equipment;* Temperature control enclosures MPK sections and blocks using a liquid coolant;* Construct the multi-loop temperature control system as a system with a hydraulic discon-nection of circuits;

To reflect solar radiation outside the MPK screen-vacuum thermal insulation is used.MLI is a multi-layered set of metallized polyethylene terephthalate film and glass haze hav-ing high vacuum high thermal resistance. MLI is performed in the form of panels, the outersurface of which is closed with glass. TCS consists of two closed not hydraulically intercon-nected circuits: the heating circuit (HCI) and the cooling circuit (CCI). Thermal connectioncircuits by means of liquid-liquid heat exchanger. Contours are duplicated when the primarycircuit (KOB1; KOH1) backup circuit (KOB2; KOH2) is in a ”cold” standby. During oper-ation, the MPK is constantly used one set of circuits: KOB1/KOH1 or KOB2/KOH2.

Heating circuit (HCI) is located within the MPK and serves to collect heat from theworking units (LSS etc.) and its distribution throughout the volume of the ship, providinga temperature of 20...25◦C.Circulation of the working fluid (coolant ”Triol”) is provided in the line via electric pumpunits (ENA). The composition ”Triolet” includes 70% of water, glycerol and 30% specialadditives. This liquid is safe for the crew in case of leakage.Surplus heat from the HCI using the liquid-liquid heat exchanger transfers the cooling circuit.CCI provides its radiation using radiation heat exchanger cooling - EVA.

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Coolant circuit CCI is toxic, so the pipes are only on the outside of the ship.The main mode of operation of TCS is automatic.

Moisture control

TCS provides relative humidity – 30% to 70%.To maintain the desired humidity on the IPC the air conditioning system, which consists oftwo redundant systems and SKV1 SKV2, is used.Air cooling in SKV is carried out in two stages. In the first stage of cooling air is due toconvective heat transfer between the air and coolant heating circuit in the gas-liquid heatexchanger.Cooling air to the second stage and its drainage is accomplished by convective heat transferin the evaporator - condenser between the air and halocarbon (freon).Power is provided by CFC board network voltage DC 28.5 V and the power supply unit(PSU SLE) alternating three-phase current with line voltage 115 V 50 Hz (for power microcompressor)To condensate of atmospheric moisture from water traps air conditioning system and SKV1SKV2 in water recovery from atmospheric moisture SRV-K is designed as magistral conden-sate drain (IOC).

Ventilation

Ventilation system (VS) is designed to create a purposeful air circulation in the habitablezone of pressurized compartment and instrument IPC to address the following objectives:* Providing the required atmospheric composition in all zones sealed compartment;* Providing a predetermined thermal balance (temperature gradient) over the entire volumesealed compartment;* Clean atmosphere sealed compartment of household dust.

Experimentally established that the premises (including the ones in sealed compartments)for air velocity less than 0.073 m/s have formed stagnant zones. By reason of insufficientventilation and as a consequence - increase of concentration of carbon dioxide - a person hasa feeling stuffiness while at speeds exceeding 0.3 m/s , there is a draft, which may cause thecommon cold. Comfortable for the person considered the flow rates of air between 0.12 -0.18 m/s. Quite suitable air velocity in the range 0.1 - 0.25 m/s.A person feels uncomfortable in those cases when the temperature gradient (temperaturedifference between separate areas of the room) is greater than 4◦C. In IPC establish a suffi-cient number of fans, which should provide comfort to the crew.

Fans are located:- In CA - 2 pcs.;- The working volume of the IPC 4 pcs.;- The panels working volume of 4 pcs.;- In the transition compartment Pho and overview dome - 4 pcs.

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Also, the crew can use portable ventilators installed in case of need, such as during phys-ical exercise. There are 4 such fans.Experience in the use of fans on station ”Mir” and the ISS RS showed that their workinghours usually exceed the warranty period of work, but we will post onboard 5 spare fans.In CA and PhO stretch soft ducts to deliver by force the air enriched with oxygen from thesystem ”Electron” in there, air is returned back through the openings of manhole covers.In case of activation of smoke detectors and fire suppression algorithm, all the fans TCS willbe disabled to stop the stirring air.

2.6 Onboard computer system

Onboard computer system (OCS) is the set of computing facilities intercommunicatingthrough some interfaces. By means of some data transmission unit adapters, or interfaces,the onboard computer system joins the other onboard systems into an integrated structurewhich is designed for execution of informational and control tasks.

The onboard computer system interacts with a motion and navigation control system(MNCS) during onboard decision making of the ship’s motion. OCS communicates with theMission control center (MCC) and performs the preliminary processing of telemetric data.MNCS, OCS and equipment control onboard (SECO) form all together the control systemonboard (CSO).OCS itself is applied on the bus-modular principle with a hierarchy structure. The mod-ules of the system are connected by some exchange transit lines, which are corresponded bymultiplex exchange channels (MEC), such as MIL STD 1553B. The functions of OCS aredivided between different modules. Such a structure of the system allows perform a scalingwithout any critical changes in software.

OCS consists of the following buses:• control bus;• MNCS bus;• telemetry bus.

Apart from the OCS there is an embedded computer (EC) in the descent module (DM).

Hardware

OCS structure is represented two interchanging contours with different functionalities.The first contour is formed by computing facilities of the OCS which serve for motion controlof the ship and control the onboard systems in real time and connecting busses.

The hardware environment of this contour:• central computer (CS);• control post’s computer (CPC);

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• interleavers and controllers.

The second contour is formed by LAN which controls the onboard systems, payload andapplied processes. Interaction between the crew and the network is carried out by the centralcontrol post and additional one (laptop).

The hardware environment of this contour:• control post’s computer (CPC);• personal computer (laptop)

The first contour is built for the solving of the following problems:• the providing the onboard systems with required compute capacity for performing thefunctions of ship control;• control of the onboard systems;• data exchange between the OCS and the onboard systems;• the receiving control commands from Earth and control boards, the processing and thesubsequent sending to the onboard systems;• automatic execution of the diagnostic routines for the onboard systems;• collection and the processing of telemetric data;• delegation of the computational tasks and data flow control.

The second contour is built for the solving of the following problems:• provision of the control and monitoring functions of the different objects for an operatorin the dialogue mode;• control of a technological and science equipment of the station in the real-time mode;• ship control by the first contour;• the handling of big data in the LAN;• management of computations for the central post.

Taking into account the fact that a sufficient part of the mission will take place far fromEarth, a proper data storage system is set on the ship. Solid-state drive (SSD) is plannedas a physical drive.

Software

The software of the CS is meant for execution of the following tasks:• automatic and automated ship control during all the life-cycle stages;• ensure proper opportunities of ship control and its status monitoring from the direction ofthe crew or the MCC;• provision of data exchange with MCC;• navigation and motion control of the ship;• provision of data exchange with MNCS;• control of the interfaces;• control of the input commands;

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• control of the commands for the SECO;• pre-processing of telemetry data and the subsequent sending it to the MCC;• onboard systems management;• data recording on the data bank.

The software of the CPC is meant for execution of the following tasks:• support of ship and onboard systems control;• data exchange with the CC;• warning in case of any emergency;• the data bank management.

Continuation of the text in Annex

2.7 The power system

The power system is designed for:- providing onboard equipment and systems of spaceship by energy during the flight- charging batteries from solar panels

The power system includes:- 4 solar panel- 4 backup batteries- 2 buffer batteries- bus power- current regulator- sensor unit’s

The total power of all devices and systems which include spaceship with a safety factorof 1.3:- 6 kW.

In moments, when spaceship flyby the Mars, the spaceship will be in the shadow. So itwill use the power from buffer battery. And it is planning, that consumption of devices andsystems will be lower.The total power of all devices and systems which include spaceship with a safety factor of1.3 in the shadow of Mars:- 4 KW.

ATV’s solar panels, which area is 33.6 sq.m. give the power of 4.8 kW. But if we use inthe same area on factory ”KVANT”, where we will get from the 1 sq.m 295 W, the resultingpower from solar panels - 9.9 kW.Power which generated by solar cells decreases with distance from the Sun. Near the Mars ,solar panels will get 50% of that power, which was prepared at about the Earth, The power-5 kW.The buffer battery (chemical current source which based on a silver- zinc battery) will be

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constantly connected to the output buses and the Solar battery will provide power the con-sumer board, when the solar cell current will equal to 0 (in shadow). If the current SB morethan current regulator, the buffer battery accumulates electrical energy.Also in spaceship there will be the backup battery designed to maintain on-board networkand to provide electricity in the case of complete consumption of energy backup batteries.

2.8 Protection against radiation

Total contribution to the background radiation in interplanetary flight Earth-Mars-Earthwill consist of solar cosmic rays (SCR), Galactic cosmic rays (GCR), as well as the Earth’sradiation belts (ERB).Let’s think, according to equipment of radiation rover Curiosity received during the flightEarth-Mars is 380 mSv. It gives meaning to believe that the total background radiationobtained for the entire flight crew did not exceed 1 Siever, with appropriate radiation pro-tection. This is the maximum permissible dose for human health. Lethal single dose ofradiation for humans is 3-5 Sievert value.

Large amount of information on the radiation environment and the effects of radiationon the human body were obtained in Earth orbital station. It should be noted that in lowEarth orbit crew protected powerful Earth’s magnetosphere. On average astronaut on theInternational Space Station for Radiation Protection 10-15 g/cm2 per day gets dose of 0.6-0.9 mSv. Summary background radiation obtained in 3 space flights lasting 747 days bycosmonaut Sergei Avdeev was 380 mSv.While the 9-day mission to the moon, the crew ”Apollo 14” has received an average radiationdose of 11.4 mSv with the protection of not more than 7.5 g/cm2.

Ship design provides the most secure shelter from radiation. This lander with fixed onthe outer surface of the torus-shaped tank with fuel and industrial water. Total protection inthis part of the ship will be variable with changes in the amount of liquid in the tank and willbe 10-15 g/cm2. This will allow the importance of protecting the crew protect themselveseven from the powerful solar flares. In the descent vehicle exactly crew spends maximumtime during the flight. Going into the main module of the ship is associated with physicalexercise and other needs. Protection of the basic module consists of the module housing andlaid inside the payload. Importance of protecting and variable (3-5 g/cm2) and will decreasein sync with decreasing of stocks payloads.

Radiation protective layer. Figure 1.Special contribution to the value of background radiation in interplanetary missions have

flares on the sun. Upon detection of such outbreaks, threatening the spaceship, the crewtakes place in the descent module to the end of the threat. Selection should consider the dateof the flight time of minimum solar activity of 11-year cycle. 2018 is suitable for committingsuch interplanetary flight. Space weather prediction center allows you to monitor the activityof the sun (Fig.2)

Schedule solar cycle progression. Figure 2.

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Subject to the conditions set out above, and in this spaceship design crew should receive adose of radiation not exceeding critical to human health. During the flight, the crew will usedosimeters and follow the maximum permissible radiation level for the day, which should notexceed 2 mSv. Beyond the project remained radiation dose calculations from various sourcesand accurate figures on the thickness of the protective layer structure. In this project, werelied on the figures given in the various reliable sources on the flight experience of orbitalspace stations, manned flights to the moon (like program “Apollo”) and flying machine MarsCuriosity.

2.9 Medical training and medical briefing

All crew members (including both of the backup crews) must pass the same medical trainingand medical briefing before the flight. Since the requirements for selection of the crew indi-cated that one of the crew members must be a doctor and have the appropriate skills, crewmembers will receive various medical instructions. Nevertheless, they should be trained thesame.

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Medical training of the crew includes:- Prevention of adverse effects of weightlessness- Standard physical training- Psychological training

Crew members will be trained at one of the centers for training of astronauts on thestandard requirements for medical training.Medical instruction (briefing) will mostly include instructing crew members with no medicaltraining for situations requiring emergency medical care. Also, both crew members requireto be trained in using the code to enable emergency protocols in case of emergency, requiringemergency medical care. Due to signal delay, communication with the Centre provides op-tions to include emergency protocols in case of emergencies. The astronauts will be equippedwith the recorded video and text files, while entering activating the emergency protocol code.In addition, a crew member without a medical education will have to be trained in first aid(with the mandatory training and passing the exam).Measures of medical accounting and control in the appropriate section application will alsorequire further clarification and training on the part of both the crew members for furtherapplication of such positive measures on board during the mission.

Prevention of adverse effects of weightlessness

Each of the crew members during a standard physical training will have to take trainingcycle to prepare for further exposed weightlessness: vestibular apparatus training and an-other one to prevent the musculoskeletal and cardiovascular system overload. Also, membersof the crew will be equipped with special antigravity suit to prevent the adverse effects ofweightlessness on board.We should also mention that two crews passing the mission on Earth will not be equippedwith an environment of weightlessness, so for them these measures may be subject to modi-fications (perhaps they will be left for a complete psychological immersion in the atmosphereof being on a spaceship).

Standard physical training

Each crew member is required to pass a standard physical training norms and regulationsat the astronaut training center. Physical training includes endurance and speed training,training of the vestibular apparatus and the preventive measures of basic body systems over-load and subsequent work in zero gravity.

Psychological training

Considering the long-term stay in a confined space during the mission, the future crewmembers will be required to undergo a profound psychological training. The goal of trainingis identifying potential weaknesses in the psychological profile of the astronaut, their abilityof teamwork (focusing on the team rather than personal goals) and temper compatibilitywith each other. It is assumed that both of the crew members are from one culture field,

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so that intercultural problems may flatten, however, other problems may arise. Professionalpsychologists and psychiatrists will be working with members of the crew during trainingmission and throughout its course.

Engineering briefing and engineering training

All crew members (including both of the backup crews) must pass the same engineeringtraining and engineering briefing before the flight. Since the requirements for selection ofthe crew indicated that one of the crew members must be an engineer and have the appro-priate skills, crew members will receive various engineering instructions. However, trainingshould be the same to avoid possible misunderstanding of vehicle systems onboard. Crewmembers will be trained at one of the centers for training of astronauts on a mission to thespecialized requirements of Inspiration Mars: all crews will be required to pass the exam onthe knowledge and understanding of vehicle systems, incorporating emergency protocols andEarth connection to be able, if necessary, to make the required repairs inside and outsidethe ship.Engineering instruction will mostly include instructing a crew member without engineer-ing education for situations requiring emergency engineering intervention and inability toproduce the interference with the help of the second crew-member.

Briefing for emergencies

All crew members (including both of the backup crews) must listen to the same instructionsfor emergencies. Instruction must include a set of theoretical rules of behavior in case ofemergency as well as practical training. It’s worth noting that the first backup crew emer-gencies would be modeled on basis of scientifical experiment Mars-500, the second backupcrew will face false emergencies same to the ones on board the ship.

2.9.2 Onboard training schedule

In flight is used the training system provided with four day microcycle, which includes threedays of training and 1 day of rest. At different days of the cycle exercise aimed at main-taining speed, speed-strength and overall endurance. The total load from the 1st to 3rd dayincreases microcycle completed a day of rest. Duration of training - 1 hour.

1st day. Training aimed at maintaining speed- endurance and strength training includewalking, running at a pace of 120-140 steps per minute sessions and high-speed running ata pace of 240 steps per minute and more.2nd day. Training is aimed at maintaining the power of endurance.3rd day. Basis training - monotonous running relatively low and medium speed for a rel-atively long time intervals (4-6 minutes) and pedaling on a bicycle ergometer in the samemode.4th day. Available optional training.

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On request can be selected the astronaut training on a bicycle ergometer, includingpedaling, alternating with work with expanders.The studies confirmed the high efficiency of interval training on the track with a large numberof shifts short intervals of intense jogging intervals of walking and training with a share ofthe passive mode of the web path not less than 30% of the total.Astronauts begin to perform physical exercise 6-7 days of flight , with a gradual increasein load and reaching its highest level in 2 month flight. Further training is planned in aserpentine pattern: a slight decrease in intensity to the 3 month flight, an increase of 4months to a second month, 5 month again reducing the intensity, etc.Astronauts are recommended to wear a suit ”Penguin” for 8-12 hours a day, allowing theload size, reaching up to 30% ”Earth weight” astronaut.Pinch cuff “Bracelet” is used in the acute period of adaptation to weightlessness on the 7thday of the flight 10s. Is recommended wearing products 10-12 hours a day.At the final stage of the flight ODNT workout (negative pressure on the lower part of thebody) will be conducted starting 26 days until the end of the flight.Electromyostimulation is used in the acute period of adaptation to weightlessness and thefinal phase of flight.

2.9.3 Diet

Regular diet for the spaceship crew is designed as a 3-day menu with 4 meals a day, andincludes the products of heat sterilization, freeze drying, intermediate moisture and naturalform suitable for human consumption without the need of prior preparation and heating,having weight daily set of products Net 1360 and the energy value of 2600 kcal ( DobrovolskyVF, Theoretical and practical aspects of improving the technology of production of cannedfoods and diets for the crews of space ships and stations . Dis.d.t.n. - Moscow NII PP andSPT , 2000, p.9-10).

Continuation of the text in Annex

2.9.4 Radiation monitoring.

Means of individual monitoring

One of the main components of the SORB (System of Radiation Safety) is a CPM (radiationmonitoring system). The objectives of this system are monitoring and forecating the radia-tion environment on the path of the flight and within the plant and determine the radiationdose of the crew. This system consists of active radiation monitoring equipment and themeans of individual monitoring.Further funds will be considered individual monitoring.Individual monitoring is carried out by means of active and passive dosimeters.Active personal dosimeter IAP -2.Used for operative dosimeter.Dimensions dosimeter 87h62h21 mm, weight - 0.2 kg.Polling frequency depends on the radiation situation and is 1 time a week.

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Passive monitoring

Individual dosimeters integrated ID- 3M are designed for continuous wearing for each crewmember during the flight. These dosimeters shall record the total absorbed dose.Dimensions dosimeter 42h40h11 mm, weight - 0,025 kg.Way to get information - processing in the laboratory after returning to Earth.

Radiation protection

Inside the ship astronauts will use personal radiation protection.Chemical protection involves the use of radioprotective short and prolonged action. Forbriefly radioprotectors including medications protective effect will manifest itself during 0.5-4 hours after administration. They can be used in solar flares and while passing through theradiation belts. By means of long-term protection drugs with radioprotection are used fromone day to several weeks. In pulsed ionizing radiation, they usually show a smaller effectthan the funds short-term protection.In the experiment, ”Matryoshka-R” along the outer walls of the cabins will be installed”Safety Shutters” which presents a screen with pockets that hold napkins and wet towels.Expected dose reduction due to ”Styling - blind” - 15%.Clothing astronauts will also provide protection from ionizing radiation.

Continuation of the text in Annex

2.10 Materials for the crew

Accessories for hygiene

Equipment

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Clothing

3 Mass analysis

3.1. Space tugs

3.1.1. Space tug 1, Space tug 2, Space tug 3

3.1.2. Space tug 4

3.2. Interplanetary Manned Spacecraft

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4 Leading out process and Ballistics

4.1 Leading out process

1. Fitting complex

The first launch of Proton-M displays the support circular orbit of 175 km and an inclinationof 51.6 spaceship (OK), mass 23.000 kg. It is further shifted into waiting orbit altitude of220 km, which is starting next to Proton-M.

The second launch Proton-M displays the support circular orbit 175 km booster WP1.OK enters support orbit for the waiting orbit WP1, which is joined with it, after the complexshifts into the waiting orbit.

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Third launch Proton-M displays the support circular orbit 175 km RB2. OK enterssup-port orbit for the waiting orbit RB2, which is joined with it, after the complex shifts intowaiting orbit.

Fourth launch of Proton-M displays the reference circular orbit 175 km RB3. OK enterssupport orbit for the waiting orbit RB3, which is joined with it, after the complex shifts intowaiting orbit.

Fifth launch Proton-M outputs to support a circular orbit 175 km RB4 Dwell . OK enterssupport orbit for the waiting orbit RB4, which isjoined with it. Ship complex assembly iscompleted.

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Spacecraft ”Soyuz-MS” with future crew of the OK is launched on the “Soyuz”. ”Soyuz-MS” goes to the support orbitof OK whereit fits in with it, thenthe crew of two people goeswith it on OK. Commander of spacecraft ”Soyuz-MS” undocks from the ship complex andis returned to Earth. Crew OK after finished verifying the complex systems on reaching thestarting period proceeds to launch the departure trajectories to Mars.

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The change in mass of the complex and the cost of fuel assembly are shown in Table1

Table 1.

2. Leading out on departure trajectories

First ignition is made in support orbit perigee and shifts complex intermediate orbit withan apogee of 561.6 km.

Second ignition is made in an intermediate orbit perigee and apogee altitude brings itup to 992.9 km.

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Third ignition is made to an intermediate orbit perigee and apogee altitude brings itup to 1477.3 km.

Fourth ignition is made in the intermediate orbit perigee and apogee altitude brings itup to 2025.2 km. Resets DTB RB4.

Fifth ignition is made in an intermediate orbit perigee and apogee altitude brings it upto 2963.7 km. CB resets RB4.

Sixth ignition is made in support orbit perigee and shifts complex intermediate orbitwith an apogee of 561.6 km.

Seventh ignition is made in intermediate orbit perigee and apogee altitude brings it upto 992.9 km.

Eighth ignition is made in intermediate orbit perigee and apogee altitude brings it upto 1477.3 km.

Ninth ignition is made in intermediate orbit perigee and apogee altitude brings it upto 2025.2 km. Resets DTB RB3.

Tenth ignition is made in intermediate orbit perigee and apogee altitude brings it upto 2963.7 km. CB resets RB3.

Eleventh ignition is made in support orbit perigee and shifts complex intermediateorbit with an apogee of 561.6 km.

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Twelfth ignition is made in intermediate orbit perigee and apogee altitude brings it upto 992.9 km.

Thirteenth ignition is made in intermediate orbit perigee and apogee altitude bringsit up to 1477.3 km.

Fourteenth ignition is made in intermediate orbit perigee and apogee altitude bringsit up to 2025.2 km. Resets DTB RB2.

Fifteenth ignition is made in intermediate orbit perigee and apogee altitude brings itup to 2963.7 km. CB resets RB2.

Sixteenth ignition is made in support orbit perigee and shifts complex intermediateorbit with an apogee of 561.6 km.

Seventeenth ignition is made in intermediate orbit perigee and outputs complex hy-perbolic trajectory. Resets DTB WP1.

Eighteenth reset ignition is made after DTB WP1 and shifts to a predetermined setof escape trajectories. CB resets WP1.

Changes in the mass and its complex with excretion rate shown in Table 2, the eliminationsequence diagram in Figure 1.

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Table 2.

Continuation of the text in Annex

4.2 Ballistics and flight path

The flight can be divided into following stages:

1. The acceleration from the low-earth orbit (height h = 220km up to the V velocityand coasting in the Earth’s scope of activity. In the process:

V = V0 + ∆V (1)

where V0 = 7777m/s is the vehicle’s orbital speed and ∆V is a velocity increment. Due tothe vehicle’s weight and the amount of fuel during the launching stage, ∆V cannot exceed4900m/s, from which V cannot exceed 12677m/s. As a first approximation it is possible tocalculate the vehicle’s pathway in geocentric coordinate system, taking into account only the

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Earth gravity. At this case the velocity of leaving the Earth’s scope of activity approximatesthe asymptotic velocity Va1, calculated via the following formula

V 2a1 = V2–V

22 /(1 + h/R) (2)

where V2 = 11186m/s is the Earth parabolic velocity and R = 6400km is the Earth’s radius.Therefore Va1 cannot exceed 6304m/s.

2. Elliptic heliocentric path flight between Earth’s andMars’ activity scopes. At the beginning of the stagethe correction should be done to enter the Mars’ activ-ity scope. About the end of the stage another cor-rection might be necessary to enter the Mars’ activityscope at the desired position. This position is set withthe parameters of the gravitational slingshot of the nextstage.

3. Mars’ activity scope coasting, in which the vehicle doesthe gravitational slingshot: orbits the Mars hyperbolically,changing the course. Like the first stage, it is possible to cal-culate the vehicle’s pathway in the areocentric system of co-ordinates, taking into account only the Mars’ gravity. Whilethe vehicle is “following” the Mars (and “leaves off” the Earth,which orbits faster than Mars), its heliocentric velocity should be put together with theMars’ orbital velocity.

The Mars’ activity sphere entry point determines the angle of maneuver, andthe height hM, at which the flight would go on the Mars. The height should berestricted: hM cannot exceed 100 km, so that the vehicle would not get into theplanet’s atmosphere (in that case it would be difficult to predict its further pathway).

The angle and height are determined so that the vehicle could reach theEarth’s activity sphere at the next stage. Due to the favorable position ofthe Mars in 2018 it is close to the ecliptic. In the process the vehicle fliesaround the Mars from the counter-solar side and, accelerating, “catches” theEarth.

4. Elliptic heliocentric path flight between Earth’s and Mars’ activity scopes. At thebeginning of the stage the correction should be done to enter the Earth’s activity scopes.About the end of the stage another correction might be necessary to enter the Earth’s ac-tivity scope at the desired position.

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5. Hyperbolic path coasting in the Earth’s sphere activity. Once again, at the calculationof the approximate pathway in the heliocentric coordinate system only the Earth’s gravitycould be taken into account. The entry point should be determined to enter the atmosphereat the angle, providing the safe descent.

6. The separation of the descent vehicle (DV), its atmosphere reentry at a given angleand its descent at a sliding pathway. The descent would be managed only by its lift-dragratio: turning DV (changing its rolling angle) one could manage the course of lifting force.

At the first stage of descent DV goes down, moving along the lower borderline of theacceptable reentry corridor. Gravity load increases due to the air resistance. The liftingforce should be thus upwards directed, so that the vehicle would not go into the dense at-mosphere too fast. At the second stage, after the maximum gravity load DV goes to theupper borderline of the acceptable corridor, while the Earth is round, and the DV pathwayis about the bee-line. In that case the lifting force should be directed downwards, so that theDV, going through the light air, would not leave it for the Earth low orbit. Even if it goesto the orbit, it would get into the atmosphere once again at the next loop. But the descentwould last too long time and DV would also mean to pass the radiation belts several times,which is harmful for the cosmonauts’ health.

At the third stage DV descends once again, and the lifting force is directed upwards, butthe highest gravity load is lower, than at the first stage. At the fourth stage DV starts thefreefall in the lower atmosphere, which is slowed by the parachutes and the rest of the fuel.It is advisable to land on water to provide the soft landing. As 75% of the Earth surface iscovered by the oceans, it is easy to achieve at the stage of the correction before the entry tothe Earth’s activity scope.

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It is considered that the atmosphere starts at the height of 100km. Let us take thegravity load 9g as maximum allowed. Then the vehicle with the lift-drag ratio 0.3, as DVof ”Sojuz”, would have the reentry velocity not more than Vmax = 17300m/s. The width ofthe reentry corridor with the veclocity a bit lower than Vmax would be 6km and it reducespromptly to null as the velocity reaches Vmax . But taking into account that we can ”aim”at the Earth with precision about 13km, the width of the reentry corridor must be equal13km. The appropriate reentry velocity is 14200m/s.

Therefore, the speed Va2 of the Earth’s activity scope entry can be estimated with theformula (2) – it cannot exceed 8857m/s.

The restrictions for the speeds Va1 and Va2 determine the time slot, which allows thestart: from 2017 to 6th January 2018. Hence, the vehicle would need the fuel stock for 3-4corrections. To calculate the amount of fuel for one correction, one could use the analog ap-proach. Similar ballistics analogue is unmanned interplanetary probe “Vega”, which has thetotal characteristic velocity of the corrections 160m/s. Therefore, there should be enoughfuel stocked to reach 5060m/s.

5 Scientific experiments

5.1 Medical and biological experiments

The main directions of research programs in the period of Inspiration Mars missions areresearch and experimental work on the effect on the human factors of a flight to Mars.

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The expedition members will be exposed to complex simultaneously or sequentially actingfactors inherent in the dynamics of interplanetary flight, space environment and conditionsof life in a confined space. Main groups of factors: the general conditions of the expedition,physical factors of interplanetary space, dynamic factors of interplanetary flight, closed habi-tat factors, psychosocial factors. A considerable part of the factors in these groups will bedifferent from the factors affecting the astronauts during orbital flights at the Earth, even atcomparable long flight crews. Most of the experiments are aimed at studying the adaptationof the cardiorespiratory system and at metabolism studies in microgravity.

Experiment ”Pnevmokard”

Study of the influence of space flight factors on the autonomic regulation of blood flow andcontractile function of the heart in long-term space flight.

Goal: Preparation of new scientific information to deepen the understanding of the mech-anisms of adaptation of the cardiorespiratory system and the whole organism to space flight.

Goals:• comprehensive study of the cardiovascular system of astronauts in different stages of pro-longed space flight in order to clarify the mechanisms and stages of adaptation and to identifydiagnostic criteria for individual assessment of adaptation to weightlessness;• synchronization of indicators of cardiac activity and respiration, as well as the study ofthe cardiorespiratory system control processes in terms of variability of physiological param-eters;• study of the relationship between the functional state of the cardiorespiratory systemduring a long flight and orthostatic tolerance and physical activity in the initial period ofrehabilitation in order to predict the possible reactions of crew members while returning toEarth.

The study will be conducted using the hardware-software complex ”Ecosan- 2007”, whichincludes the device ”Pnevmokard”.With the onboard device ”Pnevmokard” ISS obtained a number of new scientific evidenceon the high individuality of adaptive reactions to long-term effect of weightlessness. It hasalso confirmed the high efficiency and practical importance of the probabilistic approach toassessing the risk of disease based on the analysis of heart rate variability.

Experiment ”Kosmokard”

Study of the influence of space flight factors on the electrophysiological characteristics ofthe myocardium and on their relationship with the processes of the autonomic regulation ofcirculation at long-term weightlessness.

Research goals:1) research and evaluation of the electrophysiological characteristics of the myocardium un-der long-term weightlessness;

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2) study the possibility of early detection of probable prenosological (prepathological) ab-normalities that cannot be detected by conventional electrocardiography;3) examine the relationship between changes in the electrophysiological characteristics of themyocardium and the vegetative regulation of heart rate during the prolonged space flight;4) investigate the relationship between changes in the electrophysiological characteristics ofmyocardium in flight and orthostatic tolerance and physical activity in the initial periodof rehabilitation with a view to forecasting the possible reactions of crew members whilereturning to Earth.

Scientific appartura:Device ”Ecosan-2007” Laying KOSMOKARD- DEVICE, dimensions: 140h100h80 mm, weight0.30 kg;Laying KOSMOKARD – ASO, dimensions: 300h270h80 mm, weight 0.60 kg;Media KOSMOKARD – DATA, dimensions: 23h23h85 mm, weight 0.04 kgIn the course of the experiment will be studied Kosmokard energy-metabolic processes to en-sure the myocardium under conditions of prolonged weightlessness that will give new insightsinto the mechanisms of adaptation of the body of astronaut in space flight.

Experiment ”Sonokard”

A comprehensive study of physiological functions by contactless method during sleep duringlong-duration spaceflight.The aim of the experiment is to develop proposals to improve the system of medical super-vision of astronauts using the method of non-contact removal of physiological data duringsleep.During sleep the astronauts will be going through the contactless removal of physiologicaldata using the device ”Sonokard” located in a breast pocket of T-shirts.

On the basis of contactless registration indicators of cardiorespiratory system during thenighttime days can develop efficient criteria for evaluating and predicting adaptive capa-bilities of the organism in the long-term space flight. It has not only scientific but also ofpractical importance for the further development of operational health monitoring of thehealth of astronauts. Such a system will be an important element in ensuring the safety ofmanned space flights since it will go to the continuous monitoring of the functional state ofthe astronauts’ organism. Moreover, long recording complex of physiological indicators willprovide new information on the status of the different management levels of physiologicalfunctions, their coordination and communication with the degree of adaptation of the bodyduring weightlessness.

Investigation of autonomic regulation of circulation.

The purpose of this experiment is to determine the effectiveness of a new method of eval-uation of the functional state of the organism, which is to study the risk of abnormalitiesbased on the analysis of heart rate variability (HRV).

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A hardware-software complex ”Ecosan-2007” is used for the experiment. Vegetative regula-tion of blood circulation is studied using the method of HRV analysis.Studies carried out in conditions of prolonged isolation in modeling ”Mars mission” showedthat in general there is no significant change in the functional status and in most cases, theadaptive response of the crew members are adequate.

Experiment ”Diuresis”

Study of water-salt metabolism and hormonal regulation in spaceflight.The purpose of the experiment - to obtain new data on the state of water-salt metabolism andhormonal regulation of volemy in weightlessness and re-adaptational period after spaceflight.

The goals of the experiment are to study:- The state of water-salt metabolism and hormonal regulation of volemy at different stagesof space flight and early re-adaptational period;- The relationship between renal excretory activities and its hormonal regulation on thebackground of water-salt loads during adaptation to weightlessness and the after-flight termperiod;- Fluid balance and key electrolytes in microgravity.

The equipment used:- Complex for processing, freezing and impact gates biomaterial samples to Earth;- Hematocrit kit for determining the hematocrit in the peripheral blood,- Complex-4 Reflotron for determining hemoglobin creatinine and urea,- Laying M receivers for collecting urine (urine tanks with adapters for syringe (FRG), sy-ringes for sampling urine (FRG), clips) 180h120h50 mm, 0.50 kg

At the moment, after the experiment on ISS following results were obtained:During the flight, the amount of fluid intake in the morning significantly reduced withdownward trend in daily water consumption and aldosterone concentration in the blood,which could be due to the peculiarities of work and rest, changing the composition of liquidmedia and circulating blood volume. While in microgravity, the concentration of potassiumin the blood significantly increased, probably due to malnutrition of muscles in antigravity,as evidenced by significant negative correlation of this index with a BMI (body mass index).Data correlation analysis indicates that there is a close relationship of age and BMI withother studied parameters. These results should be considered in assessing the nutritionalstatus and condition of the physiological activity of the crew members. The concentrationof cortisol and aldosterone in the blood, urinary excretion of VLA (vanillylmandelic acid) inmicrogravity is not much different from the background that allows us to conclude the absenceof activation of sympathetic nervous system and maintaining its functional connections inthe final stage of prolonged space flight.In microgravity and after the flight there was a decrease in concentration of prolactin in theblood, which indirectly indicates the increased dopaminergic activity of the CNS (centralnervous system), because the regulation of secretion of this hormone pituitary prolactotropheessentially depends mainly on the activity of dopaminergic neurons tuberinfundibular brain

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areas.Direct evidence of increasing dopaminergic activity is to increase the body’s excretion ofHVA (homovanillic acid) in the urine in the air, while the ratio of ICH/HVA did not change.Increased CNS dopaminergic activity can lead to increased peripheral vascular resistance,systolic blood pressure and increase in cardiac output and cause symptoms of agitation andimbalance of crew members in the final stages of flight that must be considered in planningthe level of physical and mental activity of crew members.

Continuation of the text in Annex

5.2 Other experiments

One of the most important tasks onboard of the spacecraft making a long-term flight (asin mission Inspiration Mars) is to conduct scientific experiments using the forces of actingcrew. Since the amount of space missions with high duration is limited, verification of al-ready carried out experiments is required. It is also possible to conduct new experiments,the design of which will be specially made for mission Inspiration Mars.

Proposed concept of experiments may be divided into three groups:- Psychological and psychophysical studies- Sanitation and microbiological studies- Operational and technological research

Psychological/psychophysical studies

We have three main areas of research during the flight of a manned expedition to Mars:

1. Maintaining the psycho-emotional state, general and professional mental health duringover than 520 days of the expedition;

2. Ensuring effective intragroup interaction in a multicultural crew;

3. Crew interaction with the Control Center in the long-term autonomous flight withthe increasing communication delay. On the basis of tasking programs of psychological ex-periment Mars-500 and current requirements and the needs of the mission crew InspirationMars, we can formulate the following tasks to be flown:- Assessment of mental and emotional state, mental performance and alertness level crewmembers;- Study of the features of the crew communications with the outside world with the limita-tions (communication delay) of the inherent flight to Mars;- Study of the processes of group and individual adaptation to the 501-day isolation (andchecking the results of the experiment Mars-500 with 520-day isolation);- Study of personal values and relationships in pairs;- Study the professional skills of the operator’s activity under 501-day isolation (and checkingthe results of the experiment Mars-500 with 520-day isolation);

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- Development of new tools psychological support developed based on virtual reality tech-nology;- Study of the influence of different means psychological prophylactics (including the presenceon board of higher plants) to optimize the psychophysiological status of the crew members;- Study of the role of unconscious psychophysiological reactions in adaptation to prolongedisolation.

In psychological and psychophysiological studies regularly examines the state of highermental functions, mechanisms of emotional stress, the effectiveness of control methods ofmental performance, especially intra- and interpersonal dynamics and crew communicationswith the outside world, the state and dynamics of professional management skills to theexact process benches and simulators.

We will investigate the state of operator functions, types of resistance responses to stres-sors activities.We are going to study the effectiveness of the influence of regular exercise on autologousclassical techniques on the psychophysiological state of operators during the sessions of thetest control at all stages of the experiment.During the Mars-500 experiment were observed the manifestations of ”problems of the wayhome”, compounded by mental asthenia on the background of sensory deprivation andmonotony. We should expect the corresponding effects in the mission Inspiration Mars,perhaps exacerbated by the lack of physical possibility of withdrawing from the missionahead.

Sanitation and microbiological studies

In hygienic and microbiological studies will be examined the dynamics of changes in habi-tat conditions, cyclical changes in its toxicological and hygienic characteristics, prognosticsignificance of changes and their causes.

Operational and technological research

In operational and technological research conducted study of growth and plant life in a closedvolume with given environmental conditions by installing and maintaining greenhouses withgrowing number of plants as elements of psychological support.Conducted development of methods and means of providing medical help in case of emer-gency, medical monitoring, telemedicine means of medical monitoring and diagnostics.We study a number of new funds for sanitary control environment.

Psychological support

As psychological support of the crew we will use the same methods and tools that on ISS(books, movies, music, news and reviews, etc.).Means of psychological support will be established after taking into account the opinion of

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each member of the crew and loaded prior to the mission. Surveys of news will be transmit-ted three times a week over a computer network.

6 Quick start guide

In accordance with the Regulations, the beginning of candidates selection for cosmonauts isthe moment of placing online MVK solution to hold it. Relevant notice on the site shouldcontain information on the timing and form of statements and documents participating inselection, amount of astronaut candidates, conditions and order of selection.According to the following terms, ”applicant for selection” is a citizen of Earth, whoseapplication to participate in the selection of candidates for the astronauts is accepted byCommission of the competition. ”Candidate” is a person selected from among applicants forselection for training for manned flight at the approved program. Applicants for selectionare persons whose applications for participation in the selection with a package of supportingdocuments were accepted by the Competition Commission before the deadline. Applicantsare considered qualified in case MVK has chosen them the best in performing professionalastronauts activities.The Regulations introduce some serious limitations for applicants: their age should not ex-ceed 33 years. Applicant may be declared unfit for further selection for non-compliance ofany of its specified requirements (criteria). In this case into the selection of candidates for theastronauts persons against whom criminal proceedings are pending are not allowed; havingunexpunged (outstanding) conviction as well as violation the legislation of their country forthe Protection of State Secrets are unfit too.

The document sets out the requirements to be met by applicants:• requirements for education, professional qualifications and experience of applicants• medical requirements• moral and psychological demands• requirements for physical fitness• requirements for professional competence

Applicants are required to have higher education (”bachelor”, ”graduate” or ”master”)in engineering or medical specialty, with priority in the selection of persons with experiencein the aviation and aerospace industry. Applicants must have work experience of at least 5years, with at least 3 years of working in one place.Pilots and test pilots need to have higher education and proficiency flight not less than thirdclass, and also not less than 3 years of experience in flight (service) in the organizationsassociated with the operation, use, testing or aviation and space technology.

Noteworthy is the Regulation’s requirement that military experts who have successfullypassed the selection can be enrolled in the astronaut force only after leaving the military.Requirements for the medicine, determining the degree of life - be astronauts are set out inthe Regulations on Medical Examination and monitoring the health of candidates for the

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astronauts, astronauts and astronauts instructors.

During selecting applicants for compliance with the requirements of the psychologicalqualities of the candidates are evaluated in:• personality: individual psychological temperament, individually-typological, charactertraits, the type of higher nervous activity, abilities, needs, attitudes, motives, etc.;• professionally important psychological: memory, attention, thinking, perception;• moral: moral values, attitudes towards people, willingness to self-improvement, etc.;• socio-psychological: the ability to interact interpersonal positively, tolerance and pronenessto conflict.• be evaluated intellectually creative potential applicants, including cognitive and creativeactivity, the willingness and ability to learn.• with the use of test methods are also investigated psychological immunity, ability to workunder time pressure, cognitive behavior, etc.• in selecting applicants for compliance with the moral and ethical requirements evaluatedare:• biographical data, including information about the identity of the candidate and his family;• training and employment, including data on the behavior, activities and relationships inthe team;• motivation for choosing a new profession;• features and behavior in normal and emergency situations;• bad habits, etc.

Continuation of the text in Annex

7 Mission control center

1. Simulator spacecraft (SC) should be a testing and training mean for the Mission ControlCenter (MCC), and provide compliance testing , accuracy and completeness related to space-craft operating procedures . The simulator must also provide an effective means of testingthe readiness of the ground control in terms of its basic functions for processing telemetry,telecommand preparation and delivery , and display data.

2. SC model should accurately represent the characteristics of the SC, as they are con-trolled by the Operator SC MCC in all phases of flight. For Interplanetary manned spacecraft(IMS) control must create a computer model, as well as ground-based analogue ship for flightsimulation and possible emergency situations on board, as well as to find ways of counteringthem when they occur.

3. For the purpose of receiving and inspection of the simulator must be ensured thatpossible tracking to record all necessary data for offline analysis. Suitable autonomous ser-vice analysis should also be provided.

4. The simulator must provide mode of operation in which it left with the duty not later

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than 2 minutes after, as well as to respond to the simulation commands issued by the oper-ator from the keyboard for 2 seconds. The simulator must respond to the request operationfor 5 seconds.

5. Need to develop software for spacecraft control, including software simulator, put itin the DRM software and debug if the use of such software is required on the operationaland technical documentation (OTD) on the management of SC.

6. To control the spacecraft can be used by MCC and other available funds of the CentralResearch Institute of Machine Building (CRIMB).

7. MCC should contain all the necessary equipment and software to perform the tests inorbit and normal operation. MCC should in particular contain a means for processing anddisplay telemetry data check instruction before sending, validation program execution com-mand, receiving telemetry data and management data for analysis of anomalous situations,the initiation of the measurement range and the angle of observation and motion control SCthe orbit and its orientation, due to the management stations and receiving TMI and landfillrun.

8. When operating the spacecraft must not have potential single failure points, ie duringnormal operation should not be the potential deterioration of the spacecraft or its satisfac-tory operation by unauthorized issuing any command.

9. There should be no potential to cause irreparable damage to the spacecraft by theerroneous granting aboard one telecommand.

10. Must be capable of continuously transmitting telemetry information about the cur-rent state of the spacecraft at the expense of the GCC for the duration of active existence.

11. It shall be possible to lock the team work with ground control (GC) all automaticdevices. Any deviation from this requirement must be explained.

12. It shall be possible to lock the team with GC any equipment having a waiver of anyautomatic connections that may occur in the future, including in survivability mode.

13. It must be possible, as a means of overcoming unforeseen circumstances, any lock-board control mode using either the new regime loaded in the onboard computer with NFC,or by using the control mode by commands from the GCC, in which data is read from therespective sensors and control signals are generated for relevant executive bodies.

Due to the fact that the IGC flight passes at a considerable distance from the Earth tocommunicate with the crew and obtain telemetric information from the board, as well astransfer of control commands to be used aboard Ground stations receiving sufficient powerand covering all the space around the Earth. For this purpose, suitable antenna AmericanNetwork Deep Space Network, which currently provide a link with a lot of automated vehi-

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cles, studying objects in the solar system, including AMC ”Voyager 1” , which reached theborders of our system.

8 The cost of the mission

Analyzing this table, we concluded that Proton-M and Soyuz-FG are the most suitable car-rier rockets for the mission. Our project includes five launches of Proton-M which will carryfour booster blocks Breeze-M and IMS to the LEO as well as one launch of Soyuz FG todeliver the crew to the IMS. The choice of these rockets was made due to several aspects:1) Proton-M and Soyuz FG are produced in Russia and have the Russian Baikonur Cosmod-rome as the launch site. This fact is reflected in their cost in best way for us.2) Proton-M in its current modifications has been used since 2001 (10-12 launches per year)and currently has an excellent statistics of successful launches (91% successfull).3) Today Soyuz-FG is the main mean of delivering astronauts to the ISS, as it has no morereliable (100% successful launches) and cheaper analogs.

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According to our calculations, the approximate total cost of the mission is $ 1.3 billion,which is less than the initial evaluation of $3 billion given by Dennis Tito’s team by morethan a half. Reaching the cost of only $1,3 billion became possible through the use of carrierrockets and equipment mainly produced in Russian and partly in Europe. These reducedthe level of economic costs. The main expense items are the creation of the InterplanetaryManned Spacecraft and carrying it to the Mars flyby trajectory.

9 Conclusion

Before summing up our work on the flyby mission within Mars Society International StudentDesign Competition, we would like to say few words about Inspiration Mars news. Due tothe lack of financial support and delays in creating heavy and super-heavy-lift launch systemssuch as Falcon 9 Heavy and Space Launch System (SLS) it turns out that the flyby of Marsbecame almost impossible by the year of 2018. On the one hand, it is really disappointing asfar as next such opportunity will only be available in 2031. Yet on the other hand, additionaltime for preparing the mission gives hope that NASA would possibly support a little longerflyby around Venus and Mars. We really look forward to such mission becoming real.

Returning to our work, we would like to say that we tried to fulfil the task laid upon usby the rules of the contest, that is to create a project of flyby mission to Mars starting in2018 using resources existing nowadays.The analysis done showed that among existing heavy-lift launch systems only Proton-M suitsour mission. There is no surprise that exactly this system was chosen as basic for leadingout modules of interplanetary space ship and accelerating blocks. Lack of super-heavy-liftlaunch systems led us to necessity of low-earth orbital joining with further leading out of aspace ship on an interplanetary trajectory. Calculations proved that such approach can bebrought to reality.

Unfortunately, accelerating block Briz-M, which we will be able to use, is not reliableenough. If we take exploitation reliability of accelerating block as 0.92, not taking in accountany adaptations of the construction, and reliability of launch system as 0.975 then in case offive starts, not taking in account reliability of a space ship (if it does not break during theprocess of installation) we will have WHAT IS THAT (coefficient of reliability or what??)reliability coefficient equal (0.924) ∗ (0.9755) = 0.63.Still even such a low calculated reliability allows us to carry out the mission.

Of course, for real manned flights the development of new space equipment will be es-sential, which follows from analysis of existing and developing means of leading out.As a base for our space ship we took a modified module of ATV ship, for in our opinionit mostly suits the demands of mass, capacity and reliability. Moreover, it’s main body iscreated by Italian company Alenia Spazio, which made major part of hermetically sealedmodules for American segment of International Space Station.

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We chose landing section from a manned ship Soyuz-TMA, however it requires furtherimprovement of thermal shield to reach the second cosmic speed. Originally Soviet shipsSoyuz were designed for the moon program. They flew around the moon and came back.The turtles aboard managed to return alive. Onboard systems, medical and scientific equip-ment are based on those made for space station Mir and ISS. These systems proved theirreliability for more than a year long flights. The only complication our team faced is a lackof publicly available information about size, mass and cost of the systems. Thus we managedto make only approximate analysis and calculation of costs.

Anyhow, in first approximation the possibility of a flyby mission was shown by the workof our team. We are sure that the efforts spent are justified at least by the fact that youngpeople all over the world would see what the humanity is capable of in moving further intofar space and what difficulties will stand on our way there.Mars is an understandable goal for our civilization and we really hope that exactly our gen-eration will make this important and meaningful step towards exploration of Solar systemand further moving of humanity into space.

10 Sources:

1. Kosmicheskaya biology and medicine in 2 volumes. Volume 1. Medical support long-duration missions. State Scientific Center of the Russian Federation - Institute for Biomed-ical Problems of the Russian Academy of Sciences.2. Baraboi LM - ”Ionizing radiation” - M.1991.3. Budarkov SG - ”Radiobiological Handbook” - Moscow 19924. VM Petrov, VA Shurshakov Radiation Physics Research on the ISS during the period2001 - 2008 were as follows: Experiment ”Matryoshka -R”. In the book. : Medical bio-logicheskpie research on the Russian segment of the ISS. 2011. T. 2. Pp. 389-426.5. Shibanov GP Habitability and safety of space remaining in the man. M.: Engineering,2007. - 544 p.: Il.6. http://niichimmash.ru/projects/elektron-vm/7. http://papers.sae.org/2006-01-2092/8. http://niichimmash.ru/press/publications/regeneratsiya-vody-i-atmosfery-na-kosmicheskoy-stantsii-opyt-orbitalnykh-stantsiy-salyut-mir-i-mks-p/9. Space Biology and Medicine in 2 volumes. Volume 1. Medical support long-duration mis-sions. State Scientific Center of the Russian Federation - Institute for Biomedical Problemsof the Russian Academy of Sciences.10. AV Vasin, E.A.Kobzev, Improving prevention of adverse effects of weightlessness duringtraining astronauts.11. http://www.nasa.gov/pdf/284273main Radiation HS Mod1.pdf12. http://www.swpc.noaa.gov/SolarCycle/13. http://ligaspace.my1.ru/news/2013-02-24-43414. Getselev IV Radiation situation on board the spacecraft Tsipko 2001.15. Space Weather Effects on Humans: in Space and on Earth Proceedings of the Inter-

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national Conference Space Research Institute, Moscow, Russia, June 4-8, 2012, Ed. A.I.Grigoriev, L.M. Zeleny

11 Team

Alexandr Khokhlov -Saint Petersburg StatePolytechnical University;

Nikolay Shelakhaev -The University of AppliedSciences Wiener Neustadt;

Nataliya Lakhvich -Bauman Moscow StateTechnical University;

Anna Golovchenko -Voronezh State University;

Anna Kuksa - PirogovRussian National ResearchMedical University;

Olesia Dogonasheva -Saint-Petersburg NationalResearch University OfInformation Technologies,Mechanics and Optics.

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Anna Pavlysh - StateUniversity of Saint-Petersburg;

Ilya Ovchinnikov -Moscow Aviation Institute;

Alexander Farafonov- Bauman Moscow StateTechnical University;

Andrey Parfenov -State University of Saint-Petersburg;

Daniil Prokopenko -Moscow Aviation Institute;

Anton Matveev - Bau-man Moscow State Techni-cal University;

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ANNEX

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