Navigation Past Present and Future

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AE 457 - SPACE FLIGHT NAVIGATION & GUIDANCE

AE 641 - INTRODUCTION TO NAVIGATION AND GUIDANCE

DISCLAIMER: MOST MATERIAL PRESENTED HERE IS TAKEN FROM VARIOUS INTERNET

WEBSITES. CREDIT IS CITED WHERE THE SOURCE OF THE MATERIAL IS KNOWN. NO CLAIM

OF ORIGINALITY IS INTENDED. THE MATERIAL IS GATHERED HERE FOR EDUCATION, WITH

NO FINANCIAL INTERESTS.

Hari B. Hablani

Department of Aerospace Engineering Spring2012


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Ref.: unknown


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EXPLORATION IN 14-16CENTURIES


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Trading routes used around the 1st century CE centered on the Silk Road

http://en.wikipedia.org/wiki/Trade_route


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Chola territories during Rajendra Chola I, c. 1030http://en.wikipedia.org/wiki/Chola_dynasty


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Map with the main voyages of the age of discoveries, 1482-1524

http://en.wikipedia.org/wiki/Age_of_Discovery


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Age of Discovery: Overview

http://en.wikipedia.org/wiki/Age_of_Discovery

The Portuguese began systematicallyexploring the Atlantic coast of Africa from1418, under the sponsorship of PrinceHenry I

In 1488 Bartolomeu Dias reached theIndian Ocean by this route.

In 1492, racing to find a trade route to

Asia, the Spanish monarchs fundedChristopher Columbuss plan to sail westto reach the Indies by crossing the

Atlantic. He landed on an unchartedcontinent, then seen by Europeans as anew world, America.

To prevent conflict between Portugal andSpain, a treaty was signed dividing the

world into two regions of exploration,where each had exclusive rights to claimnewly discovered lands.

In 1498, a Portuguese expeditioncommanded by Vasco da Gama finallyachieved the dream of reaching India bysailing around Africa, opening up directtrade with Asia.

Soon, the Portuguese sailed furthereastward to the valuable s ice islands in

East and west exploration overlapped in1522, when Portuguese navigatorFerdinand Magellan led a Spanishexpedition West, achieving the firstcircumnavigation of the world, whileSpanish conquistadors explored inland

Americas, and later, some of the SouthPacific islands.

Since 1495, the French and Englishand, much later, the Dutch entered therace of exploration after learning ofthese exploits, defying the Iberianmonopoly on maritime trade bysearching for new routes, first to thenorth, and into the Pacific Ocean around

South America, but eventually byfollowing the Portuguese around Africainto the Indian Ocean, discovering

Australia in 1606,

New Zealand in 1642, and

Hawaii in 1778.

Meanwhile, from the 1580s to the 1640s

Russians explored and conqueredalmost the whole of Siberia.


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CHRISTOPHER COLUMBUS AND THE SPANISH EMPIRE

http://www.ucalgary.ca/applied_history/tutor/eurvoya/columbus.html

Prior to 1492 and Christopher Columbus' voyage to theAmericas, Spain's only possession of any consequenceoutside Europe were the Canary Islands.

By the mid-sixteenth century, however, Spain would controlmuch of the Caribbean, large portions of the Americas andparts of Africa.

This rapid acquisition of overseas possessions wasaccompanied and aided by the establishment andconsolidation of hegemony in Europe through a series ofpolitical marriages.

Instead of waging battles to spread its power and influence,the prolific Habsburgs preferred to use the bonds of marriageto link their household to others. This ensured that thenumber of threats to Habsburg possessions in Europe would

remain at a minimum and would free Spanish resources toconquer overseas territory.

Spain politically, socially, and economically dominated herlarge empire and, unlike the Portuguese, who were limited tocoastal regions and tenuously held outposts, the Spaniardswere able to penetrate inland and establish much morepermanent settlements.


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Portuguese trade routes (blue) since Vasco da Gama's 1498 journey and

the Spanish Manila-Acapulco galleons trade routes (white) established in

1568

http://en.wikipedia.org/wiki/Trade_route


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Vasco da Gama's passage to

India

A 16th-centuryPortuguesship usedin theIndianOceantraderoutes

http://www.bbc.co.uk/history/british/tudors/vasco_da_gama_01.shtml


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http://people.hofstra.edu/geotrans/eng/ch2en/conc2en/map_VOC_Trade_Network.html


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http://www.mapsofindia.com/maps/india/india-political-map.htm


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Air Routes In Indiahttp://www.jaipurmart.net/air_route_map_of_india.htm


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Global Air Routeshttp://www.airlineroutemaps.com/


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AAI manages 126 airports, which include 11 international airports, 89 domestic airportsand 26 civil enclaves at Defense airfields.

All major air-routes over Indian landmass are Radar covered (24 Radar installations at 11locations) along with VOR (Omnidirectional Radio Range) /DVOR (Doppler VOR)coverage (72 installations) co-located with Distance Measuring Equipment (71installations)

39 runways provided with ILS installations; Night Landing Facilities at 36 airports; andAutomatic Message Switching System at 15 airports.

Automatic Dependence Surveillance system, using indigenous technology, at Kolkataand Chennai Air Traffic Control Centers, enabling effective Air Traffic Control over

oceanic areas using satellite communication.

Use of remote controlled VHF coverage, along with satellite communication links, hasgiven added strength to our Air Traffic Management System.

Linking of 80 locations by V-Sat installations vastly enhances Air Traffic Managementand safety of aircraft operations besides enabling administrative and operational controlover our extensive airport network.

http://www.aai.aero/public_notices/aaisite_test/main_new.jsp


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Functions of AAI

Control and management of the Indian airspace extending beyond the territorial

limits of the country, as accepted by ICAO

Design, Development, Operation and Maintenance of International and Domestic

Airports and Civil Enclaves.

Construction, Modification and Management of Passenger Terminals

Development and Management of Cargo Terminals at International and Domestic

airports.

Provision of Passenger Facilities and Information System at the Passenger

Terminals at airports.

Expansion and strengthening of operation area viz. Runways, Aprons, Taxiway, etc.

Provision of visual aids.

Provision of Communication and Navigational aids viz. ILS, DVOR, DME, Radar,

etc.

http://www.aai.aero/public_notices/aaisite_test/main_new.jsp


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Air Navigation Services

In tune with global approach to modernization of Air Navigation infrastructure for

seamless navigation across state and regional boundaries, AAI has plans fortransition to satellite based Communication, Navigation, Surveillance and Air Traffic

Management.

A number of co-operation agreements and Memoranda of Co-operation have been

signed with US Federal Aviation Administration, US Trade and Development Agency,

European Union, Air Services Australia and the French Government, co-operative

projects and studies initiated to gain from their experience.

Through these activities more and more executives of AAI are being exposed to

the latest technology, modern practices and procedures to improve the overall

performance of Airports and Air Navigation Services.

New and improved procedure have been adopted with induction of newequipments. Some of the major initiatives in this direction are introduction of:

Reduced Vertical Separation Minima (RVSM) in Indian airspace to increase

airspace capacity and reduce congestion in the air and

implementation of GPS and Geo Augmented Navigation GAGAN jointly with

ISRO which, when in operation, would be one of the four such systems in theworld.


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Precision Approaches and their Accuracies

Courtesy:Per Enge, Aircraft Landing Systems Based on GPS & GALILEO


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Precision Landing Approaches with Local Area Augmentation System

(1 of 2)

GAGAN is a space-based augmentation system, in contrast with a

wide area augmentation system (WAAS) or local area augmentation

system (LAAS)

For precise landing approaches, the Local Area Augmentation System

(LAAS) is employed which works in a sequence depicted in the figures

below:

Courtesy:www.faa.gov


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Precision Landing Approaches with Local Area Augmentation System (2 of 2)


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Aircraft Navigation

Using GAGAN and IRNSS


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GPS Augmentation for Civil Aviation

Courtesy: ISRO


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GAGAN: GPS Aided Geostationary Satellite Augmented

Navigation System

Courtesy: ISRO


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Courtesy:www.isro.org


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Use OF GAGAN and IRNSS for Position, Velocity,

and Time Determination

The GPS receivers on the ground stations receive the signals from four or

more GPS satellites.

The receivers comprehend the navigation data contained in the signals

and send a message to the Master Control Centre (MCC) where the

errors in the GPS signals are calculated.

A message containing the corrections in the received GPS signals is

generated at the MCC and is sent to the Land Uplink Stations, whichtransmit these messages to the geostationary satellites.

The geostationary satellites broadcast these corrections in order that the

navigating vehicle, equipped with a GPS receiver, receives these

correction messages and corrects the GPS signals accordingly. In this

manner, the navigating vehicle can determine its position, velocity andtime with an increased accuracy.

The above technique uses the GPS signals. In future, after the

implementation of the IRNSS, the GPS satellite signals would be replaced

by the IRNSS signals.


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An independent regionalnavigation system coveringIndia and an area of about 500Km around India

The system will consist ofseven satellites, 3geostationary and 4geosynchronous

The target position accuracy is

of less than 10 m over theIndian subcontinent and within20 m over the Indian Ocean

Courtesy: ISRO

IRNSS Satellites: Three Geostationary and Four Geosynchronous A


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IRNSS Satellites: Three Geostationary and Four Geosynchronous A

Nice Geometry for Navigation

Courtesy: ISRO


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Global Navigation

System

Controlled by the

US Government

Medium Earth Orbit

Satellites

Regional

Navigation System

It will be under full

control of the

Government of

India Geosynchronous

Orbit Satellites

IRNSS GPS


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Inertial Measurements to Aid GPS Tracking

P = position, V = velocity, A = attitude, T = time,

rho = range, rho_dot = range rate, del_theta = incremental attitude,

del_v = incremental_velocityCourtesy:Per Enge, Aircraft Landing Systems Based on GPS & GALILEO

Defence Research & Development Organization (DRDO)


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Defence Research & Development Organization (DRDO)

Ministry of Defence, Govt of India

courtesy: DRDO websites

DRDO is a network of more than 50 laboratories deeply engaged in developing defensetechnologies covering various disciplines such as aeronautics, armaments, electronics, combatvehicles, engineering systems, instrumentation, missiles, advanced computing and simulation,special materials, naval systems, life sciences, training, information systems and agriculture.

The Organization employs over 5000 scientists and about 25,000 other scientific, technical andsupporting personnel.

Several major projects for the development of missiles, armaments, light combat aircrafts,radars, electronic warfare systems etc are on hand and significant achievements have been madein several such technologies.


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VISIONMake India prosperous by establishing world class science and

technology base and provide our Defence Services decisive edge byequipping them with internationally competitive systems and solutions.

MISSION

Design, develop and lead to production state-of-the-art sensors,

weapon systems, platforms and allied equipment for our DefenceServices.

Provide technological solutions to the Services to optimise combateffectiveness and to promote well-being of the troops.Develop infrastructure and committed quality manpower and buildstrong indigenous technology base.

courtesy: DRDO websites


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Defence Research andDevelopment Laboratory (DRDL)Defence Research Complex, Kanchanbagh, Hyderabad

Formerly directed by A.P.J. Abdul Kalam,

The main research center for the Integrated Missile Development Program

DRDL is responsible for the Integrated Guided Missile Program, whichincludes five components:

Prithvi, a surface-to-surface battlefield missile;

Nag, an anti-tank missile (ATM);

Akash, a swift, medium-range surface-to-air missile (SAM); Trishul, a quick-reaction SAM with a shorter range; and

Agni, an intermediate range ballistic missile.


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Prithvi Agni III Test Flight


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DRDO's Prithvi-II, Agni-I, Agni-II, Agni-IIAT, Agni-3 (TD,+,++,SL)

[Image Arun Vishwakarma]

DRDO's Prithvi-II, Agni-I, Agni-II, Agni-IIAT, Agni-3 (TD,+,++,SL)[Image Arun Vishwakarma]
http://www.bharat-rakshak.com/MISSILES/Images/Prithvi%20&%20Agni%202,3,SL%20r15c-1500pixle.jpghttp://www.bharat-rakshak.com/MISSILES/Images/Prithvi%20&%20Agni%202,3,SL%20r15c-1500pixle.jpghttp://www.bharat-rakshak.com/MISSILES/Images/Prithvi%20&%20Agni%202,3,SL%20r15c-1500pixle.jpghttp://www.bharat-rakshak.com/MISSILES/Images/Prithvi%20&%20Agni%202,3,SL%20r15c-1500pixle.jpghttp://www.bharat-rakshak.com/MISSILES/Images/Prithvi%20&%20Agni%202,3,SL%20r15c-1500pixle.jpg


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[ g ]

Agni-IAgni-II Agni-

IIATAgni-3 TD Agni-3 A Agni-3 B Agni-3 C Agni-3SL

Length (m) 15 20 20 16.7[0.A] 17[0.A] 17[0.A] 14.6 12

Diameter (m) 1 1 1.2 2 2 2 2 2

Launch Weight(kg) (Including Payload)

12,000 16,000 27,000 48,300 [0.A] 51,500(Estimated)

53,100(Estimated)

44,400(Estimated)

37,600(Estimated)

Propellant Solid(HTPB/AP/AI)

High energy, high density Solid Propellant(HTPB/AP/AI)

Number of Stages 1 2.5 2.5 2 3 4 3 3

Payload - kg 800 -1,000

800 -1,000

300 -1,000

600 - 1,500[1]2,490

(conventional)

1,500 600 - 3490 600 - 3490(8 - 12 RV )

600 - 3490(8 - 12 RV )

Warhead Strategic nuclear (15 KT to 250 KT), conventional [2]HE-unitary, penetration, sub-munitions, incendiary or fuel airexplosives.

Guidance Strap Down - INS (InertialNavigation System), optionally

augmented byGPS terminalguidance with possible radar scene

correlation.

INS (full Inertial platform)[3], optionally augmented by

GPS/GLONASS/IRNSS, possibly with radar scene correlation.

Range (Payload) 850 km(1,000kg

)

3,300 km(1,000kg)

,4,450 km(700kg)

4,000 km(1,500kg

)

5,500 km(1,500kg) [4]

8,100 Km(1,500kg)

>18,000km[4.A]

11,500

km

10,300

(1050kg)

5,200Km

(1,400Kg),11,600Km

(700kg)

CEP Accuracy 120meters

40meters

20meters(estimated)

16 meters[4.B]

Launch Platform 8 x 8 Tatra TELAR (Transporter

Erector Launcher)Rail Mobile Launcher

8 x 8 Tatra TELARRail Mobile Launcher

Submarine

Launcher


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Shourya lifts off from the Integrated Test Range

at Balasore, Orrissa, on November 12, 2008

The successful first test of the surface-to-surface Shourya missile from the IntegratedTest Range at Chandipur-on-sea nearBalasore in Orissa on November 12

Shourya is a hypersonic missile; it can reach avelocity of Mach 6 even at low altitudes.On November 12, it reached

a velocity of Mach 5, heating up its surface to700+ degree Celsius.

The missile performed aningenious maneuver of rolling to spread the heatuniformly on its surface. Its high maneuverabilitymakes it less vulnerable to present-day anti-missile

defense systems.

Shourya can reach targets 700 km away, carrying bothconventional and nuclear warheads. It is 10 metres long and74 cm in diameter and weighs 6.2 tonnes. It is a two-stagemissile and both its stages are powered by solid propellants.Its flight time is 500 seconds to 700 seconds.

Shouryas Navigation system uses ring-laser gyros and


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Shourya s Navigation system uses ring-laser gyros and

accelerometers

Ref.: unknown

In the estimate of V.K. Saraswat, Chief Controller, Missiles and Strategic Systems, DRDO,Shourya is among the top 10 missiles in the world in its class, with its high-performancenavigation and guidance systems, efficient propulsion systems, state-of-the-art controltechnologies and canisterised launch signature it cannot be easily detected bysatellites and makes its deployment easy.

Shourya was ejected from the canister by a gas generator, developed by the High EnergyMaterials Research Laboratory (HEMRL), Pune, and the ASL. The gas generator, locatedat the bottom of the canister, fires for about a second and a half. It produces highpressure gas, which expands and ejects the missile from the tube. The missile has sixmotors; the first one is the motor in the gas generator.

The centerpiece of a host of new technologies incorporated in Shourya is its ring-laser

gyroscope and accelerometer. The ring-laser gyroscope, a sophisticated navigation andguidance system made by the RCI, is highly classified technology. Advanced countrieshave denied this technology to India. In Shouryas flight, it functioned exceptionally well.

M. Natarajan, Scientific Adviser to the Defense Minister and Director-General of theDRDO, praised the way the ring-laser gyroscope functioned in Shouryasflight. We flewour own navigation system in this missile. It worked very well. This is an important stepforward for the country in the navigation of missiles, aircraft and spacecraft. No othercountry will provide India this navigation system, he said.

Aft th fl l l h f th f t f i il Sh th


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After the flawless launch of the surface-to-surface missile Shourya, the

DRDO is set to fire an interceptor missile.

Missile technologists of the DRDO are engaged in preparing for the launch of aninterceptor missile.

The launch, scheduled to take place in the second half of December, will feature twomissiles.

While the target missile, with a range of 1,500 km, will be fired from a ship in the Bay ofBengal towards Wheeler Island, located off the Orissa coast, the interceptor missile,which will be fired from the island, will engage an incoming enemy missile in theterminal phase of its flight at an altitude of 80 km in the exo-atmosphere and decimate it.

The enemy missile will be a modified version of Dhanush.

Intense high-technology work at the Defence Research and Development Laboratory(DRDL), the Advanced Systems Laboratory (ASL), and the Research Centre, Imarat (RCI),all located on the serene DRDO campus.

Agni-V will have a range of 5,000 km. It will be launched in 2010.

The ASL is also preparing for a flight trial of Agni-IIIA in 2009. The missile will be anadvanced version of Agni-II, which has a range of more than 2,500 km.

O N b 27 I di i d t f l b lli ti


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On November 27 India carried out a successful ballistic

missile interception test.

The target vehicle was a modified Prithvi SRBM fired in a trajectory meant to

simulate the terminal phase maneuver of a longer range missile.

The interceptor was fired a minute after the target, and intercepted it an

altitude of 50km.

The interceptor is 10-12 metres long, and has two stages. It uses an active

seeker guidance system in its terminal phase.


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A i II I t di t R B lli ti Mi il di l d t th R bli D


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Agni-II Intermediate Range Ballistic Missile displayed at the Republic Day

Parade on New Delhi's Rajpath, January 26, 2004


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A i 3 D2 ASL' A Ch d


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Agni-3 D2: ASL's A.Chander,Defense MoS Pallam Raju,with users[Source: India Strategic]
http://www.bharat-rakshak.com/MISSILES/Images/IndiaStrategic_May%2007_Agni_article_Page_16-PhotoOp.jpg


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Hindustan Aeronautics Limited (HAL) came into existenceon 1st October 1964. The Company was formed by the merger of HindustanAircraft Limited with Aeronautics India Limited and Aircraft ManufacturingDepot, Kanpur.

The Company traces its roots to the pioneering efforts of an industrialist withextraordinary vision, the late Seth Walchand Hirachand, who set up Hindustan

Aircraft Limited at Bangalore in association with the erstwhile princely State

of Mysore in December 1940.The Government of India became a shareholder in March 1941 and took overthe Management in 1942.

Today, HAL has 19 Production Units and 9 Research and Design Centres in 7locations in India. The Company has an impressive product track record

12 types of aircraft manufactured with in-house R & D and 14 typesproduced under license.

over 3550 aircraft

3600 engines, and

overhauled over 8150 aircraft and 27300 engines.

HAL has been successful in numerous R & D programs developed for bothDefence and Civil Aviation sectors.


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HAL Products


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HAL Products

Chief of Air Staff Air Chief Marshal F H Major flew the Advanced Light Helicopter


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Chief of Air Staff Air Chief MarshalF.H. Major flew the Advanced Light Helicopter(ALH) Dhruv -- powered by the Shakthiengine in Bangalore

Air Chief Marshal F.H. Major, PVSM, AVSM, SC, VM, ADC, Chief of Air Staff

with Shri Ashok K Baweja, Chairman HAL with the weaponised Dhruvhelico ter ALH at Helico ter Division of HAL


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HAL has made substantial progress in its currentprojects : Dhruv, which is Advanced Light Helicopter (ALH)

Tejas - Light Combat Aircraft (LCA)

Intermediate Jet Trainer (IJT) Various military and civil upgrades.

HAL has played a significant role in India's spaceprograms by participating in the manufacture of

structures for Satellite Launch Vehicles like PSLV (Polar Satellite Launch Vehicle)

GSLV (Geo-synchronous Satellite Launch Vehicle)

IRS (Indian Remote Satellite)

INSAT (Indian National Satellite)

LIGHT COMBAT AIRCRAFT (LCA) TEST FLOWN SUCCESSFULLY 4


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LIGHT COMBAT AIRCRAFT (LCA) TEST-FLOWN SUCCESSFULLY on 4

January, 2001

LCA is an advanced technology, single seat, single engine,

supersonic, light-weight,

all-weather, multi-role,

air superiority fighter designed for

air-to-air, air-to-ground and

air-to-sea combat roles.

The purpose of flight test program was to validate a number of

advanced technologies incorporated in LCA. These include:

Unstable configuration, quadruplex fly-by-wire digital flight control system,

integrated avionics with glass cockpit,

advanced composite materials for primary structure and

a novel utility systems management system.

LCA T j


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LCA Tejas

http://en.wikipedia.org/wiki/File:Lca1.jpg

Indian Navy has shown interest in the Air Force'sAd d M di C b t Ai ft


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Advanced Medium Combat Aircraft

http://en.wikipedia.org/wiki/File:Medium_combat_aircraft.jp

g

INS Vikrant circa 1984 carrying a unique complement of Sea Harriers,


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Sea Hawks, Allouette & Sea King helicopters and Alize ASW.jpg

http://en.wikipedia.org/wiki/Indian_Navy

INS Mysore on deployment in the Gulf of Aden to check


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INS Mysore on deployment in the Gulf of Aden to check

piracy


Indian Navy Tu-142 and IL-38SD stationed at Arakkonam Naval


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Indian Navy Tu 142 and IL 38SD stationed at Arakkonam Naval

Air Station


INS Shivalik the first indigenous stealth ship of the Indian


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g p

navy


INS Sindhurakshak (S63), a Sindhughosh class


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( ) g

submarine


Conceptual Drawing of INSArihant, India's first ballistic


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p g ,

missile nuclear submarine


INS Arihant India's first ballistic missile nuclear submarine


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INSArihant, India's first ballistic missile nuclear submarine

http://en.wikipedia.org/wiki/INS_Arihant

Career (India) Name: INSArihant Builder: Shipbuilding Centre (SBC), Visakhapatnam, India

Launched: 26 July 2009

Status: Sea trials

General characteristics

Class and type:Arihant-class submarine

Type: SSBN or SSGN

Length: 111 m (364 ft)

Beam: 15 m (49 ft) Draft: 11 m (36 ft)

Propulsion: PWR using 40% enriched uranium fuel (80 MWe ); one turbine(47,000 hp/70 MW); one shaft; one 7-bladed, high-skew propeller

(estimated) Range: unlimited except by food supplies

Test depth: 300 m (980 ft) (estimated) Complement: 95100 officers and men

Sensors and processing systems: BEL USHUS

Armament:

6 x 533mm torpedoes12 x K-15 Sagarika SLBMShaurya missile (expected)

Satellite Launch Vehicle 3 (SLV 3)


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Satellite Launch Vehicle 3 (SLV - 3)

Project Director: Abdul Kalam

Weight (t) : 17

Payload (kg) : 40

Height(m) : 22 Orbit : Low - earth orbit


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Polar Satellite Launch Vehicle (PSLV)


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Polar Satellite Launch Vehicle(PSLV)

Developmental flights completed with successful thirddevelopmental launch in March 1996.

IRS-1D launched by PSLV-C1 on September 29, 1997.

Suitable for launching 1,000-1,200 kg class of remote sensingsatellites into polar sun-synchronous orbit.

IRS-P4 (OCEANSAT) and two piggy back small satellites

Korean KITSAT-3 (Korean Institute of Technology) and German TUBSAT (Technical University of Berlin)

launched by PSLV-C2 on May 26,1999.

Technology Experiment Satellite (TES) of ISRO, and

BIRD (a small satellite mission) of DLR Germany,

PROBA (Project for Onboard Autonomy) of Belgium

into their intended orbits launched by PSLV-C3 on October 22,2001.

The 1060 kg KALPANA-1 satellite - into a GeosynchronousTransfer Orbit (GTO) launched by PSLV-C4 on September 12,2002.

RESOURCESAT-1 (IRS-P6) satellite launched by PSLV-C5 onOctober 17, 2003.

CARTOSAT-1 and HAMSAT satellites launched by PSLV-C6 on

Weight (t) : 294Payload (kg) :

1000-1200Height (m) : 44.43Orbit : Polar orbit


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Satish Dhawan Space Center (SDSC), SHAR, the Launch Station


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for GSLV


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LN-100G Inertial Navigation System with Embedded


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GPS

By combining the Zero-lock LaserGyro, (ZLG), with the latesttechnology, electronics, and GPS,the LN-100G represents the highest

quality INS/GPS in the world.

Embedded GPS inertial system 0.8 nmi/hr free inertial Inertial, GPS, and hybrid navigation solutions SPS, PPS, all-in-view, and GRAM/SAASM (?) GPS receivers available Low power, lightweight

High MTBF (?) Two dual 1553B data bus terminals High integrity, endurance tested design Validated Ada-based software Nondithered RLG (No acoustic noise; no SAR jitter) Ease of missionization, >70 applications to date


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ISRO I ti l S t U it (IISU)


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ISRO Inertial Systems Unit (IISU)

Carries out development of inertial sensors and systems for satellites

and launch vehicles covering navigation systems, satellite inertial

systems, bearing and space tribology, and inertial systems integration

and simulation.

Facilities include precision fabrication, assembly, integration andtesting.

Achievements include development of inertial systems for ISRO

launch vehicles and satellites, solar array drive assemblies, scanning

mechanisms, etc. Currently engaged in development of Inertial Navigation System for

PSLV, GSLV, INSAT and IRS satellites.


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Additional Sources

Visit websites of Northrop Grumman, Honeywell,

Systron Donner,. for much more details.

GPSoft toolboxes

GIPSY from Jet Propulsion Lab, Cal Tech, Pasadena

Three-Axis Motion Simulator for Gyro


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Three Axis Motion Simulator for Gyro

Testing and Calibration

Courtesy: Zetatek;http://www.zetatekindia.com/products_motinsimulators.htm

INS d N Aid f Ci il A i ti


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INS and Nav-Aids for Civil Aviation

Introduction to Civil Aviation

Specific references

Dead reckoning (that is, Inertial Navigation: rate of changeof lat, long; relative bearing, distance on great circle)

Nav Aids: VHF Omni-directional range (VOR),

DME (distance measuring equipment),

Tactical Air Navigation (TACAN),

Instrument Landing System (ILS),

LORAN-C (Long Range Navigation),

OMEGA,

RADAR (Radio detection and ranging)


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INS for Civil Aviation

Fundamental Principals of Inertial Navigation 1-d, 2-d strapdown navigation, 2-d rotating,

3-d strapdown navigation system: General Analysis

Navigation with respect to an inertial frame

Navigation with respect to a rotating frame, ECEF

Navigation in Local Geographic Navigation Frame, NED: Vectorequations and scalar equations

Terrestrial Navigation

Shape of the Earth: Ref. Ellipsoid, Geoid, WGS, geocentric and geodeticlatitudes; variation of g

Revised transport rate (rate of change of lat, lon) in geodetic frame ECEF coordinates from lat-lon-height

Geodetic lat-lon-height from the ECEF coordinates using Newton-Raphsontechnique (Prob. 4.2-4.3, Rogers)

C AE 457 S Fli ht N i ti & G id


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Course AE 457 - Space Flight Navigation & Guidance

Navigation: Fundamentals of Navigation

Stellar navigation

inertial navigation

radio and radar based navigation systems,

satellite based navigation systems, global positioning systems(GPS)

Performance comparison of various types of navigation systems.

Guidance:

Fundamentals of Guidance, intercept geometry and collisiontriangle,

proportional navigation and guidance, concept of miss distance and line of sight.

Augmented proportional navigation and guidance,

command to LOS guidance and

beam rider guidance

Strategic consideration, pulsed guidance and Lambert guidance.

Concept of Kalman filters, fading memory filters and noise

AE 641 I t d ti t N i ti d G id


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AE 641 - Introduction to Navigation and Guidance

Navigation: Fundamentals of Navigation,

Stellar Navigation,

Inertial Navigation,

Radio and Radar based Navigation Systems,

Global Positioning System,

Other Specialized Navigation Systems,

A Comparison of the various Navigational Aids,

Some Case Studies.

Guidance:

Fundamentals of guidance,

Concepts of Intercept Geometry,

Line of Sight and Collision Triangle,

Proportional Navigation & Guidance (PNG) and Determination of Miss Distance,

Augmented PNG and its comparison with PNG,

Command to LOS & Beam Rider Guidance,

Pulsed and Lambert`s Guidance,

Tactical Vs. Strategic Considerations in Guidance,

Impact of Noise on Guidance, Target maneuver and Evasion

Some References


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Some References

Kayton, M., and Fried Navigation : Avionics Parkinson, B.E. & Spilker, J.J., Global Positioning System : Theory and Applications; Vol.1-2, Progress In Aeronautics

and Astronautics Series, Vol.163, AIAA Publication,1996

Farrell, James L., Integrated Aircraft Navigation, Academic Press, 1976

Farrell, J.L., GNSS Aided Navigation and Tracking, 2007

Farrell, Jay A., Aided Navigation: GPS with High Rate Sensors, McGraw Hill, 2008

Titterton, D.H., and Weston, J.L., Strapdown Inertial Navigation Technology, 2nd Ed., 2004

Kaplan, E.D., and Hagarty, C.J., (Ed.), Understanding GPS: Principles and Applications, Artech House 2006

Groves, P.D., Principles of GNSS, Inertial, and Multisensor Integrated Navigation Systems, Artech House, 2008

Gleason, S., and Gebre-Egziabher,D., GNSS Applications and Methods, Artech House 2009

Grewal, M.S., Weill, L.R., and Andrews, A.P., Global Positioning Systems, Inertial Navigation, and Integration, 2nd Ed.,2007

Grewal, M.S., Kalman Filtering,

Montenbruck, O., and Gill, E., Satel l i te Orbi ts: Models, Methods, App l icat ions, Springer 2000

Noton, M., Spacecraft Navigation and Guidance, Springer 1998

Rogers, R.M., Applied Mathematics in Integrated Navigation Systems, 3rd Ed., AIAA Education Series, 2007

Misra, P., Enge, P., Global Positioning System: Signals, Measurements, and Performance, Ganga-Jamuna Press, 2006

Zipfel, P.H., Modeling and Simulation of Aerospace Vehicle Dynamics, AIAA Education Series, 2000

Siouris, G.M., Aerospace Avionics Systems: A Modern Synthesis

P. Zarchan, Tactical and Strategic Missile Guidance, AIAA Education Series, 5th Edition, 2010

Shneydor, N.A., Missile Guidance and Pursuit, Horwood, 1998

Yanushevsky, R., Modern Missile Guidance, CRC Press, 2008

Siouris, G.M., Missile Guidance and Control Systems, Springer 2004

Weight distribution last


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g

semester: Assignment 20% Midsem: 32%

Quiz 1: 3%

Quiz 2: 3%

Endsem: 42%

Rules and Guidelines of the Institute: Relative weight for in-semester evaluations is typically between 50 and

60 per cent. This will consist of one mid-semester test of two hours duration of about 25-30 per cent weight,

Two quizzes or one quiz and one test

assignments and viva-voce

may also include up to a maximum of 10 per cent of the in-semester marks foractive participation in the class and the initiatives shown by the student.

The semesterend examinations relative weight would be 40 to 50 percent.

It is normally of 3 hours duration and will cover the full syllabus of the

Documents

Navigation Past Present and Future