ANGELS Power Slice Electronics Simulations Overview · 2014. 5. 28. · Student Object Designation Diameter Date (dV) Est. ΔV. Distance. Alex Christensen (2001 QC34) 166 - 743 6/17/2019

RUNNER

Alex Christensen, William Hatch, Keyvan Johnson, Jorden Luke, Benjamin Maxfield, Andrew Mugleston, Cody Palmer, Jackson Pontsler,

Jacob Singleton, Nathan Spencer, Erik Stromberg, Bryce Walker, Cameron Weston

ECE 5240 Space Systems Design Spring 2014

Center for Space Engineering

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Picture of Team

Cameron Weston

Charles Swenson

William Hatch

Jackson Pontsler

Nathan Spencer

Bryce Walker

Keyvan Johnson

Jorden Luke

Alex Christensen

Andrew Mugleston

Benjamin Maxfield

Cody Palmer

Jacob Singleton

Erik Stromberg

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RUNNER

• Research Utility Nanosatellite for Near Earth object Rendezvous

• Acronym Invokes image of a “fast scout” – A spacecraft that is a “Runner”, scout, or explorer that

will characterize the selected Near Earth Object and pave a way for future NASA missions. Future missions include advanced manned and robotic exploration and sample return.

= +

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Presentation Overview • Mission Objectives

• Concepts of Operation

• Spacecraft Description – Science Payload – Propulsion – Navigation – Attitude Determination and

Control System – Power – Communications – Onboard Computing Data Handling – Mechanical Systems – System Budgets

• Summary / Appendix

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Mission Objectives 1 & 2

• Objective 1 Investigate a near-Earth object through proximity operations to characterize its mass, orbital position, rotational dynamics, and appearance in support of future manned and robotic missions.

• Objective 2 Observe the thermal, mechanical, mineralogy and water content at the surface of a near Earth object in order to better understand the formation process of our solar system and to enable the future use of mineral resources from these objects.

NEO Properties Objectives Mass and density Orbit and rotational period Dimensions, appearance, and albedo Surface thermal and mechanical properties Surface mineralogy Near surface water content

http://neo.jpl.nasa.gov/neo/

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Mission Objective 3

• Objective 3 – Demonstrate the technologies required to rendezvous a 6U CubeSat launched

as a secondary payload from the NASA Space Launch System EM-1 mission to a wide variety of near Earth object orbits.

6U CubeSat Deployer

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Objectives and Payload Instruments

• Traceability from Objective 1 to Science Instrument Selection – Mass → Camera & Rendezvous Dynamics – Orbit → Camera & Spacecraft Ranging – Rotational period→ Camera – Dimensions → Camera & IR Camera

• Traceability from Objective 2 to Science Instrument Selection – Chemical constituents → Magnetometer; Ablation

Laser / TOF Mass Spectrometer; Near Range Camera; IR Camera; Magnetometer

– Mechanical structure → Impact Boom, Accelerometer; Near Range Camera; IR Camera

RUNNER ECE5240 Spring 2014 8

• Near-Earth Object Human Space Flight Accessible Targets Study (NHATS) – Total ΔV ≤12 km/s – Launch 2015 - 2020 – Visual Magnitude ≥ 22

• Found 66 Objects – Est. Diameters 69 – 3243 m – Encounter Range from Earth

• 0.015 – 1.334 AU

• Focused on 12 objects – JPL's HORIZONS system

Target NEO’s Considered

Student Object Designation Diameter Date (dV) Est. ΔV DistanceAlex Christensen (2001 QC34) 166 - 743 6/17/2019 5.028 0.015Erik Stromberg (2001 VC2) 100 - 448 12/7/2018 2.102 0.212Bryce Walker (2003 GA) 105 - 469 9/26/2015 4.792 0.331Jacob Singleton 138404 (2000 HA24) 263 - 1177 4/5/2016 3.099 0.350Cody Palmer (2008 DG5) 200 - 893 4/11/2018 3.901 0.371Cameron Weston 152563 (1992 BF) 191 - 853 8/19/2016 3.526 0.402William Hatch (2003 YX1) 115 - 514 11/18/2017 3.018 0.480Jackson Pontsler (2012 DK61) 110 - 491 2/25/2019 3.028 0.487Andrew Mugleston 251732 (1998 HG49) 76 - 340 3/18/2018 3.028 0.790Keyvan Johnson 101955 Bennu (1999 RQ36) 115 - 514 3/26/2018 2.006 0.870Benjamin Maxfield 3361 Orpheus (1982 HR) 272 - 1216 9/23/2017 2.338 1.298Jorden Luke 216985 (2000 QK130) 132 - 590 9/15/2017 2.549 1.336

JPL Small-Body Database

http://neo.jpl.nasa.gov/cgi-bin/nhatshttp://ssd.jpl.nasa.gov/?horizons


• Launch – Secondary payload on SLS EM-1

and/or latter missions – Launch opportunities between 2015-

2020 – Size limited to 6U, 12 Kg CubeSat – Compliance with containerized

specifications of PSC Launcher – No pressurized vessels and no

pyrotechnic devices

• Target – Object within 5 km/s ΔV for

rendezvous after EM-1 ejection

• Communications – Use of the NASA Deep Space Network.

Mission Constraints and Assumptions


Transfer to NEO rendezvous point

Rendezvous

Space Launch System

Loiter near Moon, await NEO phasing

Secondary payload

Proximity operations

Data downlink

DSN

RUNNER Mission Concept

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Perpendicular to Ecliptic Plane

http://lcogt.net/spacebook/equatorial-coordinate-system

Solar Arrays Track Sun

Solar array axis normal to ecliptic

Communication Antenna

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Goal: Eclipse avoidance Dawn-Dusk Orbit / Noon Vector

NEA Rendezvous Science Phase 1

Characterize appearance and size Photograph and map Determine size and other characteristics / features

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Characterize appearance and size Photograph and map Determine size and other characteristics / features

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Do science: Ablation laser Magnetometer Accelerometer Spectrometers and cameras Probe / Joust

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Do science: Ablation laser Magnetometer Accelerometer Spectrometers and cameras Impact Probe Accelerate

towards NEO

Impact Probe

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Do science: Ablation laser Magnetometer Accelerometer Spectrometers and cameras Impact Probe Move to Noon-Midnight vector

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RUNNER Spacecraft Break Down

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Science Payload Breakdown

Payload

Dimensions and Appearance

Thermal Properties Mineralogy

Mechanical Properties

Long-range Camera

Short-range Camera

Rangefinder

IR Camera (2x) Ablation Laser

Mass Spectrometer

Magnetometer

Impact Probe

High Gain Accelerometer

Low Gain Accelerometer

Laser Pulse

Atoms, Ions, Particles

Mass Spectrometer

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Instrument Mass

• Estimated total mass approximately 1 kg

Instrument Quantity Unit (kg) Total (kg) Total (cm3)Visible Imager 2 0.200 0.400 14.00

Microbolometer 2 0.028 0.056 29.04Ablation Laser 1 0.195 0.195 106.50

Mass Spectrometer 1 0.300 0.300 300.00Magnetometer 1 0.005 0.005 0.75

Rangefinder 1 0.022 0.022 40.96Low Gain Accel 1 0.001 0.001 0.03High Gain Accel 1 0.002 0.002 0.04

Science Board 1 0.150 0.150 150.00Total 0.981 (kg) 641.3 (cm3)

Items in red are low TRL and estimated masses

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Instrument Telemetry

• Total Science Telemetry is 2.4 Gb – Total bits are based off the rate of the instrument and the time instrument is on

according to the concept of operations (~20 days)

Instrument Rate Sample Size (bits) Total Bits over Mission (Mbits)Visible Imager Once per Day 72000000 2160Microbolometer Once per Day 15728640 157.3Mass Spectrometer 10 Hz for 2 min 256 3.072Magnetometer 1 Hz 48 86.4Rangefinder Once per Day 16 4.8E-04Low Gain Accel 10 Hz for 5 min 32 0.960High Gain Accel 10 Hz for 5 min 32 0.960

Total 2409

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BFRIT-3 Busek 3-cm Ion Thruster

• Thruster, cathode, PPU – 1U, 1kg • Iodine Propellant (TRL-4)

Image courtesy of Busek.com

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Maximum Capabilities (6 Panels, 1 AU)

Nominal Operations Nominal Operations

ISP (s) ISP (s)


Rendezvous STK Astrogator

1992_Bf leaving orbit on 5 Aug, 2017 resulted in an orbit very similar to the 1992_BF asteroid, but off phase.

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ADCS Break Down Diagram

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Solar Panel Study

30 cm

60 c

m

20 cm

Total Number of Subpanels

Solar cell placement study 2 panels with 3 subpanels (0.18 m2)

Requirement

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Communication Concept of Operations


Design Element Symbol Units S-Band X-band Optical Link Frequency f GHz 2.4 8.5 5.66E+05 Transmitter Power Ptx Watts 10.66 2.00 0.10

Transmitter Power Ptx dBW 10.28 3.01 -10.00 Transmitter

Antenna Diameter D m 34.000 0.300 0.010 Antenna Gain Gtx dB 55.63 20.07 92.45 Antenna Transmitter Losses Ltx dB -0.5 -0.5 -3 Antenna Beam width θtx Deg 0.26 15.44 0.00 Antenna Misalignment αtx Deg 0.2 1 0.002 Alignment Loss Lθtx dB -7.25 -0.05 -3.48

Data Rate and Margin Calculations

Rates

Data Rate R Bps 1000 1000 1000

Eb/No Available Eb/No dB 8.60 9.21 16.37

Required Eb/No - Modulation Format Eb/No dB 9.6 9.6 13.3

Coding gain dB 7 7 7

Required Eb/No Eb/No dB 2.60 2.60 6.30

Required Margin dB 3 3 3

Margin dB 3.00 3.61 7.07

Receiver Antenna Diameter D m 0.2 34.0 1.00 Antenna Gain Gr dB 20.00 67.44 133.59 Antenna Receiver Loss Lr dB -0.5 -0.5 -3 Antenna Beam width θr Deg 48.61 0.08 0.00

Antenna Misalignment αr Deg 0.01 0.01 0

Alignment Loss Lθr dB 0.00 -0.21 0.00 Total Receiver G dB 19.50 66.73 130.59

• Trade Study – S-band, X-band, Optical

• Pros vs cons of each

• X-Band Selected for RUNNER

• DSN 34 Meter Dish Antenna

Band Pro Con S-band Lots available

hardware Low data rates

X-band Better data rates Not much hardware available

Optical Best data rates To complex


• TX (8.2GHZ) Length = 9.8414 mm Width = 12.2634 mm Input Impedance = 200.25 Ω USE 18 total patches

• RX (7.2GHZ) –Length = 10.25 mm –Width = 13.97 mm –Input Impedance = 200.25 –Use 18 total patches

Antenna Patch Calculations


Data Rate VS Distance

0

5000

10000

15000

20000

25000

30000

35000

0 0.05 0.1 0.15 0.2 0.25 0.3 0.35 0.4

Dat

a R

ate

(Bits

/sec

)

Distance (AU)

34 Meter Dish

2W TX4W TX8W TX

1.1kbits/s

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RUNNER Spacecraft

6U Spacecraft

Rx & Tx Antennas

Transmit Antenna

Solar Panels

Solar Panels

Rx & Tx Antennas

Propellant Tank

Thruster and pointing Gimbal

PPU Electronics

L-3 Radio Tx / Rx

ADCS System & wheels Power

Management

On-Board Computer

Battery System

Imager (near) Imager (far)

Microbolometers Laser

Range Finder

TOF Mass Spectrometer

Ablation Laser

Star Tracker

Impact Boom

μPPT Attitude Thrusters

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Small Satellite Cost Model

Total Spacecraft Cost ($K) = $14,226

Total Instrument & Science Cost ($K) = $6,000

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Navigation Conclusions

• Fly by missions are relatively easy to accomplish. Matching an asteroids orbit will take significantly more planning.

• Based on our simulations, it is possible to reach Near Earth Asteroids using cube sat technology.

• RUNNER’s distance from earth will be a key consideration in planning missions.

• The NEA ‘2000 HA24’ has an especially promising orbit in 2018

�RUNNERPicture of TeamRUNNERPresentation OverviewMission Objectives 1 & 2Mission Objective 3Objectives and Payload InstrumentsTarget NEO’s ConsideredMission Constraints and� AssumptionsRUNNER Mission ConceptPerpendicular to Ecliptic PlaneNEA Rendezvous Science Phase 1NEA Rendezvous Science Phase 1NEA Rendezvous Science Phase 2NEA Rendezvous Science Phase 2NEA Rendezvous Science Phase 2RUNNER Spacecraft Break DownScience Payload BreakdownInstrument MassInstrument TelemetryBFRIT-3 Busek 3-cm Ion ThrusterMaximum Capabilities (6 Panels, 1 AU)Rendezvous STK AstrogatorADCS Break Down DiagramSolar Panel StudyCommunication Concept of OperationsData Rate and Margin CalculationsAntenna Patch CalculationsData Rate VS DistanceRUNNER SpacecraftSlide Number 31Small Satellite Cost Model Navigation Conclusions

Documents

ANGELS Power Slice Electronics Simulations Overview · 2014. 5. 28. · Student Object Designation Diameter Date (dV) Est. ΔV. Distance. Alex Christensen (2001 QC34) 166 - 743 6/17/2019