Picture of Team. Bryce Walker. Charles Swenson. Alex Christensen. Jackson Pontsler. Erik Stromberg. Cody Palmer. Benjamin Maxfield.

Transcription

1 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

2 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 2

3 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. = + 3

4 Mission Objectives Concepts of Operation Spacecraft Description Science Payload Propulsion Navigation Presentation Overview Attitude Determination and Control System Power Communications Onboard Computing Data Handling Mechanical Systems System Budgets Summary / Appendix 4

5 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 5

6 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 6

7 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 7

8 Target NEO s Considered Near-Earth Object Human Space Flight Accessible Targets Study (NHATS) JPL Small-Body Database Total ΔV 12 km/s Launch Visual Magnitude 22 Found 66 Objects Est. Diameters m Encounter Range from Earth AU Focused on 12 objects JPL's HORIZONS system Student Object Designation Diameter Date (dv) Est. ΔV Distance Alex Christensen (2001 QC34) /17/ Erik Stromberg (2001 VC2) /7/ Bryce Walker (2003 GA) /26/ Jacob Singleton (2000 HA24) /5/ Cody Palmer (2008 DG5) /11/ Cameron Weston (1992 BF) /19/ William Hatch (2003 YX1) /18/ Jackson Pontsler (2012 DK61) /25/ Andrew Mugleston (1998 HG49) /18/ Keyvan Johnson Bennu (1999 RQ36) /26/ Benjamin Maxfield 3361 Orpheus (1982 HR) /23/ Jorden Luke (2000 QK130) /15/ RUNNER ECE5240 Spring

9 Mission Constraints and Assumptions Launch Secondary payload on SLS EM-1 and/or latter missions Launch opportunities between 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. RUNNER ECE5240 Spring

10 RUNNER Mission Concept Loiter near Moon, await NEO phasing Transfer to NEO rendezvous point Proximity operations Secondary payload Rendezvous Space Launch System DSN Data downlink RUNNER ECE5240 Spring

11 Perpendicular to Ecliptic Plane Solar Arrays Track Sun Communication Antenna Solar array axis normal to ecliptic 11

12 NEA Rendezvous Science Phase 1 Goal: Eclipse avoidance Dawn-Dusk Orbit / Noon Vector Characterize appearance and size Photograph and map Determine size and other characteristics / features 12

13 NEA Rendezvous Science Phase 1 Characterize appearance and size Photograph and map Determine size and other characteristics / features 13

14 NEA Rendezvous Science Phase 2 Do science: Ablation laser Magnetometer Accelerometer Spectrometers and cameras Probe / Joust 14

15 NEA Rendezvous Science Phase 2 Impact Probe Do science: Ablation laser Magnetometer Accelerometer Spectrometers and cameras Impact Probe Accelerate towards NEO 15

16 NEA Rendezvous Science Phase 2 Do science: Ablation laser Magnetometer Accelerometer Spectrometers and cameras Impact Probe Move to Noon-Midnight vector 16

17 RUNNER Spacecraft Break Down 17

18 Science Payload Breakdown Payload Dimensions and Appearance Thermal Properties Mineralogy Mechanical Properties Long-range Camera IR Camera (2x) Ablation Laser Impact Probe Short-range Camera Mass Spectrometer Mass Spectrometer High Gain Accelerometer Rangefinder Magnetometer Low Gain Accelerometer Atoms, Ions, Particles Laser Pulse 18

19 Instrument Mass Estimated total mass approximately 1 kg Instrument Quantity Unit (kg) Total (kg) Total (cm 3 ) Visible Imager Microbolometer Ablation Laser Mass Spectrometer Magnetometer Rangefinder Low Gain Accel High Gain Accel Science Board Total (kg) (cm 3 ) Items in red are low TRL and estimated masses 19

20 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 Microbolometer Once per Day Mass Spectrometer 10 Hz for 2 min Magnetometer 1 Hz Rangefinder Once per Day E-04 Low Gain Accel 10 Hz for 5 min High Gain Accel 10 Hz for 5 min Total

21 BFRIT-3 Busek 3-cm Ion Thruster Thruster, cathode, PPU 1U, 1kg Iodine Propellant (TRL-4) Image courtesy of Busek.com 21

22 Maximum Capabilities (6 Panels, 1 AU) ISP (s) ISP (s) Nominal Operations Nominal Operations 22

23 Rendezvous STK Astrogator leaving orbit on 5 Aug, 2017 resulted in an orbit very similar to the 1992_BF asteroid, but off phase. 1992_Bf RUNNER ECE5240 Spring

24 ADCS Break Down Diagram 24

25 Solar Panel Study Total Number of Subpanels 60 cm Requirement 20 cm 30 cm Solar cell placement study 2 panels with 3 subpanels (0.18 m 2 ) 25

26 Communication Concept of Operations 26

27 Data Rate and Margin Calculations Design Element Symbol Units S-Band X-band Optical Link Frequency f GHz E+05 Transmitter Power P tx Watts Transmitter Power P tx dbw Transmitter Antenna Diameter D m Antenna Gain G tx db Antenna Transmitter Losses L tx db Antenna Beam width θ tx Deg Antenna Misalignment α tx Deg Alignment Loss L θtx db Receiver Antenna Diameter D m Antenna Gain G r db Antenna Receiver Loss L r db Antenna Beam width θ r Deg Antenna Misalignment α r Deg Alignment Loss L θr db Total Receiver G db Rates Data Rate R Bps Eb/No Available E b /N o db Trade Study S-band, X-band, Optical Pros vs cons of each Band Pro Con S-band Lots available hardware X-band Better data rates Low data rates Not much hardware available Optical Best data rates To complex Required Eb/No - Modulation Format E b /N o db Coding gain db Required Eb/No E b /N o db Required Margin db Margin db X-Band Selected for RUNNER DSN 34 Meter Dish Antenna RUNNER ECE5240 Spring

28 Antenna Patch Calculations TX (8.2GHZ) Length = mm Width = mm Input Impedance = Ω USE 18 total patches RX (7.2GHZ) Length = mm Width = mm Input Impedance = Use 18 total patches RUNNER ECE5240 Spring

29 Data Rate VS Distance Meter Dish Data Rate (Bits/sec) W TX 4W TX 8W TX Distance (AU) 1.1kbits/s RUNNER ECE5240 Spring

30 RUNNER Spacecraft Solar Panels Rx & Tx Antennas Rx & Tx Antennas 6U Spacecraft Solar Panels Transmit Antenna 30

31 Imager (near) Imager (far) Microbolometers Laser Range Finder L-3 Radio Tx / Rx ADCS System & wheels Propellant Tank PPU Electronics Star Tracker TOF Mass Spectrometer Ablation Laser Impact Boom Battery System On-Board Computer Power Management μppt Attitude Thrusters Thruster and pointing Gimbal

32 Small Satellite Cost Model Total Spacecraft Cost ($K) = $14,226 Total Instrument & Science Cost ($K) = $6,000 32

33 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