compass orion design session • purpose: – a cubesat design for sls launch opportunity for em -1...
TRANSCRIPT
![Page 1: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/1.jpg)
1
DAVID: Diminutive Asteroid Visitor with Ion Drive
A Cubesat Asteroid Mission Geoffrey A. Landis
NASA Glenn Research Center
COMPASS Team at NASA Glenn: Steve Oleson, Melissa McGuire, Aloysius Hepp, James Stegeman, Mike Bur, Laura Burke,
Michael Martini, Jim Fittje, Lisa Kohout, James Fincannon, and Tom Packard Collaborating Institutions:
Busek (propulsion); COSMIAC (spacecraft integration); Case Western (Ralph Harvey, Asteroid Science lead); Planetary Science Institute (Asteroid Science)
![Page 2: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/2.jpg)
DAVID visualization
2
![Page 3: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/3.jpg)
Background:
• Purpose: – a cubesat design for SLS
launch opportunity for EM-1 – EM-1 launch (2018) to a
lunar free return trajectory. – A small ∆V before lunar fly-by
can adjust the escape trajectory to C3 =0 (co-orbital to Earth)
• Mission: visit an asteroid
3
![Page 4: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/4.jpg)
Highly Constrained Project:
• Size constrained: – 6U – about the size of a large shoebox
• Mass constrained – 12 kg total mass – including 1.3 kg assumed growth
• Propulsion constrained – no energetic components
• Cost constrained – $5.6 million dollar cost cap – about $5 million after subtracting
required cost reserves – (does not include launch)
4
![Page 5: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/5.jpg)
Choice of Target
• 12874 close approaches by asteroids were analyzed • List narrowed down:
– nearest approach no earlier than 2019 (>1 year after launch date) – Nearest approach no later than 2020.
• 2001 GP2 was chosen as a target. – From visual magnitude, estimate* ~18-meter diameter.
• Fly-by and Rendezvous missions analyzed • From escape, ∆V of ~400 m/s needed for May 2020 fly-by.
• October 2020 fly-by was just outside the window of the solicitation
• ∆V ~2000 m/s needed to achieve a rendezvous.
*depending on asteroid albedo
5
![Page 6: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/6.jpg)
Asteroid 2001 GP2 Earth Fly-by
• Closest pass: Oct 3, 2020 • Closest approach at 0.5 to 4.3 time Lunar distance • (~100,000 to 1 million miles)
– Further observations will decrease uncertainty • V relative: 2.37 km/sec
6
Near Earth asteroid Eros (viewed by the NEAR spacecraft)
![Page 7: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/7.jpg)
Itokawa: the smallest asteroid ever visited by a spacecraft
viewed by the Hayabusa spacecraft
![Page 8: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/8.jpg)
What makes Asteroid 2001 GP2 Interesting?
• 10-20 meters in diameter – Two orders of magnitude smaller than any other
asteroid ever visited – Typical of “city killer” impact threats (much more
frequent than extinction-level threats)
8
Asteroid Itokawa
![Page 9: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/9.jpg)
What makes Asteroid 2001 GP2 Interesting?
• Asteroids this tiny have never been visited by spacecraft – Recent modeling suggests YORP-induced spin-ups
can disaggregate bodies smaller than 150 m in size. – 2001–GP2 sits significantly below this model’s
threshold for stability: • Will it be an Itokawa-like body with a blocks and finer
grained material, or a single cohesive block? • Will it be tumbling chaotically or spinning? • What history is evident or implied?
9
Asteroid Itokawa
Representative of a whole class of objects that are numerous and interesting, but have never been observed up close
![Page 10: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/10.jpg)
DAVID (Diminutive Asteroid
Visitor using Ion Drive)
10
• 6-U cubesat • Mass limit 12 kg • Design must include
margin on all systems
![Page 11: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/11.jpg)
Size
23.94 cm
36.59 cm
11.28 cm
Planetary Systems Corporation Canisterized Satellite Dispenser
![Page 12: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/12.jpg)
SLS 6U Cubesat Deployed Dimensions
13.86 cm
52.29 cm
33.8 cm
81.46 cm
Arrays Rotated 90 Degrees
32.69 cm
![Page 13: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/13.jpg)
System Schematic
13
![Page 14: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/14.jpg)
Propulsion Trade Off
Mission is mass and volume constrained
Electric propulsion systems:
• High Specific Impulse: Low propellant use, high power requirement
– If Isp is too high, the power system mass dominates the system
• Low Specific Impulse: High propellant use, low power requirement • If Isp is too low, the propellant mass dominates the system
14
![Page 15: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/15.jpg)
Propulsion Choice
• Trade-off study included many propulsion systems • The Hall thruster has the greatest base of experience in
operation in space, but the cases analyzed exceeded the initial mass allowance of 12 kg, as did the Xe ion thruster.
• A case with two 10-W PUC (Propulsion Unit for Cubesats) electrospray thrusters also exceeded the mass allowance, but a revised case where this was reduced to lower power and a single thruster was run, which met the requirements.
• Single PUC electrospray thruster chosen for baseline design
• Rendezvous case requires higher Isp and larger solar array – ion engine needed
15
![Page 16: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/16.jpg)
16
Electrospray Thruster
Propellant: high density ionic liquid
![Page 17: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/17.jpg)
Busek Electrospray Thruster
• Mechanical Simplicity: No Moving Parts • Small Volume, Mass, and Power • Leverages $20M NASA ST7 Technology Flight
Development • Leverages SBIR Work on Micro-Valves and Power
Management • Non-Volatile Propellant • Multi-Emitter Design • Lisa Pathfinder Flight Heritage • Propellant Stored in Low Pressure Stainless Steel
Bellows Tank • Cold Ion Plume (No Hot Gas) • Self Regulating Feed System • Piezo-Actuated Isolation Micro-Valve
17
Busek Electrospray Thruster
Integrated PPU/DCIU (Engineering Model)
![Page 18: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/18.jpg)
LISA Pathfinder Thruster Integration
18
![Page 19: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/19.jpg)
2001 GP2 Interplanetary Trajectory 2018 Launch
• Colloid (Electrospray) Thruster Parameters:
– Power to thruster = 9W – Isp = 800s – Efficiency = 31% – Duty Cycle = 90%
• Trajectory Assumptions: – Fly-by of 2001 GP2 – Constant 9W to thruster – SLS Launch Date: 12/17/2018
• 4 days, 10 m/s to correct for worst-case SLS injection
– Spacecraft Wet mass = 12 kg • Trajectory Details:
– Delta-V = 390 m/s – Required Prop Mass = 0.58 kg – TOF = 507 days – Total Thrusting Time = 89 days
![Page 20: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/20.jpg)
2018 Thrust Profile
![Page 21: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/21.jpg)
2001 GP2 Interplanetary Trajectory mid-2018 Launch (Double Fly-by)
• Colloid (Electrospray) Thruster Parameters:
– Power to thruster = 9W – Isp = 800s – Efficiency = 31% – Duty Cycle = 90%
• Trajectory Assumptions: – Double Fly-by of 2001 GP2 – Constant 9W to thruster – SLS Launch Date: 7/31/2018
• 4 days, 10 m/s to correct for worst-case SLS injection
– Spacecraft Wet mass = 12 kg • Trajectory Details:
– Delta-V = 365 m/s – Required Prop Mass = 0.546 kg – TOF = 1037.8 days – Total Thrusting Time = 75 days
![Page 22: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/22.jpg)
2001 GP2 Interplanetary Trajectory
Fly-by 2001 GP2
![Page 23: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/23.jpg)
2001 GP2 Interplanetary Trajectory
Fly-by 2001 GP2
![Page 24: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/24.jpg)
2001 GP2 Interplanetary Trajectory 2018 Launch (October Fly-by)
• Colloid (Electrospray) Thruster Parameters:
– Power to thruster = 9W – Isp = 800s – Efficiency = 31% – Duty Cycle = 90%
• Trajectory Assumptions: – Fly-by of 2001 GP2 – Constant 9W to thruster – SLS Launch Date: 12/17/2018
• 4 days, 10 m/s to correct for worst-case SLS injection
– Spacecraft Wet mass = 12 kg • Trajectory Details:
– Delta-V = 43 m/s – Required Prop Mass = 0.065 kg – TOF = 660 days – Total Thrusting Time = 57 days
![Page 25: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/25.jpg)
2018 Thrust Profile (October Fly-by)
![Page 26: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/26.jpg)
Instruments
26
![Page 27: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/27.jpg)
SLS 6U Cubesat External Components
Sun Sensor
Science Camera
Solar Array Wing
X-Band Patch Antenna
Neutralizer
Solar Array Wing Sun Sensors
X-Band Patch Antenna
Electrospray Thruster
Sun Sensor
Solar Array Gimbal Unit
Solar Array Wing
X-Band Omni Antennas
Space Weather Science
Sun Sensor
Star Tracker
Sun Sensor
![Page 28: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/28.jpg)
Status
28
• Proposal submitted to SIMPLEX solicitation, but not selected for the EM-1 Mission Opportunity
• Proposal was rated highly, and selected for a one-year technology development study • Asked by program office to focus work on maturing the instrumentation
• Continuing to working on the engineering design • Looking for a launch opportunity to C3=0 in 2019 or
early 2020
![Page 29: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/29.jpg)
Where do we go if we find a launch, but miss the window for the Oct 2020 fly-by?
29
• Latest possible launch for 2020 fly-by is ~May 2020 • Asteroid 2011-CL50 has December 24 2020 fly-by
• not quite as good, but almost • only slightly later
• If we miss that, 2010 UE51 has opportunity Dec. 2023 • Tiny asteroid (~10 m class) • Farther away, but much slower fly-by speed • Possibility to do a rendezvous mission
![Page 30: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/30.jpg)
Conclusions
• Asteroid mission is possible with a 6-U cubesat Targeting near earth asteroids that fly close to Earth minimizes the propulsion required for fly-by/rendezvous
• Upcoming Oct 2020 fly-by has VERY low ∆V *assuming you can reach escape
• Rendezvous mission is possible as a stretch goal
– ∆V is very significant for a 6U cubesat: – ~2000 m/s needed for rendezvous with 2001 GP2
30
![Page 31: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/31.jpg)
DAVID visualization
31
![Page 32: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/32.jpg)
Backup/Slides not used
32
![Page 33: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/33.jpg)
Mission Delta-V Summary
• Total propellant in table represents usable propellant • Additional 5% of usable carried as margin in inert mass of vehicle • Isp = 800 s
![Page 34: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/34.jpg)
Reacquiring 2001 GP2
• Asteroid hasn't been seen since its discovery year • Uncertainty in orbit is a million miles!
– we need to refine orbit or else we miss it entirely
• The good news: it makes an Earth close approach in May 2019, at a distance of 0.154 AU • can reacquire asteroid and refine orbit one year before the May 2020
fly-by; 17 months before the Oct 2020 fly-by • plenty of time to fine-tune trajectory • phase angle to sun ~90° (directly ahead of Earth in orbit)
• The bad news: estimated magnitude at this approach is about ~24 – need a big telescope to see object that faint.
• Keck or similar capability ground-based telescope • Hubble space telescope
• February 2020 close approach at 0.124 AU is near opposition – 3 month lead time for May 2020 fly-by, 8 month for Oct 2020 fly-by
34
![Page 35: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/35.jpg)
Propulsion System Layout
35
Micro Valve Bellows Tank
Electrospray Thruster\l PPU/DCIU Propellantless Cathode
NEXT Style
Gimbal
![Page 36: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/36.jpg)
SLS Cubesat Bus Propulsion (EP Hardware) MEL
• SLS Cubesat Bus Propulsion (EP Hardware) Subsystem MEL
36
WBS Description QTYUnit
MassBasic Mass Growth Growth
Total Mass
Number Case #3.5 SLSCubesat 2013 CD-2013-101 (kg) (kg) (%) (kg) (kg)12/3/201306 SLS Cubesat 7.80 16.8% 1.31 9.1106.1 Cubesat Bus 7.80 16.8% 1.31 9.11
06.1.9 Propulsion (EP Hardware) 1.40 10.7% 0.15 1.55
06.1.9.a Primary EP System Hardware 0.72 10.8% 0.08 0.80
06.1.9.a.a EP System Hardware 0.72 10.8% 0.08 0.80
06.1.9.a.a.a Electrospray Thruster 1.00 0.52 0.52 8.0% 0.04 0.56
06.1.9.a.a.b Gimbal 1.00 0.20 0.20 18.0% 0.04 0.24
06.1.9.b Power Processing Unit (PPU) 0.50 8.0% 0.04 0.54
06.1.9.b.a Integrated PPU/DCIU 1.00 0.50 0.50 8.0% 0.04 0.54
06.1.9.c Propellant Management (EP) 0.18 18.0% 0.03 0.21
06.1.9.c.a EP Propellant Tank system 0.18 18.0% 0.03 0.21
06.1.9.c.a.a Custom Tank 1.00 0.13 0.13 18.0% 0.02 0.15
06.1.9.c.a.b Feed System 1.00 0.05 0.05 18.0% 0.01 0.06
![Page 37: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/37.jpg)
SLS Cubesat Bus Propellant (EP) MEL
• SLS Cubesat Bus Propellant (EP) Subsystem MEL
37
WBS Description QTYUnit
MassBasic Mass Growth Growth
Total Mass
Number Case #3.5 SLSCubesat 2013 CD-2013-101 (kg) (kg) (%) (kg) (kg)12/3/201306 SLS Cubesat 7.80 16.8% 1.31 9.1106.1 Cubesat Bus 7.80 16.8% 1.31 9.11
06.1.10 Propellant (EP) 0.69 0.0% 0.00 0.69
06.1.10.a Main Propellant (EP) 0.69 0.0% 0.00 0.69
06.1.10.a.a Primary EP Propellant Used 1.00 0.63 0.63 0.0% 0.00 0.63
06.1.10.a.b Primary EP Propellant Residulals (Unused) 1.00 0.03 0.03 0.0% 0.00 0.03
06.1.10.a.c Primary EP Propellant Performance Margin (Unused) 1.00 0.03 0.03 0.0% 0.00 0.03
![Page 38: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/38.jpg)
Communication
38
For analysis purposes, a transmission antenna gain of 8 dBi was used for both systems, not taking advantage of the ability of X-band to produce a tighter beam spread. Both S-band and X-band transmission can accomplish the required data rate of 174 bps with either receiving antenna. The encounter data can thus be downlinked in two DSN sessions with the 34-m receiver, or in less than one session, if the 70-m dish can be used.
![Page 39: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/39.jpg)
CMAD Spectrometer
39
![Page 40: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/40.jpg)
2001 GP2 Interplanetary Trajectory Rendezvous 2017 Launch
• 3cm RF Ion Thruster Parameters: – Power to thruster = 50W – Isp = 2200s – Efficiency = 27% – Duty Cycle = 90%
• Trajectory Assumptions: – Rendezvous of 2001 GP2 – Constant 50W to thruster – SLS Launch Date: 12/17/2017
• 4 days, 10 m/s to correct for worst-case SLS injection
– Spacecraft Wet mass = 12 kg • Trajectory Details:
– Delta-V = 2088 m/s – Required Prop Mass = 1.11 kg – TOF = 611 days – Total Thrusting Time = 456 days
![Page 41: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/41.jpg)
2001 GP2 Interplanetary Trajectory
Arrive at 2001 GP2
Requires 11,000 hours (456 days) of thrust -ion thruster needs qualification for this duration of operation
![Page 42: COMPASS Orion Design Session • Purpose: – a cubesat design for SLS launch opportunity for EM -1 – EM-1 launch (2018) to a lunar free return trajectory. – A small ∆V before](https://reader034.vdocument.in/reader034/viewer/2022051601/5ad884e07f8b9a5b538dfbed/html5/thumbnails/42.jpg)
Fly-by versus rendezvous summary
42