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1 The Aerospace Corporation / 22
2 Aerospace PICOSAT Program Value 2 / 22 Perform Missions - two types: High risk for maximum return Use latest technology Create capability roadmap Risk reduction for sponsor s main program We have rapid response We are payload centric We allow fluid requirements We resolve technical questions Develop Technology by: Sustained internally funded effort Constant pursuit of limits Resident quality workforce Appropriate corporate structure Develop Workforce by Providing: Engineering exercise Policy exercise Contractor-like experience Program leadership opportunities Support AF Acquisitions by Developing: Cost models Concept Design Center models Mission assurance guidelines
3 Aerospace s PICOSAT History* from 1999 to / 22 OPAL PicoSats (2) Minotaur I 250 grams MEPSI (2) STS grams each MEPSI (2) STS and 1.4 kilograms Minotaur I 1.1 kilograms PSSC Testbed-2 STS kilograms REBR2 (2) H-IIB 4.5 kilograms with heat shield First University CubeSat Launch MightySat II.1 PicoSats (2) Minotaur I 250 grams AeroCube-1 Dnepr grams Failed to Reach orbit AeroCube-2 Dnepr grams PSSC Testbed STS kilograms REBR (2) H-IIB 4.5 kilograms with heat shield AeroCube-4.0 (1) AeroCube-4.5 (2) Atlas V, NROL kilograms * Timeline is for delivery date and not launch date
4 AeroCube-2 Launched May inclination 650 x 770 km altitude 1U CubeSat form factor 1 kg mass Norad ID (Still in orbit) 4 solar cells total Tumbler no attitude control 4 / 22 Cal Poly CubeSat CP-4 photographed by AeroCube-2. The first and, so far, only instance of one CubeSat photographing another. Lasted 1 day only because of insufficient energy for recharging batteries
5 Launched May inclination 460 km altitude 1U CubeSat form factor 1.1 kg mass Norad ID Reentered 7 solar cells total Permanent magnet* Central Mexico 640x480 pixels 135 diagonal FOV 1200 mile horizon 2009 The Aerospace Corporation 5 / 22 North* 640x480 pixels 135 diagonal FOV 1200 mile horizon 2009 The Aerospace Corporation Pacific Ocean Corrected and improved AeroCube-2
6 Features 6 / 22 Y, B Tether cutting mechanism** 135 visible camera Y Y-axis reaction wheel (inside) Tether reel (inside) -Z Z X Triax rotation rate sensors (inside) 56 visible camera Sensor A Sensor B Earth sensor 2-angle Sun sensor ** 200 of Dyneema is spooled inside Substantial number of new subsystems X 2-food diameter Mylar balloon stowed under this cover B B B Triax magnetic field sensors (inside)
7 New Solar Cell Laydown Method 7 / 22 Testing a new method for solar cell installation Nusil CV4 is a double sided tape with space rated outgassing properties 1U CubeSat solar cells laid down in 1 day Solar cell CIC NuSil CV Polyimide tape Substrate Reference: Karuza, et al, Solar Cell Installation Using Double Sided Polysiloxane Pressure Sensitive Adhesive (PSA) Polyimide Film, 2009 Much quicker and cleaner than liquid adhesive
8 Concept of Operations 8 / km altitude 40.5 deg inclination Launched May 2009 Permanent magnet will keep same face pointing North AC3 can scan about permanent magnet axis using a reaction wheel (RW) B 40 deg Fields of View (FOV) 1. Narrow camera 2. Earth sensor 3. Sun sensor 4. Sensor A 5. Sensor B 2-foot dia deorbit balloon (end of mission) Legend Blue line = orbit ground track Yellow line = orbit latitude limits Red line = magnetic field lines Green circle = AGO ground station FOV 40 deg Mission = test new sensors, comm link, power system, deorbit device
9 Earth Photo 9 / x480 pixels 135 diagonal FOV 1200 mile horizon 2009 The Aerospace Corporation 2700 mile diameter of cloud cover (same size as the United States!)
10 Earth Photo 10 / x480 pixels 135 diagonal FOV 1200 mile horizon 2009 The Aerospace Corporation Approaching the California Coast
11 Earth Photo 11 / 22 Ahome, Sonora, Mexico May 29, km altitude 190x240 mile area Approx. 1 mile resolution 640x480 pixels 56 diagonal FOV 2009 The Aerospace Corporation Intelligence, Surveillance, and Reconnaissance
12 Earth Photo 12 / x480 pixels 135 diagonal FOV 2009 The Aerospace Corporation Day / night terminator
13 Earth Photo 13 / x480 pixels 135 diagonal FOV 1200 mile horizon 2009 The Aerospace Corporation New Harmony fire (Utah) Station fire (Los Angeles) Locating gigantic fires! (September 1, 2009)
14 Deorbit Balloon 14 / The Aerospace Corporation 6 panel x 2-foot diameter AC3 balloon inflated in vacuum chamber Uninflated 2-foot diameter AC3 balloon. Kapton fill tube has kinks that prevented inflation. Spherical balloon would be easy to spot from earth with binoculars AC3 balloon inflation module
15 Altitude (km) Deorbit Balloon Performance P-POD 450 Satellite Altitude vs. Time 15 / 22 HawkSat HawkSat Balloon Ejection deorbited CP-6 CP6 deorbited 150 5/1/09 10/1/09 3/3/10 8/3/10 1/3/11 6/5/11 11/5/11 Date All three CubeSats were launched from the same P-POD launch tube
16 B-Star Drag Term Deorbit Balloon Performance 16 / Satellite Drag vs. Time deorbited Balloon Ejection deorbited HawkSat-1 CP /1/09 10/1/09 3/3/10 8/3/10 1/3/11 6/5/11 11/5/11 Date Balloon deployed (uninflated due to fault in inflation system) on
17 Solar Up-converter Voltages - Baseline 17 / Lithium ion batteries charge at 4.2V
18 Solar Up-converter at 0 and 60 days 18 / 22 Mission Day 1 Mission Day 60 Yellow / Blue / Pink lines are solar array upconverted voltages No change in solar array performance in 60 days
19 Temperatures at 0 and 60 days 19 / 22 Mission Day 1 Mission Day 60 Blue / Pink lines are temperature sensors located on 2 different exterior walls of Yellow / Black / Purple lines are temperature sensors located on the electronics module Note that interior temperatures do not fluctuate as much by design
20 Battery Data at 0 and 60 days 20 / 22 Mission Day 1 Mission Day 60 Blue / Yellow lines are Battery 1 and Battery 2 voltages (V) Cyan / Pink lines are Battery 1 and Battery 2 currents (ma) No change in battery performance in 60 days
21 AeroCube-4 Preview Launch August inclination 470 x 780 km altitude 1U CubeSat form factor 1.3 kg mass 10 solar cells total Full attitude control Sun sensors Earth nadir sensor 1600x1200 cameras Adjustable wings for variable drag 2 ft dia x 1.5ft tall conical deorbit chute GPS Redundant radios Redundant software Reprogrammable on orbit Triax reaction wheels Triax torque coils Minimum drag configuration Maximum drag configuration 21 / 22 Vast improvement in capability over
22 Acknowledgements 22 / 22 Dr. James Gee, Principal Director, Developmental Planning and Projects, The Aerospace Corporation This work was supported by The Aerospace Corporation's Independent Research and Development program.
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