5 Dnepr2 Riki Munakata
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Transcript of 5 Dnepr2 Riki Munakata
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Dnepr 2 Satellite Identificationand the Mk.III P-POD
Jonathan Brown and Riki Munakata
California Polytechnic State University
April 10, 2008
CubeSat Developers’ Workshop
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Dnepr Launch 2
• April 17, 2007, 6:46:35 UTC
• 7 CubeSats in 3 P-PODs
• P-POD A: CSTB1, AeroCube2, CP4
P-POD B: MAST
P-POD C: Libertad-1, CAPE1, CP3
• CP4, Libertad-1, and CAPE1 had beacons
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Integration Timeline
• 2 months: CubeSats delivered to Cal Poly
for integration and acceptance
• 6 weeks: Ship P-PODs to launch site
• 3 weeks: Arrive at launch site, inspect P-
PODs, integrate with LV• Launch!
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Integration Timeline
• Early Dec. – CubeSats shipped to Cal Poly
– P-POD A integrated and accepted
• Mid Dec. – Launch delay• Early Mar. – Libertad-1 arrives at Cal Poly
• Mid Mar. – P-PODs hand-carried to Baikonur
• End Mar. – Launch delay
• Mid Apr. – Launch (finally!)
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Tracking Data
• Preliminary TLEs were used to track firstpasses; heard all CubeSats with beacons
• First TLEs on Space Track available within
12 hours of launch
• All CubeSats independently identified after
one week, most within 2 days
• Four weeks before data became
consistent
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P-POD A
0 10 20 30 40 50 60 70
7086.4
7086.6
7086.8
7087
7087.2
7087.4
7087.6
7087.8
Days after Launch
S e m i m a j o r A
x i s [ k m ]
CP4
AeroCube2
CSTB1
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P-POD C
0 10 20 30 40 50 60 70
7097.45
7097.5
7097.55
7097.6
7097.65
7097.7
7097.75
7097.8
7097.85
7097.9
Days after Launch
S e m i m a j o r A
x i s [ k m ]
CP3
CAPE1
Libertad-1
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Separation Rates
• Analytical separation rates
~5 cm/s between CubeSats
• Reasons for discrepancies:
– Friction – Different strength springs on
CubeSats
– Separation springs inP-POD A likely not fully
compressed
Between
CubeSats
Observed
Relative
Speed [cm/s]
CP4/
AeroCube2
0.3
AeroCube2/
CSTB1
1.5
CP3/CAPE1
4.9
CAPE1/
Libertad-1
2.2
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Satellite Misidentification
• Order of CubeSats in cluster was still
unclear after a month
• First and last CubeSats in each P-PODwere interchanged when names were
assigned to objects• Problem not discovered for two months,
when CP3 was contacted for the first time
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Recommendations forImprovement
• Stronger separation springs to disperse
CubeSats faster
• P-POD redesign allows for visualconfirmation of total spring compression
• Beacons!
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Poly Picosatellite Orbital Deployer
• Standard deployment
system – Tubular frame
– Spring assisted ejection
– Payload of 3 single
CubeSats
• P-POD missionobjectives – Protect LV and primary
payload
– Safe/reliable deployment
– Compatibility with many
LV
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• Mark III P-POD
– Increased Side Panel Accessto facilitate CubeSat integrationprocess
– The Mk III can accommodateboth the Qwknut and NEA9102G release mechanisms tomeet different launch vehicle
requirements. – Release door modified to
account for shear relief from
NEA
P-POD Mark III Structure
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The CubeSat Standard• Shape and size (10 cm
cube)
• Mass (up to 1 kg)
• Interface to P-POD
– Rails
– Access ports
• Materials and tolerances
• Operations – Deployables
– Communication
• Different configurationspossible
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6-Pack Concept• Larger form factor
• Fully enclosed
deployer
• One NEA
• One satellite
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6-Pack• Mass: +6kg
• Size: +6U
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Major Domestic Launch Vehicles
2 8 .0 ”
2 4.
0 ”
3 5 .
5 ”
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HeritageLaunch
Number of
P-PODSCubeSat Missions
Eurokot 2 P-POD A:CanX-1, DTUsat, AAU CubeSatP-POD B: QuakeSat
SSETI
Express1 CubeSat XI-V, NCUBE-2, UWE-1
Belka: Dnepr(Rocket Failure)
5
P-POD A: ION, Sacred
P-POD B: KUTESat Pathfinder
P-POD C: SEEDS, HAUSAT 1, Ncube 1
P-POD D: MEROPE, AeroCube-1, CP2
P-POD E: CP1, Ice Cube 2, Mea Huaka (Voyager)
TacSat-2:
Minotaur1 Modified P-POD: GeneSat-1
EgyptSat:
Dnepr 3
P-POD A: CP4, AeroCube 2, CSTB 1
P-POD B: MASTP-POD C: CP3, CAPE 1, Libertad-1
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Upcoming Launches• Falcon-1 3rd flight
– 2 P-PODs• NASA Ames 3U
• NASA Marshall 3U
• Falcon-1 RazakSat
– 2 P-PODs
• Minotaur-I TacSat 3
– 2 P-PODs