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AeroCube 10A, 10B

Aerocube 10B and 10A [Aerospace Corp.]

Aerocube 10 (AC10) are a pair of 1.5U Cubesats developed by the Aerospace Corporation of El Segundo to demonstrate several technologies.

The purpose of the mission is to demonstrate

  • precision satellite-to-satellite pointing,
  • deployment of atmospheric probes for in-situ measurement of air density,
  • small-spacecraft proximity operations using propulsion from a steam thruster (no docking is planned), and
  • solar cell performance degradation experiment that will correlate data from radiation sensors tuned to the energy levels suspected of causing damage to a drop in solar cell power output.

The AeroCube-10a spacecraft has two payloads. The first is a dispenser with a magazine of 29 identical atmospheric probes. Each probe weighs 16 grams and consist of three 98 mm diameter aluminum sheets at 90 degrees to each other, effectively forming a sphere. The intent is to be lightweight and have a constant cross section, independent of orientation to the velocity direction so that atmospheric drag can be measured in-situ. RF modeling predicts that the atmospheric probes will have a radar cross section equal to 1U CubeSats, which have been tracked on-orbit many times. The probes are dispensed individually upon command and it is predicted that each has a lifetime of 0.74 years when deployed from the highest altitude of 500 km. The second payload is an optical beacon. It is used to verify that the AeroCube-10a satellite is indeed pointing at the AeroCube-10b. It consists of a 4 W laser diode with a 1 full-width-half-max beam divergence.

The AeroCube-10b spacecraft replaces the payload volume area used for the dispenser on the 10a satellite with three different payloads. One is a steam propulsion unit identical to the one in AeroCubes-7b and 7c. It will dispense water vapor to create a 4 mN thrust to change the range between the two satellites. It holds up to 30 grams of water and can affect, best case a 10 meter per second delta velocity. Water is non-toxic and the pressure inside the steam propulsion unit is at atmospheric pressure, so it is not a pressure vessel. The other is an electron and proton spectrometer called the micro-Charged Particle Telescope (μCPT). It will measure radiation flux impinging on the satellite, in specific energy levels that are suspected to cause solar cell degradation. The third payload is a sensor that will confirm when the optical beacon is impinging on the satellite. It is a light sensor, tuned to the optical beacon and amplified because the intensity is predicted to be faint.

Nation: USA
Type / Application: Technology
Operator: Aerospace Corporation
Contractors: Aerospace Corporation
Equipment:
Configuration: CubeSat (1.5U)
Propulsion:
Power: Solar cells, batteries
Lifetime:
Mass:
Orbit: 400 km × 400 km, 51.6 (typical)
Satellite COSPAR Date LS Launch Vehicle Remarks
AeroCube 10A - 2019 WI LC-0A Antares-230 with Cygnus CRS-11, CAPSat, HARP, OPAL, TJREVERB, VCC A, B, C, Światowid, KrakSat, AeroCube 10B, SASSI2, NSLSat 1, EntrySat, ThinSat 1A, ..., 1L
AeroCube 10B - 2019 WI LC-0A Antares-230 with Cygnus CRS-11, CAPSat, HARP, OPAL, TJREVERB, VCC A, B, C, Światowid, KrakSat, AeroCube 10A, SASSI2, NSLSat 1, EntrySat, ThinSat 1A, ..., 1L

References: