Lunar spacecraft
Lunar spacecraft
Lunar spacecraft
CubeSat
CUBESAT 6U SATELLITE
CubeSat 6U satellite
DESCRIPTION
CubeSat 6U, injected into the circumlunar orbit as the piggyback payload on one of the scheduled lunar missions, accommodates up to 2U payload to solve the mission-oriented tasks (imager, polarimeter or radiometer).
SATELLITE BASIC SPECIFICATIONS
| Satellite mass, kg | no more 14 |
| Power supply system capacity, W | |
| – average | 60 – 65 |
| – peak | up to 130 |
| Accuracy of the angular attitude, deg | 0.5 |
| Accuracy of the angular stabilization, deg/s | 0.005 |
| Active lifetime, years | 1 |
CUBESAT 12U SATELLITE
CubeSat 12U satellite
DESCRIPTION
CubeSat 12U accomplishes solo flight to the circumlunar orbit from GTO, accommodating up to 4U payload to solve the mission-oriented tasks or serves as orbital transport module to deliver the payload to the circumlunar orbit or interplanetary trajectories.
SATELLITE BASIC SPECIFICATIONS
| Satellite mass, kg | no more 20 |
| Power supply system capacity, W | |
| – average | 80 – 200 |
| – peak | up to 230 |
| Main propulsion system: | |
| – working medium | Iodine |
| – thrust, N | 2× 1.24·10-3 |
| – total impulse, N•s | 2× 3.7·104 |
| Accuracy of angular attitude, deg | 0.5 |
| Accuracy of angular stabilization, deg/s | 0.005 |
| Active lifetime, years | 3 |
EARTH REMOTE SENSING SPACECRAFT
CUBESAT 6U SATELLITE
CubeSat 6U satellite
DESCRIPTION
CubeSat 6U, injected into the circumlunar orbit as the piggyback payload on one of the scheduled lunar missions, accommodates up to 2U payload to solve the mission-oriented tasks (imager, polarimeter or radiometer).
SATELLITE BASIC SPECIFICATIONS
| Satellite mass, kg | no more 14 |
| Power supply system capacity, W | |
| – average | 60 – 65 |
| – peak | up to 130 |
| Accuracy of the angular attitude, deg | 0.5 |
| Accuracy of the angular stabilization, deg/s | 0.005 |
| Active lifetime, years | 1 |
CUBESAT 12U SATELLITE
CubeSat 12U satellite
DESCRIPTION
CubeSat 12U accomplishes solo flight to the circumlunar orbit from GTO, accommodating up to 4U payload to solve the mission-oriented tasks or serves as orbital transport module to deliver the payload to the circumlunar orbit or interplanetary trajectories.
SATELLITE BASIC SPECIFICATIONS
| Satellite mass, kg | no more 20 |
| Power supply system capacity, W | |
| – average | 80 – 200 |
| – peak | up to 230 |
| Main propulsion system: | |
| – working medium | Iodine |
| – thrust, N | 2× 1.24·10-3 |
| – total impulse, N•s | 2× 3.7·104 |
| Accuracy of angular attitude, deg | 0.5 |
| Accuracy of angular stabilization, deg/s | 0.005 |
| Active lifetime, years | 3 |