Integrated antenna system for imaging microsatellites
Examples of imaging microsatellites are described that have an imaging system and antenna system disposed within the microsatellite body when the microsatellite is in a non-deployed state. The properties of the antenna system can be adjusted such that the antenna system does not impact, contact, or displace the imaging system when the microsatellite is in the non-deployed state. The properties of the antenna system can be adjusted such that the antenna system does not contact or impact the body of the microsatellite or any other structure when the microsatellite transitions to a deployed state. The antenna system can be configured to achieve a desired gain and/or data transmission rate by adjusting properties of the antenna system based on the radiation pattern of an antenna feed and geometric constraints imposed by the imaging system. Examples of methods for designing such imaging microsatellites are provided.
1. An imaging satellite comprising:
a body having an opening;
an imaging system disposed within the body, wherein the imaging system comprises a telescope comprising:
a primary mirror;
a secondary mirror; and
a secondary mirror support configured to secure the secondary mirror relative to the primary mirror;
a door attached to the body, the imaging satellite configured to have:
a non-deployed state in which the opening is covered by the door, and
a deployed state in which the opening is not covered by the door, the opening configured to allow radiation to enter the imaging system such that the imaging system can image a field of view through the opening; and
an antenna system mounted to an interior surface of the door, wherein the imaging satellite is configured such that:
when the imaging satellite is in the non-deployed state, the antenna system is configured to not displace the imaging system,
while the imaging satellite transitions from the non-deployed state to the deployed state, the antenna system is configured not to contact the body of the imaging satellite, and
when the imaging satellite is in the deployed state, the antenna system is configured to transmit imaging data acquired by the imaging system.
2. The imaging satellite of claim 1 , wherein the imaging satellite has a volume that is less than or equal to 125 cm by 125 cm by 175 cm.
3. The imaging satellite of claim 1 , wherein the imaging satellite has a mass that is less than or equal to 500 kg.
4. The imaging satellite of claim 1 , wherein the imaging satellite has a mass that is in a range between 1 kg and 10 kg.
5. The imaging satellite of claim 1 , wherein the imaging satellite is configured to launch as a secondary payload on a launch vehicle configured to launch a primary payload.
6. The imaging satellite of claim 1 , wherein the imaging system further comprises:
a primary baffle associated with the primary mirror; or
a secondary baffle associated with the secondary mirror.
7. The imaging satellite of claim 1 , further comprising a release mechanism configured to secure the door to the body when the door is in the closed state, the release mechanism actuatable to release the door and allow the door to move from the closed state to the open state.
8. The imaging satellite of claim 7 , wherein the release mechanism comprises a spring.
9. The imaging satellite of claim 1 , further comprising one or more solar panels configured to provide power to electrical components in the imaging satellite.
10. The imaging satellite of claim 1 , wherein the antenna system comprises one or more of a feed horn, a dipole driven element, a waveguide, an orthomode transducer, or a polarizer.
11. An imaging satellite comprising:
a movable door configured to:
cover a radiation entrance to the imaging satellite when the movable door is in a closed position; and
uncover the radiation entrance to the imaging satellite when the movable door is in an open position;
an imaging system disposed in the imaging satellite, the imaging system configured to receive radiation through the radiation entrance when the movable door is in the open position, wherein the imaging system comprises a telescope comprising:
a primary mirror;
a secondary mirror; and
a secondary mirror support configured to secure the secondary mirror relative to the primary mirror; and
an antenna system coupled to an inner surface of the movable door,
wherein the imaging satellite is configured such that while the movable door moves from the closed position to the open position, the antenna system does not contact or displace any portion of the imaging system.
12. The imaging satellite of claim 11 , wherein the imaging satellite has a volume that is less than or equal to 125 cm by 125 cm by 175 cm or a mass that is less than or equal to 500 kg.
13. The imaging satellite of claim 11 , wherein the imaging satellite is configured to launch as a secondary payload on a launch vehicle configured to launch a primary payload.
14. The imaging satellite of claim 11 , further comprising an opening mechanism configured to move the door from the closed position to the open position when the opening mechanism is actuated.
15. The imaging satellite of claim 14 , wherein the opening mechanism comprises a spring.
16. The imaging satellite of claim 11 , further comprising one or more solar panels configured to provide power to electrical components in the imaging satellite.
17. The imaging satellite of claim 11 , wherein the antenna system is configured to transmit imaging data acquired by the imaging system when the door is in the open position.
18. The imaging satellite of claim 11 , wherein the antenna system comprises one or more of a feed horn, a dipole driven element, a waveguide, an orthomode transducer, or a polarizer.