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. A method of deploying an imaging satellite, the method comprising:
transitioning an imaging satellite from a non-deployed state to a deployed state, the imaging satellite comprising a body having an opening, an imaging system disposed within the body, a door attached to the body, and an antenna system mounted to an interior surface of the door of the imaging satellite, 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, wherein:
in the non-deployed state, the opening is covered by the door and the antenna system is configured to not displace the imaging system;
in the deployed state, the opening is not covered by the door; and
during the transitioning from the non-deployed state to the deployed state, the antenna system does not contact the body of the imaging satellite, and wherein the transitioning the imaging satellite from the non-deployed state to the deployed state comprises rotating the door such that the door and the antenna system do not obstruct the field of view of the imaging system through the opening;
securing the imaging satellite in the deployed state, wherein the opening allows radiation to enter the imaging system such that the imaging system can image a field of view through the opening;
orienting the imaging satellite such that the antenna system is directed toward a ground receiving station; and
when the imaging satellite is in the deployed state, transmitting, with the antenna system, imaging data acquired by the imaging system to the ground receiving station.
2. The method of claim 1 , wherein transitioning the imaging satellite from the non-deployed state to the deployed state comprises releasing a release mechanism that secures the door when the imaging satellite is in the non-deployed state.
3. The method of claim 1 , wherein the transmitting provides a data transmission rate between 1 Mbit/s and 100 Mbit/s.
4. The method of claim 1 , wherein the transmitting is across one or more communication channels within a band of frequencies between 8.0 GHz and 8.4 GHz.
5. The method of claim 1 , further comprising launching the imaging satellite as a secondary payload on a launch vehicle configured to launch a primary payload.
6. The method 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 or a mass that is less than or equal to 500 kg.
7. The method of claim 1 , further comprising deploying one or more solar panels configured to provide power to electrical components in the imaging satellite.
8. A method of manufacturing an imaging satellite, the method comprising:
attaching a movable door to an imaging satellite, the 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;
disposing an imaging system 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 minor relative to the primary mirror; and
coupling an antenna system 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.
9. The method of claim 8 , 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.
10. The method of claim 8 , wherein the imaging satellite is configured to launch as a secondary payload on a launch vehicle configured to launch a primary payload.
11. The method of claim 8 , wherein attaching the movable door to the body of the imaging satellite comprises attaching an opening mechanism to the imaging satellite, the opening mechanism configured to move the door from the closed position to the open position when the opening mechanism is actuated.
12. The method of claim 11 , wherein the opening mechanism comprises a spring.
13. The method of claim 8 , further comprising attaching one or more solar panels to the imaging satellite.
14. The method of claim 8 , further comprising configuring the antenna system to transmit imaging data acquired by the imaging system when the door is in the open position.
15. The method of claim 14 , wherein configuring the antenna system comprises configuring the antenna system to communicate across one or more communication channels within a band of frequencies between 8.0 GHz and 8.4 GHz.
16. The method of claim 14 , wherein configuring the antenna system comprises configuring the antenna system to transmit the imaging data at a data transmission rate between 1 Mbit/s and 100 Mbit/s.