# US 8,786,703 B1 · Integrated antenna system for imaging microsatellites > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,786,703 B1 - Document ID: US8786703B1 - Status: Granted - Kind: B1 - Application number: 14/132,963 - Filed: 2013-12-18 - Granted: 2014-07-22 - Earliest claimed: 2010-12-15 - Assignees: Skybox Imaging, Inc. - Applicants: Skybox Imaging, Inc. - Inventors: Henrique do Carmo Miranda - Web page: https://patentgrep.com/patent/US8786703B1 ## CPC - H04N 7/005: {using at least one opto-electrical conversion device} - B64G 1/1021: {Earth observation satellites} - B64G 1/222: {for deploying structures between a stowed and deployed state} - B64G 1/66: Arrangements or adaptations of apparatus or instruments, not otherwise provided for - H01Q 1/08: Means for collapsing antennas or parts thereof (collapsible loop antennas H01Q7/02; means for collapsing H-antennas or Yagi antennas H01Q19/04) - H01Q 1/288: {Satellite antennas} - H01Q 19/10: using reflecting surfaces - H04B 7/18515: {Transmission equipment in satellites or space-based relays} - H04N 7/18: Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast - H04N: PICTORIAL COMMUNICATION, e.g. TELEVISION - B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR - H01Q: ANTENNAS, i.e. RADIO AERIALS (radiators or antennas for microwave heating H05B6/72) - H04B: TRANSMISSION ## Abstract 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 1) The method of claim 1, wherein the transmitting provides a data transmission rate between 1 Mbit/s and 100 Mbit/s. ### Claim 4 (depends on 1) 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. ### Claim 5 (depends on 1) 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. ### Claim 6 (depends on 1) 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. ### Claim 7 (depends on 1) The method of claim 1, further comprising deploying one or more solar panels configured to provide power to electrical components in the imaging satellite. ### Claim 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. ### Claim 9 (depends on 8) 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. ### Claim 10 (depends on 8) 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. ### Claim 11 (depends on 8) 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. ### Claim 12 (depends on 11) The method of claim 11, wherein the opening mechanism comprises a spring. ### Claim 13 (depends on 8) The method of claim 8, further comprising attaching one or more solar panels to the imaging satellite. ### Claim 14 (depends on 8) 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. ### Claim 15 (depends on 14) 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. ### Claim 16 (depends on 14) 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.