# US 2022/0033111 A1 · Stackable satellite structure and deployment method > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2022/0033111 A1 - Document ID: US20220033111A1 - Status: Published application - Kind: A1 - Application number: 16/943,203 - Filed: 2020-07-30 - Published: 2022-02-03 - Earliest claimed: 2020-07-30 - Assignees: The Aerospace Corporation - Applicants: The Aerospace Corporation - Inventors: Richard P. WELLE - Web page: https://patentgrep.com/patent/US20220033111A1 ## CPC - B64G 1/641: {Interstage or payload connectors (docking systems B64G1/646)} - B64G 1/10: Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) - B64G 1/1085: {Swarms and constellations} - B64G 1/64: Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements - B64G 1/643: {for arranging multiple satellites in a single launcher} - B64G 1/2222: {Folding} - B64G 1/244: {Spacecraft control systems} - B64G 1/443: {Photovoltaic cell arrays} - B64G 1/6425: {arrangements for damping vibrations} - B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR ## Abstract An apparatus includes a satellite in the form of a plate having a thickness being smaller than a width of the satellite. The apparatus also includes a plurality of contact points distributed on a face of the satellite, allowing for one or more additional satellites to be stacked upon the satellite. ## Claims ### Claim 1 An apparatus, comprising: a satellite in the form of a plate having a thickness being smaller than a width of the satellite; and a plurality of contact points distributed on a face of the satellite, allowing for one or more additional satellites to be stacked upon the satellite. ### Claim 2 (depends on 1) The apparatus of claim 1, wherein the plate is fabricated from a sandwich panel comprising two face sheets bonded to a core material, the core material being situated between the face sheets. ### Claim 3 (depends on 2) The apparatus of claim 2, wherein the core material is a honeycomb material or a foam material configured to provide structural rigidity while minimizing mass. ### Claim 4 (depends on 2) The apparatus of claim 2, wherein the two face sheets are composed of aluminum or composite material, or printed circuit board material. ### Claim 5 (depends on 2) The apparatus of claim 2, further comprising: non-structural components between the two face sheets in one or more cavities of the core material. ### Claim 6 (depends on 2) The apparatus of claim 2, further comprising: one or more solar cells capable of being exposed to sunlight are distributed on one or both of the two face sheets. ### Claim 7 (depends on 2) The apparatus of claim 2, wherein the sandwich panel comprises one or more gaps through the core material and the one or both of the two face sheets into which non-structural components are inserted. ### Claim 8 (depends on 7) The apparatus of claim 7, wherein the one or more gaps allow for the non-structural components to be distributed in a chassis box sized to fit the one or more gaps. ### Claim 9 (depends on 8) The apparatus of claim 8, wherein the chassis box incorporates a structural element in form of a pin supporting a top and bottom of the plurality of contact points, preventing there from being any gaps in a pattern of the plurality of contact points. ### Claim 10 (depends on 2) The apparatus of claim 2, wherein the plurality of contact points are distributed across the two face sheets in a pattern common to all satellites in a stack. ### Claim 11 (depends on 2) The apparatus of claim 2, wherein the plurality of contact points are configured to carry launch loads through a stack of satellites without surface-to-surface contact between the satellite and other satellites in the stack. ### Claim 12 (depends on 2) The apparatus of claim of claim 2, wherein each of the plurality of contact points are load-bearing pins extending through a thickness of the satellite and protruding through the two face sheets. ### Claim 13 (depends on 12) The apparatus of claim 12, wherein the load bearing pins are configured to carry a load without damaging the satellite, and the load bearing pins being attached to the satellite, restraining the satellite from movement relative to the load bearing pins. ### Claim 14 (depends on 12) The apparatus of claim 12, wherein the load bearing pins comprise a spherical top surface combined with a conical recess, and when the satellite is stacked on top of another satellite, a surface of the conical recess rests on top of a spherical surface of a load bearing pin of the other satellite. ### Claim 15 (depends on 1) An apparatus of claim 1, wherein, when the satellite is stacked on another satellite, the satellite is oriented at an angle with respect to the other satellite, allowing protruding elements of the satellite to fit within gaps of the other satellite. ### Claim 16 An apparatus, comprising: a satellite in the form of a plate having a thickness being smaller than a width of the satellite; and a plurality of contact points distributed on a face of the satellite, allowing for one or more additional satellites to be stacked upon the satellite, wherein the plate is fabricated from a sandwich panel comprising two face sheets bonded to a core material, the core material being situated between the face sheets. ### Claim 17 (depends on 16) The apparatus of claim 16, wherein the sandwich panel comprises one or more gaps through the core material and the one or both of the two face sheets into which non-structural components are inserted. ### Claim 18 (depends on 17) The apparatus of claim 17, wherein the one or more gaps allow for the non-structural components to be distributed in a chassis box sized to fit the one or more gaps. ### Claim 19 (depends on 18) The apparatus of claim 18, wherein the chassis box incorporates a structural element in form of a pin supporting a top and bottom of the plurality of contact points, preventing there from being any gaps in a pattern of the plurality of contact points. ### Claim 20 (depends on 16) The apparatus of claim 16, wherein, when the satellite is stacked on another satellite, the satellite is oriented at an angle with respect to the other satellite, allowing protruding elements of the satellite to fit within gaps of the other satellite.