Spacecraft chassis and component configuration

Abstract

A chassis for a spacecraft includes a solid plate that includes a first side and an opposing second side, and also includes a plurality of transverse walls extending from a surface of the second side and configured to radiate heat generated from the spacecraft into outer space.

1 . A chassis for a spacecraft, the chassis comprising:
 a solid plate comprising a first side and an opposing second side; and   a plurality of transverse walls extending from a surface of the second side and configured to radiate heat generated from the spacecraft into outer space.   
     
     
         2 . The chassis of  claim 1 , wherein the plurality of transverse walls defines a cellular grid structure. 
     
     
         3 . The chassis of  claim 1 , wherein the plate is formed from a metal material. 
     
     
         4 . The chassis of  claim 1 , further comprising at least one mounting feature defined on the first side that is configured to secure at least one heat-generating component directly to the plate. 
     
     
         5 . The chassis of  claim 4 , wherein the at least one mounting feature is a threaded hole configured to receive a threaded fastener after passing through a portion of the at least one heat-generating component. 
     
     
         6 . The chassis of  claim 4 , wherein the at least one heat-generating component is a payload component selected from a group consisting of phased array transmit and receive panels, a satellite network computer, and modem boards. 
     
     
         7 . The chassis of  claim 4 , wherein the at least one heat generating component comprises a plurality of heat generating components spaced apart to facilitate heat dissipation. 
     
     
         8 . A spacecraft, comprising:
 a chassis body defining a first side and an opposing second side;   a solar array assembly carried by the chassis body; and   a plurality of transverse walls extending from a surface of the second side and configured to radiate heat generated from the spacecraft into outer space.   
     
     
         9 . The spacecraft of  claim 8 , further comprising at least one heat-generating component mounted to the chassis body, wherein heat generated by the at least one heat-generating component is transferrable to the chassis body. 
     
     
         10 . The spacecraft of  claim 9 , further comprising at least one mounting feature defined on the first side that is configured to secure the at least one heat-generating component directly to the chassis body. 
     
     
         11 . The spacecraft of  claim 10 , wherein the at least one mounting feature is a threaded hole defined in the chassis body that is configured to receive a threaded fastener after passing through a portion of the at least one heat-generating component. 
     
     
         12 . The spacecraft of  claim 9 , wherein the at least one heat-generating component comprises a plurality of heat-generating components spaced apart to facilitate heat dissipation. 
     
     
         13 . The spacecraft of  claim 9 , wherein the at least one heat-generating component is a payload component selected from a group consisting of phased array transmit and receive panels, a satellite network computer, and modem boards. 
     
     
         14 . The spacecraft of  claim 8 , wherein the plurality of transverse walls defines a cellular grid structure. 
     
     
         15 . The spacecraft of  claim 8 , wherein the chassis body is an elongated solid flat panel. 
     
     
         16 . The spacecraft of  claim 8 , further comprising at least one power storage and distribution component mounted to the chassis body at substantially a center of the chassis body. 
     
     
         17 . The spacecraft of  claim 16 , wherein the at least one power storage and distribution component is one of a battery and a flight computer connected to at least one heat-generating component of the spacecraft through at least one power harness connection. 
     
     
         18 . The spacecraft of  claim 8 , further comprising at least one low heat component mounted to the chassis body near a perimeter of the chassis body. 
     
     
         19 . The spacecraft of  claim 18 , wherein the at least one low heat component is one of an antenna system, a star tracker, a magnetometer, a tracking and telemetry radio, a camera, a GPS antenna thruster, a thruster propellant container, a torque rod, a solar array steering actuator, and a reaction wheel. 
     
     
         20 . The spacecraft of  claim 18 , wherein the at least one low heat component is cantilevered from the chassis body.