Spacecraft that provides operating resources for externally docked modules
The method and the system of this invention center around the innovative concept of an orbit-independent spacecraft comprised of a physical structure that provides multiple docking devices placed in a spatial relationship and orientation on the exterior of the spacecraft. The docking devices provide a standard interface to the spacecraft by which to attach and detach modular components (payloads). Payloads to be docked to the spacecraft have identical docking devices as part of their physical assemblies. A payload that has been launched into space is navigated towards the spacecraft using a transfer vehicle. Payload and spacecraft docking devices are brought into physical contact where internal locking mechanisms create a secure attachment of the payload to the spacecraft. Physical connections within the payload and spacecraft docking devices are made, allowing the payload to access bus capabilities such as electrical power, data communications, sensor readings, and thermal management from the spacecraft.
1 . A spacecraft structure comprising:
one or more trusses or platforms configured to host a plurality of components, payloads, and modules at various docking locations, each truss or platform having one or more main internal physical conduits that are configured to provide power distribution infrastructure, data communications links, and connections to available spacecraft resources to the plurality of components, payloads, and modules, and wherein each main internal physical conduit connects to one or more side conduits and terminates at the various docking locations;
a plurality of spacecraft docking devices present at the various docking locations on the one or more spacecraft trusses or platforms and configured to provide standard attachment and resource interfaces, to attach and detach to the plurality of components, payloads, and modules, to connect the plurality of components, payloads, and modules via one or more spacecraft docking device connections to the one or more internal physical conduits, and to provide fuel, power, external and on-platform data communications, sensor readings, thermal management and available spacecraft resources to the plurality of components, payloads, and modules via the spacecraft docking device connections to the one or more internal physical conduits of the one or more spacecraft trusses or platforms, wherein the plurality of components, payloads, and modules each have a corresponding docking device configured to attach to and detach from one or more of the plurality of spacecraft docking devices located on the one or more trusses or platforms.
2 . The spacecraft structure of claim 1 , wherein each of the one or more trusses or platforms comprises a unit section of the spacecraft structure that attaches to other trusses or platforms end-to-end, extending or repeating along the length of the spacecraft structure, wherein the one or more main internal physical conduits pass through each unit section at first and second ends to connect to and continue into adjacent unit sections, wherein the one or more side conduits connect orthogonally to the main internal physical conduit and terminate at one or more corresponding side faces, comprising the docking locations with spacecraft docking devices positioned at the center of each side face of the respective spacecraft unit section, wherein the plurality of spacecraft docking devices and the corresponding component, payload, and module docking devices each include one or more of contact sensors, pre-marked fiducials, locking mechanisms, and actuators, and wherein the plurality of spacecraft docking devices have docking aids configured to monitor fiducials and correct for rotational errors prior to docking and locking.
3 . The spacecraft structure of claim 1 , wherein one or more of the plurality of components, payloads, and modules comprise mission-critical components, payloads, and modules, including one or more of computers, sensors, batteries, thermal management and control, actuators, mechanisms, solar panel arrays, sun sensors, radio/optical communications, data communications, gimbaled and fixed antenna payloads, phased array antennas, radar payloads, collapsible booms, scientific research, navigation, propellant tanks, and propulsion systems, that are configured to be docked to one or more of the plurality of docking devices located on the one or more spacecraft trusses or platforms.
4 . The spacecraft structure of claim 3 , wherein the one or more main internal physical conduits protrude from the spacecraft structure to allow attachment to and connection with one or more solar array assemblies and sun sensor payloads, wherein one or more gimbaled antenna payloads and phased array payloads are mounted to a nadir pointing deck, and wherein one or more collapsible booms are configured to extend to hold electromagnetically sensitive components, payloads, or modules away from the spacecraft structure during operation.
5 . The spacecraft structure of claim 1 , wherein solar panel arrays comprising one or more of the plurality of components, payloads, and modules docked to one or more of the plurality of docking devices located on the one or more spacecraft structure trusses or platforms prior to launch of the spacecraft structure may obstruct one or more of the plurality of docking devices not docked to the solar panel arrays during launch, and reveal the previously blocked docking devices once the solar panel arrays are fully deployed and extended away from the spacecraft structure.
6 . The spacecraft structure of claim 1 , wherein the plurality of components, payloads, and modules are configured to receive communications and instructions for navigation and docking from the spacecraft structure, and one or more of the plurality of components, payloads, and modules is launched into outer space and configured to navigate to and rendezvous and dock with the spacecraft structure.
7 . The spacecraft structure of claim 1 , wherein the spacecraft structure includes a transfer vehicle configured to navigate one or more of the plurality of components, payloads, and modules between post-launch deployment and the spacecraft structure.
8 . A modular spacecraft system comprising:
one or more trusses or platforms configured to host a plurality of modular components, payloads, and modules at various docking locations, each truss or platform having one or more main internal physical conduits that are configured to provide power distribution infrastructure, data communications links, and connections to available spacecraft resources to the plurality of modular components, payloads, and modules, and wherein each main internal physical conduit connects to one or more side conduits and terminates at the various docking locations;
a plurality of truss or platform docking devices present at the various docking locations on the one or more spacecraft trusses or platforms and configured to provide standard attachment and resource interfaces, to attach and detach to the plurality of modular components, payloads, and modules, to connect the plurality of modular components, payloads, and modules via one or more truss or platform docking device connections to the one or more internal physical conduits, and to provide fuel, power, external and on-platform data communications, sensor readings, thermal management and available spacecraft resources to the plurality of modular components, payloads, and modules via truss or platform docking device connections to the one or more internal physical conduits of the one or more spacecraft trusses or platforms, wherein the plurality of modular components, payloads, and modules each have a corresponding docking device configured to attach to and detach from one or more of the plurality of truss or platform docking devices.
9 . The modular spacecraft system of claim 8 , wherein each of the one or more trusses or platforms comprises a unit section of modular spacecraft system that attaches to other trusses or platforms end-to-end, extending or repeating along the length of modular spacecraft system, wherein the one or more main internal physical conduits pass through each unit section at first and second end faces to connect to and continue into adjacent unit sections, wherein the one or more side conduits connect orthogonally to the main internal physical conduit and terminate at one or more corresponding side faces, comprising the docking locations with truss or platform docking devices positioned at the center of each side face of the respective modular spacecraft system unit section, wherein the plurality of truss or platform docking devices and the corresponding component, payload, and module docking devices each include one or more of contact sensors, pre-marked fiducials, locking mechanisms, and actuators, and wherein the plurality of truss or platform docking devices have docking aids configured to monitor fiducials and correct for rotational errors prior to docking and locking.
10 . The modular spacecraft system of claim 8 , wherein one or more of the plurality of modular components, payloads, and modules comprise mission-critical components, payloads, and modules, including one or more of computers, sensors, batteries, thermal management and control, actuators, mechanisms, solar panel arrays, sun sensors, radio/optical communications, data communications, gimbaled and fixed antenna payloads, phased array antennas, radar payloads, collapsible booms, scientific research, navigation, propellant tanks, and propulsion systems, that are configured to be docked to one or more of the plurality of truss or platform docking devices located on the one or more spacecraft trusses or platforms prior to launch of the modular spacecraft system.
11 . The modular spacecraft system of claim 10 , wherein the one or more main internal physical conduits protrude from modular spacecraft system to allow attachment to and connection with one or more solar array assemblies and sun sensor payloads, wherein one or more gimbaled antenna payloads and phased array payloads are mounted to a nadir pointing deck, and wherein one or more collapsible booms are configured to extend to hold electromagnetically sensitive components, payloads, or modules away from the modular spacecraft system during operation.
12 . The modular spacecraft system of claim 8 , wherein solar panel arrays comprising one or more of the plurality of modular components, payloads, and modules docked to one or more of the plurality of truss or platform docking devices prior to launch of the modular spacecraft system may obstruct one or more of the plurality of truss or platform docking devices not docked to the solar panel arrays during launch, and unblock and reveal the previously obstructed one or more truss or platform docking devices when the solar panel arrays are fully deployed and extended away from the spacecraft.
13 . The modular spacecraft system of claim 8 , wherein the plurality of modular components, payloads, and modules are configured to receive communications and instructions for navigation and docking from the spacecraft system, and one or more of the plurality of modular components, payloads, and modules is launched into outer space and configured to navigate to and rendezvous and dock with a spacecraft.
14 . The modular spacecraft system of claim 8 , wherein the modular spacecraft system includes a transfer vehicle configured to navigate one or more of the plurality of modular components, payloads, and modules between post-launch deployment and a spacecraft.