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Integrated glass ceramic spacecraft include a plurality of glass ceramic components including molded, tempered, annealed, and patterned glass ceramic components coupled together for forming a support structure or frame or housing through which is communicated optical signals through an optical commu

Integrated glass ceramic spacecraft include a plurality of glass ceramic components including molded, tempered, annealed, and patterned glass ceramic components coupled together for forming a support structure or frame or housing through which is communicated optical signals through an optical communications grid and electrical signals through an electrical communications grid, with the optical communications grid and electrical communication grid forming a composite electrooptical communications grid for spacecraft wide intercommunications. The support structure multifunctions as a frame, a housing, a support, a thermal control system, and as part of an electrooptical communications grid while encapsulating a plurality of optical, electronic, electrical, and MEMS devices between which is communicated the electrical and optical signals over the electrooptical communication grid.In a preferred form, the integrated glass ceramic spacecraft providing internal and external communications, includes a plurality of patterned glass ceramic substrates stacked together to form the spacecraft support structure, with each substrate having a primary function such as thrusting, optical communications, battery power storage, propellant storage, sensing, and central processing.

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1. A spacecraft providing internal and external communications, the spacecraft comprising,glass ceramic components being coupled together for forming a support structure for the spacecraft, one of the glass ceramic components being made of a photostructurable glass ceramic material and,an antenna su

1. A spacecraft providing internal and external communications, the spacecraft comprising,glass ceramic components being coupled together for forming a support structure for the spacecraft, one of the glass ceramic components being made of a photostructurable glass ceramic material and,an antenna supported by one of the glass ceramic components for external communications,operational devices supported by the support structure, two of the operational devices are optical devices for communicating an optical signal through one of the glass ceramic components providing an optical path along which is communicated the optical signal, two of the operational devices are electronic devices for communicating an electrical signal through one of the glass ceramic components providing an electrical path along which is communicated the electrical signal, one of the operational devices is coupled to the antenna for enabling external communications, andan optoelectronic communications grid enabling intercommunications of the electrical signal between the two electronic devices along the electrical path and enabling intercommunications of the optical signal along the optical path and between the two optical devices. 2. The spacecraft of claim 1, whereinone of the glass ceramic components is a substrate for encapsulating a thruster comprising a nozzle. 3. The spacecraft of claim 1, whereinone of the glass ceramic components is a substrate for encapsulating a battery. 4. The spacecraft of claim 1, whereinone of the glass ceramic components is a substrate for encapsulating a sensor. 5. The spacecraft of claim 1, whereinone of the glass ceramic components is a substrate for encapsulating a communications processor for enabling the external communications. 6. The spacecraft of claim 1, whereinone of the glass ceramic components is a substrate for encapsulating a RF communications processor for enabling the intercommunications. 7. The spacecraft of claim 1, whereinone of the glass ceramic components is a substrate for encapsulating photonic devices for communicating the optical signal. 8. The spacecraft of claim 1, whereinone of the glass ceramic components is a molded component being shaped in a dome for encapsulating a propellant. 9. The spacecraft of claim 1, whereinone of the glass ceramic components is a molded component being shaped in a dome for encapsulating a propellant and for supporting an antenna. 10. The spacecraft of claim 1, wherein,the antenna is disposed on an exterior surface of the support structure and connected to the electrooptical communications grid for enabling the external communications. 11. The spacecraft of claim 1, whereinone of the glass ceramic components is a substrate for encapsulating a thruster comprising a nozzle,one of the glass ceramic components is a substrate for encapsulating a battery,one of the glass ceramic components is a substrate for encapsulating a sensor,one of the glass ceramic components is a substrate for encapsulating a communications processor for enabling the external communications,one of the glass ceramic components is a substrate for encapsulating a RF communications processor for enabling the intercommunications, andone of the glass ceramic components is a substrate for encapsulating a photonic devices for communicating the optical signal. 12. The spacecraft of claim 11, whereinthe molded component being shaped in a dome for encapsulating a propellant and for supporting an antenna. 13. The spacecraft of claim 11, further comprising,an antenna disposed on an exterior surface of the support structure and connected to the electrooptical communications grid for enabling the external communications. 14. The spacecraft of claim 1, whereinthe operational devices are selected from the group consisting of electronic and electrical and photonic and microelectromechanical systems devices,the electrical devices are selected from the group consisting of batteries and power supplies and power converters ,the electronic devices are selected from the group consisting of active sensors and processors and optoelectronic interfaces and RF transmitters and RF receivers,the photonic devices selected from the group consisting of optical transceivers and optical transmitters and optical receivers and optical detectors and mirrors and splitters and reflectors, polarizers and lenses and optical fibers, andthe microelectromechanical systems are selected from the group consisting of gyros and accelerometers and passive sensors and chemical sensors. 15. The spacecraft of claim 1 wherein,the glass ceramic patterned components are direct-write laser milled components, photolithographic exposed and etched components, and direct-write laser exposed and etched components. 16. A spacecraft providing internal and external communications, the spacecraft comprising,glass ceramic components being coupled together for forming a support structure for the spacecraft, one of the glass ceramic components being made of a photostructurable glass ceramic material and, one the glass ceramic components being a molded component,operational devices supported by the support structure, one of the operational devices is an optical device for communicating an optical signal through one of the glass ceramic components providing an optical path along which is communicated the optical signal, andan optoelectronic communications grid enabling intercommunications of electrical and optical signals between the operational devices and for providing the external communications. 17. The spacecraft of claim 16 wherein,the molded component and patterned component comprise a tempered portion. 18. A spacecraft providing internal and external communications, the spacecraft comprising,glass ceramic components being coupled together for forming a support structure for the spacecraft, one of the glass ceramic components being made of a photostructurable glass ceramic material,operational devices supported by the support structure, two of the operational devices are optical devices for communicating an optical signal through one of the glass ceramic components providing an optical path along which is communicated the optical signal, two of the operational devices are electronic devices for communicating an electrical signal through one of the glass ceramic components providing an electrical path along which is communicated the electrical signal, andan optoelectronic communications grid enabling intercommunications of the electrical signal between the two electronic devices along the electrical path and enabling intercommunications of the optical signal along the optical path and between the two optical devices, whereineach of the glass ceramic components has a primary operational function,one of the glass ceramic components is a substrate for encapsulating a thruster comprising a nozzle,one of the glass ceramic components is a substrate for encapsulating a battery,one of the glass ceramic components is a substrate for encapsulating a sensor,one of the glass ceramic components is a substrate for encapsulating a RF communications processor for enabling the intercommunications, andone of the glass ceramic components is a substrate for encapsulating a photonic devices for communicating the optical signal. 19. The spacecraft of claim 18 wherein,one of the glass ceramic components is selected from the group consisting of a molded component, a tempered component, and an annealed component.