[특허]Partial automated alignment and integration system

Partial automated alignment and integration system 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64G-001/00
출원번호	US-0312481 (2011-12-06)
등록번호	US-8694183 (2014-04-08)
발명자 / 주소	Kelley, Gary Wayne
출원인 / 주소	The United States of America as Represented by the Administrator of the National Aeronautics and Space Administration
대리인 / 주소	Absolute Technology Law Group, LLC
인용정보	피인용 횟수 : 0 인용 특허 : 42

초록 ▼

The present invention is a Partial Automated Alignment and Integration System (PAAIS) used to automate the alignment and integration of space vehicle components. A PAAIS includes ground support apparatuses, a track assembly with a plurality of energy-emitting components and an energy-receiving component containing a plurality of energy-receiving surfaces. Communication components and processors allow communication and feedback through PAAIS.

대표청구항 ▼

1. A Partial Automated Alignment and Integration System (PAAIS) comprised of: at least one horizontally movable equipment component;at least one vertically movable equipment component;a track assembly comprised of a plurality of transportation beams, anda plurality of energy-emitting components movably attached to said transportation beams, wherein at least one of said energy-emitting components is positioned to emit energy along a first axis, wherein at least one of said energy-emitting components is positioned to emit energy along a second axis, wherein at least one of said energy-emitting components is positioned to emit energy along a third axis, wherein said first, second, and third axes intersect at a predetermined end-position and end-orientation of a space vehicle component;at least one energy-receiving component comprised of a six-sided housing, wherein one side is configured to engage an external surface of said space vehicle component and provide a path for electrical power to enter an electrical power system of said space vehicle component,a plurality of energy-receiving surfaces fixedly attached to at least one of said housing sides and configured to receive energy emitted by said energy-emitting components, wherein at least one of plurality of energy-receiving surfaces is oriented to receive energy along said first axis when said space vehicle component is in a first position and a first orientation, wherein at least one of plurality of energy-receiving surfaces is oriented to receive energy along said second axis when said space vehicle component is in a second position and a second orientation, wherein at least one of plurality of energy-receiving surfaces is oriented to receive energy along said third axis when said space vehicle component is in a third position and a third orientation;at least one communication hardware component; andat least one hardware processing component. 2. The system of claim 1 wherein said energy-receiving surface contains nine sub-surfaces. 3. The system of claim 1 wherein said energy-receiving component is configured with software to communicate with said hardware processing component. 4. The system of claim 1 wherein said one side of said six-sided housing configured to engage a space vehicle component engages said space vehicle component at a ground umbilical carrier plate. 5. The system of claim 1 wherein said hardware processing component is configured with software to move said energy-emitting components on said transportation beams. 6. The system of claim 1 wherein said at least one energy-receiving component is configured to convert thermal energy to electrical energy. 7. The system of claim 1 wherein said at least one energy-receiving component is configured to provide continual feedback to said at least one processing component. 8. The system of claim 1 wherein said energy-emitting components contain a high-power laser energy source and a low-power laser energy source. 9. The system of claim 1 wherein at least one of said energy-emitting components emits energy along an x axis, at least one of said energy-emitting components emits energy along a y axis, and at least one of said energy-emitting components emits energy along a z axis. 10. The system of claim 1 wherein said horizontally movable equipment component is configured to move said space vehicle component along an axis selected from the group consisting of an x-axis, a y-axis and combinations thereof. 11. The system of claim 10 wherein said movement is automated. 12. The system of claim 1 wherein said vertically movable equipment component is configured to move said space vehicle component along a z-axis. 13. The system of claim 12 wherein said movement is automated. 14. A computer system-implemented method for aligning a space vehicle component comprising the steps of: engaging an external surface of said space vehicle component with at least one energy-receiving component comprised of a six-sided housing, wherein at least one of said sides is configured to engage said external surface and provide a path for electrical power to enter an electrical power system of said space vehicle component and wherein a plurality of energy-receiving surfaces are fixedly attached to at least one of said sides,receiving input relating to positions of at least three energy-emitting components;adjustably positioning said at least three energy-emitting components along a plurality of transportation beams so that axes of emitted energy from each of said energy-emitting components intersect at a target location corresponding to a predetermined end-position and end-orientation of said space vehicle component;emitting energy from said energy-emitting components;moving said space vehicle component operatively connected to said at least one energy-receiving component with at least one horizontally vertically movable equipment component and at least one vertically movable equipment component until said energy-receiving component receives said emitted energy, wherein said energy-receiving component engages an external surface of said space vehicle component and provides a path for electrical power to enter an electrical power system of said space vehicle component;converting said emitted energy into electrical energy;feeding said electrical energy into an electrical power system of said space vehicle component,sending a signal to a feedback processor using said electrical energy to communicate an exact position of said space vehicle component;readjusting said position of said space vehicle component based on feedback from said feedback processor;continuously providing a signal to said feedback processor to communicate said exact position of said space vehicle component to create a feedback loop;ending said feedback loop when said space vehicle component reaches said target location. 15. The method of claim 14 wherein said energy-receiving component contains at least one energy-receiving surface. 16. The method of claim 15 wherein said energy-receiving surface contains 9 sub-surfaces. 17. The method of claim 16 which further includes the step of determining which of said 9 sub-surfaces is receiving said emitted energy. 18. The method of claim 14 wherein said energy-emitting components emit low-power laser energy to be received by said at least one energy-receiving component. 19. The method of claim 18 which further includes the step of emitting high-power laser energy upon feedback from said energy-receiving component indicating that said energy-receiving component is receiving said emitted energy. 20. The method of claim 14 which further includes the step of repeating said method with further space vehicle components.

이 특허에 인용된 특허 (42)

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Polidoro Roger J. ; Bass Henry M. ; Churchill Russell J. ; Thomas Bruce L. ; Loftus Lloyd K., Laser aligned robotic machining system for use in rebuilding heavy machinery.
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Summerville David F. (Garland TX) Williston John P. (Plano TX) Wand Martin A. (Plano TX) Doty Thomas J. (Dallas TX) Rice Haradon J. (Plano TX), Method for controlling the movements of a mobile robot in a multiple node factory.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
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A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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Partial automated alignment and integration system 원문보기

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