Spacecraft body with roller mechanism for deployable-retractable thin film solar array
阅读：294发布：2023-09-18
专利汇可以提供Spacecraft body with roller mechanism for deployable-retractable thin film solar array专利检索，专利查询，专利分析的服务。并且Rotatable, roller booms are carried by an extendable member which moves outward from a spacecraft body with one end of each flexible solar cell panel rigidly coupled to the spacecraft body and the other end rigidly coupled to the periphery of a rotatable roller boom. During deployment, the solar cell panels which are rolled up on the roller booms unwind. A spring-operated negator motor coupled to the rotating boom at one end and to the fixed housing at the end of the deployment member, winds up during deployment of the solar cell panel to facilitate retracting of the thin film solar array by rewinding the flexible solar panels about the periphery of the roller booms.，下面是Spacecraft body with roller mechanism for deployable-retractable thin film solar array专利的具体信息内容。
1. In combination, a spacecraft including a spacecraft body, extensible and retractable support means carried by said spacecraft and movable outwardly of said spacecraft body, roller boom means rotatably coupled to the outer end of said support means, flexible panel means comprising at least one flexible solar cell panel having its inner edge fixed to said body for both mechanical and electrical connection thereto and its outer edge fixed to the periphery of said roller boom means, and motor means carried at the outer end of said extensible support means and operatively coupled to said roller boom means for applying tension to said panel during extension of said support means and maintaining tension on said panel while said support means is extended and for exerting a force on said roller boom means to cause rotation of said roller boom means and wrapping of said panel means about said roller boom means during retraction of said support means.
2. In combination, a spacecraft including a spacecraft body, extensible and retractable support means carried by said spacecraft and movable outwardly of said spacecraft body, roller boom means rotatably coupled to the outer end of said support means, flexible panel means comprising dual flexible solar panels having their inner edges respectively fixed to said body and their outer edges respectively fixed to the periphery of said roller boom means with said extensible support means comprising a light weight metal tube, and wherein a housing is fixed to the outer end of said tube and includes annular bearings internally thereof, a rotatable shaft is mounted within said housing on said annular bearings and has ends extending outwardly from both sides of said housing, and means coupling the outer edge of each solar cell panel to said rotatable shaft on respective sides of said housing, said spacecraft further comprising means for applying tension to said flexible panels during deployment and maintaining said tension when deployed.
3. The spacecraft as claimed in claim 1, wherein; said flexible panel means comprise dual flexible solar cell panels, said extensible and retractable support means comprises a light weight metal tube, a housing is fixed to the outer end of said tube and includes annular bearings internally thereof, a rotatable shaft is mounted within said housing on said annular bearings and has ends extending outwardly from both sides of said housing, and wherein means couple the outer edge of each solar cell panel to said rotatable shaft on respective sides of said housing.
4. The spacecraft as claimed in claim 2, wherein said means for applying tension to said flexible panel means includes negator motor means comprising a steel negator spring coiled about said rotatable shaft with one end of said spring fixed to said housing and the other end of said spring fixed to said rotatable shaft whereby; extension of said support means results in unwrapping of said flexible solar cell panels from the periphery of said shaft and winding up of said steel negator spring.
5. The spacecraft as claimed in claim 4, wherein: said housing includes threaded, metal bushings at respective ends, said rotatable shaft includes a pair of shoulders formed on the outer periphery anD axially inwards of said threaded metal housing bushings, and said spacecraft further includes lightweight metal ballbearings sandwiched between said shoulders and said bushings for rotatably mounting said shaft within said relatively fixed housing.
6. The spacecraft as claimed in claim 4 further comprising paired, Teflon bailers positioned on either side of said steel negator spring, and snap rings carried by peripheral slots within said rotatable shaft for locating said spring axially with respect to said rotatable shaft.
7. The spacecraft as claimed in claim 1, wherein; said flexible panel means comprises a pair of solar cell panels and wherein said roller boom means comprises: a rotatable shaft extending through a housing fixed to the outboard end of said support means, Teflon end caps mounted on said rotatable shaft adjacent to the ends of the housing and at the ends of said rotatable shaft, a sleeve member extending between respective end caps on each side of said housing to define individual roller booms for each solar cell panel and means for fixing the outer edge of said solar cell panels to the periphery of respective sleeve members.
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