Aeronautics and astronautics – Spacecraft – Spacecraft formation – orbit – or interplanetary path
Reexamination Certificate
2000-04-25
2001-10-30
Jordan, Charles T. (Department: 3644)
Aeronautics and astronautics
Spacecraft
Spacecraft formation, orbit, or interplanetary path
Reexamination Certificate
active
06308919
ABSTRACT:
BACKGROUND
The present invention relates generally to spacecraft, and more particularly, to a dual reflector holddown for use in supporting and deploying nested reflectors disposed on a spacecraft.
The assignee of the present invention manufactures and deploys spacecraft that have reflectors (communication antennas) disposed on the spacecraft body that are used to reflect communication signals. Heretofore, nested reflectors have not been used on any spacecraft developed by the assignee of the present invention. Single reflectors are supported and released by commonly available holddowns. Part numbers E008080-01 and E028600-01 manufactured by the assignee of the present invention are examples of such commonly available holddowns. However, it would be desirable to provide for the use and deployment of nested reflectors on spacecraft.
Accordingly, it would be advantageous to have a dual reflector holddown for use in supporting and deploying nested reflectors disposed on a spacecraft.
SUMMARY OF THE INVENTION
The present invention provides for a spacecraft having nested reflectors that are released and deployed during a single release event. One or more dual reflector holddowns are provided that support and deploy the nested reflectors. The nested reflectors are held in place prior to release by the one or more dual reflector holddowns and then released using a ground command during the release event.
The spacecraft has a body to which the nested reflectors are secured using the one or more dual reflector holddowns. Reflector backup structures are secured to rear surfaces of the reflectors. The reflector backup structures each comprise a generally triangular tubular structure connected to a hinge and to the rear surfaces of the respective reflectors. The reflector backup structures are secured to the dual reflector holddowns by means of reflector interface brackets that are part of the dual reflector holddowns located adjacent vertices of the triangular tubular structure. The dual reflector holddowns releasably secure the reflector backup structures to the body.
An exemplary dual reflector holddown comprises a separable tubular housing which may include an outer housing, an outer insert, a middle insert, and inner housing and an inner insert longitudinally secured together, using a single (tensioned) rod. An end cap and a release device are disposed on opposite ends of the tubular housing. The rod extends axially through the end cap, the tubular housing and the release device. The rod is secured by a nut at the end cap and a ball retained by the release device. A retraction spring is disposed around the exterior of the housing adjacent to the end cap. Reflector interface brackets are secured to the housing that attach the plurality of reflectors to the holddown.
The one or more dual reflector holddowns may be used to support the reflectors during launch and orbit raising of the spacecraft. The single release event separates components of the outer reflector holddown from the components of the inner reflector holddown, and components of the inner reflector holddown from interfaces on the spacecraft. The reflectors are then free for deployment.
The various housings of the dual reflector holddown are mutually threaded and hence adjustable along the axis of the holddown. The dual reflector holddown also has three rotational degrees of freedom due to the construction of the interface brackets and the manner in which they are attached to their respective housings. Furthermore, the dual reflector holddown also has zero, one or two translational degrees of freedom due to the adjustable floating interfaces at the holddown attachments to the reflector backup structure.
REFERENCES:
patent: 4491446 (1985-01-01), Ewald
patent: 267876 (1983-06-01), None
patent: 2517626 (1983-06-01), None
patent: 87/04372 (1987-07-01), None
Baghdasarian Varouj G.
Palmer Tyler A.
Dinh Tien
Float Kenneth W.
Jordan Charles T.
Space Systems Loral, Inc.
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