DEPLOYABLE SOLAR ARRAY FOR A SPIN STABILIZED SPACECRAFT

• US 3,817,481 A
• Filed: 11/17/1971
• Issued: 06/18/1974
• Est. Priority Date: 11/17/1971
• Status: Expired due to Term

• Current Assignee: Hans F. Meissinger, William I. Berks
• Original Assignee: Hans F. Meissinger, William I. Berks
• Inventors: Berks, William I., Meissinger, Hans F.
• Primary Examiner(s): Halvosa, George E. A.
• Assistant Examiner(s): Kelmachter, Barry L.
• Application Number:
  US05/199,539
• Time in Patent Office: 944 Days
• Field of Search: 244/1SS,1SA 136/89
• US Class Current: 244/172.7
• CPC Class Codes: B64G 1/222 for deploying structures between a stowed and deployed state
• CPC Class Codes: B64G 1/281 Spin-stabilised spacecraft
• CPC Class Codes: B64G 1/443 Photovoltaic cell arrays
• CPC Class Codes: Y10S 136/292 Space - satellite

Abstract

A deployable solar array for a spin stabilized spacecraft having a number of thin flexible solar panels spaced circumferentially about the spacecraft body, and deployment means secured to the panel ends for effecting centrifugal deployment of the panels from a launch configuration in which the panels are drawn firmly against the body so as to conform to the circumferential surface to a deployed configuration in which the panels are disposed outwardly from the body, at least between the panel ends, to provide a solar array having an effective area exceeding substantially the circumferential surface area of the body. In certain disclosed embodiments, the ends of the solar panels are wound on rotary drums from which the panels unwind during deployment in such a way that the deployed panels have lobe-like or wing-like configurations and the panels may be retracted to stowed configuration and deployed any number of times in flight. In other disclosed embodiments, the ends of the solar panels are attached to cables which are payed out from the spacecraft to deploy the panels. The panels of the latter embodiment may be joined end to end so as to deploy to an annular panel structure surrounding the body in outwardly spaced relation to the body. In one of these latter embodiments, the cables are attached to drums on the spacecraft body on which both the cables and panels may wind to permit both deployment and retraction of the panels in flight.

Claims

1. A spin stabilized spacecraft comprising:

a spacecraft body;

a number of thin flexible solar panels of approximately equal length joined end to end to form an annular flexible solar array surrounding said body circumferentially; and

deployment means including rotary storage drums spaced circumferentially about said body inwardly of its circumference in its deployed position; and

secured to said panels along their joined ends anD means to effect rotation of said drums for reeling said panel ends inwardly to contract said solar array to a launch configuration wherein said panels are held firmly against and conform to the circumference of said body and unreeling said panel ends outwardly to effect centrifugal deployment of said solar array to a deployed configuration wherein said panels billow outwardly from said body, said drums being located inwardly of the body circumference in the deployed configuration of said panels.

2. A spacecraft according to claim 1 wherein:

said panel ends are directly attached to said drums.

3. A spacecraft according to claim 1 wherein:

said panel ends are attached to said drums by cables which wind on and unwind from said drums.