Deployable solar array for small spacecraft

Patent metadata

Field	Value
Publication number	US-10793296-B2
Application number	US-201815890163-A
Country	US
Kind code	B2
Filing date	Feb 6, 2018
Priority date	Oct 24, 2014
Publication date	Oct 6, 2020
Grant date	Oct 6, 2020

Abstract

The present disclosure provides, among other things, a deployable solar array comprising: an array of electromagnetic transducer devices such as photovoltaic devices; and a flexible, elongated, rectangular sheet for supporting the array of electromagnetic transducer devices composed of a composite laminate having a predetermined pattern of graphite fiber plies which impart a predefined tension in the planar surface of the sheet so that it curls into a planar sheet with a uniform radius of curvature along its major axis.

First claim

What is claimed is:

1. A spacecraft comprising:
a housing having deployment apertures;
a spool disposed within the housing;
first and second deployable arrays, each of the deployable arrays including:
an array of photovoltaic devices, each of which has a backside surface mounted on a polyimide carrier; and
a flexible sheet for supporting the array of photovoltaic devices,
wherein each of the sheets is composed, respectively, of a composite laminate to which the polyimide carrier is bonded,

wherein the spool is operable to support the sheet of each of the deployable arrays in a stowed configuration in which the sheets are coiled under compressive force, wherein, in the stowed configuration, each of the sheets is wound about the spool, and wherein each respective sheet is operable to curl into a curvilinear sheet when the sheet is unwound from the stowed configuration, wherein a respective end of a first one of the sheets directly contacts and overlaps a respective end of a second one of the sheets in the stowed configuration and in a deployed configuration; and
a structure operable to enable automatic unwinding of the sheets from the spool during a deployment operation so that the sheet of the first deployable solar array is deployed through a first one of the deployment apertures in a first direction from the spacecraft and the sheet of the second deployable solar array is deployed through a second one of the deployment apertures in a same plane as the sheet of the first deployable solar array but in an opposite direction from the spacecraft.

2. The spacecraft of claim 1 wherein each of the deployable arrays comprises a string of solar cell assemblies connected in at least one of a serial or parallel electrical configuration.

3. The spacecraft of claim 1 wherein the spool is disposed within a one unit CubeSat housing.

4. The spacecraft of claim 1 wherein each of the sheets is operable to form into a respective planar sheet having a uniform curvature as the sheet unwinds from the support.

5. The spacecraft of claim 1 wherein each of the sheets has a width of less than 100 mm.

6. The spacecraft of claim 1 wherein each of the sheets has a thickness of between 0.1 mm and 0.3 mm.

7. The spacecraft of claim 1 wherein each of the sheets is composed, respectively, of a composite laminate that includes a pattern of plies which impart a tension to the surface of the sheet so that the sheet curls into a curvilinear sheet when the sheet is unwound from the stowed configuration.

8. The spacecraft of claim 7 wherein the composite laminate comprises graphite fiber plies.

9. The spacecraft of claim 1 wherein each of the sheets is a single rectangular sheet.

10. A method of deploying the spacecraft of claim 1 in space, the method comprising:
providing the spacecraft of claim 9 ;
supporting the sheets
under compression in the stowed configuration; and
releasing the sheets from the stowed configuration during a deployment operation so that the sheets automatically deploy.

11. The method of claim 10 wherein the sheet of the first deployable solar array is deployed through the first one of the deployment apertures in the first direction from the spacecraft, and the sheet of the second deployable solar array is deployed through the second one of the deployment apertures in the same plane as the sheet of the first deployable solar array but in the opposite direction from the spacecraft.

Assignees

• Solaero Tech Corp

Inventors

• Steele Kenneth Loyd
• Stern Theodore Garry

Classifications

• B64G1/407

  Solar sailing · CPC title

• B64G1/2229

  characterised by the deployment actuating mechanism (inflating B64G1/2227) · CPC title

• B64G1/2225

  Rolling or unfurling (B64G1/2227 takes precedence) · CPC title

• H10F77/80

  Arrangements for preventing damage to photovoltaic cells caused by corpuscular radiation, e.g. for space applications · CPC title

• H02S30/20 Primary

  Collapsible or foldable PV modules · CPC title