Spacecraft solar array biasing and tensioning system

1. A system for deploying a solar array blanket portion relative to a spacecraft and supporting the solar array blanket portion in a deployed position, the system comprising:

an extendable frame moveable between a collapsed configuration and an extended configuration, comprising:

a first support arm having first and second opposing distal ends;

a second support arm having first and second opposing distal ends;

a third support arm having first and second opposing distal ends;

a fourth support arm having first and second opposing distal ends;

a first pivot pin assembly defined at an intersection of the first and third support arms and a second pivot pin assembly defined at an intersection of the second and fourth support arms;

a first hinge assembly defined between the second distal end of the first support arm and the first distal end of the second support arm;

a second hinge assembly defined between the second distal end of the third support arm and the first distal end of the fourth support arm; and

a first biasing member having a first end coupled to the first support arm and a second end coupled to the second support arm, the first biasing member extending between the second and first distal ends of the first and second support arms along an exterior portion of the first hinge assembly.

2. The system of claim 1 , further comprising a second biasing member having a first end coupled to the third support arm and a second end coupled to the fourth support arm, the second biasing member extending between the second and first distal ends of the third and fourth support arms along an exterior portion of the second hinge assembly.

3. The system of claim 1 , wherein the first biasing member is an extension spring extending between the second and first distal ends of the first and second support arms that wraps around an exterior portion of the first hinge assembly.

4. The system of claim 1 , further comprising a first hinge bracket secured within the second distal end of the first support arm and a second hinge bracket secured within the first distal end of the second support arm, wherein the first biasing member extends between a first retaining pin secured within the first hinge bracket and a second retaining pin secured within the second hinge bracket.

5. The system of claim 4 , wherein the first retaining pin is secured within at least first and second pin-mounting protrusions extending from a portion of the first hinge bracket, and wherein an annular protrusion defined on a body of the first retaining pin is configured to retain the first retaining pin within the first and second pin-mounting protrusions after passing through the first and second pin-mounting protrusions.

6. The system of claim 4 , further comprising a grooved knuckle assembly defined between the first and second hinge brackets configured to receive the first biasing member as it extends between the first and second hinge brackets.

7. The system of claim 1 , wherein in the collapsed configuration, the first, second, third, and fourth support arms are substantially parallel.

8. The system of claim 7 , further comprising a stop assembly having a bracket configured to substantially prevent at least one of the first, second, third, and fourth support arms from moving into an inverted configuration.

9. A solar array system for a spacecraft, comprising:

a solar array blanket portion moveable from a stowed configuration into a deployed configuration;

an extendable frame coupled to the spacecraft and the blanket portion and moveable from at least a collapsed configuration into an extended configuration to move the solar array blanket portion from the stowed configuration into the deployed configuration, wherein the extendable frame includes at least first and second support arms; and

at least one biasing member extending across an exterior portion of a first hinge assembly that is configured to bias at least a portion of the extendable frame into the deployed configuration, wherein the first hinge assembly pivotally connects a second distal end of the first support arm to a first distal end of the second support arm, and wherein the at least one biasing member is a spring extending between the second and first distal ends of the first and second support arms that wraps around an exterior portion of the first hinge assembly.

10. The solar array system of claim 9 , wherein the at least one biasing member is configured to urge the first and second support arms away from each other.

11. The solar array system of claim 9 , wherein in the collapsed configuration, the first support arm and the second support arm are substantially parallel.

12. The solar array system of claim 9 , wherein the first biasing member extends between a first retaining pin secured within a first hinge bracket and a second retaining pin secured within a second hinge bracket.

13. A spacecraft assembly, comprising:

a chassis;

a solar array blanket portion moveable relative to the chassis from a stowed configuration into a deployed configuration;

an extendable frame coupled to the chassis and the blanket portion and moveable from at least a collapsed configuration into an extended configuration to move the solar array blanket portion from the stowed configuration into the deployed configuration, wherein the extendable frame includes at least first and second support arms;

at least one biasing member having a first end coupled to the first support arm and a second end coupled to the second support arm, the first biasing member extending across an exterior portion of a first hinge assembly that is configured to bias at least a portion of the extendable frame into the deployed configuration; and

a stop assembly having a bracket configured to substantially prevent the first and second support arms from moving into an inverted configuration past a substantially horizontal configuration relative to the spacecraft.

14. The spacecraft of claim 13 , wherein the extendable frame is moveable into the extended configuration along a deploy axis that is substantially transverse to the chassis of the spacecraft.

15. The spacecraft of claim 14 , wherein the extendable frame is movably coupled to the spacecraft about a steering axis that is substantially transverse to the deploy axis.