Component Deployment System

Abstract

A method and apparatus for deploying a group of panels. An apparatus comprises a group of panels in a folded configuration against a side of a spacecraft, a group of flexible members connected to the group of panels, and an interface system associated with the group of panels and the group of flexible members. The interface system is configured to move the group of panels from the folded configuration to a deployed configuration when the group of flexible members is extended from the spacecraft.

1 - 21 . (canceled) 
     
     
         22 . A steering system comprising:
 a platform in a folded configuration and associated with a housing of a satellite, wherein the platform comprises:
 a first set of solar modules configured to be folded along a longitudinal axis; and 
 a second set of solar modules configured to be folded along a diagonal axis to form the folded configuration; and 
   a movement system associated with the platform and configured to change an orientation of the platform to maneuver a group of components in space after the group of components is deployed from the satellite, wherein the group of components includes at least the first set of solar modules and the second set of solar modules.   
     
     
         23 . The steering system of  claim 22 , wherein the movement system is configured to tilt the group of components by changing the orientation of the platform such that the group of components has a desired orientation. 
     
     
         24 . The steering system of  claim 23 , wherein the movement system comprises an actuator configured to extend and retract such that the platform moves about a pivot point. 
     
     
         25 . The steering system of  claim 24 , wherein the movement system is configured to tilt the platform to receive a desired amount of electromagnetic signals. 
     
     
         26 . The steering system of  claim 22 , wherein the platform is located within the housing of the satellite. 
     
     
         27 . The steering system of  claim 22  further comprising:
 a spring configured to reduce torque needed from the movement system to change the orientation of the platform. 
 
     
     
         28 - 32 . (canceled) 
     
     
         33 . A solar panel comprising:
 a solar array having a first set of solar modules configured to be folded along a longitudinal axis and a second set of solar modules configured to be folded along a diagonal axis to form a folded configuration for the solar array.   
     
     
         34 . The solar panel of  claim 33 , wherein the solar array is associated with a satellite and configured to be deployed from the satellite using a deployment system. 
     
     
         35 . The solar panel of  claim 33 , wherein the first set of solar modules is folded along the longitudinal axis and the second set of solar modules is folded along the diagonal axis such that a risk of damage to one or more solar cells within the solar array is reduced. 
     
     
         36 . The solar panel of  claim 33  further comprising:
 a movement system connected to the solar array and to a satellite, the movement system configured to change an orientation of the solar array to maneuver the first set of solar modules and the second set of solar modules. 
 
     
     
         37 . The solar panel of  claim 36 , wherein the solar array is initially deployed inside a housing of the satellite, and wherein the movement system is further configured to move the solar array outside the satellite. 
     
     
         38 . The solar panel of  claim 37  further comprising a flexible member connected to the solar array and to the movement system, and wherein the movement system is further configured to extend the flexible member. 
     
     
         39 . The solar panel of  claim 38 , wherein the flexible member is initially stored inside the housing with the solar array. 
     
     
         40 . The solar panel of  claim 39 , wherein the flexible member is connected to the satellite at two points to form one of an ellipse or a circle when the flexible member is extended. 
     
     
         41 . The solar panel of  claim 40 , wherein the flexible member is connected to the solar array at a plurality of different points such that, when extended, the solar array extends across a major axis or a semi-major axis or the ellipse, or a diameter of the circle. 
     
     
         42 . The solar panel of  claim 41 , wherein the movement system further comprises an actuator configured to extend and retract such that the solar array moves about a pivot point. 
     
     
         43 . The solar panel of  claim 42 , wherein the movement system is further configured to tilt the solar array to receive a desired amount of electromagnetic signals. 
     
     
         44 . The solar panel of  claim 43  further comprising:
 a spring configured to reduce torque needed from the movement system to change the orientation of the solar array. 
 
     
     
         45 . The solar panel of  claim 44  further comprising:
 a plurality of additional flexible members and a plurality of additional solar arrays that extend from different sides of the satellite. 
 
     
     
         46 . The solar panel of  claim 45 , wherein the solar array, the flexible member, the plurality of additional flexible members, and the plurality of additional solar arrays extend from opened pivoting panel doors connected to corners of the satellite.