Large solar arrays with high natural frequencies

A solar array having a stowed and a deployed configuration for use with a satellite, said array comprising:

• an array support frame comprising a pair of spaced-apart substantially parallel spanwise continuous structural members;
• and
• a solar array substrate having a major surface and supported by said frame;
• said spanwise members being fabricated of a material and having a configuration which when said array is in said stowed configuration, enables said array support frame to be wound about said satellite in a direction perpendicular to said major surface of said substrate without exceeding the yield stress of said spanwise members and which causes said spanwise members to unwind said array frame from said satellite;
• said spanwise members, when said array is in said deployed configuration, having a substantially increased stiffness in said direction perpendicular to said major surface of said substrate;
• each spanwise member comprising:
• first and second parallel, relatively rigid beams;
• and
• means for flexibly interconnecting said first and second relatively rigid beams, said interconnecting means being connected to said first and second beams and spacing said beams apart in a direction perpendicular to said major surface of said solar array substrate when said array is in said deployed configuration and being bent when said array is in said stowed configuration

A solar array having a stowed and a deployed configuration for use with a satellite, said array comprising:

• an array support frame comprising a pair of spaced-apart substantially parallel spanwise continuous structural members;
• and
• a solar array substrate which is supported by said frame and which has a major surface;
• each of said spanwise members including a deployable stiffener member and being fabricated of a material and having a stowed configuration in which said array support frame can be wound about said satellite in a direction perpendicular to said major surface of said substrate without exceeding the yield stress of said spanwise members and which provides said spanwise members with a straightening force to unwind said array frame from said satellite;
• said stiffener members being deployed when said array is in its deployed configuration, said stiffener members in their deployed configuration providing said spanwise members with a substantially increased stiffness in said direction perpendicular to said major surface of said substrate;
• wherein:
• each of said stiffener members comprises a relatively rigid beam which is disposed substantially adjacent the plane of said solar array substrate when said stiffener member is in its stowed configuration and which is displaced from the plane of said solar array substrate when said stiffener member is in its deployed configuration.

A satellite comprising:

• a main body;
• first and second solar arrays attached to and extending from said main body and having a stowed and a deployed configuration, each of said solar arrays including:
• a solar array support frame comprising a pair of spaced-apart substantially parallel spanwise continuous structural members;
• a solar array substrate which is supported by said frame and which has a major surface;
• a plurality of solar cells disposed on said major surface of said substrate;
• each of said spanwise members including a deployable stiffener member and being fabricated of a material and having a stowed configuration in which said array support frame including said stiffener member can be wound about said satellite in a direction perpendicular to said major surface of said substrate without exceeding the yield stress of said spanwise members and which provides said spanwise members with a straightening force to unwind said array frame from said satellite;
• said stiffener members being deployed when said array is in its deployed configuration, said stiffener members in their deployed configuration providing said spanwise members with a substantially increased stiffness in said direction perpendicular to said major surface of said substrate.

A satellite comprising:

• a main body;
• first and second solar arrays attached to and extending from said main body and having a stowed and a deployed configuration, each of said solar arrays including:
• a solar array support frame comprising a pair of spaced-apart substantially parallel spanwise continuous structural members;
• a solar array substrate which is supported by said frame and which has a major surface;
• a plurality of solar cells disposed on said major surface of said substrate;
• each of said spanwise members including a deployable stiffener member and being fabricated of a material and having a stowed configuration in which said array support frame can be wound about said satellite in a direction perpendicular to said major surface of said substrate without exceeding the yield stress of said spanwise members and which provides said spanwise members with a straightening force to unwind said array frame from said satellite;
• said stiffener members being deployed when said array is in its deployed configuration, said stiffener members in their deployed configuration providing said spanwise members with a substantially increased stiffness in said direction perpendicular to said major surface of said substrate;
• wherein:
• each of said stiffener members comprises a relatively rigid beam which is disposed subtantially adjacent the plane of said solar array substrate when said stiffener member is in its stowed configuration and is displaced from the plane of said solar array substrate when said stiffener member is in its deployed configuration.

A satellite in a stowed configuration for launching comprising:

• a main satellite body;
• first and second solar arrays wound around said satellite, each of said arrays comprising:
• an array support frame comprising a pair of spaced-apart substantially parallel spanwise continuous structural members, each of said spanwise members including a deployable stiffener member;
• a solar array substrate which is supported by said frame and which has a major surface;
• a plurality of solar cells disposed on said major surface of said substrate;
• said spanwise members including said stiffener members in said stowed configuration being wound around said satellite in a direction perpendicular to said major surface of said substrate without exceeding their yield stress and providing a straightening force to unwind said array frame from said satellite body, said deployable stiffener members in their deployed configuration providing said spanwise members with a substantially increased stiffness in said direction perpendicular to said major surface of said substrate.

A satellite in a stowed configuration for launching comprising:

• a main satellite body;
• first and second solar arrays wound around said satellite body, each of said arrays comprising:
• an array support frame comprising a pair of spaced-apart substantially parallel spanwise continuous structural members;
• a solar array substrate which is supported by said frame and which has a major surface;
• a plurality of solar cells disposed on said major surface of said substrate;
• said spanwise members in said stowed configuration being wound around said satellite in a direction perpendicular to said major surface of said substrate without exceeding their yield stress, each of said spanwise members including a deployable stiffener member which in its deployed configuration provides said spanwise member with a substantially increased stiffness in said direction perpendicular to said major surface of said substrate;
• wherein each of said stiffener members comprises a first relatively rigid beam and each of said spanwise members further comprises:
• a second relatively rigid beam disposed laterally adjacent said first beam when said stiffener member is in its stowed configuration;
• and
• a plurality of flexible webs each attached at one end to said first beam and at the other end to said second beam, each of said webs being bent through substantially a 180.degree. arc in said stowed configuration.