A large area, deployable flexible blanket photovoltaic solar array architecture for high power applications is disclosed. The structure is a modularized and scalable solar array system that provides high power level scalability. The structure is comprised of repeating, similar modular deployable roll-out solar array wings mounted in an opposing manner and along the length of a rigid, strong and efficiently packaged deployable backbone structure. The deployable roll-out solar array building block modular winglet elements can be comprised of either a rolled or z-folded flexible photovoltaic blanket configuration, and their structural deployment is motivated by the elastic strain energy of longitudinal roll-out booms. The backbone structure is comprised of a stiff deployable beam structure articulated that is deployed perpendicular with respect to the spacecraft sidewall and latched out. Deployment of the winglets can be conducted once the articulated backbone structure has been deployed, is latched, and forms a rigid beam.

A deployable structure comprises a mast and two storage rollers each supporting a flexible solar generator, the two storage rollers being articulated on the mast. The mast comprises at least one longitudinal rod and two lateral arms, inclined angularly in two opposite directions that are symmetrical relative to the longitudinal rod, each lateral arm comprising an end provided with a hollow guide. Each storage roller has a longitudinal axis comprising a bent end forming a pivot respectively articulated inside the hollow guide of a corresponding lateral arm, the pivot of each storage roller having an axis of revolution different from the longitudinal axis of the corresponding storage roller.

A spacecraft with a linear extension boom, an antenna feed, and a rigid antenna reflector is provided. The rigid antenna reflector may be connected with one end of the linear extension boom, and the other end of the linear extension boom may be connected with the spacecraft main body. In a launch configuration of the spacecraft, the linear extension boom may be retracted into a stowed configuration, and in an on-orbit configuration of the spacecraft, the linear extension boom may be extended into a deployed configuration, thereby moving the rigid antenna reflector away from the yaw axis of the spacecraft and positioning the rigid antenna reflector such that the focal point of the rigid antenna reflector may be oriented to align on, and be collocated with, the antenna feed. The rigid antenna reflector may be connected with the linear extension boom by a positioning mechanism that provides for adjustment in the angular orientation of the rigid antenna reflector relative to the linear extension boom.

A deployable structure comprises: a support, a tape spring fixed to the support, able to pass from a wound configuration wound about an axis Z, to a deployed configuration, and a mobile arm able to rotate with respect to the support about the Z-axis, able to form a first contact with the tape spring so as to control the deployment of the tape spring.

An extensible mast according to the present disclosure includes a first fiber layer made of a fiber-reinforced plastic, a second fiber layer that is arranged in contact with the first fiber layer and made of a fiber-reinforced plastic having a thermal expansion coefficient in a longitudinal direction larger than a thermal expansion coefficient in the longitudinal direction of the fiber-reinforced plastic applied to the first fiber layer, and an electric heating wire arranged on the second fiber layer. The number of times of overlapping of the electric heating wire in different layers when the first fiber layer, the second fiber layer, and the electric heating wire are wound and retracted in a roll shape is minimized. Thus, the elastic restoring force of the extensible mast can be maintained while an increase in weight and volume is suppressed.

A mechanical switching unit for selectively moving a functional component from a first position to a second position has an input element, an output element, a first holding point and a second holding point. The input element is set in motion by a drive. The output element is in engagement with the input element and is set in motion by the input element. The input element moves the output element from the first position to the second position, and vice versa. In the process, the functional component is moved from the first position to the second position, and vice versa. The first holding point exerts a first holding force on the functional component in the first position. The second holding point exerts a second holding force on the functional component in the second position.

A deployable truss with modified primary orthogonal joints. The construction of these joints causes the center-hinged primary chords on opposite sides of a truss bay to fold inward in a plane orthogonal to the folding planes of the side diagonals while the two secondary chords fold in planes orthogonal to the plane of the in-folding primary chords. This provides for stiffness and stability during deploy and retract. The unique joint configuration permits the truss to deploy one bay at a time in a stable manner while having lateral bending stiffness, and the truss thus can extend and retract in a sequential manner. It can deploy integral flat panels nested between the secondary folding chords, or use cross bracing in lieu of panels. The truss can be triangular, square or rectangular in cross-section. A powered support frame may be used in conjunction with the truss.

The present invention relates to a light baffle assembly including a base baffle member comprising a base wall portion positioned substantially parallel to a longitudinal axis, an upper baffle member comprising an upper wall portion coupled to an upper blade portion, the upper wall portion positioned substantially parallel to the longitudinal axis, and the upper blade portion positioned to extend inwards from the upper wall portion towards the longitudinal axis, and a resilient member configured to extend the upper baffle member away from the base baffle member.

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.

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.