Abstract: A deployable membrane structure for an antenna comprises a membrane comprising a plurality of first regions of higher-stiffness material integrally connected via one or more second regions of lower-stiffness material, wherein the one or more second regions are formed from compliant material configured to permit the membrane to be folded into a collapsed configuration and subsequently unfolded into a deployed configuration, and are arranged so as to allow adjacent ones of the plurality of first regions to be folded so as to lie against one another. In some embodiments the membrane is formed of a composite material comprising a plurality of fibres in a compliant matrix, and the plurality of first regions comprise material with a higher fibre density than the one or more second regions. A deployable antenna comprising the deployable membrane structure is also disclosed.

Abstract: A deployable reflector for an antenna is disclosed. The deployable reflector comprises a deployable membrane configured to adopt a pre-formed shape in a deployed configuration, and an electrically conductive mesh disposed on a surface of the membrane wherein the electrically conductive mesh is configured to permit relative lateral movement between the electrically conductive mesh and the membrane during deployment of the reflector. In the deployed configuration, the conductive mesh adopts the shape of the membrane and forms a reflective surface of the reflector. A method of manufacturing the deployable reflector is also disclosed.

Abstract: A deployable membrane structure for an antenna comprises a membrane comprising a plurality of first regions of higher-stiffness material integrally connected via one or more second regions of lower-stiffness material, wherein the one or more second regions are formed from compliant material configured to permit the membrane to be folded into a collapsed configuration and subsequently unfolded into a deployed configuration, and are arranged so as to allow adjacent ones of the plurality of first regions to be folded so as to lie against one another. In some embodiments the membrane is formed of a composite material comprising a plurality of fibres in a compliant matrix, and the plurality of first regions comprise material with a higher fibre density than the one or more second regions. A deployable antenna comprising the deployable membrane structure is also disclosed.

Abstract: A deployable membrane structure for an antenna comprises a membrane comprising a plurality of first regions of higher-stiffness material integrally connected via one or more second regions of lower-stiffness material, wherein the one or more second regions are formed from compliant material configured to permit the membrane to be folded into a collapsed configuration and subsequently unfolded into a deployed configuration, and are arranged so as to allow adjacent ones of the plurality of first regions to be folded so as to lie against one another. In some embodiments the membrane is formed of a composite material comprising a plurality of fibres in a compliant matrix, and the plurality of first regions comprise material with a higher fibre density than the one or more second regions. A deployable antenna comprising the deployable membrane structure is also disclosed.

Abstract: A spacecraft is disclosed, comprising a deployable spacecraft body (110) comprising a plurality of sub-systems (321-324) for controlling operations of the spacecraft, and a plurality of panels (101, 102) and a plurality of hinges (112-115) each connecting adjacent ones of the plurality of panels, the hinges being arranged to permit the plurality of panels to be folded into a stowed configuration and unfolded into a deployed configuration, wherein the plurality of sub-systems are fixed to and supported by one or more of the plurality of panels. By forming the body of the spacecraft from a deployable structure, the overall size of the spacecraft can be significantly reduced in the stowed configuration.

Abstract: A deployable reflector for an antenna is disclosed. The deployable reflector comprises a deployable membrane configured to adopt a pre-formed shape in a deployed configuration, and an electrically conductive mesh disposed on a surface of the membrane wherein the electrically conductive mesh is configured to permit relative lateral movement between the electrically conductive mesh and the membrane during deployment of the reflector. In the deployed configuration, the conductive mesh adopts the shape of the membrane and forms a reflective surface of the reflector. A method of manufacturing the deployable reflector is also disclosed.

Abstract: A deployable structure includes a plurality of interconnected elongated support members, deployed from a stowed state to an expanded state in which the support members are arranged in a ring. Each support member is provided with a connector (28) for longitudinal movement during deployment with respect to the support member. An actuating support member (27) has a drive member (50) for longitudinal movement with respect to the actuating support member, and an electromagnetic device arranged to drive the drive member in one direction with respect to the actuating support member. The drive member is connected to the connector by a lost motion connector, thus the connector is capable of moving in said one direction even if the drive member is not moved by the electromechanical device.

Abstract: A deployable membrane structure for an antenna comprises a membrane comprising a plurality of first regions of higher-stiffness material integrally connected via one or more second regions of lower-stiffness material, wherein the one or more second regions are formed from compliant material configured to permit the membrane to be folded into a collapsed configuration and subsequently unfolded into a deployed configuration, and are arranged so as to allow adjacent ones of the plurality of first regions to be folded so as to lie against one another. In some embodiments the membrane is formed of a composite material comprising a plurality of fibres in a compliant matrix, and the plurality of first regions comprise material with a higher fibre density than the one or more second regions. A deployable antenna comprising the deployable membrane structure is also disclosed.

Abstract: A spacecraft is disclosed, comprising a deployable spacecraft body (110) comprising a plurality of sub-systems (321-324) for controlling operations of the spacecraft, and a plurality of panels (101, 102) and a plurality of hinges (112-115) each connecting adjacent ones of the plurality of panels, the hinges being arranged to permit the plurality of panels to be folded into a stowed configuration and unfolded into a deployed configuration, wherein the plurality of sub-systems are fixed to and supported by one or more of the plurality of panels. By forming the body of the spacecraft from a deployable structure, the overall size of the spacecraft can be significantly reduced in the stowed configuration.

Abstract: A deployable structure includes a plurality of interconnected elongated support members, deployed from a stowed state to an expanded state in which the support members are arranged in a ring. Each support member is provided with a connector (28) for longitudinal movement during deployment with respect to the support member. An actuating support member (27) has a drive member (50) for longitudinal movement with respect to the actuating support member, and an electromagnetic device arranged to drive the drive member in one direction with respect to the actuating support member. The drive member is connected to the connector by a lost motion connector, thus the connector is capable of moving in said one direction even if the drive member is not moved by the electromechanical device.

Abstract: A linear bearing (1) includes a collar (2) arranged to receive a shaft (30) therethrough. The linear bearing (1) also has at least one resiliently sprung member (12) mounted within the collar (2) that contacts the shaft (30) when the shaft (30) is mounted inside the collar (2). The at least one resiliently sprung member (12) is arranged to permit displacement of the collar (2), relative to the shaft (30), in a direction substantially perpendicular to the main axis of the collar (2).