GB2097460A - Clamp for spacecraft - Google Patents

Abstract

A clamping device for a stack 3 of deployable solar cell panels carried on a space vehicle 1 comprises a toggle lever 4 pivotably connected at one end with the space vehicle and at the other end with a clamp block 9 at pivots 5 and 11 respectively. The toggle is connected at pivot 12 with an actuator 13 serving to move the toggle, and block, between a secured position shown and a released position shown by broken lines. The block is pivotally attached to the space vehicle at 10. The arrangement allows reclamping to be effected for testing or recovery of the vehicle. <IMAGE>

Description

SPECIFICATION Clamping device for apparatus carried on a spacecraft This invention relates to a clamping device primarily for a stack of solar cells or other devices which are to be deployed or extended by hinges which attach same to a space vehicle.

In space vehicles clamping devices serve to keep deployable or extensible devices, such as stacks of solar cells or aerials, secured tightly against the body of the space vehicle during the launch and transit phase using a rocket.

The clamping devices must be designed so that the acceleration and vibration occurring during the ascent phase does not lead to uncontrolled movements of the apparatus to be secured but they must also allow the apparatus to be reliably deployed when required after reaching the station where the space vehicle is to be used.

U.S. Patent 3 326 497 discloses a space vehicle in which the solar cell panels extending over a large area are secured together, during the launch phase, by means of hinges which are rotatably mounted on the space vehicle. The hinges extend along the space vehicle and are opened out onto the external edges of the collapsed stack of solar cells.

This device is only usable if the stack to be secured is generally flat, since otherwise the hinges would have to be made too large. With solar cell panels used at present and comprising quadrangular or polygonal frames of carbon fibre (KFR) reinforced plastics, this securing technique cannot be used.

The clamping systems which have hitherto been developed and used for panels of the aforementioned type ali suffer from the disadvantage that no provision is made to ensure that when the stack has been refolded it can be secured with the same clamping system. This is a disadvantage for ground test purposes, since it is then necessary to effectively launch an untested component into space. With the use of a space shuttle it is possible for space vehicles to be brought back after a mission and in this case a means has to be provided for refolding and also securing parts which extend from the space vehicle.

It is therefore an object of this invention to provide a clamping device which ensures that relevant components will not only be reliably secured but also released, but also to make it possible to refold and secure the components.

According to this invention there is provided a clamping device for use on a space vehicle to secure devices which are to be deployed or extended by hinges which attach same to the space vehicle, the device comprising a toggle lever rotatably attached at one end to the space vehicle and carrying at the other end a clamp block which may rotate about a shaft secured with the space vehicle, an actuator serving to secure or release the clamping device by movement of the toggle lever joint.

The clamping device thus provides a simple and advantageous means for reversing the operation, so that retracted and collapsed components can be again secured without difficulty.

The invention is explained in more detail with reference to the accompanying drawing, showing an embodiment by way of example.

Referring to the drawing a space vehicle 1 (not shown in detail) has a clamping device 2 serving to secure a stack 3 of collapsed solar cells. The device 2 is provided with a toggle lever system 4 which is rotatable about a shaft 5 at one end and provided on the space vehicle. A clamp block 9 is mounted at the other end 8 of the toggle lever 4 in such a way that it can rotate about a shaft 11.

The clamp block 9 is rotatably mounted on a shaft 10 integral with the space vehicle. An actuator 1 3 which opens and closes the clamping device 2 acts on a joint 12 forming the toggle 4.

The continuous lines show the clamping device in the securing state, while the broken lines show the state prevailiny when the clamping device is released. The release and securing operations take place as follows. For the securing operation the actuator 13 moves the toggle lever 4 in the direction of the stack 3 and as a result the block 9, pivoting about fixed shaft 10 is forced against the stack of folded solar cells 3 by the movement about the shaft 11.

For the release operation of the clamping device the actuator 13 is released by a central opening unit (not shown in detail) and as a result the toggle lever 4 assumes the position shown by the broken lines. The block 9 is thus rotated about the shaft 10 to move away from the stack of solar cells 3. As a result of the action of the actuator 13 the device remains in this released position without interfering with the functions of the solar cell assembly.

The actuator 1 3 can be operated by cables and a spring means (not shown in the drawings). It may also be an electrohydraulic component of a known type.

One or more clamping devices can be used, according to requirements, and these may be operated either individually or from a central operating point.

Claims

1. A clamping device for use on a space vehicle to secure devices which are to be deployed or extended by hinges which attach same to the space vehicle, the device comprising a toggle lever rotatably attached at one end to the space vehicle and carrying at the other end a clamp block which may rotate about a shaft secured with the space vehicle, an actuator serving to secure or release the clamping device by movement of the toggle lever joint.

2. A clamping device in accordance with the Claim 1, wherein a number of clamping devices are operated simultaneously by a single actuator.

**WARNING** end of DESC field may overlap start of CLMS **.

Claims (4)

**WARNING** start of CLMS field may overlap end of DESC **. SPECIFICATION Clamping device for apparatus carried on a spacecraft This invention relates to a clamping device primarily for a stack of solar cells or other devices which are to be deployed or extended by hinges which attach same to a space vehicle. In space vehicles clamping devices serve to keep deployable or extensible devices, such as stacks of solar cells or aerials, secured tightly against the body of the space vehicle during the launch and transit phase using a rocket. The clamping devices must be designed so that the acceleration and vibration occurring during the ascent phase does not lead to uncontrolled movements of the apparatus to be secured but they must also allow the apparatus to be reliably deployed when required after reaching the station where the space vehicle is to be used. U.S. Patent 3 326 497 discloses a space vehicle in which the solar cell panels extending over a large area are secured together, during the launch phase, by means of hinges which are rotatably mounted on the space vehicle. The hinges extend along the space vehicle and are opened out onto the external edges of the collapsed stack of solar cells. This device is only usable if the stack to be secured is generally flat, since otherwise the hinges would have to be made too large. With solar cell panels used at present and comprising quadrangular or polygonal frames of carbon fibre (KFR) reinforced plastics, this securing technique cannot be used. The clamping systems which have hitherto been developed and used for panels of the aforementioned type ali suffer from the disadvantage that no provision is made to ensure that when the stack has been refolded it can be secured with the same clamping system. This is a disadvantage for ground test purposes, since it is then necessary to effectively launch an untested component into space. With the use of a space shuttle it is possible for space vehicles to be brought back after a mission and in this case a means has to be provided for refolding and also securing parts which extend from the space vehicle. It is therefore an object of this invention to provide a clamping device which ensures that relevant components will not only be reliably secured but also released, but also to make it possible to refold and secure the components. According to this invention there is provided a clamping device for use on a space vehicle to secure devices which are to be deployed or extended by hinges which attach same to the space vehicle, the device comprising a toggle lever rotatably attached at one end to the space vehicle and carrying at the other end a clamp block which may rotate about a shaft secured with the space vehicle, an actuator serving to secure or release the clamping device by movement of the toggle lever joint. The clamping device thus provides a simple and advantageous means for reversing the operation, so that retracted and collapsed components can be again secured without difficulty. The invention is explained in more detail with reference to the accompanying drawing, showing an embodiment by way of example. Referring to the drawing a space vehicle 1 (not shown in detail) has a clamping device 2 serving to secure a stack 3 of collapsed solar cells. The device 2 is provided with a toggle lever system 4 which is rotatable about a shaft 5 at one end and provided on the space vehicle. A clamp block 9 is mounted at the other end 8 of the toggle lever 4 in such a way that it can rotate about a shaft 11. The clamp block 9 is rotatably mounted on a shaft 10 integral with the space vehicle. An actuator 1 3 which opens and closes the clamping device 2 acts on a joint 12 forming the toggle 4. The continuous lines show the clamping device in the securing state, while the broken lines show the state prevailiny when the clamping device is released. The release and securing operations take place as follows. For the securing operation the actuator 13 moves the toggle lever 4 in the direction of the stack 3 and as a result the block 9, pivoting about fixed shaft 10 is forced against the stack of folded solar cells 3 by the movement about the shaft 11. For the release operation of the clamping device the actuator 13 is released by a central opening unit (not shown in detail) and as a result the toggle lever 4 assumes the position shown by the broken lines. The block 9 is thus rotated about the shaft 10 to move away from the stack of solar cells 3. As a result of the action of the actuator 13 the device remains in this released position without interfering with the functions of the solar cell assembly. The actuator 1 3 can be operated by cables and a spring means (not shown in the drawings). It may also be an electrohydraulic component of a known type. One or more clamping devices can be used, according to requirements, and these may be operated either individually or from a central operating point. Claims

1. A clamping device for use on a space vehicle to secure devices which are to be deployed or extended by hinges which attach same to the space vehicle, the device comprising a toggle lever rotatably attached at one end to the space vehicle and carrying at the other end a clamp block which may rotate about a shaft secured with the space vehicle, an actuator serving to secure or release the clamping device by movement of the toggle lever joint.

2. A clamping device in accordance with the Claim 1, wherein a number of clamping devices are operated simultaneously by a single actuator.

3. A clamping device as described herein and with reference to the accompanying drawings.

4. A space vehicle incorporating deployable or extensible devices and having a clamping device as claimed in any preceding claim.