JPH03164400A - Separating device for spacecraft - Google Patents

Abstract

PURPOSE:To obtain a light and simple separating device by drawing a power link mechanism by extending a wire by an adjusting screw when an outer force control mechanism pushes a support lever, and cutting the wire to release it when the support lever is released. CONSTITUTION:A support lever 3 installed rotatably on the side of a subject matter 5 is pushed by a power link mechanism to fasten an aircraft 4 with the subject matter 5. For the power link mechanism, ends of levers 1, 2 are connected by hinges, and a power of a restraining force (b) is generated by drawing them in a direction of a support force (a) for pushing the lever 3. The wire 6 is restrained to a support metal 8 mounted to the aircraft 4. A wire cutter 9 fixed to a holding metal 10 mounted at the aircraft 4 is then actuated to cut the wire 6, so the levers 1, 2 and the support lever 3 are released, thereby the subject matter 5 is released from the aircraft.

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a spacecraft separation device, and in particular, to a separation device for a spacecraft, particularly for separating solar battery paddles, antennas, etc. of a plurality of satellites that were integrated at the time of launch in order to be transported to space. This article relates to a spacecraft separation device for separation in space. [Conventional technology] In recent years, as the capabilities of launch vehicles have improved, a launch method in which multiple satellites are integrated, launched at once, and separated in orbit is being implemented. Conventionally, this type of spacecraft separation device has a band with a V-shaped cross section, as shown in the front view of Figure 3 (a) and the sectional view taken along line A-A in Figure 3 (b). (The spacecraft 20 and the separated object 21 are connected by tightening the V-band>11 with the explosive bolt l2.Next, when separating the spacecraft 20 and the separated object 21, see Figure 4. (a)
, (As shown in the front view and A-A sectional view of b, respectively, the two were separated by operating the explosive bolt 12 or separation nut 13 or the like to release the V band 11. [Issues to be solved] The above-mentioned conventional separation device for spacecraft is heavy because it connects the spacecraft and the object to be separated using the entire V band, and the part to be fastened to the object to be separated also has to be tightened by the band. This caused an increase in weight because the bolts were designed to withstand loads sufficiently.Also, it was difficult to adjust the tightening force to achieve evenly distributed loads, so conventionally strain gauges were attached to each of the two bolts. As a result, the load on both is monitored and the bolt tightening force is adjusted, which has the disadvantage of making assembly work difficult.Furthermore, after the separated object is separated, a tray is provided to handle the band. This resulted in a further increase in weight.

[Means to solve the problem]

The separation device for a spacecraft of the present invention is a separation device for a spacecraft that restrains or releases a separated object mounted on a main body of a spacecraft, and is rotatably attached to a structure on the side of the separated object. a support lever that restrains the contact surface between the body and the separated object; and a boosting link mechanism that has one end rotatably attached to the spacecraft and whose other end presses or releases the support lever under the control of an external force control mechanism. When the external force control mechanism presses the support lever, the wire is expanded by the adjustment screw to pull the boost link mechanism, and when the support lever is released, the wire is cut and released.

〔Example〕

Next, the present invention will be explained with reference to the drawings. FIG. 1 is a structural diagram of a first embodiment of the present invention, showing a state in which the separation device of this embodiment is mounted on a spacecraft 4 and a separation object 5, and the two are coupled. In the figure, a support lever 3 rotatably attached to the side of the separated object 5 is pressed by a booster link mechanism, which will be described later, to fasten the spacecraft 4 and the separated object. The boosting link mechanism connects each end of the levers 1 and 2 with a hinge, and by pulling it with a wire 6 in the direction of the supporting force a shown in the figure, a boosting force of the restraining force b shown by the arrow is generated, and the supporting lever 3
is being pressed. The wire 6 has a structure in which it is restrained by a support fitting 8 mounted on the spacecraft 4.

Next, as shown in FIG. 2, the wire cutter 9 fixed to the holding fitting 10 mounted on the spacecraft 4 operates to cut the wire 6, thereby removing the lever 1.2 and the support. The structure is such that the lever 3 becomes free and releases the separated object 5 from the spacecraft 4. Note that the tension of the wire 6 can be adjusted by adjusting the adjustment screw 7, and the restraining force b of the separated object 5 with respect to the supporting force a of the lever 2 is
The structure is such that the separated object 5 can be restrained with a restraining force doubled by the leverage ratio b/a. Next, a second embodiment of the present invention will be described with reference to the drawings.
FIG. 3 is a configuration diagram of a second embodiment of the present invention, in which all the separation devices of this embodiment are mounted on the spacecraft 4 and the two are connected. The spacecraft suspension 4 and the separation object 5 are fastened together by a freely attached support lever 3A. One end of the support lever 3A is lever I
It is connected to A, and the other end is connected to two levers. The boosting link mechanism controlled by the levers IA and 2A is restrained by a wire 6 having a tension adjustment screw 7, and generates a tensile restraining force b in the direction of the supporting force a. The restraining force e of the separated object with respect to the supporting force a of the lever 2A is b. c.
The structure is such that the separated object 5 can be restrained with a restraining force that is doubled by the lever ratio. Next, Figure 4 shows separation from spacecraft 4! This figure shows a structure in which Pff5 is released by cutting the wire 6, and the operating procedure is the same as in the first embodiment.

〔Effect of the invention〕

As explained above, according to the present invention, it is possible to reliably restrain a separated object to a spacecraft using a restraint mechanism having a boosting link mechanism with a sufficiently large leverage ratio. Therefore, it is possible to provide a lightweight and simple separation device. Further, after the separated object is separated, each lever is held by the spacecraft and the separated object or by the spacecraft, so there is no need to specially process the restraint mechanism after use, and there is an effect that it can be effectively reused.

[Brief explanation of the drawing]

1 and 2 are a configuration diagram and a state diagram of the first embodiment of the present invention, FIGS. 3 and 4 are an elliptical diagram and a state diagram of the second embodiment of the present invention, and FIG. 5 (a) (b) and Figure 6 (a)
) and (b) are R-shaped diagrams showing the configuration of the main parts of a conventional spacecraft separation device and its released state. 1, 2, IA, 2A... lever, 3, 3A... support lever, 4... spacecraft, 5... separated object, 6...
・Wire 7... Adjustment screw, 8... Support metal fittings, 9
...Wire power vine, 10...Holding metal fittings, 11...
・V band, 12...Explosion bolt, 13...Separation nut.

Claims (1)

[Scope of Claims] 1. In a separation device for a spacecraft that restrains or releases a separated object mounted on a spacecraft main body, the spacecraft main body is rotatably attached to a structure on the separated object side; a support lever that restrains the contact surface of the separated object; a booster link mechanism that has one end rotatably attached to the spacecraft and whose other end presses or releases the support lever under the control of an external force control mechanism; When the external force control mechanism presses the support lever, a wire is expanded by an adjustment screw to pull the boost link mechanism, and when the support lever is released, the wire is cut and released. spacecraft separation device. 2. The spacecraft separation device according to claim 1, wherein one end of the support lever is attached to the spacecraft body, and the other end is connected to one end of the booster mechanism.