JPH051698U - Deployment mechanism - Google Patents

Abstract

(57) [Summary] [Purpose] Deploy and hold the solar array paddle in orbit,
After that, a deployment mechanism is obtained that allows the panel to be stored again. [Structure] In a deployment mechanism of a deployment type solar cell paddle having a plurality of panels deployable in outer space, a first hinge clevis metal fitting 3 and a metal fitting 3 fixed to a first panel 1 serving as an outer end. A second hinge clevis metal fitting fixed to a second panel adjacent to the paired panel 1, a hinge bin 5 for rotatably connecting the two hinge clevis metal fittings, and a first panel coaxially attached to a hinge pin. Metal spiral coil spring 6, which acts in the direction of expansion,
Similarly, the shape memory alloy spring 7 and the electric wire 8 for flowing a current through the shape memory alloy spring are fixed at positions symmetrical to the spring 6 and act in the direction of housing the first hinge clevis fitting and the first panel. To have. [Effect] The first panel can be deployed and stored only by performing a simple repair such as providing a spiral coil spring, a shape memory alloy spring, and an electric wire for energization.

Description

[Detailed description of the device]

[0001]

[Industrial applications]

 The present invention relates to a deploying mechanism of a deployable solar cell paddle that can be deployed in space, for example.

[0002]

[Prior Art]

 5 to 8 are views showing a conventional expansion mechanism, which has a hinge structure in which clevis fittings 3 and 4 to which panels 1 and 2 are attached are rotatably connected via a hinge pin 5. A spiral coil spring 6 is fixed to the hinge pin 5 at the center and to the clevis fitting 3 at the outer end.

Next, the operation will be described. FIG. 5 shows the state before the panels 1 and 2 are stored, and FIG. 6 shows the state after the panels 1 and 2 have been deployed. Due to the action of the spiral coil spring 6, the clevis fitting 3 and the panel 1 rotate around the hinge pin 5. When the clevis metal fitting 3 has rotated 180 degrees, it comes into contact with the clevis metal fitting 4 and the rotation stops and the expanded state is maintained. The spiral coil spring 6 is set in a rolled-in state even when the panel is in a deployed state, and gives a sufficient deployment holding torque.

[0004]

[Problems to be solved by the device]

 In the conventional deployment mechanism as described above, the deployment is performed only in one direction by the action of the spiral coil spring 6. However, as shown in FIG. 9 in recent years, after the hygiene 9 flies in orbit, the space shuttle 10 collects the hygiene 9 and reuses it for repair of the hygiene 9, replacement of mounted equipment, refueling, etc. Things are planned. In order to collect the hygiene 9, it has been necessary to fold and store the solar cell paddle 11 again. With the conventional deployment mechanism, however, it is necessary to fold it and store it again afterwards. It was impossible.

The present invention has been made in order to solve the above problems, and obtains a deployment mechanism capable of deploying and holding the solar cell paddle 11 on an orbit and then re-storing the panel. The purpose is to

[0006]

[Means for Solving the Problems]

 The deploying mechanism according to the present invention comprises a first hinge clevis fitting fixed to an outer end of a first panel, a pair of the first hinge clevis fitting, and a second panel adjacent to the first panel. Fixed to the second hinge clevis fitting, a hinge pin that connects the first hinge clevis fitting and the second hinge clevis fitting rotatably, and the first hinge clevis coaxially attached to the hinge pin. It is connected to a metal fitting, and is fixed in a position symmetrical to the metallic hinge coil spring and the spiral coil spring, which act in the direction of expanding the first hinge crepe fitting and the first panel around the rotation axis of the hinge pin. A current is applied to the shape memory alloy spring that acts in the direction in which the first hinge clevis fitting and the first panel are stored, and the shape memory alloy spring. And those provided with the wire for generating heat deformation.

[0007]

[Action]

 In the deploying mechanism in this invention, when the shape memory alloy spring is not energized, the panel is deployed and the panel is held in the 180 degree deployed state by the rotational torque of the spiral coil spring. The energization of the shape memory alloy heats the shape memory alloy spring, and torque is generated when the temperature of the shape memory alloy exceeds the transformation point.Therefore, the panel moves from the expanded state to the stored state around the rotating shaft. The panel is stored while the coil spring is rolled in to start rotation.

[0008]

【Example】

 Example 1. FIG. 1, FIG. 2, FIG. 3 and FIG. 4 are views showing an example of execution of this invention. In FIGS. 1, 2, 3, and 4, 1 is a first panel, 2 is a second panel adjacent to the first panel 1, 3 and 4 are the first and second panels 1 and 2. First and second hinge clevis fittings for connecting the first and second hinge clevis fittings, 5 is a hinge pin that serves as a rotation center of the first and second hinge clevis fittings 3, 4, and 6 is coaxially attached to the hinge pin 5. A metallic spiral coil spring which is connected to the clevis metal fitting 3 and acts in a direction to expand the first hinge clasp metal fitting 3 and the first panel 1 around the rotation axis of the hinge pin 5, and 7 is symmetrical with the spiral coil spring 6. A shape memory alloy spring fixed in the same position and acting in a direction in which the first hinge clevis fitting 3 and the first panel 1 are accommodated, and 8 is energized to the shape memory alloy spring 7. Was It is an electric wire.

Next, the operation will be described. 1 and 2 show a state before expansion. When the restraint of the first panel 1 is released, the clevis tool 3 and the panel 1 rotate around the hinge pin 5 due to the action of the coiled coil spring 6 that has been pre-loaded. 3 and 4 show the state after deployment. When the clevis metal fitting 3 has rotated 180 degrees, it hits the clevis metal fitting 4 and stops rotating to maintain the expanded state. The spiral coil spring 6 is set in a rolled-in state even when the panel is deployed, so that sufficient deployment holding torque is given. Next, in the storage process, when a current is directly applied to the shape memory alloy spring 7 through the electric wire 8, the shape memory alloy spring 7 generates heat due to its own electric resistance. Since the temperature of the shape memory alloy spring 7 rises and torque is generated when the temperature exceeds the transformation point, the clevis metal fitting 3 and the panel 1 rotate around the hinge pin 5 and the spiral coil spring 6 is rolled up as shown in FIG. The state before unfolding in FIG. 2 is reached. The hygiene 9 containing the solar cell paddle 11 as described above is recovered by the space shuttle 10 and brought back to the ground again for reuse by repair and refueling.

[0010]

[Effect of the device]

 As explained above, this invention is a simple modification compared to the conventional hinge in which a spring made of a shape memory alloy and a wire for energization which act in the storing direction are provided symmetrically to the spiral coil spring which acts in the deploying direction as described above. There is an effect that the first panel can be expanded and stored simply by applying.

[Brief description of drawings]

FIG. 1 is a front view of a storage state according to an embodiment of the present invention.

FIG. 2 is a side view of the storage state of the embodiment of the present invention.

FIG. 3 is a view showing an embodiment of the present invention and is a front view in a state after being developed.

FIG. 4 is a side view of an embodiment of the present invention in a developed state.

FIG. 5 is a view showing a conventional deployment mechanism and is a front view of a retracted state.

FIG. 6 is a side view showing a conventional unfolding mechanism in a stored state.

FIG. 7 is a view showing a conventional deployment mechanism and is a front view of the state after deployment.

FIG. 8 is a side view of the state after the deployment, showing a conventional deployment mechanism.

FIG. 9 is a diagram showing a space shuttle collecting hygiene during orbit flight.

[Explanation of symbols]

 1 1st panel 2 2nd panel 3 1st hinge clevis metal fittings 4 2nd hinge clevis metal fittings 5 Hinge pin 6 Hinge coil spring 7 Shape memory alloy spring 8 Energizing wire 9 Sanitary 10 Space shuttle 11 Solar cell paddle

Claims (1)

[Claims for utility model registration] 1. In a deployment mechanism of a deployment type solar cell paddle having a plurality of panels deployable in outer space, a first panel fixed to an outer end of a first panel. Second hinge clevis metal fitting, a second hinge clevis metal fitting that is paired with the first hinge clevis metal fitting, and is fixed to a second panel adjacent to the first panel, the first hinge clevis metal fitting, and the second hinge clevis metal fitting. The hinge clevis metal fitting of No. 2 is rotatably connected, and is connected to the first hinge clevis metal fitting mounted coaxially to the hinge pin, and the first hinge clevis metal fitting and the first hinge clevis metal fitting around the rotation axis of the hinge pin. A metallic spiral coil spring acting in the direction of expanding the panel, similarly fixed at a position symmetrical to the spiral coil spring, and the first hinge clevis gold. Deployment mechanism, characterized in that that comprises a wire for supplying a current to the shape memory alloy spring and the shape memory alloy spring acting in the direction for housing the first panel.