JPH04243699A - Connector separating device for flying body - Google Patents

Abstract

PURPOSE:To simplify constitution and reduce dimension by realizing the sure operation control. CONSTITUTION:The first and second connectors 10 and 11 are held in engagement state by carrying out position regulation by using a link connection member 16, and when the holding of the position regulation is released, and an energizing power is applied in the direction crossing nearly at right angle with a connector shaft X through a spring member 18, on the bent part A of the link connection member 16, and the energizing power which is boosted through the link connecting member 16 is applied, and the connectors can be separated.

Description

[Detailed description of the invention]

0001

[Industrial Application Field] This invention utilizes a well-known push button to electrically connect electronic equipment to the flying object when electronic equipment including a solar array paddle mounted on a flying object such as an artificial satellite is released and dumped. -Relates to a connector separation device used to separate pull-type connectors.

0002

[Prior Art] Conventionally, when electronic equipment, including unnecessary solar array paddles, mounted on a satellite is released into space and dumped, the connector that electrically connects the electronic equipment from the satellite body has been separated. At the same time, the release and jettisoning is performed by separating the coupling part that mechanically connects each other from the satellite body.

FIG. 3 shows a connector separation device that separates connectors that electrically connect electronic devices that are ejected and jettisoned in this way. Attached via 3,
This first connector 1a is connected to an internal device (not shown) via a harness 4a. A second connector 1b is separably engaged with the first connector 1a.
An electronic device 5 is electrically connected to the connector 1b via a harness 4b. In the engaged state of the first and second connectors 1a and 1b, the separation spring member 6 applies a biasing force in the separation direction (pulling direction) between the satellite main body 2 and the electronic device 5. be mediated.

[0004] With the above configuration, a mechanical connection point (not shown) of the electronic device 4 is activated by an explosion bolt or the like and the satellite main body 2
When separated, the first and second connectors 1a, 1b
The electronic device 5 is separated by the biasing force of the spring member 6, and electrically separated therefrom to realize ejection and dumping of the electronic device 5.

However, the above-mentioned connector separation device is not effective when a certain contact area exists between the satellite body 2 and the electronic equipment 5, and both the satellite body 2 and the electronic equipment 5 have relatively rigidity. Therefore, there is a problem that a spring member 6 with a relatively strong spring force is required and the device becomes large. Furthermore, according to this, flexible structures recently developed in the field of space exploration, such as those shown in Figure 5, do not have sufficient rigidity when applied to the electrical connection points of solar cell arrays. Moreover, since it is difficult to maintain a constant contact area at the joint portion, there is a problem in that it is difficult to control the joint/separation operation with high precision.

[0006]

[Problems to be Solved by the Invention] As described above, conventional connector separation devices require a certain contact area and a certain rigidity for electronic equipment, resulting in large size and limitations in the scope of application. I had the problem of receiving it.

The present invention has been made in view of the above circumstances, and it is an object of the present invention to provide a connector separation device for a flying object, which has a simple structure, can be downsized, and can realize reliable operation control. The purpose is to

[0008]

[Means for Solving the Problems] The present invention provides a first push-pull method for electrically connecting electronic equipment inside a flying object and separable electronic equipment mounted on the flying object.
and a second connector, and an intermediate portion whose one end is connected to one of the first and second connectors and whose other end is fixedly supported in the separation direction on the connector axis, in a direction substantially perpendicular to the connector axis. a separation member that is bendably provided; and an attachment that separates one of the first and second connectors from the other by urging an intermediate portion of the separation member in a direction substantially perpendicular to the connector axis. a regulating means for regulating the position of the separation member on the axes of the first and second connectors against the biasing force of the biasing means; and a regulation releasing means for releasing the positional regulation of the regulating means. A connector separation device for a flying object is constructed by comprising:

[0009]

[Operation] According to the above structure, when the restriction of the restriction means is released, the urging force of the urging means is applied to the intermediate portion of the separating member, and the urging force pushes the separating member. By being given a boost through the medium, it is removed. Therefore, the engagement and separation operations can be controlled without being affected by the contact area for holding the first and second connectors in the engagement position, and the urging force of the urging means can be reduced. .

0010

Embodiments Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings.

FIG. 1 shows a connector separating device for a flying object according to an embodiment of the present invention, with FIG. 1(a) showing the connected state and FIG. 1(b) showing the separated state. That is, Figure 1
, 10 and 11 are push-pull.
These are first and second connectors 10 and 11 of the pull type. Of these, the first connector 10 is attached to a spacecraft-side support 12 such as an artificial satellite, and connected to an internal device (not shown) via a harness 13.

On the other hand, the second connector 11 is connected via a harness 14 to an electronic device for discharge and disposal (not shown). A pull-out member 15 called a lanyard is attached to the second connector 11. One end of a link coupling member 16 is linked to this pull-out member 15 . The other end of the link coupling member 16 is ring-coupled to a fixed part 17 in the separation direction (pulling direction) of the connector axis X, and the link coupling member 16 is bendable in a direction substantially perpendicular to the connector axis X by a hinge or the like in the middle part. A bent portion A is formed. One end of the spring member 18 is engaged with this bent portion A. The other end of the spring member 18 is attached to the bent portion A so as to apply a biasing force in a direction substantially perpendicular to the connector axis X. Furthermore, one end of a wire rope 19 constituting a position regulating mechanism is attached to the bent portion A. The wire rope 19 moves and urges the bent portion A of the link coupling member 16 against the biasing force of the spring member 18 to regulate the position of the link coupling member 16 substantially parallel to the connector axis X. A wire cutting mechanism such as an explosion bolt (not shown) for release is interposed and fixedly supported.

In the above configuration, the second connector 11 connected to the electronic device (not shown) via the harness 14 has the bent portion A of the link coupling member 16 resisting the biasing force of the spring member 18. Connector axis X with wire rope 19
The first connector 10 is engaged with the first connector 10 while being held substantially parallel to the first connector 10 . In this state, the first and second connectors 10, 1
1 electrically connects internal equipment (not shown) of the spacecraft and ejection and jettisoning electronic equipment (not shown) via harnesses 13 and 14.

When electronic equipment (not shown) is to be released and dumped, the wire cutting mechanism (not shown) is first activated to cut the wire rope 19. Then, as shown in FIG. 2, the link coupling member 16 is bent by the biasing force P of the spring member 18 applied to the bending portion A thereof. At this time, the pulling member 15 is given a biasing force F which is boosted by the boosting action of the link coupling member 16, and the second connector 1
1 is separated by pulling it out from the first connector 10. This biasing force F is expressed as F=P/2tanθ, where θ is the bending angle of the link coupling member 16. At this time, the electronic device (not shown) is mechanically separated by a combination/separation mechanism (not shown) and discharged and dumped.

[0015] In this way, the above-described connector separation device for a flying object uses the link coupling member 16 to regulate the positions of the first and second connectors 10 and 11 to maintain the engaged state, and to maintain the position regulation. When released, a biasing force is applied to the bent portion A of the link coupling member 16 via the spring member 18 in a direction substantially perpendicular to the connect axis X, thereby increasing the force via the link coupling member 16. The configuration is such that the biasing force applied is applied and separated. According to this, engagement and separation operation control is realized without being affected by the contact area for holding the first and second connectors 10 and 11 in the engagement position, and the separation spring member 18 can be reduced. According to this, it is also possible to apply it as a connector separation device at an electrical connection point of a flexible structure that is being researched in the recent field of space development.

[0016] In the above embodiment, the case where the application is applied to a space vehicle as a flying object was explained, but the invention is not limited to this, and the application is not limited to this. It can also be applied to electrical connection points when dumping. Therefore, it goes without saying that the present invention is not limited to the above embodiments, and that various modifications can be made without departing from the spirit of the invention.

[0017]

[Effects of the Invention] As described in detail above, the present invention provides a connector separation device for a flying object, which has a simple structure, can be downsized, and can realize reliable operation control. can do.

[Brief explanation of the drawing]

FIG. 1 is a sectional view showing a connector separation device for a flying object according to an embodiment of the present invention.

FIG. 2 is a diagram shown to explain the operation of FIG. 1;

[Fig. 3] A diagram showing a conventional connector separation device,

[Fig. 4] A diagram shown to explain conventional problems,

[Explanation of symbols]

10, 11...first and second connectors, 12...support body,
13, 14... Harness, 15... Pulling member, 16... Link coupling member, 17... Fixing part, 18... Spring member, 19... Wire rope.

Claims (1)

[Claims] 1. Push-pull type first and second connectors for electrically connecting an electronic device inside a flying object and a separable electronic device attached to the flying object; a separation member connected to one of the first and second connectors, the other end of which is fixedly supported in the separation direction on the connector axis, and whose intermediate portion is bendable in a direction substantially perpendicular to the connector axis; , a biasing means for biasing an intermediate portion of the separation member in a direction substantially perpendicular to the connector axis to separate one of the first and second connectors from the other; and a biasing force of the biasing means. A flying object characterized by comprising: a regulating means for regulating the position of the separating member on the axis of the first and second connectors against the above-mentioned pressure, and a regulating means for releasing the positional regulation of the regulating means. Connector separation device.