JP6637260B2 - Satellite separation device - Google Patents

Description

  The present invention relates to an artificial satellite separation device used for sequentially separating an upper first satellite and a lower second satellite mounted in a rocket fairing from an upper stage.

  2. Description of the Related Art As a conventional artificial satellite separating device, for example, there is a device described in Patent Document 1 under the name of a multiple artificial satellite mounting mechanism. The separation device described in Patent Literature 1 has an upper first satellite and a lower second satellite mounted in a rocket fairing. The fairing is divided into an upper fairing that houses the first satellite and a lower fairing that houses the second satellite, with an adapter between the first and second satellites in between. It is provided. The adapter is connected to the upper part of the lower fairing via a hinge, and is used as a mounting base for the first satellite.

  Further, the above-mentioned separating device includes a first separating mechanism of the first satellite between the first satellite and the adapter, and a second separating mechanism of the second satellite between the second satellite and the top stage of the rocket. And a fairing separating mechanism between the upper and lower fairings, and an adapter driving mechanism for rotating the adapter to the outside of the rocket on the lower fairing. This separation device separates the first satellite by the first separation mechanism after separating the upper fairing by the fairing separation mechanism, and then rotates the adapter to the outside of the rocket by the adapter drive mechanism. The second satellite is separated by the two separating mechanism.

JP-A-8-164899

  However, the above-described conventional satellite separation device prevents the generation of debris (space debris) that can be an obstacle in orbit by connecting an adapter to the lower fairing. Since the configuration includes the second separation mechanism, the fairing separation mechanism, and the adapter driving mechanism, the structure and control are complicated, and there is a problem that it is difficult to reduce the weight. That was the challenge.

  SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional problems, and is an apparatus for separating an artificial satellite which can realize simplification of structure and control and weight reduction, and can prevent generation of debris. It is intended to provide.

An artificial satellite separating apparatus according to the present invention is an apparatus for sequentially separating an upper first satellite and a lower second satellite mounted in a rocket fairing from an upper stage, and separates a second satellite by a lower stage separating mechanism. A satellite base operably mounted, and a plurality of supports disposed around the second satellite on the satellite base and supporting the first satellite. In the separation device, the lower end of each support is rotatably connected to the satellite base in the rocket inward and outward directions, and the upper stage detachably connects the first satellite to the upper end. and separating mechanism, along with the separating operation of the upper separating mechanism and a deployment spring for rotating the support rocket outside Rutotomoni, in a state in which against the repulsive force of the expansion spring is restrained by the upper separation mechanism The first configuration supports the first satellite, and the above configuration serves as means for solving the conventional problems.

  In the artificial satellite separation device according to the present invention, when the fairing is opened, the first satellite supported by each support is exposed to outer space. Then, when the separation device separates the first satellite by the upper separation mechanism provided on each support, each support is automatically rotated to the outside of the rocket by the action of the deployment spring with the separation operation, The second satellite is exposed to space. Thereafter, the separation device separates the second satellite by the lower separation mechanism.

  As described above, in the artificial satellite separation device according to the present invention, each support has both the support function and the separation function of the first satellite, and after the separation of the first satellite, only the deployment spring is used. Since each support automatically rotates by the simple structure of, the structure and the control can be simplified and the weight can be reduced. Further, since each support does not separate from the satellite base, The generation of debris can also be prevented.

BRIEF DESCRIPTION OF THE DRAWINGS It is a side view of the rocket with an enlarged view explaining one Embodiment of the separation device of the artificial satellite concerning this invention. It is sectional explanatory drawing which shows the state before the separation of a separation apparatus. A cross-sectional view showing the separation of the first satellite by omitting one side (A), a cross-sectional view showing the state after the separation of the first satellite (B), and a cross-sectional view showing the separation of the second satellite (C). It is.

Hereinafter, an embodiment of an artificial satellite separating apparatus according to the present invention will be described with reference to the drawings.
The rocket R shown in FIG. 1 has a fairing F on its head, and an upper first satellite S1 and a lower second satellite S2 are mounted in the fairing F together with an artificial satellite separation device. The separation device is a device that sequentially separates the upper first satellite S1 and the lower second satellite S2 from the upper stage. The fairing F can be opened, for example, in a craniotomy manner.

  The artificial satellite separation device is roughly a satellite base 1 on which a second satellite S2 is separably mounted by a lower separation mechanism J2, and is arranged around the second satellite S2 in the satellite base 1 and includes a first satellite S1. And a plurality of supports 2 for supporting.

  Although not shown, the lower separation mechanism J2 includes, for example, a separation nut that connects the satellite base 1 and the second satellite S2 so as to be separable, and a separation spring that applies a separation force to the second satellite S2. I have. The satellite base 1 is fixed to the uppermost stage of the rocket R.

  The support 2 of this embodiment has a truss structure having an upper end as a vertex, and is disposed at equal intervals around the machine axis. In the illustrated example, the support 2 is disposed at four positions at 90-degree intervals. . As shown in FIG. 2, the lower end of each support 2 is connected to the satellite base 1 by a hinge 3 so as to be rotatable inside and outside the rocket. In FIG. 2, the illustration of the support at the front center is omitted.

  Further, each support 2 has an upper separation mechanism J1 that detachably couples the first satellite S1 to the upper end thereof, and a development that rotates the support 2 to the outside of the rocket with the separation operation of the upper separation mechanism J1. Spring 4. The deployment spring 4 is a torsion coil spring attached to the hinge 3, and applies a repulsive force to the support 2 in the outward direction of the rocket.

  Further, the upper separating mechanism J1 includes a connecting means 5 for connecting each support 2 and the first satellite S1, a separating rod 6 having a head 6A in contact with the first satellite S1, and a connecting means for connecting the connecting means 5. A separation spring 7 for applying a separation force to the first satellite S1 via the separation rod 6 upon release is provided.

  More specifically, each support 2 includes a guide piece 8 extending from the upper end to the inside of the rocket, a support piece 9 extending to the inside of the rocket at a position lower than the guide piece 8, and a support piece 9 extending from the upper end. And a coupling flange 10 protruding outside the rocket. On the other hand, the lower end of the first satellite S1 has a coupling flange 11 that contacts the upper surface of the coupling flange 10 of the support 2.

  The connecting means 5 is a well-known separation band for the support 2, and is provided with a suitable number of frames which are engaged with the connecting flanges 10 and 11 which are vertically contacted on one side of a metal band 5A. 5B. The connecting means 5 includes two members each having a length of about half of the circumference passing through the upper end of each support 2, and connecting the ends with a connecting tool such as a bolt or a separation nut. Then, each support 2 and the first satellite S1 are separably connected. When a bolt is used as the connecting tool, a bolt cutter is mounted.

  The separation rod 6 penetrates the guide piece 8 and the support piece 9 of the support 2 so as to be able to move up and down, and makes the head 6A on the upper end side contact the lower part of the first satellite S1. The separating spring 7 is a compression coil spring, which is mounted on the outside of the separating rod 6, and is formed by connecting the head 6 A of the separating rod 6 and the supporting piece 9 with the guide piece 8 penetrating vertically. It is interposed in between. The separating rod 6 may be provided with a portion that regulates the upper limit position so that the separating rod 6 does not separate from the support body 2, thereby preventing the separating spring 7 from separating.

  Furthermore, the separating device includes a stopper 12 for restraining the support, the upward movement of which is restricted by the separating rod 6 in a state where the separating spring 7 is compressed, on the satellite base 1, and an upward force on the stopper 12. And a stopper receiving portion 14 that engages with the stopper 12 and releases the engagement at the upper limit position of the stopper 12.

  The stopper 12 is an inverted L-shaped member, and is attached to the satellite base 1 so as to be able to move up and down with the upper horizontal side 12A facing the outside of the rocket below the separating rod 6 described above. . The stopper 12 has an engaging portion 12B that protrudes in a lateral direction (a direction perpendicular to the paper surface of FIG. 2) at the tip of the horizontal side 12A. The stopper 12 is arranged such that the vertical side 12C is coaxial with the separating rod 6, and a moving spring 13 is mounted outside the vertical side 12C. The moving spring 13 is a compression coil spring, and is interposed between the horizontal side 12A of the stopper 12 and a spring seat 15 provided on the satellite base 1 side. The stopper 12 may be provided with a portion that regulates the upper limit position so as not to separate from the satellite base 1, similarly to the separation rod 6, so that the movement spring 13 can be prevented from separating.

  On the other hand, the stopper receiving portion 14 is an inverted L-shaped slit or groove formed near the lower end of the support 2 and has a width dimension in which the engaging portion 12B of the stopper 12 is slidably engaged. The upper horizontal side 14A is open to the inside of the rocket. As a result, the stopper receiving portion 14 engages with the engaging portion 12B of the stopper 12 on the vertical side 14B, and engages with the engaging portion 12B at the upper limit position of the stopper 12 on the horizontal side 14A opened inside the rocket. The engagement is released.

  As shown in FIG. 2, in the artificial satellite separating device having the above-described configuration, when the first satellite S1 and the second satellite S2 are mounted, the separating rod 6 is located at the lowermost position, and the head 6A and the The separation spring 7 is compressed between the support piece 9 and the support piece 9. In addition, the upper end of the stopper 12 abuts on the lower end of the separating rod 6, whereby the stopper 12 is restricted to the lower limit and compresses the moving spring 13 between the horizontal side 12 </ b> A and the spring seat 15. ing. Further, in the separation device, the engaging portion 12B of the stopper 12 and the vertical side 14B of the stopper receiving portion 14 are engaged.

At this time, each support 2 stands up against the repulsive force of the deployment spring 4 and is restrained by the coupling means 5 of the upper separation mechanism J1 and the engagement between the stopper 12 and the stopper receiving portion 14, The first satellite S1 is supported with sufficient strength.

  When the fairing F is opened, the above-mentioned separation device exposes the first satellite S1 supported by each support 2 to the outer space. In this state, the upper-stage separation mechanism J1 is operated to disconnect the first satellite S1. To separate. At this time, as shown in FIG. 3 (A), the upper separation mechanism J1 releases the connecting tool and separates the connecting means (separation band) 5, thereby connecting the first satellite S1 to each support 2. Is released, and the first satellite S1 is separated via the separation rod 6 by the action of the separation spring 7 which has been compressed.

  Subsequently, as shown in FIG. 3 (B), the separating device automatically rotates each support 2 to the outside of the rocket by the action of the deployment spring 4 with the separating operation of the first satellite S1. The second satellite S2 is exposed to outer space.

  That is, in the separating device, when the separating rod 6 is raised by the separating spring 7, the stopper 12 is raised in conjunction with the separating rod 6 by the action of the moving spring 13 which has been compressed. During this time, the stopper 12 is disengaged from the stopper receiving portion 14 when the engaging portion 12B rises on the vertical side 14B of the stopper receiving portion 14 and reaches the horizontal side 14A which is the upper limit position. You.

  That is, since the horizontal side 14A of the stopper receiving portion 14 is open to the inside of the rocket, the engaging portion 12B of the stopper 12 can be detached to the inside of the rocket at the horizontal side 14A. Further, since the repulsive force of the deployment spring 4 is applied to each support 2, the support 2 automatically pivots to the outside of the rocket as the engagement between the stopper 12 and the stopper receiving portion 14 is released.

  Thereby, after the separation of the first satellite S1, all the supports 2 are automatically deployed outside the rocket, and the separation device exposes the second satellite S2 to outer space. As described above, the separation device turns each support 2 to the outside of the rocket, leaving only the space around the second satellite S2 as an environment in which the separation can be reliably performed. After that, as shown in FIG. 3C, the separation device operates the lower separation mechanism J2 to separate the second satellite S2. FIG. 3C shows a separation spring 16 and a separation rod 17 as one configuration of the lower separation mechanism J2.

  In the process of separating the first and second satellites S1 and S2, the attitude control of the uppermost stage of the rocket including the satellite base 1 may be performed. The upper processing (orbit change, etc.) is performed.

  In the satellite separating apparatus according to the above embodiment, each support has both the supporting function and the separating function of the first satellite, and the conventional separating apparatus having an adapter between upper and lower satellites. As compared with the case of (1), since an adapter and a driving mechanism for the adapter are unnecessary, the number of parts can be significantly reduced. Moreover, after the separation of the first satellite S1, the separation device automatically rotates each support 2 with a simple structure of only the deployment spring 4, and separates each support 2 from the satellite base 1. Nor. Thereby, the separation device can realize simplification and weight reduction of the structure and control, and can also prevent generation of debris that becomes an obstacle on the orbit.

  The above separating apparatus employs an upper separating mechanism J1 including a coupling means 5, a separating rod 6, and a separating spring 7, and is interlocked to the separating base 6 by a moving spring 13 on the satellite base 1. And a stopper receiving portion 14 that engages with the stopper 12 and releases the engagement at its upper limit position, so that the first satellite S1 can be completely After the separation, the support 2 rotates, so that the separation of the first satellite S1 and the rotation of the support 2 can be performed more reliably.

  It should be noted that the satellite separating device according to the present invention can sufficiently separate the first satellite S1 and rotate the support 2 even if the configuration does not use the stopper 12 and the stopper receiving portion 14. Yes, as an example, it is also possible to provide a guide means for separation on the first satellite S1 or the support 2. However, if the above-mentioned stopper 12 and stopper receiving portion 14 are employed, the separating device has an extremely simple structure, and ensures that the separation of the first satellite S1 and the subsequent rotation of the support 2 can be performed reliably. It can be done smoothly.

  The configuration of the artificial satellite separation device according to the present invention is not limited to the above embodiment, and the configuration can be changed without departing from the gist of the present invention. For example, various coupling and separation devices including pyrotechnics can be used for the upper and lower separation mechanisms and the coupling means of the upper separation mechanism. It is of course possible to do so.

DESCRIPTION OF SYMBOLS 1 Satellite base 2 Support 4 Deployment spring 5 Coupling means (upper separation mechanism)
6 Separation rod (upper separation mechanism)
7 Spring for separation (upper separation mechanism)
DESCRIPTION OF SYMBOLS 12 Stopper 13 Moving spring 14 Stopper receiving part F Fairing J1 Upper separation mechanism J2 Lower separation mechanism R Rocket S1 First satellite S2 Second satellite

Claims (2)

An apparatus for sequentially separating an upper first satellite and a lower second satellite mounted in a rocket fairing from an upper stage,
A satellite base on which the second satellite is separable by the lower separation mechanism,
A plurality of supports disposed on the satellite base around the second satellite and supporting the first satellite;
Each support has a lower end portion rotatably connected to the satellite base in a direction inside and outside the rocket, and an upper separation mechanism for detachably connecting the first satellite to the upper end portion, and an upper separation mechanism. the support with the separating operation of the mechanism Rutotomoni a deployment spring for rotating the rocket outside, in a state in which against the repulsive force of the expansion spring, supports the first satellite is constrained by the upper separation mechanism separator satellite, wherein to Rukoto.
An upper separating mechanism includes a connecting means for connecting each support and the first satellite, a separating rod having a head in contact with the first satellite, and a separating rod via the separating rod when the connecting means is released. A separation spring for giving separation force to one satellite,
The satellite base has a stopper for restraining the support member, the upward movement of which is restricted by the separating rod in a state where the separating spring is compressed, and a moving spring for applying an upward force to the stopper,
2. The artificial satellite separation device according to claim 1, wherein the support has a stopper receiving portion that engages with the stopper and releases the engagement at the upper limit position of the stopper.

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