JP5888671B2 - Vibration relaxation device - Google Patents

Description

  The present invention is arranged between a rocket motor (sometimes referred to as a rocket engine) and a payload located at the upper stage of this rocket motor, so-called interstage part, to reduce vibration and impact transmitted from the rocket motor to the payload. The present invention relates to a vibration mitigation device used to perform the above.

Conventionally, as the above-described vibration relaxation device, for example, there is one disclosed in Patent Document 1.
This vibration mitigation device includes a plurality of flexible blocks made of titanium, and the plurality of the above-described plurality of blocks are provided at the interstage portion between the upper end of the rocket motor and the lower end of the payload positioned above the rocket motor. Each block is arranged side by side in the circumferential direction.

The block includes two beams arranged in parallel with each other at a predetermined interval, and these beams are arranged along the radial direction at the interstage.
One beam of this block is fixed to the upper end side of the rocket motor, and the other beam is fixed to the lower end side of the payload, and the two beams are deformed in a direction approaching and separating from each other, Vibration transmitted from the rocket motor to the payload is reduced.

US6290183

  However, in the above-described vibration mitigation device, a plurality of blocks are arranged so that each of the two metal beams follows the radial direction, so a large space is required in the interstage portion. There is a problem of doing.

  Further, in the above-described vibration mitigation device, the two metal beams of the block are bent and deformed in the direction of approaching and separating from each other. The amount of vibration displacement is small, and it is difficult to say that vibration in the machine axis direction transmitted to the payload can be sufficiently reduced. In addition, since the two metal beams are easily deformed in the machine axis direction, a difference in deformation amount is likely to occur between a plurality of blocks arranged side by side in the circumferential direction. As a result, the payload falls sideways. There is a problem that it cannot be said that there is no possibility of doing (tilting with respect to the axis), and it has been a conventional problem to solve these problems.

  The present invention has been made by paying attention to the above-described conventional problems, and it is possible to absorb vibration displacement in the axial direction on the rocket motor side after realizing compactness of the interstage part. An object of the present invention is to provide a vibration mitigation device that can eliminate the risk of the payload falling down.

According to a first aspect of the present invention, there is provided a motor-side annular wall formed around an axle on the rocket motor side in an interstage portion between a rocket motor and a payload detachably coupled to the upper stage of the rocket motor. And a payload-side annular wall portion that is formed on the payload side and is opposed to the motor-side annular wall portion of the rocket motor, the motor-side annular wall portion and the payload side The deformation means sandwiched between the annular walls so as to be deformable in the axial direction, and is disposed between the motor-side annular wall portion and the payload-side annular wall portion, and the deformation is performed while maintaining the posture of the payload with respect to the rocket motor. comprising a position maintaining means for allowing only deformation axis direction means, said deformable means comprises an elastic rubber layer which enables shear deformation in the axis direction The elastic rubber layer has one side fixed to the motor-side annular wall and the other side fixed to the payload-side annular wall, and the posture maintaining means is disposed on the motor-side annular wall. A motor-side regulating body having a block shape, and a payload-side regulating body having a block shape which is disposed on the payload-side annular wall portion and abuts on the motor-side regulating body of the motor-side annular wall portion. The body and the payload side regulating body are characterized in that when the deformation means is deformed in the axial direction, the body and the payload side regulating body are configured to slide in the axial direction while restricting the change in posture of each other. Is a means for solving the above-described conventional problems.

  The vibration mitigation device according to the present invention is disposed in the vicinity of a coupling / separation device that detachably couples the rocket motor and the payload, and descends together with the rocket motor after the payload is separated.

  In the vibration mitigation device according to the present invention, the rocket motor side motor-side annular wall portion and the payload-side payload-side annular wall portion face each other, but the payload-side annular wall portion is outside the motor-side annular wall portion. It may be located or may be located inside.

In here, the elastic rubber layer as a modification means may be a single layer, may be a two-layer or more, such as when the elastic rubber layer forms a two layers, the strength of the elastic rubber layer In order to increase, it is desirable to interpose a metal shim between the layers, and it is desirable to interpose a metal shim between the annular wall portion and the elastic rubber layer.

  At this time, the motor-side restricting body arranged on the motor-side annular wall and the payload-side restricting body arranged on the payload-side annular wall have a metal plate, It is desirable to use a block, and it is desirable to employ stainless steel or an aluminum alloy as the metal material in order to suppress the generation of rust that hinders the sliding in the machine axis direction.

Furthermore, as in the vibration mitigating device according to claim 2 of the present invention, graphite, molybdenum disulfide, polytetrafluoroethylene are provided on the contact surfaces of the motor-side regulating body and the payload-side regulating body in the posture maintaining means. A solid lubricating surface formed by coating a solid lubricant such as the above, or a solid lubricating surface formed by performing a chrome plating process can be formed.

Furthermore, in the vibration mitigation device according to claim 3 of the present invention, a plurality of the posture maintaining means are arranged at predetermined intervals in the circumferential direction between the motor-side annular wall portion and the payload-side annular wall portion. It is said.

  In this case, in order to more reliably maintain the posture of the payload with respect to the axle of the rocket motor, it is desirable to arrange the posture maintaining means at three or more locations, for example, 16 locations with an interval of 22.5 °. Can be arranged.

  In the vibration mitigation device according to the present invention, when the rocket motor is operated, if the vibration of the rocket motor is transmitted to the interstage portion with the payload, the deformation means is deformed in the axial direction, so that the displacement due to the vibration is absorbed. Therefore, vibration transmitted to the payload side can be reduced.

  At this time, the posture maintaining means allows only the deformation of the deformation means in the axial direction while maintaining the posture of the payload with respect to the rocket motor, so that the payload is applied to the rocket motor axle while reducing the vibration in the axial direction transmitted to the payload. It is possible to prevent the payload from falling down.

Moreover, since the deforming means the elastic rubber layer, that the elastic rubber layer is a shearing deformation in the axis direction, after compactified, it may enhance the absorption capacity of the axis direction of the vibration displacement and Become.

Furthermore, since the motor-side restricting body and the payload-side restricting body that are in contact with each other are used as the posture maintaining means , it is possible to reliably regulate the mutual posture change without disturbing the deformation of the deformation means in the axis direction. If the contact surfaces of the motor-side regulating body and the payload-side regulating body are coated with a solid lubricant, the deformation means can be smoothly deformed in the axial direction.

  Furthermore, if a plurality of posture maintaining means are arranged at a predetermined interval in the circumferential direction, it is possible to reliably prevent the payload from falling down.

  Since the vibration mitigation device according to claim 1 of the present invention has the above-described configuration, it is possible to reduce vibration transmitted from the rocket motor side to the payload, and to prevent the payload from being inclined with respect to the axle. It has a very good effect that it is possible.

Further, in the vibration absorbing device according to claim 1 of the present invention, since was configured as described above, after realizing compactness of the interstage portion, to absorb even a large vibration displacement of the axis direction of the rocket motor side It has a very good effect of being possible.

Furthermore, since the vibration mitigation device according to claims 1 and 2 of the present invention has the above-described configuration, it is possible to reliably prevent the payload from being tilted with respect to the axle while reducing the vibration transmitted from the rocket motor side to the payload. This is a very good effect that is possible.

Furthermore, since the vibration mitigating device according to claim 3 of the present invention has the above-described configuration, it is possible to provide a very excellent effect that the payload can be reliably prevented from falling down.

Half side explanatory drawing (a) which showed the part by which the deformation | transformation means of this vibration mitigation device is arrange | positioned in the step part between the flying bodies in which the vibration mitigation device by one Example of this invention is installed was shown in section (a), FIG. FIG. 4A is a cross-sectional explanatory view (b) of a portion where the posture maintaining means of the vibration mitigation device is disposed in the flying body interstage portion of a) and a partial side explanatory view (c) of the flying body interstage portion where the vibration mitigation device is provided. is there. It is the expansion side explanatory view (a) and expansion cross-sectional explanatory view (b) of the elastic rubber layer which comprise the deformation | transformation means in the vibration relaxation apparatus shown to Fig.1 (a). It is the plane explanatory view (a) and side surface explanatory view (b) which show the motor side control body which comprises the attitude | position maintenance means of the vibration relaxation apparatus in FIG. It is plane explanatory drawing (a) and side surface explanatory drawing (b) which show the payload side control body which comprises the attitude | position maintenance means of the vibration relaxation apparatus in FIG. FIG. 1 is a perspective explanatory view (a), a cross-sectional explanatory view (b), and a cross-sectional explanatory view (c) at the time of absorbing a compressive vibration displacement, illustrating an operation state of the elastic rubber layer and the regulating body of the vibration reducing device in FIG. It is. It is expansion side explanatory drawing of the deformation | transformation means of the vibration relaxation apparatus by other Example of this invention.

Embodiments of the present invention will be described below with reference to the drawings.
1 to 5 show a vibration mitigation device according to an embodiment of the present invention.
As shown in part in FIG. 1 (a), this vibration mitigation device 10 is in an interstage part between a rocket motor 2 of a flying object 1 and a satellite (payload) 3 located on the upper stage of the rocket motor 2. The rocket motor 2 and the satellite 3 are arranged in the vicinity of a coupling / separating device (not shown) that detachably couples, and descend with the rocket motor 2 after the satellite 3 is detached.

  In this embodiment, as shown in FIGS. 1B and 1C, the vibration mitigation device 10 includes a motor-side annular wall 2a formed around the axis L on the rocket motor 2 side, and a satellite 3 side. The rocket motor 2 is installed between the motor-side annular wall 2a of the rocket motor 2 and the satellite-side annular wall 3a facing on the outer peripheral side, and the axis between the motor-side annular wall 2a and the satellite-side annular wall 3a. The deformation means 11 sandwiched so as to be deformable in the L direction, and is arranged between the motor-side annular wall portion 2a and the satellite-side annular wall portion 3a. Posture maintaining means 12 that allows only direction deformation is provided.

As shown in FIG. 2, the deformation means 11 includes two elastic rubber layers 11 in and 11 out that are laminated in the radial direction of the rocket motor 2 and can be sheared and deformed in the axis L direction. The elastic rubber layer 11in is fixed to the motor-side annular wall 2a via a metal shim 13, and the outer elastic rubber layer 11out is fixed to the satellite-side annular wall 3a via a metal shim 13.
In this case, in order to increase the strength of the elastic rubber layer, a metal shim 13 is also interposed between the two elastic rubber layers 11in and 11out.

The attitude maintaining means 12 includes a motor-side slider (motor-side regulating body) 12in fixed to the motor-side annular wall 2a, and a satellite-side slider (payload) fixed to the satellite-side annular wall 3a and in contact with the motor-side slider 12in. Side regulating body) 12out.
The motor side slider 12in has a block shape as shown in FIG. 3, while the satellite side slider 12out also has a block shape as shown in FIG. These sliders 12in and 12out are both made of stainless steel, and a solid lubricating surface 15 formed by coating polytetrafluoroethylene is formed on the contact surface of the motor-side slider 12in. A solid lubrication surface 16 is formed on the surface by chrome plating.

  These sliders 12in and 12out slide in the direction of the axis L while regulating the mutual attitude change when the vibration displacement from the rocket motor 2 is transmitted to the interstage and the deformation means 11 is deformed in the direction of the axis L. That is, the satellite 3 is prevented from falling down while allowing the deformation means 11 to be deformed in the axis L direction.

  In this case, the two elastic rubber layers 11in and 11out, which are the deformation means 11, are arranged at a plurality of locations in the circumferential direction in the interstage portion (in this embodiment, 16 locations at intervals of 22.5 °). The sliders 12in and 12out of the posture maintaining means 12 are disposed between the elastic rubber layers 11in and 11out disposed at the plurality of locations.

  In the vibration mitigation device 10 described above, when the vibration of the rocket motor 2 is transmitted to the interstage portion with the satellite 3 during the operation of the rocket motor 2 of the flying object 1, as shown in FIG. When the two elastic rubber layers 11in and 11out, which are 11, are deformed in the direction of the axis L, respectively, the tensile vibration displacement x (+) shown in FIG. 5B and the compression vibration displacement x shown in FIG. Since (−) is absorbed, the resonance frequency on the satellite 3 side can be controlled, and the vibration transmitted to the satellite 3 side can be suppressed to a low level.

  At this time, the sliders 12in and 12out of the attitude maintaining means 12 slide in the direction of the axis L while restricting mutual attitude changes, that is, the two layers of elasticity while maintaining the attitude of the satellite 3 relative to the rocket motor 2. Since only the deformation of the rubber layers 11in and 11out in the direction of the axis L is allowed, it is possible to prevent the satellite 3 from falling down while reducing the vibration in the direction of the axis L transmitted to the satellite 3.

  In this embodiment, since the two elastic rubber layers 11in and 11out which are laminated in the radial direction of the rocket motor 2 and can be sheared and deformed in the direction of the axis L are used as the deformation means 11, both elastic rubber layers 11in and 11out are respectively provided. As a result, it is possible to enhance the absorption capacity of vibration displacement in the direction of the machine axis L while achieving compactness.

In this embodiment, since the motor-side slider 12in and the satellite-side slider 12out that are in contact with each other are used as the attitude maintaining means 12, the deformation of the two elastic rubber layers 11in and 11out in the axis L direction can be prevented without interfering with each other. It will be possible to reliably regulate the change in posture.
In addition, since the solid lubricating surfaces 15 and 16 are formed on the contact surfaces of the motor-side slider 12in and the satellite-side slider 12out, the elastic rubber layers 11in and 11out of the two layers are deformed in the axis L direction. Can be carried out smoothly.

  Further, in this embodiment, the two elastic rubber layers 11in and 11out are arranged at 16 positions with an interval of 22.5 °, and the slider of the posture maintaining means 12 is interposed between the plurality of elastic rubber layers 11in and 11out. Since 12 in and 12 out are arranged, the satellite 3 can be reliably prevented from falling down.

  In this vibration mitigation device 10, the satellite-side annular wall 3a is opposed to the motor-side annular wall 2a on the outside, but the satellite-side annular wall 3a is opposed to the inside of the motor-side annular wall 2a. You may make it do.

  Further, in the above-described vibration mitigation device 10, the two elastic rubber layers 11in and 11out, which are laminated in the radial direction of the rocket motor 2 and are capable of shearing deformation in the axis L direction, are used as the deformation means 11. For example, as shown in FIG. 6, the elastic rubber layer may be a single elastic rubber layer 21 fixed to the motor-side annular wall portion 2 a and the satellite-side annular wall portion 3 a via a metal shim 13. Alternatively, the elastic rubber layer may be three or more layers.

  Furthermore, in the above-described vibration mitigation device 10, stainless steel is used as the metal material constituting the motor side slider 12in and the satellite side slider 12out, but the present invention is not limited to this, and other metal materials are used. For example, an aluminum alloy can be employed.

  The configuration of the vibration mitigation device according to the present invention is not limited to the configuration of the above-described embodiment.

2 Rocket motor 2a Motor side annular wall 3 Satellite (payload)
3a Satellite side annular wall (payload side annular wall)
DESCRIPTION OF SYMBOLS 10 Vibration relaxation device 11 Deformation means 11in Elastic rubber layer inside (deformation means)
11out outer elastic rubber layer (deformation means)
12 posture maintaining means 12in motor side slider (motor side regulating body; posture maintaining means)
12out satellite side slider (payload side regulating body; attitude maintaining means)
15, 16 Solid lubricating surface L

Claims (3)

In the interstage part between the rocket motor and the payload that is separably coupled to the upper stage of the rocket motor, the motor-side annular wall part formed around the axle on the rocket motor side, and the payload side formed on the payload side A vibration mitigation device installed between the motor-side annular wall of the rocket motor and the payload-side annular wall facing the rocket motor,
Deformation means sandwiched between the motor-side annular wall portion and the payload-side annular wall portion so as to be deformable in the axis direction,
A posture maintaining means disposed between the motor-side annular wall portion and the payload-side annular wall portion and allowing only deformation of the deformation means in the axial direction while maintaining the posture of the payload with respect to the rocket motor ;
The deformation means includes an elastic rubber layer that can be shear-deformed in the axial direction, and one side of the elastic rubber layer is fixed to the motor-side annular wall portion, and the other side is the payload-side annular wall portion. Fixed to
The posture maintaining means is in contact with the motor-side regulating body arranged in the block on the motor-side annular wall and the motor-side regulating body in the payload-side annular wall arranged on the payload-side annular wall. A payload-side restricting body having a block shape is provided, and the motor-side restricting body and the payload-side restricting body slide in the axial direction while restricting a change in posture of the deforming means when the deforming means is deformed in the axial direction. A vibration mitigation device characterized by: Wherein the respective contact surface of said at position maintaining means motor side regulating member and a payload side regulating member, the vibration absorbing device according to claim 1, solid lubricant surface is formed. The vibration mitigating device according to claim 1 or 2 , wherein a plurality of the posture maintaining means are arranged at a predetermined interval in the circumferential direction between the motor-side annular wall portion and the payload-side annular wall portion.

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