JP3918031B2 - Shock absorber and flying object launcher using the same - Google Patents

Description

  The present invention relates to an impact mitigation device and a flying object launching device using the same.

  As a flying object launching device, for example, there is a flying object launching device described in Patent Document 1 described later. In this flying object launching apparatus, a flying object is loaded into a canister, and the flying object is held by the canister until just before the launching.

JP 11-183089 A (paragraph [0002] and FIG. 5)

Flying object launchers, when mounted on a moving body such as a ship or vehicle, may receive a large impact from the outside. When such an impact is applied, the flying object is reliably protected. There is a demand for a structure that can be used.
However, most of the flying object launching device is used as the flying object storage space and flying object launching path, and it is not possible to provide a large impact shock absorber, so the impact resistance performance is low. It was.

  The present invention has been made in view of such circumstances, and has an impact buffering device capable of reliably protecting a flying object from an impact received from the outside while having a small size and high impact resistance performance. It aims at providing the used flying object launching device.

In order to solve the above problems, the shock absorbing device of the present invention and the flying object launching device using the same adopt the following means.
That is, the shock absorber according to the present invention is an impact shock absorber that protects a flying body held by a restraint in the launching device body from an impact applied to the flying body launching device, and the launching device body And the restraining tool, and an impact buffer is used, and a ring spring is used as the impact buffer.

  In the impact shock absorber configured as described above, a ring spring is provided as an impact shock absorber between the launcher main body and the restraining tool. In this configuration, when an impact (external force) is applied to the flying object launching device from the outside and the launching device main body and the restraining tool are brought close to each other, the ring spring provided between them is compressed and the launching device main body is compressed. Since the impact transmitted to the restraint is buffered by the ring spring, the flying object held by the restraint is protected from the impact.

  Here, as a general shock absorber, a coil spring that absorbs an impact received from the axial direction mainly by elastic deformation in the axial direction, or an impact input from the axial direction by stroking the cylinder in the axial direction is used. Although there is an oil damper or the like to absorb, these shock absorbers have large axial dimensions due to the shock buffer principle. In addition, the coil spring needs to use a very thick and large coil spring in order to obtain a load-bearing performance sufficient to buffer a large impact applied to the flying object launching device due to the limitation of the spring constant. .

On the other hand, when a ring spring used as an impact buffer in the present invention receives an impact (compression force) in a direction of compressing in the axial direction, the ring spring mainly elastically deforms in the radial direction to thereby apply this impact (compression force). It absorbs, and the stroke amount in the axial direction when absorbing the impact in the axial direction is shorter than that of the other impact buffer. For this reason, the dimension of an axial direction may be short compared with the said other shock-absorbing body. Further, the spring constant of the ring spring can be set higher than that of the coil spring.
Since the shock absorbing device according to the present invention uses a ring spring as the shock absorbing member, the size in the shock absorbing direction may be shorter than that of the shock absorbing device using the other shock absorbing member.

  An impact shock absorber according to the present invention is an impact shock absorber that protects a flying object held by a restraining tool in a launching device body from an impact applied to the flying object launching device. It has an impact buffer inserted between the restraint and a disc spring is used as the impact buffer.

  In the shock absorbing device configured as described above, a disc spring is provided as an shock absorbing member between the launching device main body and the restraining tool. In this configuration, when an impact (external force) is applied to the flying object launching device from the outside and the launching device main body and the restraining tool are brought close to each other, the disc spring provided between them is compressed and the launching device main body is compressed. Since the impact transmitted from to the restraint is buffered by the disc spring, the flying object held by the restraint is protected from the impact.

The disc spring used as an impact buffer in the present invention absorbs the impact (compression force) by elastically deforming in the radial direction and the axial direction when receiving an impact (compression force) in the direction of axial compression. Therefore, the stroke amount in the axial direction when buffering the impact in the axial direction is shorter than that in the other impact buffer. For this reason, the dimension of an axial direction may be short compared with the said other shock-absorbing body. Further, the disc spring has higher load bearing performance than the coil spring.
Since the shock absorbing device according to the present invention uses a disc spring as the shock absorbing member, the size in the shock absorbing direction may be shorter than that of the shock absorbing device using the other shock absorbing member.

  In the impact buffering device, the impact buffer may be provided before and after the restraint in a direction in which impact buffering is required.

In the shock absorbing device configured as described above, when an impact is input and the launching device main body and the restraining tool are relatively brought closer to each other on the front side in the direction in which the shock is required to be shocked, the shock absorbing device is provided on the front side. The impact buffer is compressed and acts on the impact buffer. Similarly, when an impact is input and the launching device main body and the restraint are brought relatively close to each other on the rear side in the direction in which the shock is required to be shocked, the shock buffer provided on the rear side is compressed and the impact is reduced. Acts on buffering.
That is, in the shock absorbing device having this configuration, when the impact is input to the launching device main body, the restraint is relatively displaced to the front side in the direction in which it is desired to buffer the impact with respect to the launching device main body, and relative to the rear side. Since the shock is buffered by the shock buffer when it is displaced, the shock buffering performance is high.

  The shock absorber may include a compression mechanism that causes the external force applied to the launching device main body to act on the compression of the impact cushioning body by separating an external force that separates the firing device main body and the restraining tool. .

In the impact mitigation device configured as described above, when an impact is applied to the flying object launching device from the outside and the launching device main body and the restraining tool are separated, the impact (external force) is transmitted to the impact buffer by the compression mechanism. And acting on the compression of the shock absorber.
That is, in the shock absorber configured as described above, the same shock absorber is used both when the launching device body and the restraining tool are brought close to each other by an external force and when the launching device body and the restraining tool are separated from each other. Since shocks are buffered by the body, the number of shock buffering devices can be halved. Further, when the number of installations is not reduced, the impact buffer can be reduced in size, so that the impact buffer can be further reduced in size.

  In this shock absorber, the compression mechanism is provided so as to be displaceable between the launcher main body and the restraining tool, and receives the end of the shock absorber on the launcher main body side; and A second plate provided to be displaceable between the launcher main body and the restraint and receiving an end of the impact buffer on the restraint side; and the second plate relative to the launcher main body You may be set as the structure which has the 1st guide which prescribes | regulates the range which can displace relatively, and the 2nd guide which prescribes | regulates the range in which the said 1st plate can displace relatively with respect to the said restraint tool.

In this compression mechanism, the range in which the first plate can be displaced with respect to the restraining tool is defined by the second guide. Therefore, when the firing device main body and the restraining tool are separated by a predetermined distance or more, the first plate is restrained. At the same time, it is moved in a direction relatively away from the launcher body.
Then, the impact buffering body is moved together with the first plate in a direction away from the launching device main body.
However, since the displaceable range of the second plate with respect to the launcher body is defined by the first guide, if the launcher body and the restraint are separated by a predetermined distance or more, the first plate and the second plate Are made relatively close to each other, and the shock absorber provided between them is compressed.

A flying object launching apparatus according to the present invention is a flying object launching apparatus that holds a flying object in a launching device body by a restraining tool, and has the above-described impact buffering device.

  In the flying object launching device configured as described above, since the impact buffering device having a higher impact buffering capacity than the conventional one is used as the impact buffering device, the flying object can be more reliably protected.

  According to the impact buffering apparatus and the flying object using the same according to the present invention, since it has a high impact buffering performance while being small in size, the flying object can be more reliably protected.

Embodiments according to the present invention will be described below with reference to the drawings.
[First embodiment]
Hereinafter, a first embodiment of the present invention will be described with reference to FIGS. 1 to 5.
A flying object launching apparatus 1 according to the present embodiment is mounted on a moving body such as a ship or a vehicle. For example, as shown in FIG. 1, a cylindrical canister (launching apparatus) having a substantially quadrangular sectional view. Main body) 2. In the canister 2, a flying body 3 having a substantially cylindrical shape is stored in a state where its axis O is substantially coaxial with the axis of the canister 2.

  Here, the flying body 3 has a tapered tip (upper end in FIG. 1), and the side surface of the proximal end (lower end in FIG. 1) maintains the posture of the flying body 3 during flight. The wing 3a is provided. In the present embodiment, as shown in FIG. 2 (a cross-sectional view taken along the line AA in FIG. 1), the flying body 3 is provided with four wings 3a around the axis O at equal angles. .

As shown in FIG. 2, the canister 2 has the wings 3a positioned at the corners of the canister 2, as shown in FIG. It is configured to be housed inside.
In the canister 2, a support 11 for maintaining the attitude of the flying body 3 in the canister 2 is provided on the tip side of the flying body 3. Here, the support 11 is provided at a position separated from the corner of the canister 2 so as not to interfere with the wing 3 a when the flying body 3 is launched.

  Further, in the canister 2, a restraining tool 12 that restrains the base end of the flying body 3 and holds the flying body 3 in the canister 2 is provided on the proximal end side of the flying body 3 in the axial direction of the canister 2. It is provided to be displaceable. In the present embodiment, the restraint tool 12 is a substantially flat plate-like member, and is configured to hold the flying body 3 with the axis O being substantially orthogonal to the surface formed by the restraint tool 12. ing.

  The restraining tool 12 is held by the canister 2 via the shock absorbing device 13, and when there is no load (when no impact is applied from the outside), the restraining tool 12 is substantially orthogonal to the axis of the canister 2. It is held in the state of letting. As a result, the axis O of the flying body 3 held by the restraining tool 12 is substantially aligned with the axis of the canister 2.

Here, the flying object launching apparatus 1 shown in the present embodiment is mounted on the moving body in a state where the axis of the canister 2 is substantially vertical. In such an installation form, the canister 2 is likely to be subjected to a large impact in its axial direction (that is, in the direction of the aircraft axis O of the flying body 3).
The shock absorbing device 13 shown in the present embodiment is intended to buffer the shock applied mainly in the axial direction of the canister 2.

On the inner peripheral surface of the canister 2, a first stay 14 a that holds the shock absorbing device 13 is provided so as to protrude above the restraint 12 in front of the restraint 12 in the direction of the axis O (upward in FIG. 1). cage, the axis O direction of the rear restraint 12 (downward in FIG. 1), the second stay 14b for holding the shock absorbing device 13 is provided to protrude under side of restraint 12.
Here, the first stay 14 a is provided at a position separated from the corner of the canister 2 so as not to interfere with the wing 3 a when the flying body 3 is launched.

A first wheel spring 16 is provided as an impact buffer between the first stay 14 a and the upper surface of the restraining tool 12. A second wheel spring 17 is provided between the second stay 14 b and the lower surface of the restraining tool 12. The first and second wheel springs 16 and 17 are provided with their axes substantially parallel to the axis of the canister 2.
These first and second wheel springs 16 and 17 constitute the shock absorbing device 13 according to the present embodiment.

  In the shock absorbing device 13, as described above, the first and second wheel springs 16 and 17, which are shock absorbing bodies, are arranged with respect to the restraining device 12 in a state where the main shock absorbing direction is substantially parallel to the axis O. Are provided respectively before and after the axis O direction (that is, the direction in which shock is required to be shocked).

As shown in FIGS. 3 and 4, the first wheel spring 16 has a row of inner rings 16 a and outer rings 16 b in which inner rings 16 a and outer rings 16 b are coaxially arranged alternately in the axial direction.
On the outer periphery of the inner ring 16a, an inclined surface Fa is provided at each end in the axial direction toward the radially outer side from the end in the axial direction toward the center, and the outer peripheral portion of the inner ring 16a is in the radial direction. It has a cross-sectional mountain shape that protrudes outward.
On the inner periphery of the outer ring 16b, an inclined surface Fb is provided at each end in the axial direction toward the radially inner side from the end in the axial direction toward the center, and the inner periphery of the outer ring 16b is It has a cross-sectional mountain shape that is convex inward in the radial direction.
The angle formed by the inclined surface Fa with respect to the axis of the inner ring 16a and the angle formed by the inclined surface Fb with respect to the axis of the outer ring 16b are the same angle, and the adjacent inner ring 16a and outer ring 16b are inclined surfaces. Fa and the inclined surface Fb are brought into surface contact.

  A stroke rod 18 is inserted into the row of the inner ring 16a and the outer ring 16b. The stroke rod 18 is provided with a first washer 18a that receives one end of the inner ring 16a and the outer ring 16b and a second washer 18b that receives the other end of the inner ring 16a and the outer ring 16b. Further, the stroke rod 18 is provided with a reduced diameter portion 18c in a region where the second washer 18b is inserted, and the second washer 18b is within the range where the reduced diameter portion 18c is formed. It can be slid in the axial direction.

  Here, the distance between the first washer 18a and the second washer 18b is set to be always shorter than the natural length of the row of the inner ring 16a and the outer ring 16b provided therebetween. That is, predetermined pre-compression is applied to the row of the inner ring 16a and the outer ring 16b, and the adjacent inner ring 16a and outer ring 16b are always in close contact with each other.

The first wheel spring 16 is configured such that the end of the stroke rod 18 where the first washer 18a is provided is held by the first stay 14a, and the second washer 18b is held by the restraining tool 12, whereby the first stay 14a and the restraint 12 are interposed.
Thus, when the restraint 12 is relatively displaced above the canister 2, a compressive force is applied to the row of the inner ring 16 a and the outer ring 16 b of the first wheel spring 16.

As shown in FIG. 5, the second ring spring 17 has a row of inner rings 17 a and outer rings 17 b in which inner rings 17 a and outer rings 17 b are coaxially arranged alternately in the axial direction.
On the outer periphery of the inner ring 17a, an inclined surface Fa is provided at each end in the axial direction toward the outer side in the radial direction from the end in the axial direction toward the center. It has a cross-sectional mountain shape that protrudes outward.
On the inner periphery of the outer ring 17b, an inclined surface Fb is provided at the end in the axial direction, and the inner surface of the outer ring 17b is radially inward as it goes from the end in the axial direction toward the center. It has a cross-sectional mountain shape that is convex toward the inside in the direction.
The angle formed by the inclined surface Fa with respect to the axis of the inner ring 17a and the angle formed by the inclined surface Fb with respect to the axis of the outer ring 17b are the same angle, and the adjacent inner ring 17a and outer ring 17b are inclined surfaces. Fa and the inclined surface Fb are brought into surface contact.

A stroke rod 19 is inserted through the inner ring 17a and the outer ring 17b.
The stroke rod 19 is provided with a first washer 19a that receives one end of the inner ring 17a and the outer ring 17b, and a second washer 19b that receives the other end of the inner ring 17a and the outer ring 17b. Further, the stroke rod 19 is provided with a reduced diameter portion 19c in a region where the second washer 19b is inserted, and the second washer 19b is within the range where the reduced diameter portion 19c is formed. It can be slid in the axial direction.

  Here, the distance between the first washer 19a and the second washer 19b is set to be always shorter than the natural length of the row of the inner ring 17a and the outer ring 17b provided therebetween. That is, predetermined pre-compression is applied to the row of the inner ring 17a and the outer ring 17b, and the adjacent inner ring 17a and outer ring 17b are always in close contact with each other.

The second wheel spring 17 is configured such that the end of the stroke rod 19 where the second washer 19a is provided is held by the second stay 14b, and the second washer 19b is held by the restraining tool 12, whereby the second stay 14b and the restraint 12 are inserted.
As a result, when the restraint 12 is relatively displaced below the canister 2, a compressive force is applied to the row of the inner ring 17 a and the outer ring 17 b of the second wheel spring 17.

  The first and second ring springs 16 and 17 have a greater impact buffering capacity as the number of inner rings and outer rings is increased. Further, the larger the inner ring and the outer ring (that is, the larger the diameter of the inner ring and the outer ring and the thicker the ring), the greater the shock absorbing capacity. Further, the larger the angle formed by the inclined surface Fa with respect to the axis of the inner ring (that is, the angle formed by the inclined surface Fb with respect to the axis of the outer ring), the greater the impact buffering capacity generated with the same amount of compression.

Here, since the flying body 3 is not stored below the restraining tool 12 in the canister 2, the space below the restraining tool 12 is more than that above the restraining tool 12.
For this reason, in the 2nd ring spring 17, the thing larger than the inner ring 17a and the outer ring 17b of the 1st ring spring 16 can be used as the inner ring 17a and the outer ring 17b.
In the present embodiment, the second wheel spring 17 is larger than the inner ring 17a and the outer ring 17b of the first wheel spring 16 as the inner ring 17a and the outer ring 17b, so that the dimensions in the axial direction (the inner ring 17a and the outer ring 17b) are used. The shock absorbing performance equivalent to that of the first wheel spring 16 is maintained.

  In the flying object launching device 1 configured as described above, when an impact is applied to the canister 2 from the outside, the impact is buffered by the impact buffering device 13, so that the impact is hardly transmitted to the restraining tool 12. The flying body 3 held by 12 is protected from impact.

Hereinafter, the operation of the shock absorber 13 will be described in detail.
As described above, in the first wheel spring 16, when the restraint 12 is relatively displaced above the canister 2, a compression force is applied to the row of the inner ring 16a and the outer ring 16b. On the other hand, in the second wheel spring 17, when the restraint 12 is relatively displaced below the canister 2, a compression force is applied to the row of the inner ring 17 a and the outer ring 17 b.
That is, in the shock absorbing device 13 shown in the present embodiment, when the restraint 12 is displaced in the vertical direction within the canister 2, at least one of the rows of inner and outer rings constituting the first and second wheel springs 16 and 17. A compressive force is applied to either one.

In the first ring spring 16, when a compression force is applied to the row of the inner ring 16a and the outer ring 16b, the adjacent inner ring 16a and the outer ring 16b are pressed against each other as shown in FIG. , Fb, and the inner ring 16a is compressed radially inward and the outer ring 16b is radially outward as shown by a two-dot chain line in FIG. To be spread.
At this time, the compressive force is received by the restoring force generated in the inner ring 16a and the outer ring 16b, and the impact energy is consumed by the frictional resistance generated between the inclined surfaces Fa and Fb, so that the energy is transmitted from the canister 2 to the restraint 12. Shock is buffered.

  Similarly, in the second wheel spring 17, the compression force is received by the restoring force of the inner ring 17 a and the outer ring 17 b, and the energy of impact is consumed by the frictional resistance generated between the inclined surfaces Fa and Fb, and the canister 2. The shock transmitted to the restraint 12 is buffered.

As described above, when the first and second wheel springs 16 and 17 receive an impact (compression force) in the direction of compressing in the axial direction, the first and second wheel springs 16 and 17 absorb the impact (compression force) by elastically deforming mainly in the radial direction. Therefore, the stroke amount in the axial direction when shocking in the axial direction is buffered is shorter than in other shock absorbing bodies such as a coil spring and an oil damper.
For this reason, the shock absorbing device 13 shown in the present embodiment requires a shorter axial dimension than when other shock absorbing members are used.
In addition, since the spring constant of the ring spring is higher than that of the coil spring, it is possible to buffer an impact that cannot be buffered by the coil spring.

Further, in the present embodiment, the first and second wheel springs 16 and 17 that are shock absorbers are provided respectively in the front and rear in the direction in which the shock absorber is required in the restraint tool 12.
Thereby, when an impact is input to the canister 2 and the restraint 12 is displaced relatively to the front side in the direction in which the impact is to be buffered with respect to the canister 2, and when it is relatively displaced to the rear side, respectively. Since the shock is buffered by the shock buffer, the shock buffering performance is high.

Actually, in this flying object launching apparatus 1, an impact of such a magnitude that a 70 G impact is applied to the canister 2 in the axial direction of the flying object from the axial direction to the canister 2 in the conventional flying object launching apparatus. As a result, in the flying object launching apparatus 1, the impact applied in the direction of the axis O of the flying object 3 was 40G.
As can be seen from the above, according to the flying object launching apparatus 1 according to the present embodiment, the flying object 3 can be reliably protected from the impact received from the outside.

[Second Embodiment]
Next, a second embodiment of the present invention will be described with reference to FIG.
The flying object launching device 31 according to the present embodiment uses the impact cushioning device 33 according to the present embodiment instead of the impact cushioning device 13 in the flying object launching device 1 shown in the first embodiment. It is the main feature.
Hereinafter, the same or similar members as those of the flying object launching apparatus 1 shown in the first embodiment are denoted by the same reference numerals, and detailed description thereof is omitted.

In the flying object launching apparatus 31 according to this embodiment, a set of first disc springs 36 is provided as an impact buffer between the first stay 14 a and the upper surface of the restraining tool 12.
A pair of second disc springs 37 is provided between the second stay 14 b and the lower surface of the restraining tool 12.

The first and second disc springs 36 and 37 have tapered cylindrical portions whose other ends are expanded in diameter with respect to one end in the axial direction.
In each pair of the first and second disc springs 36 and 37, adjacent disc springs are coaxially connected with one end having a small diameter or the other end having a large diameter facing each other.

  The set of the first disc spring 36 and the set of the second disc spring 37 constitute the shock absorbing device 33 according to the present embodiment, and are provided with the axes substantially parallel to the axis of the canister 2. ing. In other words, in the shock absorber 33, the first and second disc springs 36 and 37 each have a main shock buffering direction substantially parallel to the machine shaft O, with respect to the restraint 12 in the machine axis O direction ( That is, they are provided before and after the direction in which shock buffering is required.

  The larger the number of disc springs installed in the first disc spring 36 and the second disc spring 37 set, the greater the impact buffering capacity. Moreover, the larger the disc spring, the greater the impact buffering capacity. In addition, when the impact buffering capacity of the 1st, 2nd disk springs 36 and 37 single-piece | unit is high enough, you may comprise the 1st and 2nd disk springs 36 and 37 by each single body.

The impact buffer 33 is provided with a first compression mechanism 38 that applies an external force to compress the set of the first disc springs 36 when an external force that separates the first stay 14a and the restraining tool 12 is applied. ing.
Further, the impact buffer 33 has a second compression mechanism 39 for applying an external force to compress the set of the second disc springs 37 when an external force that separates the second stay 14 b and the restraining tool 12 is applied. Is provided.

The first compression mechanism 38 receives a first plate 41 that receives an end portion of the first disc spring 36 on the first stay 14a side, and a second plate that receives an end portion of the first disc spring 36 on the restraining tool 12 side. Plate 42.
The first plate 41 is connected to the restraining tool 12 via the first guide rod 43. The first plate 41 and the restraining tool 12 are slidable with each other along the first guide rod 43. Here, stoppers S are respectively provided at both ends of the first guide rod 43, and the maximum value of the distance between the first plate 41 and the restraining tool 12 is thereby determined.

The second plate 42 is connected to the first stay 14 a through the second guide rod 44. The second plate 42 and the first stay 14 a are slidable with each other along the second guide rod 44. Here, stoppers S are provided at both ends of the second guide rod 44, respectively, and thereby the maximum value of the distance between the second plate 42 and the first stay 14a is determined.
In the present embodiment, the second guide rod 44 is inserted into the set of the first disc springs 36, whereby the first disc springs 36 of the set of the first disc springs 36 are bundled.

The second compression mechanism 39 includes a second plate 46 that receives an end of the second disc spring 37 on the second stay 14 b side, and a second plate 46 that receives the end of the second disc spring 37 on the restraining tool 12 side. Plate 47.
The first plate 46 is connected to the restraining tool 12 via a first guide rod 48. The first plate 46 and the restraining tool 12 are slidable with each other along the first guide rod 48. Here, stoppers S are respectively provided at both ends of the first guide rod 48, and thereby the maximum value of the distance between the first plate 46 and the restraining tool 12 is determined.

The second plate 47 is connected to the second stay 14 b via the second guide rod 49. The second plate 47 and the second stay 14 b are slidable with each other along the second guide rod 49. Here, stoppers S are respectively provided at both ends of the second guide rod 49, and thereby the maximum value of the distance between the second plate 47 and the second stay 14b is determined.
In the present embodiment, the second guide rod 49 is inserted into the set of second disc springs 37, and thereby the first disc springs 37 of the set of second disc springs 37 are bundled.

In the impact mitigating device 33 configured as described above, in the no-load state, the restraint 12 is configured such that the restoring force of the pair of first disc springs 36 and the restoring force of the second disc springs 37 as shown in FIG. It is held in a position that balances the force.
Then, when an external impact is applied to the flying object launching device 31 and an external force that separates the first stay 14a and the restraining tool 12 acts, as shown in FIG. The second stay 14b is brought close to the second stay 14b. Then, the set of the second disc springs 37 provided between them is compressed and acts to absorb this impact.

Further, since the external force applied at this time is also applied to the compression of the first disc spring 36 by the first compression mechanism 38, the first disc spring 36 also acts to absorb this impact.
Specifically, in the first compression mechanism 38, when the first stay 14a and the restraining tool 12 are separated, the first guide rod 43 is also separated from the first stay 14a together with the restraining tool 12. Then, the first plate 41 is also separated from the first stay 14 a together with the first guide rod 43.
However, since the maximum value of the distance between the second plate 42 and the first stay 14a is regulated by the second guide rod 44, the first plate 41 and the second plate 42 are brought close to each other and between them. A compression force is applied to the row of the first disc springs 36 arranged.

  On the other hand, when an external impact is applied to the flying object launching device 31 and an external force that separates the second stay 14b and the restraining tool 12 acts, as shown in FIG. The first stay 14a is brought close to the first stay 14a. Then, the set of the first disc springs 36 provided between them is compressed and acts to absorb this impact.

Further, since the external force applied at this time is also applied to the compression of the set of the second disc springs 37 by the second compression mechanism 39, the set of the second disc springs 37 also acts to absorb this impact.
Specifically, in the second compression mechanism 39, when the second stay 14b and the restraining tool 12 are separated from each other, the second guide rod 48 is also separated from the second stay 14b together with the restraining tool 12. Then, the first plate 46 is also separated from the second stay 14 b together with the second guide rod 48.
However, since the maximum value of the distance between the second plate 47 and the second stay 14b is regulated by the second guide rod 49, the first plate 46 and the second plate 47 are brought close to each other and between them. A compression force is applied to the row of the second disc springs 37 arranged.

  In the shock absorbing device 33 configured as described above, both the row of the first disc springs 36 and the second disc are both when the canister 2 and the restraining tool 13 are displaced upward and downward by an external force. Since the shock is buffered by the row of the springs 37, the number of rows of the first disc springs 36 and the rows of the second disc springs 37 are set as compared with the case where the first and second compression mechanisms 38 and 39 are not provided. Can be cut in half. Moreover, when the number of these installations is not reduced, since the row | line | column of the 1st disc spring 36 and the row | line | column of the 2nd disc spring 37 can be reduced in size, the impact buffer 33 can be further reduced in size.

Here, in this embodiment, the shock absorbing device 33 is configured to use a disc spring as the shock absorbing body. However, the present invention is not limited to this, and as shown in the first embodiment, a ring spring is used as the shock absorbing body. It may be used.
On the other hand, in the shock absorbing device 13 shown in the first embodiment, a disc spring may be used as the shock absorbing body.

  Further, in the shock absorbing devices 13 and 33 shown in the above embodiments, the shock absorbing body may be provided only on either the upper side or the lower side of the restraint 12.

It is a longitudinal section showing the composition of the flying object launcher concerning a first embodiment of the present invention. It is AA arrow sectional drawing of FIG. It is a figure which shows the structure of the impact buffering apparatus concerning 1st embodiment of this invention. It is a figure which shows operation | movement of the shock absorbing device concerning 1st embodiment of this invention. It is a figure which shows the structure of the impact buffering apparatus concerning 1st embodiment of this invention. It is a figure which shows the structure of the impact buffer used for the flying object launcher concerning 2nd embodiment of this invention.

Explanation of symbols

1,31 Flying object launcher 2 Canister (launcher body)
3 Flying object 12 Restraint 13, 33 Shock absorbing device 16, 17 First, second wheel spring (impact buffer)
36, 37 First and second disc springs (impact buffer)
38, 39 First, second compression mechanisms 41, 46 First plates 42, 47 Second plates 43, 48 First guide rods 44, 49 Second guide rods

Claims (3)

An impact buffering device that protects the flying object held by the restraint in the launching device body from the impact applied to the flying object launching device in the longitudinal direction of the launching axis ,
The launcher body (2) has a vertical cylindrical shape, and the flying body (3) having a substantially cylindrical shape is the axis of the launcher body (2) in the launcher body (2). It is stored in a state of being almost coaxial with the base of the flying body (3), and the flying body (3) is placed inside the launcher body (2) by restraining the proximal end of the flying body (3). The restraining tool (12) made of a substantially flat plate-shaped member is provided, and the inner peripheral surface of the launching device main body (2) is protruded above and below the restraining tool (12). A stay (14a) and a second stay (14b) are provided, and the upper and lower surfaces of the first stay (14a), the second stay (14b), and the restraint (12) at the outer peripheral position of the flying body (3). between the upper and lower shock absorbing member which is interposed, as the impact cushion, the shaft of the flying object (3) Shock absorbing apparatus being characterized in that by using a loop-free spring. 2. The shock absorbing device according to claim 1 , wherein a disc spring is used as the shock absorbing body in place of the ring spring . A flying object launching apparatus for holding a flying object by a restraining tool in the launching apparatus main body, wherein the flying object launching apparatus has the shock absorbing device according to claim 1 or 2 .

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