JPH1111399A - Separating device for booster rocket - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a separating device for a booster rocket which can obtain large separating force and realize weight lightening or the like, with no necessity for reinforcing a structure in order to hold a pressure accumulating condition as in a separating device using a spring, without an influence by arranging of the booster rocket and with no necessity for providing a heat resistance means in a core rocket or the like as in a separating device using a separating motor. SOLUTION: In a device separating a booster rocket connected to a core rocket, the device is a separating device 10 of the booster rocket provided with a cylinder 11, movable body 12 mounted movably on the cylinder 11 to be moved by a pressure in the cylinder 11 to press the core rocket, and a gas generating means 13 supplying gas in the cylinder 11, in the booster rocket. In this way, during the time till separation time, without giving separating force between the core rocket and the booster rocket, and at separation time, without performing injection of gas to the outside, large separating force is obtained by a pressure of gas.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an apparatus for separating a booster rocket used for separating a booster rocket detachably connected to a core rocket.

[0002]

2. Description of the Related Art A structure in which a booster rocket is connected to a core rocket is described in, for example, "Aerospace Engineering Handbook / Supplement Edition" No. 462 issued by Maruzen on April 25, 1983.
Some are listed on the page. In this structure, the core rocket and the booster rocket are connected by upper and lower mounting brackets, and when separated, the upper mounting bracket is released to tilt the booster rocket by the action of dynamic pressure,
As a result, the lower mounting bracket was removed and the booster rocket was discarded.

In recent years, booster rockets have been increased in size. However, as the size of the booster rockets increased, the separated booster rockets entered the plume (combustion gas flow) of the core rocket, which caused the core rocket to vibrate and the tail of the tilted booster rocket to the core rocket. There has been a risk of contact. Therefore, a separation device for forcibly separating the booster rocket has been developed.As such a separation device for the booster rocket, a device using a spring or a small separation motor equipped with a solid propellant is used. There was something.

[0004]

However, in the conventional booster rocket separation device as described above,
In a separation device using a spring, it is necessary to maintain the accumulated pressure state of the spring by the time of separation. Therefore, the structure must be strengthened accordingly, and there is a problem that the weight increases. In addition, in a separation device using a separation motor, as shown in FIG.
In the case of a rocket having two booster rockets B1 and B1, in order to protect the core rocket C from the combustion gas P of the separation motor, the separation motor is configured to inject the combustion gas P obliquely avoiding the core rocket C. It is possible to arrange the second booster rockets B2 and B2, which burn for a longer time in two places 90 degrees different from the two booster rockets B1 and B1, as shown by the phantom line in FIG. It is difficult to arrange the rocket equipped with the core rocket C or the second rocket because it is difficult to arrange the rocket to avoid the combustion gas P.
It is necessary to provide heat-resistant means for the booster rockets B2 and B2, which causes a problem that the weight increases.

[0005]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional problems, and it is not necessary to reinforce the structure to maintain the pressure accumulation state unlike a separation device using a spring. It is not necessary to depend on the arrangement of the booster rocket or to provide heat-resistant means in the core rocket or the like unlike the separation device using the motor for the motor, and it is possible to obtain a large separation force and to realize weight reduction and the like. It is an object of the present invention to provide a booster rocket separation device that can be used.

[0006]

According to the present invention, there is provided a booster rocket separating apparatus for separating a booster rocket coupled to a core rocket.
The booster rocket has a structure including a cylinder, a movable body mounted movably with respect to the cylinder and moved by pressure in the cylinder to press the core rocket, and gas generating means for supplying gas into the cylinder, Claim 2 is an apparatus for separating a booster rocket coupled to a core rocket, wherein the booster rocket is mounted on a cylinder having an axis arranged toward the core rocket and movably mounted on the cylinder in the axial direction thereof. A movable body that can advance and retreat toward the core rocket is provided, and a pressure chamber whose volume increases and decreases with the advance and retreat of the movable body between the cylinder and the movable body is formed, and a gas generating unit that supplies gas to the pressure chamber is provided. With the booster rocket connected to the core rocket, move the movable body to the retracted position with respect to the cylinder, and attach the front end of the movable body to the core. A third aspect of the present invention is a configuration in which the pressure chamber is provided with an airbag which is deployed by the gas of the gas generating means, and a fourth aspect is a configuration in which the gas generating means is provided in the pressure chamber. According to a fifth aspect, the gas generating means has a configuration including a plurality of gas generators, and as a sixth aspect, the core rocket and the cylinder are connected by separable connecting means,
The above configuration is a means for solving the problem.

[0007]

The booster rocket separating device according to the first aspect of the present invention is provided on the booster rocket so that it does not remain as unnecessary weight on the core rocket side after operation, and includes a cylinder, a movable body, and gas generating means. No separation force is applied between the core rocket and the booster rocket until it operates. Further, in the separation device, when the gas is supplied to the cylinder by the gas generating means when the core rocket and the booster rocket are disconnected from each other without releasing the gas from the outside, the movable body is caused by the gas pressure. Move and press the core rocket,
The booster rocket separates from the core rocket by the reaction force.

In the booster rocket separation device according to a second aspect of the present invention, similarly to the first aspect, the booster rocket is provided on the booster rocket so that it does not remain as unnecessary weight on the core rocket side after the operation. In addition to the body and gas generating means, the front end of the movable body in the retracted position is only abutted against the core rocket, so no separation force is applied between the core rocket and the booster rocket until operation. Not. In addition, in the separation device, gas injection to the outside is not performed, and when releasing the connection between the core rocket and the booster rocket, when a high-pressure gas is supplied to the pressure chamber in the cylinder by the gas generation means, the gas pressure increases. The movable body moves forward and presses the core rocket, and the booster rocket is separated from the core rocket by the reaction force.

In the booster rocket separation device according to the third aspect of the present invention, since the airbag which is deployed by the gas of the gas generating means in the pressure chamber is provided, the airbag itself secures gas tightness. The movable body is moved by the deployment of the airbag to press the core rocket.

In the booster rocket separation device according to the fourth aspect of the present invention, since the gas generating means is provided in the pressure chamber, a gas supply path between the cylinder and the gas generating means is not required.

In the booster rocket separation device according to claim 5 of the present invention, since the gas generating means includes a plurality of gas generators, the number of gas generators can be changed, and the generated pressure can be reduced. Coordination can be addressed.

In the booster rocket separating apparatus according to the sixth aspect of the present invention, since the core rocket and the cylinder are connected by separable connecting means, the cylinder can be used as a brace for connecting the booster rocket. Alternatively, the separating device can be incorporated in the connecting brace, and the booster rocket is separated together with the release of the connecting means.

[0013]

According to the booster rocket separation device according to the first aspect of the present invention, the cylinder, the movable body, and the gas generating means are employed, so that the separation between the core rocket and the booster rocket until the separation. Since no separation force is applied, there is no need to reinforce the structure to maintain the pressure accumulation state as in the conventional separation device using a spring, and since there is no gas injection to the outside, the separation It is not necessary to provide heat-resistant means in a core rocket or the like as in a conventional separation device using a motor for use, and it is possible to realize a significant reduction in weight as compared with these conventional devices. In addition, since the gas is not injected to the outside, the movable body is securely oriented to the core rocket side without being influenced by the arrangement of the booster rocket unlike the separation device using a separation motor. And a reduction in cost as compared with a separation apparatus using a separation motor. Furthermore, the adoption of a cylinder, a movable body, and gas generating means simplifies the structure, and makes it easy to adjust and maintain the separation force. Can be obtained.

According to the booster rocket separation apparatus according to the second aspect of the present invention, similar to the first aspect, by employing the cylinder, the movable body, and the gas generating means, the core rocket is separated from the core rocket until the separation. Since no separation force is applied between the booster rockets, there is no need to reinforce the structure to maintain the pressure accumulation state as in the conventional separation device using a spring. Since it is not performed, there is no need to rely on the arrangement of booster rockets or provide heat-resistant means in core rockets, etc., unlike conventional separation devices that use a separation motor. Therefore, the weight can be reduced, and the cost can be reduced as compared with a separation device using a separation motor. Furthermore, the adoption of a cylinder, a movable body, and gas generating means simplifies the structure, and makes it easy to adjust and maintain the separation force. Can be obtained.

According to the booster rocket separation device of the third aspect of the present invention, the same effect as that of the second aspect can be obtained, and in addition, the booster rocket is provided with an air bag which is deployed in the pressure chamber by the gas of the gas generating means. As a result, airtightness against gas can be ensured by the airbag itself, whereby reliable operation can be obtained without making the airtight function of the pressure chamber so strict, further simplifying the structure and reducing the weight. Can be realized.

According to the booster rocket separation device of the fourth aspect of the present invention, the same effects as those of the second and third aspects can be obtained, and the gas generating means is provided in the pressure chamber. There is no need for a gas supply path between the gas supply means and the gas generating means, the structure is further simplified, the size and weight can be further reduced, and the storage of the booster rocket is improved.

According to the booster rocket separating apparatus of the fifth aspect of the present invention, the same effect as that of the fourth aspect can be obtained, and the gas generating means having a plurality of gas generators is employed. Therefore, the generated pressure can be easily adjusted by changing the number of gas generators.

According to the booster rocket separating apparatus according to the sixth aspect of the present invention, the same effects as those of the first to fifth aspects can be obtained, and the core rocket and the cylinder are connected by separable connecting means. Therefore, the cylinder can be used as a brace for connecting the booster rocket,
Alternatively, the separating device can be incorporated in the connecting brace, which contributes to the overall reduction in size and weight of the connecting device of the booster rocket.

[0019]

1 to 3 show an embodiment of a booster rocket separating apparatus according to claims 1, 2, 4 and 5 of the present invention.

The booster rocket B shown in FIGS. 2 and 3
Is a rocket provided with a solid propellant, for example, and is provided near the tail of the core rocket C indicated by a virtual line in each figure. Although one side is omitted in the figure, the booster rocket B
It is installed at two locations 180 degrees different from core rocket C.

The booster rocket B is connected to the core rocket C by two upper braces 1, 1 and lower braces 2, 2 provided on both upper and lower sides and two long braces 3 respectively. is there. The booster rocket B is provided with upper and lower connecting tools 4 and 5 for connecting the braces, and the core rocket C is also provided with the upper and lower connecting tools 6 and 5 for connecting the braces.
7 is provided. The long brace 3 has an upper end connected to the booster-side upper connector 4 and a lower end connected to the core-side lower connector 7.

Each of the braces 1, 2, 3 can be separated by pyrotechnics at or near the upper and lower couplings 6, 7 on the core rocket C side, and the booster is used until the separation. The rocket B is coupled to the core rocket C, and the thrust of the booster rocket B is transmitted to the core rocket C side.

The above separating device 10 for the booster rocket B
Are arranged in the center of the inside of the booster rocket B on the upper side shown in FIG. 3A, and are arranged at two places inside the lower braces 2 on the lower side shown in FIG. 3B. is there.

After operation, the separation device 10 starts the core rocket C
All of them are provided on the booster rocket B side so as not to leave unnecessary weight on the side, and as shown in FIG. A movable body 12 that moves and presses the core rocket C and a gas generating means 13 that supplies gas into the cylinder 11 are provided. In this embodiment, a pressure chamber formed between the cylinder 11 and the movable body 12 is provided. Gas generating means 13 is provided in 14.

The cylinder 11 is arranged with its axis directed toward the core rocket C on the left side in FIG. Cylinder 1
1 has a cylindrical main body 15 and a cylinder head 16 that closes the main body 15 on the side opposite to the core rocket C, and has a bottomed cylindrical shape opened to the core rocket C side. The cylinder 11 is provided inside the open end of the main body 15.
An inwardly extending portion 17 is provided in the circumferential direction, and a stepped portion formed by the inwardly extending portion 17 is provided with a ring-shaped cushion member 18 which comes into contact with the movable body 12 described later.
Is provided.

The movable body 12 has a bottomed cylindrical shape having a diameter slightly smaller than that of the cylinder 11, and has, at its open end, an outwardly extending portion 19 slidably fitted inside the cylinder 11. In the circumferential direction. An O-ring 20 is attached to the outer peripheral portion of the outwardly extending portion 19 to ensure airtightness between the inner surface of the cylinder 11 and the outwardly extending portion 19. Further, a cylindrical connecting portion 21 having a female screw hole is integrally provided at the center of the bottom outer surface of the movable body 12, and the connecting portion 21 has a pressing rod having a tip portion abutting on the core rocket C. The base end of 22 is screwed. The pushing rod 22 can adjust the amount of screwing into the connecting portion 21 in accordance with the distance between the separation device 10 and the core rocket C.

The movable body 12 is mounted on the cylinder 11 so as to be movable in the axial direction thereof, and is movable toward and away from the core rocket C. And the cylinder 11
The movable body 12 forms a pressure chamber 14 whose volume increases and decreases as the movable body 12 moves forward and backward.

The gas generating means 13 comprises a plurality of (12 in this embodiment) gas generators 24 containing a gas generating agent provided in a three-dimensional lattice-shaped holder 23. The gas generating means 13 is held in the pressure chamber 14 by fixing the flange 23 a provided on the holder 23 to the inside of the cylinder head 16 and connecting the cylinder head 16 to the main body 15. The ignition line 25 connected to each gas generator 13 is led out through a connector 26 provided at the center of the cylinder head 16 and connected to an ignition control device (not shown).

The separation apparatus 10 having the above-described structure is similar to that shown in FIG.
On the upper side of the booster rocket B shown in (a),
The cylinder 11 is fixed to a frame 27 provided inside the booster rocket B, and the cylinder 11 is fixed to a bracket 28 provided outside the booster rocket B on the lower side of the booster rocket B shown in FIG. I have. In a state where the booster rocket B is connected to the core rocket C by the braces 1, 2, and 3, FIG.
(B) As shown in the upper half of FIG.
1, the distal end of the pressing rod 22 which is the front end of the movable body 12 is in contact with the side surface of the core rocket C.

Note that, on the upper and lower sides of the booster rocket B, the pressing rod 22 of the upper separating device 10 is longer than that of the lower separating device 10 due to the difference in the mounting position of the separating device 10. Also, Core Rocket C
The contact portion of the pressing rod 22 is a portion reinforced by a conventionally known means for connecting the upper and lower braces 1 and 2.

In the separation device 10 of the booster rocket B having the above-described configuration, the tip of the pressing rod 22 which is the front end of the movable body 12 at the retracted position is merely brought into contact with the core rocket C. Until operation, no separating force is applied between the core rocket C and the booster rocket B. Therefore, there is no need to strengthen the structure in order to maintain the pressure accumulation state unlike the conventional separation device using a spring.

Then, the separation device 10 activates the gas generating means 13 when the combustion of the booster rocket B ends. That is, when the gas is generated in the pressure chamber 14 by igniting the gas generator 24 of the gas generating means 13, the movable body 12 moves forward as shown in the lower half of FIG. Become. At this time, when the connection by the braces 1, 2, and 3 is released, the separating device 10 in which the movable body 12 presses the core rocket C first.
Means that the booster rocket B is forcibly separated by the reaction force of the pressing. The movable body 12 that has moved
When the outwardly extending portion 19 comes into contact with the cushion member 18 of the inwardly extending portion 17 of the cylinder 11, the falling out is prevented.

As described above, in the separation apparatus 10, since gas is not injected to the outside, there is no need to provide heat-resistant means on the core rocket C side unlike the conventional separation apparatus using a separation motor. Further, since the core rocket C is directly pressed by the movable body 12, the core rocket C is not affected at all by the arrangement of the plurality of booster rockets. For example, the second booster rocket as shown in FIG. Also in the rocket provided with B2, there is no need to provide heat-resistant means in the core rocket C and the second booster rocket B2. Further, in the separation device 10 of the above embodiment, since the gas generating means 13 including the plurality of gas generators 24 is provided in the pressure chamber 14, the gas supply path between the cylinder 11 and the gas generating means 13 is unnecessary. Then, the structure becomes much simpler, and the storage property for the booster rocket B is good,
In addition, by changing the number of the gas generators 24, it is possible to easily cope with the adjustment of the generated pressure.

FIG. 4 is a graph showing the relationship between the stroke of the movable body 12 of the separating apparatus 10 having the structure of the above embodiment and the separating force. For comparison, data of a conventional separation device using a spring is also shown. FIG. 5 is a graph showing the relationship between the operation time of the separation device 10 having the configuration of the above embodiment and the separation force.

According to the graph of FIG.
It can be understood that a greater separation force can be obtained with the same stroke than that using a spring. 4 can be set by changing the length of the cylinder 11, and the separating force in FIG. 4 can be set by changing the diameter of the cylinder 11 and the movable body 12. Further, the separation force in FIG. 5 can increase or decrease the impulse by changing the initial volume of the pressure chamber 14.

The stroke of the movable body 12 and the pressure chamber 1
4 has an initial volume between the inwardly extending portion 17 of the cylinder 11 and the outwardly extending portion 19 of the movable body 12 or between the outwardly extending portion 19 of the movable body 12 and the cylinder head 16 in the axial direction of the cylinder 11. Can be changed by providing a spacer having a desired length, and in this case, various separation forces can be easily set using separation devices of the same size.

FIG. 6 is a view for explaining an embodiment of a booster rocket separating apparatus according to claim 3 of the present invention.
The same components as those in the previous embodiment are denoted by the same reference numerals, and detailed description is omitted.

The separation device 30 shown in FIG.
Gas generating means 13 having a plurality of gas generators 24, and airbag 3 deployed by the gas of gas generating means 13
1 is provided. The airbag 31 has a bag shape, and the entire periphery of the open end is the cylinder head 16 and the holder 23.
Is attached to the joint portion with the flange portion 23a to maintain airtightness with the cylinder head 16.

The above-mentioned booster rocket separation device 30
As shown in the lower half of FIG. 6 (b), the movable body 12 is moved by the deployment of the airbag 31, and the core rocket (FIG.
) And the reaction force separates the booster rocket.

In such a separation device 30, since the air-tightness against gas is ensured by the airbag 31 itself, for example, the air-tightness function between the cylinder 11 and the movable body 12 needs to be strict. In other words, even in an extreme case, reliable operation can be performed even if there is no airtight function between the cylinder 11 and the movable body 12, thereby further simplifying the structure and reducing the weight.

FIG. 7 is a view for explaining an embodiment of a booster rocket separating apparatus according to claim 6 of the present invention.

The separating device 40 shown in FIG. 7 (a) is mounted on the booster rocket B side with a cylinder 41 having an axis directed toward the core rocket C, and movably mounted on the cylinder 41 in the axial direction. It has a movable body 42 that can move forward and backward toward the core rocket C, forms a pressure chamber 44 whose volume increases and decreases with the movement of the movable body 42 between the cylinder 41 and the movable body 42, and supplies gas to the pressure chamber 44. Coupling means 43 for separating the core rocket C and the cylinder 41 in a separable manner.
It has.

The cylinder 41 is provided with an inner cylinder 45 having both open ends, and a bottomed cylindrical outer cylinder 46 having a bottom portion on the booster rocket B side. The inner cylinder 45 is provided with a liner 47 on the entire inside thereof, and a block 48 having a gas flow path 48a is fixed inside the end portion on the booster rocket B side, and is provided inside the end portion on the core rocket C side. A cylinder head 49 formed of a plurality of members and through which a movable body 42 described later penetrates is fixed.

A connecting member 51 attached to the booster rocket B via a connecting pin 50 is fitted to the outer end of the outer cylinder 45 on the booster rocket B side via a connecting pin 50 so as to be movable in the axial direction of the cylinder 41. The outer cylinder 45 and the connecting member 51 are connected by a turnbuckle 52. As a result, when the turnbuckle 52 is rotated, the outer cylinder 46 moves in the axial direction with respect to the connecting member 51, and adjustment according to the interval between the core rocket C and the booster rocket B is enabled.

Further, the outside of the cylinder 41 is covered with a case 53, and the block 4 is provided from the outside of the case 53.
A gas supply pipe 55 from a gas generating means is connected to a connector 54 reaching the gas flow path 48a of No. 8. In addition, a penetrating portion of the connector 54 in the connecting member 51 and the case 53 is formed as a long hole in the cylinder axis direction.
The movement of the side is not obstructed.

The movable body 42 has a structure in which a base end of a pressing rod 57 slidably passing through a cylinder head 49 is fixed to a piston 56 slidably accommodated in the cylinder 41 in the axial direction. doing. The piston 56 includes a sliding member 58 that comes into airtight contact with the inner peripheral surface of the liner 47 of the cylinder 41. Further, the pressing rod 57 is provided with a screw member 59 coaxially attached to the distal end thereof.
An abutment member 60 having a hemispherical tip is provided. The projecting position of the contact member 60 can be adjusted by changing the amount of screwing into the screw member 59.

The connecting means 43 includes a connecting member 63 attached to the connecting portion 61 of the core rocket C via a connecting pin 62.
It has. The coupling member 63 has a bottomed cylindrical shape and has a connecting portion 63b to the core rocket C at the center outside the bottom portion 63a. At the center inside the bottom portion 63a, the contacting portion which is the front end of the movable body 42 is provided. Recess 63c for receiving member 60
have. An annular block 65 provided with a linear pyrotechnic 64 over the entire circumference and a case 66 are mounted on the outer periphery of the side wall 63 d of the coupling member 63. An ignition line 67 such as a detonating wire for igniting the article 64 is connected.

The connecting means 43 connects the open end of the side wall 63d of the connecting member 63 to the outer cylinder 4 of the cylinder 41.
6, and the fitting portion is fixed by an appropriate means. When the booster rocket B is coupled to the core rocket C, the movable body 42 is at the retracted position with respect to the cylinder 41, and the contact member 60, which is the front end of the movable body 42, C
It is in a state of being in contact with and engaging with the concave portion 63c on the side.

That is, the separating device 40 is a device in which the connecting member 63 and the cylinder 41 are integrally connected by the connecting means 43, and the brace for connecting the core rocket C and the booster rocket B in a separable manner. The upper and lower braces 1 and 2 shown in FIG.
Used for 2.

When the combustion of the booster rocket B is completed, the separating device 40 supplies high-pressure gas from the gas generating means (not shown) to the pressure chamber via the gas supply pipe 55, the connector 54, and the gas flow path 48a of the block 48. 44, and the pressure is applied to the movable body 42 as shown in FIG.
To the state of being advanced to the core rocket C side. Further, following the supply of gas from the gas generating means, the linear pyrotechnics 64 of the connecting means 43 are ignited, so that the connecting members 63
Of the core rocket C and the booster rocket B are released by cutting the side wall 63d at the intermediate position indicated by the symbol S in FIG.

When the coupling of the booster rocket B is released in this manner, the separation device 40 in a state where the movable body 42 presses the core rocket C first forces the booster rocket B by the reaction force of the pressing. Finally, the contact member 60 of the movable body 42 is separated from the concave portion 63c of the coupling member 63, and the booster rocket B is completely separated.

In the booster rocket separating device 40 of the above embodiment, the same effects as those of the above embodiments can be obtained, and the core rocket C and the cylinder 41 are connected by the connecting means 43 which can be separated. , The cylinder 41 is used as a brace for connecting the booster rocket, or the separating device can be incorporated in the brace for connecting the booster rocket, so that the entire device including the connecting device of the booster rocket B can be reduced in size and weight.

[Brief description of the drawings]

FIG. 1 is a front view of one embodiment of a separation device for a booster rocket according to the first, second, fourth and fifth aspects of the present invention, in which one half of the separation device is omitted, before and after operation; FIG. 1B is a sectional view (b) showing the upper and lower parts and FIG. 1C is a sectional view taken along the line II in FIG.

FIG. 2 is a side view of a core rocket and a booster rocket with one side omitted.

3 is a sectional view taken along line II-II in FIG. 2 (a) and FIG.
FIG. 3 is a sectional view taken along line III-III in FIG.

FIG. 4 is a graph showing a relationship between a stroke of a movable body of the separation device shown in FIG. 1 and a separation force.

FIG. 5 is a graph showing a relationship between an operation time of the separation device shown in FIG. 1 and a separation force.

FIG. 6 is a front view of one embodiment of a separation device of a booster rocket according to a third embodiment of the present invention, in which one half of the separation device is omitted, and shows a state before and after operation in a vertical direction. FIG. 4C is a sectional view taken along line IV-IV in FIG.

FIG. 7 is a sectional view showing a state before operation (a) and a state after operation (b) in an embodiment of the separation device of the booster rocket according to claim 6 of the present invention.

FIG. 8 is a front view showing the direction of injection of combustion gas of the separation motor and the arrangement of booster rockets in a conventional separation apparatus using the separation motor.

[Explanation of symbols]

 B Booster rocket C Core rocket 10 30 40 Separation device 11 41 Cylinder 12 42 Movable body 13 Gas generating means 14 44 Pressure chamber 24 Gas generator 31 Airbag 43 Coupling means

Claims (6)

[Claims] An apparatus for separating a booster rocket coupled to a core rocket, wherein the booster rocket is mounted movably with respect to the cylinder and the cylinder, and moves by the pressure in the cylinder to press the core rocket. A booster rocket separation device comprising a movable body and gas generating means for supplying gas into a cylinder. 2. An apparatus for separating a booster rocket coupled to a core rocket, comprising: a cylinder having an axis oriented toward the core rocket; and a cylinder movably mounted in the cylinder along the axis thereof. A movable body that can advance and retreat toward the core rocket is provided, and a pressure chamber whose volume increases and decreases with the advance and retreat of the movable body between the cylinder and the movable body is formed, and a gas generating unit that supplies gas to the pressure chamber is provided. A booster rocket separation device wherein a movable body is set to a retracted position with respect to a cylinder and a front end of the movable body is brought into contact with the core rocket in a state where the booster rocket is coupled to the core rocket. 3. An air bag which is deployed in a pressure chamber by gas of a gas generating means.
A separation device for a booster rocket according to item 5. 4. The booster rocket separation device according to claim 2, wherein a gas generating means is provided in the pressure chamber. 5. The booster rocket separation device according to claim 4, wherein the gas generating means includes a plurality of gas generators. 6. The booster rocket separation device according to claim 1, wherein the core rocket and the cylinder are connected by a separable connection means.