JP3969606B2 - Booster rocket separator - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a booster rocket separation device used for separating a booster rocket that is separably coupled to a core rocket.
[0002]
[Prior art]
As a structure in which a booster rocket is coupled to a core rocket, for example, there is a structure described on page 462 of “Aerospace Engineering Handbook / Enhanced Edition” issued by Maruzen on April 25, 1983. In this structure, the core rocket and booster rocket are connected by upper and lower mounting brackets, and at the time of separation, the upper mounting bracket is released to cause the booster rocket to tilt by the action of dynamic pressure, thereby removing the lower mounting bracket. I was trying to dump the booster rocket.
[0003]
In recent years, booster rockets have been increased in size. However, as the size of the booster rocket increases, the separated booster rocket enters the plume (combustion gas flow) of the core rocket, causing vibration to the core rocket, or the tail of the booster rocket that has tilted the core rocket. There has been a risk of contact. Therefore, a separation device for forcibly separating the booster rocket has been developed. As a separation device for such a booster rocket, a device using a spring or a small separation motor equipped with a solid propellant was used. There was a thing.
[0004]
[Problems to be solved by the invention]
However, in the conventional booster rocket separation device as described above, in the separation device using the spring, it is necessary to maintain the pressure accumulation state of the spring by the time of separation, so the structure must be strengthened accordingly. As a result, there is a problem that the weight increases. Moreover, in the separation apparatus using the separation motor, as shown in FIG. 8, if the rocket has two booster rockets B1 and B1 on both sides of the core rocket C, the core rocket C is burned by the combustion gas of the separation motor. In order to protect against P, it is possible to arrange the separation motor so as to inject the combustion gas P obliquely while avoiding the core rocket C. However, as shown by the phantom lines in FIG. In a rocket equipped with the second booster rockets B2 and B2 that burn for a longer time at two locations 90 degrees different from the rockets B1 and B1, it is difficult to arrange to avoid the combustion gas P. Alternatively, the second booster rockets B2 and B2 need to be provided with heat-resistant means, which increases the weight.
[0005]
OBJECT OF THE INVENTION
The present invention has been made paying attention to the above-described conventional problems, and it is not necessary to reinforce the structure in order to maintain the pressure accumulation state unlike the separation device using a spring, and the separation motor is used. Separation of booster rockets that can achieve a large separation force and achieve weight reduction, etc., without being affected by the arrangement of booster rockets as in the case of separation devices or providing heat-resistant means on core rockets etc. The object is to provide a device.
[0006]
[Means for Solving the Problems]
A separator for a booster rocket according to the present invention is, as claimed in claim 1, an apparatus for separating a booster rocket coupled to a core rocket. Arranged the axis line toward the core rocket Cylinder and cylinder In its axial direction A movable body that is movably mounted and moves by pressure in the cylinder to press the core rocket, and in the cylinder To move the movable body to the core rocket side According to a second aspect of the present invention, there is provided an apparatus for separating a booster rocket coupled to a core rocket, the cylinder having an axis lined toward the core rocket, and a cylinder. A movable body that is mounted so as to be movable in the axial direction thereof and is movable back and forth toward the core rocket, and forms a pressure chamber whose volume increases and decreases between the cylinder and the movable body as the movable body advances and retreats, and With gas generating means for supplying gas to the pressure chamber, with the booster rocket coupled to the core rocket, the movable body is set in the retracted position with respect to the cylinder, and the front end of the movable body is brought into contact with the core rocket. According to a third aspect of the present invention, the pressure chamber is provided with an airbag that is deployed by the gas of the gas generating means. A structure having a gas generating means, as claimed in claim 5, the gas generating means, a structure comprising a plurality of gas generator, as claimed in claim 6, core rocket and cylinder And the end of the core rocket side Are combined by separable connecting means, and the above structure is a means for solving the problems.
[0007]
[Effects of the Invention]
The booster rocket separation device according to claim 1 of the present invention is provided in the booster rocket so as not to remain as unnecessary weight on the core rocket side after operation, and has a configuration including a cylinder, a movable body, and a gas generating means. Until separation, no separation force is applied between the core rocket and the booster rocket. Further, in the separation device, when the high-pressure gas is supplied into the cylinder by the gas generating means when releasing the coupling between the core rocket and the booster rocket without performing gas injection to the outside, the movable body is moved by the gas pressure. It moves and presses the core rocket, and the booster rocket is separated from the core rocket by the reaction force.
[0008]
In the booster rocket separation device according to claim 2 of the present invention, as in claim 1, the booster rocket is provided on the booster rocket so as not to remain as an unnecessary weight on the core rocket side after the operation. Since the generating means is provided and the front end of the movable body in the retracted position is merely brought into contact with the core rocket, no separation force is applied between the core rocket and the booster rocket until the operation. Further, in the separation apparatus, when gas is not supplied to the outside, and when the coupling between the core rocket and the booster rocket is released, if high pressure gas is supplied to the pressure chamber in the cylinder by the gas generating means, The movable body moves forward and presses the core rocket, and the booster rocket is separated from the core rocket by the reaction force.
[0009]
In the booster rocket separation device according to claim 3 of the present invention, the pressure chamber is provided with an airbag that is deployed by the gas of the gas generating means. The movable body is moved by deployment and the core rocket is pressed.
[0010]
In the booster rocket separation device according to claim 4 of the present invention, the gas generating means is provided in the pressure chamber, so that a gas supply path between the cylinder and the gas generating means becomes unnecessary.
[0011]
In the booster rocket separation apparatus according to claim 5 of the present invention, since the gas generating means includes a plurality of gas generators, it is possible to change the number of gas generators and cope with the adjustment of the generated pressure. Can do.
[0012]
In the booster rocket separation device according to claim 6 of the present invention, a core rocket and a cylinder are provided. And the end of the core rocket side Can be used as a brace for booster rocket coupling, or the separation device can be incorporated into the coupling brace, and the coupling means can be released. At the same time, the booster rocket will be separated.
[0013]
【The invention's effect】
According to the booster rocket separation apparatus according to claim 1 of the present invention, by adopting the cylinder, the movable body, and the gas generating means, any separation force is applied between the core rocket and the booster rocket until the separation. As the conventional separation device using a spring does not need to be strengthened in order to maintain the pressure accumulation state, and since no gas is injected to the outside, a separation motor is used. There is no need to provide heat-resistant means on the core rocket or the like as in the conventional separation device, and a significant reduction in weight can be realized as compared with these conventional devices. In addition, since gas is not injected to the outside, it is not affected by the placement of the booster rocket as in the separation device using the separation motor, and the movable body is securely placed toward the core rocket. In addition, the cost can be reduced as compared with a separation apparatus using a separation motor. In addition, the adoption of the cylinder, movable body, and gas generation means can simplify the structure, and it is easy to adjust and maintain the separation force. Can be obtained.
[0014]
According to the booster rocket separating apparatus according to claim 2 of the present invention, as in claim 1, by adopting the cylinder, the movable body, and the gas generating means, the core rocket and the booster rocket are separated until the time of separation. Since no separation force is applied in the meantime, there is no need to strengthen the structure in order to maintain the pressure accumulation state as in the conventional separation device using a spring, and gas injection to the outside is not performed. Unlike conventional separators that use a motor for separation, there is no need to depend on booster rocket placement or to provide heat-resistant means for core rockets, etc. In addition, the cost can be reduced as compared with a separation apparatus using a separation motor. In addition, the adoption of the cylinder, movable body, and gas generation means can simplify the structure, and it is easy to adjust and maintain the separation force. Can be obtained.
[0015]
According to the booster rocket separation apparatus of the third aspect of the present invention, the same effect as in the second aspect can be obtained, and the airbag that deploys with the gas of the gas generating means is provided in the pressure chamber. In addition, the air bag itself can ensure gas tightness, so that a reliable operation can be obtained without making the air tight function of the pressure chamber so strict, and the structure can be further simplified and lightened. be able to.
[0016]
According to the booster rocket separation device of the fourth aspect of the present invention, the same effect as in the second and third aspects can be obtained and the gas generating means is provided in the pressure chamber. The gas supply path between the means is not required, the structure is further simplified, further reduction in size and weight can be realized, and the storage capacity for the booster rocket is also improved.
[0017]
According to the booster rocket separation apparatus according to claim 5 of the present invention, the same effect as in claim 4 can be obtained, and the gas generating means including a plurality of gas generators is employed. The generated pressure can be easily adjusted by changing the number of gas generators.
[0018]
According to the booster rocket separating apparatus according to claim 6 of the present invention, the same effects as in claims 1 to 5 can be obtained, and the core rocket and cylinder And the end of the core rocket side Can be used as a brace for booster rocket coupling, or the separation device can be incorporated in the coupling brace, and the entire range of the booster rocket coupling device can be incorporated. It can contribute to miniaturization and weight reduction.
[0019]
【Example】
1 to 3 show the main Clearly It is a figure explaining one Example of the separation apparatus of the related booster rocket.
[0020]
The booster rocket B shown in FIG. 2 and FIG. 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 is attached to two places different from the core rocket C by 180 degrees.
[0021]
The booster rocket B is coupled to the core rocket C by two upper braces 1, 1 and two lower braces 2, 2 provided on both upper and lower sides and two long braces 3, respectively. The booster rocket B is provided with upper and lower connectors 4 and 5 for connecting braces, and the core rocket C is provided with upper and lower connectors 6 and 7 for connecting braces. It is. 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.
[0022]
Each brace 1, 2, 3 can be separated by pyrotechnics at the upper and lower connectors 6, 7 on the core rocket C side or in the vicinity thereof. It is coupled to the core rocket C, and the thrust of the booster rocket B is transmitted to the core rocket C side.
[0023]
The separator 10 for the booster rocket B is arranged in the center of the booster rocket B on the upper side shown in FIG. 3A, and the lower braces 2, 2 on the lower side shown in FIG. It is arranged in two places inside.
[0024]
The separation device 10 is provided on the booster rocket B side so that it does not remain as unnecessary weight on the core rocket C side after operation, and is movable relative to the cylinder 11 and the cylinder 11 as shown in FIG. And a movable body 12 that moves by pressure in the cylinder 11 and presses the core rocket C, and a gas generation means 13 that supplies gas into the cylinder 11. In this embodiment, the movable body 12 is movable with the cylinder 11. Gas generating means 13 is provided in a pressure chamber 14 formed between the body 12.
[0025]
The cylinder 11 is arranged with its axis facing the core rocket C side on the left side of FIG. The cylinder 11 includes a cylindrical main body portion 15 and a cylinder head 16 that closes the anti-core rocket C side of the main body portion 15 and has a bottomed cylindrical shape opened to the core rocket C side. Further, the cylinder 11 has an inwardly projecting portion 17 on the inner side of the open end portion of the main body portion 15 over the circumferential direction, and a movable body 12 to be described later is formed on a step portion formed by the inwardly projecting portion 17. Is provided with a ring-shaped cushioning material 18 that comes into contact.
[0026]
The movable body 12 has a bottomed cylindrical shape having a diameter slightly smaller than that of the cylinder 11, and an outward projecting portion 19 slidably fitted inside the cylinder 11 at the open end thereof in the circumferential direction. Has over. An O-ring 20 is mounted on the outer peripheral portion of the outward projecting portion 19 to ensure airtightness between the inner surface of the cylinder 11 and the outward projecting portion 19. A cylindrical connecting portion 21 having a female screw hole is integrally provided at the center of the outer surface of the bottom of the movable body 12, and the connecting rod 21 has a pressing rod whose tip is in contact with the core rocket C. The base end portion of 22 is screwed. The pressing rod 22 can adjust the amount of screwing into the connecting portion 21 according to the distance between the separation device 10 and the core rocket C.
[0027]
The movable body 12 is attached to the cylinder 11 so as to be movable in the axial direction, and is movable toward and away from the core rocket C. The cylinder 11 and the movable body 12 form a pressure chamber 14 between which the volume increases and decreases as the movable body 12 advances and retreats.
[0028]
The gas generating means 13 includes a three-dimensional lattice-like holder 23 provided with a plurality of gas generators 24 (12 in this embodiment) containing a gas generating agent. The gas generating means 13 is held in the pressure chamber 14 by fixing the flange portion 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 portion 15. The ignition line 25 connected to each gas generator 13 is led out through a connector 26 provided in the center of the cylinder head 16 and connected to an ignition control device (not shown).
[0029]
In the separating apparatus 10 having the above configuration, the cylinder 11 is fixed to a frame 27 provided inside the booster rocket B on the upper side of the booster rocket B shown in FIG. On the lower side of the booster rocket B, the cylinder 11 is fixed to a bracket 28 provided outside the booster rocket B. Then, in a state where the booster rocket B is coupled to the core rocket C by the braces 1, 2 and 3, the movable body 12 is set to the retracted position with respect to the cylinder 11 as shown in the upper half of FIG. And the front-end | tip part of the rod 22 for a press used as the front-end part of the movable body 12 is made to contact | abut to the side surface of the core rocket C. FIG.
[0030]
Note that, on the upper side and the lower side of the booster rocket B, the pressing rod 22 of the upper separating device 10 is longer than the lower one due to the difference in the mounting position of the separating device 10. Further, the abutting portion of the pressing rod 22 in the core rocket C is a portion reinforced by a conventionally known means for connecting the upper and lower braces 1 and 2.
[0031]
The booster rocket B separating device 10 having the above-described configuration is merely in contact with the core rocket C at the front end of the pressing rod 22, which is the front end of the movable body 12 in the retracted position. In the meantime, no separation force is applied between the core rocket C and the booster rocket B. Therefore, there is no need to reinforce the structure in order to maintain the pressure accumulation state as in the conventional separation device using a spring.
[0032]
And the separator 10 operates the gas generation means 13 with the completion | finish of combustion of the booster rocket B. FIG. That is, when 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 coupling by the braces 1, 2, and 3 is released, the separating device 10 that has previously pressed the core rocket C with the movable body 12 forces the booster rocket B by the reaction force of the pressing. Will be separated. The movable body 12 that has moved is prevented from falling off when the outwardly projecting portion 19 abuts against the cushion material 18 of the inwardly projecting portion 17 of the cylinder 11.
[0033]
Thus, since the separation apparatus 10 does not perform gas injection to the outside, it is not necessary to provide heat-resistant means on the core rocket C side as in the conventional separation apparatus using a separation motor. Since the core rocket C is directly pressed by the movable body 12, there is no influence on the arrangement of the plurality of booster rockets. For example, a second booster rocket B2 as shown in FIG. Even in the case of the rocket, it is not necessary to provide heat-resistant means for the core rocket C or the second booster rocket B2. Further, in the separation apparatus 10 of the above embodiment, since the gas generation means 13 including the plurality of gas generators 24 is provided in the pressure chamber 14, a gas supply path between the cylinder 11 and the gas generation means 13 is unnecessary. Thus, the structure is further simplified, the storage property to the booster rocket B is good, and the adjustment of the generated pressure can be easily handled by changing the number of the gas generators 24.
[0034]
FIG. 4 is a graph showing the relationship between the stroke of the movable body 12 and the separating force of the separating apparatus 10 having the configuration of the above embodiment. For comparison, data of a conventional separation device using a spring is also shown. FIG. 5 is a graph showing the relationship between the operating time and the separating force of the separating apparatus 10 having the configuration of the above embodiment.
[0035]
According to the graph of FIG. 4, it can be understood that the separation device 10 can obtain a clearly large separation force with the same stroke as compared with the one using a spring. 4 can be set by changing the length of the cylinder 11, and the separating force of FIG. 4 can be set by changing the diameters of the cylinder 11 and the movable body 12. Furthermore, the impulse of the separation force shown in FIG. 5 can be increased or decreased by changing the initial volume of the pressure chamber 14.
[0036]
The stroke of the movable body 12 and the initial volume of the pressure chamber 14 are determined between the inwardly projecting portion 17 of the cylinder 11 and the outwardly projecting portion 19 of the movable body 12 or the outwardly projecting portion 19 of the movable body 12 and the cylinder head. 16 can be changed by providing a spacer having a desired length in the axial direction of the cylinder 11. In this way, various separation forces can be easily obtained using a separation device of the same size. Can be set.
[0037]
Figure 6 shows the Clearly Related to the booster rocket separation device other It is a figure explaining an Example. Note that the same components as those in the previous embodiment are denoted by the same reference numerals and detailed description thereof is omitted.
[0038]
The illustrated separation device 30 includes in the pressure chamber 14 a gas generating means 13 having a plurality of gas generators 24 and an airbag 31 that is deployed by the gas of the gas generating means 13. The airbag 31 has a bag shape, and the entire circumference of the open end portion is attached to a joint portion between the cylinder head 16 and the flange portion 23 a of the holder 23, and the air tightness between the cylinder head 16 and the airbag 31 is ensured. keeping.
[0039]
The above-described booster rocket separation device 30 moves the movable body 12 as shown in the lower half of FIG. 6B by deploying the airbag 31 to press the core rocket (see FIG. 2). Separate the booster rocket.
[0040]
In such a separation device 30, the air bag 31 itself secures gas tightness, so that, for example, it is not necessary to tighten the airtight function between the cylinder 11 and the movable body 12. In other words, even if there is no airtight function between the cylinder 11 and the movable body 12, a reliable operation can be performed, thereby further simplifying the structure and reducing the weight.
[0041]
FIG. 7 shows a booster rocket separation apparatus according to the present invention. Yet another It is a figure explaining an Example.
[0042]
The separator 40 shown in FIG. 7A is provided on the booster rocket B side with a cylinder 41 having an axis lined toward the core rocket C, and mounted on the cylinder 41 so as to be movable in the axial direction. Pressure chamber whose volume increases and decreases as the movable body 42 advances and retreats between the cylinder 41 and the movable body 42. 43 Forming a pressure chamber 43 A gas generating means (not shown) for supplying gas to the cylinder, and a coupling means for detachably coupling the core rocket C and the cylinder 41 44 It has.
[0043]
The cylinder 41 includes an inner cylinder 45 whose both ends are open and a bottomed cylindrical outer cylinder 46 whose bottom is the booster rocket B side. The inner cylinder 45 is provided with a liner 47 on the entire inner side thereof, and a block 48 having a gas flow path 48a is fixed inside the end portion on the booster rocket B side, and the core rocket C side. of A cylinder head 49 formed of a plurality of members and in which a movable body 42 described later is in a penetrating state is fixed inside the end portion.
[0044]
The cylinder 41 has a connecting member 51 attached to the booster rocket B via a connecting pin 50 on the outer side of the outer cylinder 45 on the booster rocket B side so as to be movable in the axial direction of the cylinder 41. Yes, the outer cylinder 45 and the connecting member 51 are connected by a turnbuckle 52. Thereby, when the turnbuckle 52 is rotated, the outer cylinder 46 side 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.
[0045]
Further, the cylinder 41 is covered with a case 53 on the outside, and a gas supply pipe 55 from the gas generating means is connected to a connector 54 extending from the outside of the case 53 to the gas flow path 48a of the block 48. In addition, the penetration part of the connector 54 in the connecting member 51 or the case 53 is a hole that is long in the cylinder axial direction, so that the movement on the outer cylinder 46 side is not hindered.
[0046]
The movable body 42 has a structure in which a base end portion of a pressing rod 57 that slidably penetrates the cylinder head 49 is fixed to a piston 56 that is slidably accommodated in the axial direction in the cylinder 41. . The piston 56 includes a sliding member 58 that hermetically contacts the inner peripheral surface of the liner 47 of the cylinder 41. The pressing rod 57 is provided with a contact member 60 having a hemispherical tip through a screw member 59 attached coaxially at the tip. The projecting position of the contact member 60 can be adjusted by changing the screwing amount with respect to the screw member 59.
[0047]
Coupling means 44 Includes a coupling member 63 attached to a coupling portion 61 on the core rocket C side via a coupling pin 62. The coupling member 63 has a bottomed cylindrical shape and has a connecting portion 63b to the core rocket C at the center of the bottom 63a, and a contact portion 63b that is the front end of the movable body 42 at the center of the bottom 63a. A recess 63c for receiving the member 60 is provided. An annular block 65 provided with a linear pyrotechnic 64 over the entire circumference and a case 66 are attached to the outer periphery of the side wall 63d of the coupling member 63. The annular block 65 has a linear pyrotechnic. An ignition line 67 such as an explosion line for igniting the product 64 is connected.
[0048]
The above coupling means 44 In the coupling member 63, the open end of the side wall 63d is fitted to the outside of the end of the outer cylinder 46 of the cylinder 41, and the fitting portion is fixed by appropriate means. In the separation device 40, in a state where the booster rocket B is coupled to the core rocket C, the movable body 42 is in the retracted position with respect to the cylinder 41, and the contact member 60 which is the front end portion of the movable body 42 is the core rocket. It is in a state of being in contact with and engaging with the recess 63c on the C side.
[0049]
That is, the separation device 40 described above is a coupling means. 44 Thus, the coupling member 63 and the cylinder 41 are integrally coupled to each other, and also serves as a brace that separably couples the core rocket C and the booster rocket B. For example, the upper and lower portions shown in FIG. Used for braces 1 and 2.
[0050]
When the booster rocket B is combusted, the separation device 40 sends 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 48 a of the block 48. 43 The movable body 42 is advanced to the core rocket C side by the pressure as shown in FIG. In addition, following the supply of gas from the gas generating means, the coupling means 44 By igniting the linear pyrotechnic 64, the side wall 63d of the coupling member 63 is cut at an intermediate position indicated by symbol S in FIG. 7A, and the coupling between the core rocket C and the booster rocket B is released. .
[0051]
When the coupling of the booster rocket B is released in this way, the separating device 40 that has previously pressed the core rocket C with the movable body 42 forcibly separates the booster rocket B by the reaction force of the pressing. Finally, the contact member 60 of the movable body 42 is detached from the concave portion 63c of the coupling member 63, and the booster rocket B is completely separated.
[0052]
In the booster rocket separation device 40 of the above embodiment, the same effects as those of the previous embodiments can be obtained, and the core rocket C and the cylinder 41 are coupled by the separable coupling means 43. Is used as a brace for coupling a booster rocket, or the separation device can be incorporated into a brace for coupling, and the entire apparatus extending to the coupling device for the booster rocket B becomes small and light.
[Brief description of the drawings]
[Figure 1] Main departure Clearly In one embodiment of the booster rocket separating apparatus, a front view (a) in which one half of the separating apparatus is omitted, a cross-sectional view (b) in which the state before and after operation is divided into upper and lower parts, and a half on one side are omitted. It is the II sectional view taken on the line 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 a sectional view taken along line III-III in FIG.
4 is a graph showing the relationship between the stroke of the movable body and the separating force of the separating apparatus shown in FIG. 1;
FIG. 5 is a graph showing the relationship between the operating time of the separating apparatus shown in FIG. 1 and the separating force.
FIG. 6 shows a booster rocket separation apparatus according to the present invention. other In the embodiment, a front view (a) in which one half of the separation device is omitted, a cross-sectional view (b) showing the state before and after operation divided into upper and lower parts, and a line IV-IV in FIG. It is sectional drawing (c).
[Figure 7] Main departure Clearly Related to the booster rocket separation device Yet another In an Example, it is each sectional drawing which shows the state (a) before an operation | movement, and the state (b) after an operation | movement.
FIG. 8 is a front view showing the combustion gas injection direction of the separation motor and the arrangement of the booster rocket in the 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 43 Pressure chamber
24 Gas generator
31 airbag
44 Coupling means

Claims (6)

A device for separating a booster rocket coupled to a core rocket, wherein the booster rocket is mounted on the booster rocket with an axis lined toward the core rocket, and is movably mounted in the axial direction with respect to the cylinder. A booster rocket separation device comprising: a movable body that moves and presses a core rocket; and a gas generating means that supplies gas for moving the movable body toward the core rocket in a cylinder.   A device that separates a booster rocket coupled to a core rocket. The cylinder is arranged on the booster rocket with its axis lined toward the core rocket, and is attached to the cylinder so as to be movable in the axial direction. A movable body that can move forward and backward is formed, and a pressure chamber whose volume increases and decreases between the cylinder and the movable body as the movable body advances and retreats, and gas generating means that supplies gas to the pressure chamber is provided. A booster rocket separation device, wherein the movable body is set in a retracted position with respect to the cylinder in a state where the booster rocket is coupled, and the front end of the movable body is brought into contact with the core rocket.   3. The booster rocket separation device according to claim 2, further comprising an air bag deployed in the pressure chamber by the gas of the gas generating means.   4. The booster rocket separation apparatus according to claim 2, further comprising gas generating means in the pressure chamber.   5. The booster rocket separation apparatus according to claim 4, wherein the gas generating means includes a plurality of gas generators. Booster rocket separation device according to any one of claims 1 to 5, an end portion of the core rocket and the core rocket side of the cylinder, characterized in that coupled with separable coupling means.

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