JP6586018B2 - Rocket coupling and separation mechanism - Google Patents

Description

  The present invention relates to a rocket connection / separation mechanism for connecting and separating a rocket upper structure and a lower structure from each other.

  The rocket is composed of a plurality of stages that can be separated vertically. Each stage is provided with a rocket propulsion system. In order from the lower stage, the rocket propulsion system ejects the combustion gas downward by the combustion of fuel. The rocket propulsion system at each stage is separated from the rocket structure on the upper stage side when the fuel is used up. In this way, the use of the rocket propulsion system is repeated and the rocket is lifted from the ground to space.

  In order to separate the rocket structure, the rocket is provided with a connection and separation mechanism. In FIG. 1, (A) shows the entire rocket, and (B) is an enlarged cross-sectional view of a portion surrounded by a broken line X in (A), showing a conventional connection and separation mechanism.

  The connection / separation mechanism shown in FIG. 1B connects the upper structure 51 and the lower structure 52 so as to be separable from each other. The connection / separation mechanism includes flanges 53, 54 provided on the outer shell 51a of the upper structure 51 and the outer shell 52a of the lower structure 52, a metal band 55 that connects the flanges 53, 54, and the upper and lower stages. And a spring 56 disposed between the structures 51 and 52. At the time of separation, the metal band 55 is divided using, for example, a pyrotechnic (not shown). At this time, the lower structure 52 is pushed out of the upper structure 51 by the spring 56. Such a connection / separation mechanism is described, for example, in Non-Patent Document 1 below.

Junjiro Odano, Kenji Sugisugi, “Structure and Mechanism of MV Type Rocket”, Report, Special Issue, No. 47, March 2003

By the way, there is a possibility that the outer shell 52a of the separated lower structure 52 collides with the nozzle 57a (see FIG. 1) of the upper rocket propulsion system 57. This collision occurs as in the following (A) or (B).
(A) The above-described springs 56 are provided at a plurality of locations in the circumferential direction of the rocket. If there is variation in the force of these springs 56, the above-described collision may occur.
(B) At the time of separation, there may be a rotational moment of the rocket (a moment around an axis that intersects the central axis of the rocket). Due to this rotational moment, the above-mentioned collision may occur.

  There is a possibility that the nozzle 57a is damaged by the collision between the outer shell 52a of the lower structure 52 and the nozzle 57a during the separation.

  Accordingly, an object of the present invention is to provide a rocket connection / separation mechanism that can prevent damage to the nozzle due to collision between the outer shell of the separated lower structure and the nozzle in the rocket.

In order to achieve the above-mentioned object, according to the present invention, a rocket connection / separation mechanism for connecting and separating an upper stage structure and a lower stage structure from each other,
The upper stage structure includes an upper stage outer shell extending around the central axis of the rocket, and a rocket propulsion system disposed inside the upper stage outer shell, the rocket propulsion system being lower than the upper stage outer shell. Has a nozzle protruding into the
The lower-stage structure includes a lower-stage outer shell extending in a circumferential direction around the central axis, and the nozzle is located inside the lower-stage outer shell,
The rocket coupling and separation mechanism
A protective member connected to the lower end of the upper outer shell and positioned between the nozzle and the lower outer shell in the width direction orthogonal to the circumferential direction;
A connecting member operable from a connecting position for connecting the protective member to the lower outer shell to a releasing position for releasing the connection;
A connection release device for moving the connection member from a connection position to a release position,
The protective member extends in the circumferential direction so as to surround the nozzle, and is composed of a plurality of divided pieces separated from or in contact with each other in the circumferential direction,
Each divided piece is connected to the upper outer shell by engaging the upper end of each divided piece with the lower end of the upper outer shell in the axial direction of the rocket,
A rocket connection / separation mechanism is provided in which the lower outer shell is connected to the upper outer shell via the protective member.

  According to the present invention described above, the lower outer shell is connected to the upper outer shell via the protective member. Therefore, when the connection release device releases the connection between the protection member and the lower outer shell by the connection member, the lower outer shell is separated from the protection member and the upper outer shell. At this time, the collision of the lower outer shell with the nozzle is prevented by a protective member positioned between the lower outer shell and the nozzle in the width direction.

A conventional rocket and its coupling and separation mechanism are shown. 1 shows a rocket to which the present invention is applicable. 3 shows a rocket connection and separation mechanism according to an embodiment of the present invention. FIG. 4 is a view taken along arrows IV-IV in FIG. 2 and FIG. FIG. 3 shows a state when the lower structure is separated. The vicinity of the connecting portion between the upper side structure and the lower side structure is shown. The state which isolate | separated the lower stage side structure is shown. The other structural example 1 of a connection member and a connection release apparatus is shown. Another structural example 2 of a connection member and a connection cancellation | release apparatus is shown.

  Embodiments of the present invention will be described with reference to the drawings. In addition, the same code | symbol is attached | subjected to the common part in each figure, and the overlapping description is abbreviate | omitted.

  FIG. 2 shows a rocket 1 to which the present invention is applicable. The rocket 1 includes a plurality of structural bodies 3A, 3B, 3C that can be separated vertically. A rocket propulsion system 5 is provided in each stage of the structures 3A, 3B, 3C. In the uppermost structure 3A, for example, a satellite 6 is provided above the rocket propulsion system 5. In this case, in the uppermost structure 3A, the rocket propulsion system 5 and the satellite 6 are separable from each other.

  FIG. 3 is an enlarged view of a portion surrounded by a broken line X in FIG. FIG. 3 shows a rocket connection and separation mechanism 10 according to an embodiment of the present invention. The rocket connection / separation mechanism 10 is for connecting and separating the upper stage structure 3B and the lower stage structure 3C of the rocket 1 from each other.

  As shown in FIG. 3, the upper stage structure 3 </ b> B includes an upper stage outer shell 7 and a rocket propulsion system 5. The upper outer shell 7 extends in a circumferential direction (hereinafter simply referred to as a circumferential direction) around the central axis of the rocket 1. The upper outer shell 7 may be cylindrical. The rocket propulsion system 5 is disposed inside the upper stage outer shell 7. The rocket propulsion system 5 has a nozzle 5a that projects downward from the upper stage outer shell 7 (the lower end thereof). The rocket propulsion system 5 generates combustion gas by burning fuel, and jets the combustion gas downward from the nozzle 5a. Thereby, thrust is given to the rocket 1.

  The lower stage structure 3 </ b> C includes a lower stage outer shell 9. The lower outer shell 9 extends in the circumferential direction. Near the upper end of the lower outer shell 9, the nozzle 5a of the rocket propulsion system 5 of the upper structure 3B is located inside the upper end of the lower outer shell 9.

  The rocket connection / separation mechanism 10 includes a protection member 11, a connection member 13, and a connection release device 15.

  The protection member 11 is connected to the lower end portion 7 a of the upper stage outer shell 7. The protection member 11 extends downward from the lower end portion 7a in the axial direction of the rocket 1 (hereinafter simply referred to as the axial direction). The protection member 11 is positioned between the nozzle 5a of the upper structure 3B and the lower outer shell 9 in the width direction orthogonal to the circumferential direction (in this embodiment, the radial direction of the rocket 1) (hereinafter referred to as the rocket 1). Is simply referred to as the radial direction). The protection member 11 extends in the circumferential direction so as to surround the nozzle 5a. In the present embodiment, the protection member 11 is cylindrical.

  FIG. 4 is a view taken along arrows IV-IV in FIGS. 2 and 3 and shows the entire cross section of the rocket 1. As shown in FIG. 4, the protection member 11 includes a plurality of divided pieces 11 </ b> A that are adjacent to each other in the circumferential direction. Here, the protection member 11 should just be comprised from 2 or more (preferably 3 or more) division | segmentation piece 11A. In FIG. 4, illustrations other than the protective member 11, the sliding guide portion 17 described later, the lower outer shell 9 and the nozzle 5a are omitted. FIG. 3 illustrates only one divided piece 11A among the plurality of divided pieces 11A, but the other divided pieces 11A have the same configuration as the divided piece 11A of FIG.

  Each divided piece 11 </ b> A is connected to the upper stage side outer shell 7 by engaging the upper end part of each divided piece 11 </ b> A with the lower end part 7 a of the upper stage side outer shell 7 in the axial direction. For this purpose, a recess 7b is formed on the inner peripheral surface of the lower end 7a of the upper outer shell 7. On the other hand, a fitting portion 11a protruding outward in the radial direction is formed at the upper end portion of each divided piece 11A. When the fitting portion 11a is fitted into the recess 7b, the protective member 11 is engaged with the lower end portion 7a in the axial direction.

  When each divided piece 11A tries to move inward in the radial direction in FIG. 4, the divided pieces 11 </ b> A are caught with each other so that the fitting portion 11 a does not come out of the recess 7 b. For example, the circumferential dimension of the outer peripheral edge of each divided piece 11A (referred to as target divided piece 11A) is the circumference of the inner peripheral edge of two divided pieces 11A (referred to as adjacent divided pieces 11A) located on both sides in the circumferential direction of this divided piece 11A. Greater than directional spacing. Accordingly, the target divided piece 11A cannot pass the circumferential interval of the adjacent divided pieces 11A radially inward.

In addition, the assembly to the state of FIG. 3 and FIG. 4 is performed as follows, for example. First, the upper outer shell 7 is divided into a plurality of divided pieces in the circumferential direction like the protective member 11. The cylindrical protection member 11 is configured by assembling a plurality of divided pieces 11A. Next, the plurality of divided pieces of the upper outer shell 7 are assembled to the protection member 11. Thereby, it is made into the state (state of FIG. 3 and FIG. 4) in which the fitting part 11a of each division | segmentation piece 11A of the cylindrical protection member 11 was inserted in the hollow 7b of the cylindrical upper stage side outer shell 7. FIG. it can.
Moreover, you may assemble as follows. The upper outer shell 7 does not have to be divided. A plurality of divided pieces 11A assembled in a cylindrical shape are temporarily fixed loosely to each other by appropriate means (for example, a wire) so that the cylindrical shape is maintained to some extent. Next, the plurality of divided pieces 11 </ b> A are assembled to the upper outer shell 7. That is, the fitting portions 11 a of the plurality of divided pieces 11 </ b> A are inserted into the recesses 7 b of the upper stage outer shell 7. At this time, since the circumferential end surfaces of the plurality of divided pieces 11A are hooked, the divided pieces 11A may be bent with a strong force so that the insertion is possible. Next, the temporary fixing is released.

  In order to facilitate assembly, the lower outer shell 9 may be divided into an upper portion and a lower portion in the vicinity of the annular gas seal portion 19 in FIG. 3 in the axial direction. In this case, after the upper outer shell 7 and the protective member 11 are assembled together, the upper portion of the lower outer shell 9 is connected to the protective member 11 by the connecting member 13. Next, the upper part and the lower part of the lower outer shell 9 are joined together.

  The strength of the protection member 11 may be low as follows. The lower structure 3C is connected to the upper structure 3B via the protective member 11. On the other hand, the annular upper end surface 9 a of the lower outer shell 9 is in contact with the annular lower end surface 7 c of the upper outer shell 7. Accordingly, when the thrust of the rocket 1 is generated by the rocket propulsion system 5 of the lower structure 3C, this thrust is generated from the annular upper end surface 9a of the lower outer shell 9 to the annular lower end surface of the upper outer shell 7. Directly transmit to 7c. Therefore, the protection member 11 comes off the thrust transmission path. Therefore, the protection member 11 does not have to have the strength necessary for transmitting the thrust from the lower stage structure 3C to the upper stage structure 3B.

  The protection member 11 is preferably formed of a lightweight material. For example, it may be formed of a material that is lighter (that is, has a lower density) than the material that forms the upper-stage outer shell 7 and the lower-stage outer shell 9.

The connecting member 13 is provided for each divided piece 11A. Each connecting member 13 connects the divided piece 11 </ b> A to the lower outer shell 9. The connection member 13 is operable between a connection position where the protection member 11 is connected to the lower outer shell 9 and a release position where this connection is released.
In the present embodiment, the connecting member 13 is attached to the divided piece 11A so as to be movable in the radial direction with respect to the divided piece 11A. That is, the connecting member 13 is fitted to the divided piece 11A so as to be movable in the radial direction. In the example of FIG. 3, the split piece 11A is formed with a through hole 11b in the radial direction, and the connecting member 13 is fitted in the through hole 11b. The connecting member 13 may be fitted to the lower end portion of the split piece 11A by an appropriate means so as to be movable in the radial direction.

An engagement hole 9 b is formed on the inner peripheral surface of the lower outer shell 9. In a state where the connecting member 13 is in the connecting position, the tip end portion of the connecting member 13 is inserted into the engagement hole 9b. Accordingly, the lower-stage outer shell 9 (that is, the lower-stage structure 3C) is connected to the upper-stage outer shell 7 (that is, the upper-stage structure 3B) via the protection member 11. The connecting member 13 is preferably a pin-shaped member.
Since each divided piece 11A is engaged with the upper stage outer shell 7 in the axial direction as described above, the upper stage structure 3B and the lower stage structure 3C are sufficiently connected to each other via the protective member 11. It is connected with the binding force.

  The connecting elastic member 14 is provided for each divided piece 11A. The elastic member 14 is provided between the divided piece 11 </ b> A and the connecting member 13. In the state of FIG. 3, the connecting member 13 is pushed into the engagement hole 9 b by the elastic force of the elastic member 14. As a result, the connecting member 13 is prevented from coming out of the engagement hole 9b. In the example of FIG. 3, the elastic member 14 is a coil spring through which the connecting member 13 passes. One end of the coil spring 14 is locked to the outer surface 12 of the split piece 11 </ b> A, and the other end of the coil spring 14 is locked to the enlarged diameter portion 13 a of the connecting member 13. In FIG. 3, the coil spring 14 is compressed. Note that the elastic member 14 may be a leaf spring or another elastic body.

  The connection release device 15 extracts the connection member 13 from the engagement hole 9b and moves it to the release position against the elastic member 14, thereby connecting the protection member 11 and the lower outer shell 9 by the connection member 13. To release. As a result, the lower-stage outer shell 9 (ie, the lower-stage structure 3C) is separated from the protection member 11 and the upper-stage outer shell 7 (ie, the upper-stage structure 3B).

  The connection release device 15 includes a wire 15a, a pulley 15b, a drum 15c, and a motor 15d. One end of the wire 15 a is fixed to the connecting member 13. An intermediate portion of the wire 15a is hung on the pulley 15b. The other end portion of the wire 15a is wound around the drum 15c. Each of the pulley 15b and the drum 15c is attached to the protection member 11 so as to be rotatable around its own axis. The motor 15d rotates the drum 15c to wind the wire 15a around the drum 15c. Thereby, the motor 15d pulls the connecting member 13 from the engagement hole 9b through the wire 15a. FIG. 5 shows a state in which the connecting member 13 is pulled out from the engagement hole 9b as described above in FIG.

Each component (namely, wire 15a, pulley 15b, drum 15c, and motor 15d) of connection release device 15 may be provided for every division piece 11A.
Instead, the wire 15a and the pulley 15b are provided for each divided piece 11A, but the drum 15c and the motor 15d may be common to the plurality of divided pieces 11A. In this case, the other end side portions of the plurality of wires 15a fixed to the connecting members 13 of the plurality of divided pieces 11A are wound around one drum 15c. The motor 15d rotates the drum 15c, thereby winding the plurality of wires 15a around one drum 15c. Thereby, the motor 15d pulls out the plurality of connecting members 13 from the engagement holes 9b through the plurality of wires 15a.

  The sliding guide portion 17 is provided for each divided piece 11A. The sliding guide portion 17 is fixed to the outer peripheral surface of the divided piece 11A and extends in the circumferential direction. The plurality of sliding guide portions 17 respectively provided in the plurality of divided pieces 11A may be annular as a whole when viewed from the axial direction. The sliding guide part 17 is in contact with the inner peripheral surface of the lower outer shell 9. The sliding guide portion 17 has a function of smoothly sliding the lower outer shell 9 separated from the protective member 11 and the upper outer shell 7 in the axial direction.

  FIG. 6 is a partially enlarged perspective view of FIG. 2 and shows the vicinity of a connection portion between the upper stage structure 3B and the lower stage structure 3C. In FIG. 6, illustration of a part of the lower outer shell 9 is omitted.

  Preferably, the rocket connection / separation mechanism 10 further includes one or both of a pressurizing device 21 and an elastic member 29 for separation. According to the present invention, one or both of the pressure device 21 and the elastic member 29 may be omitted.

  The pressurizing device 21 pressurizes the internal space S (see FIG. 3). The internal space S is provided between the rocket propulsion system 5 of the upper stage structure 3B and the outer peripheral surface of the rocket propulsion system 5 and the inner peripheral surface of the upper stage outer shell 7, and extends in the circumferential direction to make one round. The annular gas seal portion 18, the rocket propulsion system 5 of the lower stage structure 3 </ b> C, and the outer peripheral surface of the rocket propulsion system 5 and the inner peripheral surface of the lower stage outer shell 9 extend in the circumferential direction. It is formed by the surrounding annular gas seal part 19 or the like. The pressurizing device 21 is provided in the internal space S, for example. The pressurizing device 21 may include an air accumulator 23a of the posture control device 23 provided in the upper stage structure 3B. In this case, the attitude control device 23 includes an air accumulator 23a, a liquid fuel tank 23b, a combustor 23c, and a nozzle 23d. The posture control device 23 is used as follows after the lower stage structure 3C is separated from the upper stage structure 3B. The gas accumulator 23a supplies pressurized gas to the liquid fuel tank 23b. Thereby, liquid fuel (for example, hydrazine) is pushed out from the liquid fuel tank 23b to the combustor 23c. In the combustor 23c, combustion gas is generated by the reaction between the catalyst of the combustor 23c and the fuel. This combustion gas is ejected from the nozzle 23d, and the posture (direction) of the upper structure 3B changes.

  When the pressurizing device 21 is configured by the air accumulator 23a, the pressurizing device 21 may further include a pipe 23e and a valve 23f. The pipe 23e extends from the air reservoir 23a. An opening 23e1 is formed in a part of the pipe 23e (for example, the tip of the pipe 23e). The valve 23f is provided in the pipe 23e so as to be positioned between the opening 23e1 and the air reservoir 23a. By opening the valve 23f with an appropriate driving device, the pressurized gas is supplied from the gas accumulator 23a to the internal space S. As a result, the internal space S is pressurized. In addition, the pressurization apparatus 21 may be comprised by other means (for example, another air accumulator filled with high pressure gas).

  When the pressurization device 21 is provided, the above-described sliding guide portion 17 also functions as a gas seal for sealing the internal space S from the outside of the rocket 1. That is, each sliding guide portion 17 extends in the circumferential direction so as to close a gap between the divided piece 11 </ b> A and the lower-stage outer shell 9.

  Further, when the pressurizing device 21 is provided, gas seal portions are also provided at other locations necessary for sealing the internal space S from the outside of the rocket 1. In the present embodiment, gas seal portions 25 and 27 are provided.

  As shown in FIG. 3, the plurality of gas seal portions 25 are provided between the upper outer shell 7 and the plurality of divided pieces 11A, respectively, and extend in the circumferential direction. The plurality of gas seal portions 25 are annular as a whole when viewed from the axial direction.

  As shown in FIG. 6, the gas seal portion 27 is provided at the boundary between the divided pieces 11 </ b> A adjacent in the circumferential direction. The gas seal portion 27 extends in the axial direction over the entire axial dimension of the divided piece 11A so as to close the boundary. There are as many gas seals 27 as the number of such boundaries. That is, when the number of divided pieces 11A is n, the number of boundaries is also n, and therefore n gas seal portions 27 are provided at n boundaries, respectively.

  In the example of FIG. 3, a gas seal portion (not shown) is also provided between the inner peripheral surface of the through hole 11 b and the connecting member 13.

  The elastic member 29 is provided so that an elastic force that separates each protective member 11 and the lower outer shell 9 from each other in the axial direction acts on both. The elastic member 29 is preferably a coil spring. For example, as shown in FIG. 3, the elastic member 29 may be disposed between a portion protruding from the inner surface of the lower outer shell 9 and the lower end surface of the protection member 11.

  The separation operation of the upper stage structure 3B and the lower stage structure 3C by the rocket connection / separation mechanism 10 described above is performed in the following order (1) to (4).

(1) First, it is assumed that the rocket 1 is launched from the ground and the rocket propulsion system 5 provided in the lower structure 3C is injecting combustion gas from the nozzle 5a. At this time, the rocket connection / separation mechanism 10 is in the state shown in FIGS. 3 and 6.

(2) From this state, the ejection of the combustion gas from the rocket propulsion system 5 provided in the lower structure 3C is completed. At this time, as shown in FIG. 5, the connection release device 15 simultaneously pulls out the connection members 13 of the respective divided pieces 11A from the engagement holes 9b.

(3) As a result, the lower outer shell 9 is separated from the protective member 11. That is, the lower stage structure 3C is separated from the upper stage structure 3B. At this time, the lower outer shell 9 moves along the protection member 11 by sliding on the sliding guide portion 17. Thereby, the lower stage side outer shell 9 moves away from the upper stage side structure 3B in the axial direction.

(4) When the lower structure 3C is separated as in (3) above, the lower end side portion of each divided piece 11A is displaced in the radial direction. As a result, the fitting portion 11a of each divided piece 11A is disengaged from the recess 7b.

  In the above (4), the divided piece 11A is displaced or deformed in the radial direction as follows, for example. The divided piece 11A receives force from the lower outer shell 9 (lower structure 3C) via the sliding guide portion 17. This force is generated by the rotational moment of the rocket 1 (moment about the axis intersecting with the central axis of the rocket 1) generated at the time of (3).

  When the sliding guide portion 17 functions as a gas seal as described above, the lower end side portion of each divided piece 11A may be displaced in the radial direction in the above (4) as follows. The sliding guide part 17 is formed of an elastic material (for example, rubber). Before the above (3), the sliding guide portion 17 is compressed in the radial direction between the lower outer shell 9 and the protection member 11. The sliding guide portion 17 is released from the compressed state in the radial direction by the separation of the lower-stage structure 3C in (3) above. Due to the momentum of the release, the lower end side portion of the divided piece 11A is displaced in the radial direction in the above (4).

  When the internal space S is pressurized by the pressurizing device 21, the lower end side portion of each divided piece 11A is displaced in the radial direction by the pressure of the internal space S in (4).

  In the above (4), there is no problem if the divided piece 11A is not separated from the upper outer shell 7 by any chance.

  When the pressurizing device 21 is provided, the internal space S is pressurized by the pressurizing device 21 by the time of the above (2). Therefore, in (3) above, the axial movement of the lower outer shell 9 relative to the protective member 11 is urged by the pressure in the internal space S. This movement is also urged by the elastic member 29. In the above (4), each divided piece 11A is blown outward in the radial direction by the pressure in the internal space S.

  A control device for controlling the rocket connection / separation mechanism 10 (connection release device 15, pressurization device 21, etc.) is provided in the rocket 1 so that the rocket connection / separation mechanism 10 operates in the order of (1) to (4) above. May be.

(Effect of embodiment)
According to the above-described embodiment, the protection member 11 connected to the lower end portion 7 a of the upper stage outer shell 7 is located between the nozzle 5 a and the lower stage outer shell 9. Therefore, when the lower-stage outer shell 9 is separated, the protection member 11 can prevent the lower-stage outer shell 9 from colliding with the nozzle 5a.

  Since the connecting member 13 is inserted into the engagement hole 9b of the lower outer shell 9, the protection member 11 and the lower outer shell 9 can be connected to each other. The connection release device 15 can release the connection between the protection member 11 and the lower outer shell 9 by pulling out the connection member 13 from the engagement hole 9b.

  Since the protection member 11 is composed of a plurality of divided pieces 11A, each divided piece 11A can be separated from the upper outer shell 7 as in (4) above. By this separation, it is possible to avoid the weight of the protective member 11 being added to the weight of the upper structure 3B.

  The separated divided pieces 11A may collide with the nozzles 5a of the rocket propulsion system 5 in the upper structure 3B. In this regard, the split piece 11 </ b> A is separated from the lower outer shell 9 by the connection release device 15. Therefore, even if the divided piece 11A, which is significantly lighter than the lower structure 3C, collides with the nozzle 5a, the impact is small. Therefore, damage to the nozzle 5a is prevented.

  When the internal space S is pressurized, the pressure in the internal space S acts downward on the entire lower stage structure 3C. Thereby, in said (3), the relative acceleration of the lower stage side outer shell 9 (namely, lower stage side structure 3C) with respect to the upper stage side structure 3B becomes large. Therefore, the residual thrust allowed at the time of separation increases. The residual thrust means the thrust by the combustion gas of unburned fuel. The unburned fuel is unburned fuel (in this example, solid propellant) of the rocket propulsion system 5 of the lower structure 3C, and gradually decreases without rapidly burning out completely. In order to prevent the lower stage structure 3C separated from the upper stage structure 3B from colliding with the upper stage structure 3B due to the influence of the residual thrust, the residual thrust of the rocket propulsion system of the lower stage structure 3C is allowed to a permissible value. After becoming small, the lower stage structure 3C is separated from the upper stage structure 3B.

  Further, the pressure in the internal space S acts on each divided piece 11A outward in the radial direction. Therefore, the divided pieces 11A separated in the above (4) move outward in the radial direction by the pressure in the internal space S. Therefore, it is possible to prevent the divided piece 11A from colliding with the nozzle 5a.

  Furthermore, due to the elastic force of the elastic member 29, in (3) above, the relative acceleration of the lower outer shell 9 relative to the upper structure 3B increases. Therefore, this elastic force also increases the residual thrust allowed at the time of separation.

  The present invention is not limited to the above-described embodiment, and various changes can be made without departing from the scope of the present invention. For example, any of the following modified examples 1 to 7 may be adopted, or two or more of modified examples 1 to 7 may be arbitrarily combined and employed. In this case, the points not described below are the same as described above.

(Modification 1)
The connection member 13 should just be provided with respect to at least any one of several division piece 11A which comprises the protection member 11. FIG. For example, the connecting member 13 may be provided only for one divided piece 11A.

  Alternatively, the connecting member 13 may be provided only for two or more divided pieces 11 </ b> A that are a part of the plurality of divided pieces 11 </ b> A constituting the protection member 11. In this case, regarding the configuration of FIG. 3 described above, the drum 15c and the motor 15d may be common to the two or more divided pieces 11A. That is, as described above, the wires 15a extending from the plurality of connecting members 13 provided for the two or more divided pieces 11A are wound around one drum 15c.

(Modification 2)
The upper structure and the lower structure may be the structures 3A and 3B in FIG. 2, respectively. In this case, in the above description, the upper stage structure 3B and the lower stage structure 3C are read as the upper stage structure 3A and the lower stage structure 3B, respectively.

(Modification 3)
The internal space S may be previously pressurized before the rocket 1 is launched from the ground. In this case, the pressure device 21 described above may be omitted.

(Modification 4)
In the above description, the rocket 1 is composed of the three-stage structures 3A, 3B, and 3C. However, the rocket 1 may be composed of two-stage or four-stage or more structures. In this case, the upper stage structure and the lower stage structure described above may be any two adjacent structures of the rocket 1.

(Modification 5)
In the above description, the fitting portion 11 a is provided at the upper end portion of each divided piece 11 </ b> A, and the recess 7 b is provided at the lower end portion 7 a of the upper-stage outer shell 7. According to the present invention, the upper end portion of each divided piece 11 </ b> A only needs to engage with the lower end portion 7 a of the upper outer shell 7 in the axial direction. For example, the protrusion provided on the lower end 7a of the upper outer shell 7 is fitted in the width direction in the depression or hole in the width direction (radial direction) provided on the upper end of each divided piece 11A. The upper end portion of each divided piece 11A may be engaged with the lower end portion 7a of the upper outer shell 7 in the axial direction.

(Modification 6)
The connection member 13 and the connection release device 15 are not limited to the above-described configuration. The connecting member 13 only needs to be operable from a connecting position for connecting the protection member 11 to the lower outer shell 9 to a releasing position for releasing the connection. The connection release device 15 only needs to move the connection member 13 from the connection position to the release position. For example, as a configuration of the connecting member 13 and the connection release device 15, the following other configuration examples 1 or 2 may be adopted.

<Configuration example 1>
FIG. 8A corresponds to a part of FIG. 3, but shows a configuration example 1 of the connection member 13 and the connection release device 15. The connecting member 13 is attached to the lower outer shell 9 so as to be rotatable about the axis C1.

  The connecting member 13 is in the connecting position in FIG. That is, in the state of FIG. 8A, the connecting member 13 is engaged with the divided piece 11A in the axial direction.

  In FIG. 8, the elastic member 14 gives an elastic force to the connecting member 13 in the clockwise direction of FIG. 8A around the axis C1. Thereby, the connecting member 13 is held at the connecting position.

  Such a connection member 13 and the elastic member 14 may be provided for every divided piece 11A, or may be provided for a part of the divided pieces 11A. When a plurality of connecting members 13 are provided, these connecting members 13 are arranged in alignment in the circumferential direction.

  The connection release device 15 rotates the connection member 13 to the release position against the elastic member 14. In FIG. 8B, the connecting member 13 is in the release position. The connection release device 15 includes a motor 15e. When a plurality of connecting members 13 are provided, the connection release device 15 further includes a wire 15f. The wire 15 f has an annular shape extending in the circumferential direction and is hung on the plurality of connecting members 13. Each connecting member 13 is provided with grooves or holes (holes in FIG. 8) penetrating in the circumferential direction, and wires 15f are passed through these grooves or holes. Therefore, as shown in FIG. 8, one motor 15e rotates the corresponding connecting member 13 counterclockwise in the drawing, so that the plurality of connecting members 13 rotate from the connecting position to the releasing position via the wires 15f. Be made.

  The elastic member 29 is not shown in FIG. 8, but may be provided at a circumferential position different from that in FIG.

<Configuration example 2>
FIG. 9A corresponds to a part of FIG. 3, but shows a configuration example 2 of the connection member 13 and the connection release device 15. FIG. 9B is a BB arrow view of FIG.

  As shown in FIG. 9B, the divided piece 11A is formed with a first groove 31 extending in the circumferential direction and a second groove 32 extending in the axial direction. The first groove 31 and the second groove 32 are connected to each other. The second groove 32 opens at the lower end of the divided piece 11A. The first groove 31 and the second groove 32 may penetrate the divided piece 11A in the width direction (radial direction).

  The connecting member 13 is inserted into the first groove 31 in the width direction (radial direction) in FIGS. 9A and 9B and is in the connecting position. When the connection member 13 is in the connection position, the connection member 13 is at a position shifted from the second groove 32 in the circumferential direction.

  The connection release device 15 moves the connection member 13 in the circumferential direction from the connection position to the release position. FIG. 9C shows a state in which the connecting member 13 has moved to the release position in FIG. 9B.

  Such a connection release device 15 may be an actuator that converts rotation of the motor into linear motion using a ball screw and a nut. In this case, the connection release device 15 includes a motor and a nut that engages with a male screw formed on the output shaft of the motor. The nut is attached to the lower outer shell 9 so as not to rotate but to be movable in the direction of the output shaft of the motor. The nut is fixed to the connecting member 13. With this configuration, the rotation of the motor is converted into a linear motion (that is, circumferential movement) of the nut and the connecting member 13.

  In the configuration example 2, the connection member 13 and the connection release device 15 may be provided for each of the divided pieces 11A or may be provided for a part of the divided pieces 11A.

(Modification 7)
According to the present invention, the protection member 11 only needs to be composed of a plurality of divided pieces 11A that are separated from or in contact with each other in the circumferential direction. In this case, the divided pieces 11A adjacent in the circumferential direction may be in contact with each other without any gap in the circumferential direction, and the gaps between the divided pieces 11A adjacent in the circumferential direction are filled with the gas seal portion 27 as shown in FIG. Alternatively, a space (for example, a gap) may be provided between the divided pieces 11A separated from each other in the circumferential direction.

  In the case where a space is provided between the divided pieces 11A separated from each other in the circumferential direction, for example, the divided pieces 11A are prevented from moving inward in the radial direction by the connecting member 15 shown in FIG. Can do. Thereby, the fitting part 11a is prevented from coming out of the recess 7b. As the other restraining means, for example, a configuration in which the connecting member 13 is tightly fitted in the through hole 11b and the engagement hole 9b in FIG. 3 may be employed. Alternatively, in FIGS. 9A and 9B, a configuration in which the portion of the connecting member 13 extending in the axial direction is in contact with the inner peripheral surface of the divided piece 11A may be employed as the other restraining means.

  When a space is provided between the divided pieces 11A, the divided pieces 11A can be made smaller. Accordingly, when the divided piece 11A collides with the nozzle 5a, the possibility that the nozzle 5a is damaged is further reduced. In this case, the pressurizing device 21 and the gas seal portion 27 are omitted.

1 rocket, 3A, 3B, 3C structure, 5 rocket propulsion system, 5a nozzle, 6 satellite, 7 upper outer shell, 7a lower end, 7b hollow, 7c lower end surface, 9 lower outer shell, 9a upper end surface, 9b Engagement hole, 10 rocket connection / separation mechanism, 11 protection member, 11A split piece, 11a fitting portion, 11b through hole, 12 outer surface, 13 connection member, 13a enlarged diameter portion, 14 elastic member (coil spring), 15 connection release device 15a wire, 15b pulley, 15c drum, 15d motor, 17 sliding guide, 18, 19 annular gas seal, 21 pressurizing device, 23 attitude control device, 23a air reservoir, 23b liquid fuel tank, 23c combustor, 23d nozzle, 23e piping, 23e1 opening, 23f valve, 25, 27 gas seal part, 29 elastic member, 31 first groove, 3 The second groove, S inner space

Claims (6)

A rocket connection / separation mechanism for connecting and separating a rocket upper structure and lower structure from each other,
The upper stage structure includes an upper stage outer shell extending around the central axis of the rocket, and a rocket propulsion system disposed inside the upper stage outer shell, the rocket propulsion system being lower than the upper stage outer shell. Has a nozzle protruding into the
The lower-stage structure includes a lower-stage outer shell extending in a circumferential direction around the central axis, and the nozzle is located inside the lower-stage outer shell,
The rocket coupling and separation mechanism
A protective member connected to the lower end of the upper outer shell and positioned between the nozzle and the lower outer shell in the width direction orthogonal to the circumferential direction;
A connecting member operable from a connecting position for connecting the protective member to the lower outer shell to a releasing position for releasing the connection;
A connection release device for moving the connection member from a connection position to a release position,
The protective member extends in the circumferential direction so as to surround the nozzle, and is composed of a plurality of divided pieces separated from or in contact with each other in the circumferential direction,
Each divided piece is connected to the upper outer shell by engaging the upper end of each divided piece with the lower end of the upper outer shell in the axial direction of the rocket,
The rocket connection / separation mechanism, wherein the lower outer shell is connected to the upper outer shell via the protective member. An elastic member for applying an elastic force to the connecting member so as to hold the connecting member at the connecting position;
The rocket connection / separation mechanism according to claim 1, wherein the connection release device moves the connection member to the release position against the elastic member. A sliding guide portion fixed to the outer peripheral surface of the protective member and extending in the circumferential direction;
The rocket connection / separation mechanism according to claim 1, wherein the sliding guide portion is in contact with an inner peripheral surface of a lower-stage outer shell. The internal space formed by the upper outer shell and the lower outer shell is sealed against the outside of the rocket,
The rocket connection / separation mechanism according to claim 3, wherein the internal space is pressurized in advance, or a pressurizing device that pressurizes the internal space is provided. The sliding guide portion closes a gap between the protective member and the lower outer shell,
The rocket connection and separation mechanism according to claim 4, further comprising a gas seal portion provided at a boundary between the divided pieces adjacent in the circumferential direction and extending in the axial direction of the rocket so as to close the boundary.   6. The apparatus according to claim 1, further comprising a separation elastic member that is provided for each divided piece and that causes an elastic force to axially separate the divided piece and the lower outer shell from each other. Rocket coupling and separation mechanism.

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