JPS6349680B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a coupling and separation device between each stage of a multi-stage rocket.

Multi-stage rockets are generally used to launch artificial satellites and observation rockets. This multi-stage rocket is designed so that each time the lower stage rocket completes a predetermined operation, the lower stage rocket is separated, and the rocket further flies due to the operation of the upper stage rocket. For this reason, a coupling/separation device (Japanese Patent Publication No. 34400/1983) is provided at the joint between the upper and lower stages of a multi-stage rocket to allow the lower rocket to be separated when the lower rocket finishes operating.

Conventionally, the connection and separation device for each stage of this multi-stage rocket was described in the "Aerospace Engineering Handbook" published by Maruzen Co., Ltd.
It is shown in FIG. 7, 172, and its details are shown in FIGS. 1 and 2. In Fig. 1, 1 indicates the upper stage of the rocket, and 2 indicates the lower stage of the rocket.The ends of the joints of the upper stage 1 and the lower stage 2 are respectively slightly raised in the outward direction, and the upper stage 1 and the lower stage 2 are In the joined state, these protrusions are combined to form a protrusion 3 having a substantially trapezoidal cross section.
4 is a Maruman band, in which a plurality of pieces 7 having grooves shaped to fit with the projections 3 are fixed to a band plate 6 having elasticity such as spring steel at appropriate intervals as shown in FIG. At the same time, bolt holes 12a and 12b and protrusions 3 are provided at both ends of the strip plate 6, respectively.
a connecting piece 8a having a groove shaped to fit into the connecting piece 8a;
8b is fixed. Then, connect two Maruman bands 4 to each piece 7 and connecting piece 8.
The grooves a and 8b are connected to the protrusions 3 of the upper stage 1 and lower stage 2.
The fixing release device 5
The connected state of the upper stage 1 and the lower stage 2 is maintained by tightening and connecting the upper stage 1 and the lower stage 2.

Here, the fixing release device 5 consists of a connecting bolt 10 and a separation nut 11, and the connecting bolt 10 is inserted into the bolt holes 12a, 12b of the connecting pieces 8a, 8b provided at the ends of the respective Maruman bands 4. The two Maruman bands 4 are tightened by screwing together the split nut of the separation nut 11 provided on the connecting piece 8a side and the nut provided on the connecting piece 8b side on both sides of this connecting bolt 10. are doing.

In such a connected state, when the lower stage 2 completes its predetermined operation, the control device (not shown)
The separation nut 11 is actuated by a signal from the separation nut 11, and the gas generator of the separation nut 11 generates combustion gas, and the pressure of the gas splits the splitting nut screwed into the connecting bolt 10. The Maruman Band 4 of the book is unbound. Each Maruman band 4 is extended from a semicircular shape into a substantially straight line due to the elastic force of the band plate 6, and is separated from the joint between the rocket stages 1 and 2 in both directions. As a result, the connection between the rocket stages 1 and 2 is released, and the lower stage 2 is separated from the upper stage 1.
The upper stage continues to fly.

However, in such a conventional coupling/separation device for each stage of a multi-stage rocket, a space is required for the splitting nut of the separation nut 11 serving as the fixing release device to separate and move, and a space for the gas generator to move. The projected area of the aircraft increases, and the air resistance during flight increases. In addition, when the joint between the upper and lower stages of the rocket is housed in the outer shell of the nose fairing while the rocket is flying in the atmosphere, the outer diameter of the nose fairing increases, resulting in increased air resistance and weight. There was a problem.

The present invention has been made in view of the above-mentioned problems, and an object of the present invention is to provide a coupling and separation device for each stage of a multi-stage rocket, which has a small projected area in the rocket axis direction.

This purpose is to provide a rocket coupling and separation device in which a Maruman band is hung around the joints of each stage of a multi-stage rocket, and the ends of the Maruman band are fixed by a fixing release device.
A locking member provided at one end of the Maruman band and provided with a locking hole, and a locking member provided at the other end of the Maruman band,
A locking member receiving piece includes a groove into which the locking member is inserted and a hole drilled in the rocket axis direction through the groove; A rod is inserted into the locking hole and connects the locking member and the locking member receiving piece, a gas generator generates combustion gas, and the pressure of the gas moves the rod in the rocket axial direction when each stage of the rocket is separated. This is achieved by a rocket coupling/separation device having a cylinder member which is pulled out from the locking hole.

Next, embodiments of the present invention will be described based on the drawings.

FIGS. 3 and 4 are cross-sectional views showing a coupling/separating device for a multi-stage rocket according to the present invention.

In this embodiment, the upper stage 1 and the lower stage 2 of the rocket are fixed at both ends by surrounding the protrusion 3 formed by the joint of the upper stage 1 and the lower stage 2 in an annular manner with two Maruman bands 4, as in the conventional case. They are fixedly connected with a release device. Note that S is an outer shell of the rocket such as a nose flare, and the joint portions of the upper and lower stages 1 and 2 of these rockets are covered with this nose flare during flight in the atmosphere.
The nose flare and the like are separated from the rocket body after exiting the atmosphere, and by the time the coupling/separating device is activated, the coupling/separating device is already exposed to the outside.

The structure of the Maruman band 4 is almost the same as that used in the past, and is made of a band plate 6 made of an elastic material such as spring steel, which is fitted into the projections 3 formed on each stage 1 and 2 of the rocket. A plurality of pieces 7 having matching grooves are fixed at appropriate intervals. Further, a locking piece 15 is fixed to one end of the band plate 6. This locking piece 15 includes a locking member 16 which will be described later.
A locking member insertion hole 17 into which one end is inserted is bored along the longitudinal direction of the Maruman band 4.

A locking member receiving piece 20 is fixed to the other end of the band plate 6. This locking member receiving piece 20 is provided with a groove portion 21 into which the other end of the locking member 16 is inserted. Holes 23 and 24 are formed in both side walls of the groove 21 to penetrate through the groove 21 and into which a rod 18 (to be described later) is inserted.

The locking member 16 has a male thread formed at one end, is inserted into the locking member insertion hole 17, and is connected to the locking piece 15 with a nut, and has a locking hole 19 bored at the other end. Groove portion 21 of locking member receiving piece 20
The rod 18 protrudes from the hole 23, passes through the locking hole 19, is inserted into another hole 24, and is connected to the locking member receiving piece 20.

Further, the rod 18 is connected to the cylinder member 29 so as to be pulled out of the locking hole 19 and moved into the cylinder 26 of the cylinder member 29 by the pressure of the combustion gas generated by the gas generator 28.

The cylinder member 29 includes a cylinder 26 and a piston 25 fitted into the cylinder 26 and connected to the rod 18. is connected to one wall of the Note that a stopper 27 is provided at the end of the cylinder 26 to prevent the piston 25 from flying out of the cylinder 26.
is provided.

The gas generator 28 is provided in a substantially V-shape along the outer wall of the rocket with the cylinder member 29 in between.
During operation, pressure is applied in the direction in which the rod 18 is pulled out of the locking hole 19. The gas generator 28 generates pressure by combustion of gunpowder inside.

In order to separate the lower stage of the multi-stage rocket from the upper stage using the coupling and separation device for each stage of the multi-stage rocket according to this embodiment, the gunpowder in the gas generator 28 is combusted in response to a signal from a control device (not shown) to generate combustion gas. This combustion gas is transmitted to the inside of the cylinder, and the piston 25 moves inside the cylinder 26 to the stopper 2.
Move to position 7. Therefore, the piston 25 is not ejected to the outside of the cylinder member 29. Fifth
As shown in the drawings and FIG. 6, the rod 18 moves as the piston 25 moves, is removed from the locking hole 19 of the locking member 16, and is pulled out into the cylinder member 29.

When the rod 18 is pulled out, the two Maruman bands 4 do not lose their bonding force, and due to the restoring force of the band plate 6, they extend in a substantially straight line and come off from the joints between the rocket stages 1 and 2, scattering in both directions. . Therefore, the forces acting on the rocket are in opposite directions and cancel each other out. When the Maruman band 4 is released, the rocket stages 1 and 2 are disengaged, the lower stage 2 is separated, and the upper stage 1 further operates the rocket motor to continue flying.

In this embodiment, a case has been described in which two Maruman bands 4 are used, but the number of Maruman bands 4 is not limited to this. Further, the number of gas generators 28 is set to two to ensure quick and reliable operation, but the number of gas generators 28 is not limited to this.

As described above, in this invention, there is no need to provide a space for the rocket connection bolt or the gas generator to move, and the space for the piston to move is provided along the rocket axial direction, so the projected area in the axial direction can be reduced. Air resistance during atmospheric flight can be reduced. In particular, when the connecting portion is housed in an outer shell such as a nose fairing, the outer diameter can be made smaller, which has the effect of further reducing air resistance and reducing weight.

[Brief explanation of the drawing]

Fig. 1 is a vertical sectional view showing a conventional coupling and separation device for each stage of a multi-stage rocket, Fig. 2 is a sectional view taken along the line - -, of the coupling and separation device for the multi-stage rocket shown in Fig. 1.
4 and 4 are sectional views showing a rocket coupling/separation device according to an embodiment of the present invention, and FIGS. 5 and 6 are explanatory views showing the operating state of the rocket coupling/separation device shown in FIG. 3. It is. 1... Rocket upper stage, 2... Rocket lower stage, 4... Maruman band, 16... Locking member, 18... Rod,
19... Locking hole, 20... Locking member receiver, 21... Groove, 23, 24... Hole, 28... Gas generator, 29... Cylinder member.

Claims (1)

[Claims] 1. In a rocket coupling and separation device in which a Maruman band 4 is looped around the joint of each stage 1 and 2 of a multi-stage rocket and the end of this Maruman band 4 is fixed by a fixing release device 5, the fixing release device 5 is as follows: A locking member 16 provided at one end of the Maruman band 4 and having a locking hole 19 formed therein, a groove 21 provided at the other end of the Maruman band 4 into which the locking member 16 is inserted, and a groove 21 penetrating through the groove 21. The locking member receiving piece 20 has holes 23 and 24 drilled in the rocket axial direction, and when the locking member 16 is inserted into the groove 21, the holes 23 and 24 and the locking hole 19 are inserted into the groove 21.
A rod 18 is inserted into the rocket and connects the locking members 16 and 20, a gas generator 28 generates combustion gas, and the pressure of the combustion gas moves the rod 18 in the rocket axial direction when each stage of the rocket is separated. A rocket coupling/separation device characterized by having a cylinder member 29 which is pulled out from a stop hole 19.