JPH06320Y2 - Rocket band coupling / separation device - Google Patents

Description

[Detailed Description of the Invention] [Object of the Invention] (Industrial field of application) The present invention relates to a rocket band coupling / separation device used to keep an interstage portion of a rocket separably tightened. is there.

(Prior Art) Conventionally, as a band coupling / separation device as described above,
There were those as shown in FIGS. 4 to 6.

That is, reference numeral 100 in the drawing is a Maruman band, and this Maruman band 100 is one in which a plurality of clamps 102 having a V-shaped groove 102a are provided on one surface of a flexible strip 101, and the Maruman band 100 has The V-shaped groove 102a is fitted to outward flanges 103 and 104 formed on the tail portion of the upper step portion A and the head portion of the lower step portion B and abutting each other. The Maruman band 100 is composed of two rockets each having a length of about half the circumference of the rocket, and the two end portions A and B are tightened by connecting the respective ends so as to be separable.

In the Maruman band 100 coupling / separating device, one of the coupling ends is coupled to the rocket head direction (fourth direction).
A holder portion 105 that extends in the upward direction of the drawing to form a compression chamber 105a is integrally provided, and the compression chamber 105
A piston 107 provided with a puller pin 106 is slidably provided in a, and power cartridges 108 and 108 for moving the piston 107 are fixed to both sides of the compression chamber 105a, and the compression chamber 10a is provided.
A stopper 109 for receiving the piston 107 is fixed to the end of 5a. Then, the puller pin 106 is inserted into the hole portion 110a of the eyebolt 110, and the male screw portion 110b of the eyebolt 110 is passed through the end portion of the other Maruman band 100 so that the nut 1 is formed.
The end portions of the Maruman band 100 are joined to each other by screwing 11 together. A cover 112 extending so as to surround the outer periphery of the Maruman band 100 is provided in the upper stage portion A of the rocket, and mainly the power cartridge 108 and wirings to the power cartridge 108 are protected from aerodynamic heating. I try to protect it.

When the power cartridge 108 is ignited, the above-described coupling / separating device releases the coupling by pushing the piston 107 with the explosive gas, and at the same time pulling out the puller pin 106 from the hole 110a of the eyebolt 110 to end the Marman band 100. Separate each other. Further, the upper stage part A and the lower stage part B of the rocket, which have been unfastened by the Maruman band 100, are separated by the repulsive force of the separation spring which is mounted between them in advance.

As such a coupling / separating device, for example, a device using a separation nut is described on page 461 of "Supplementary Edition Aerospace Engineering Handbook" issued by Maruzen in April 1983.

(Problem to be solved by the invention) However, in the conventional band coupling / separating device as described above, the mechanism for coupling / separating is in a protruding state to the outside of the rocket together with the Maruman band 100. However, the cover 112 must be provided in order to protect the power cartridge 108 and the wirings connected to the power cartridge 108 from aerodynamic heating, which is a problem in improving the aerodynamics of the rocket.

(Purpose of the Invention) The present invention was made in view of such conventional problems, and protects it from aerodynamic heating by providing at least the joint portion of the band end inside the rocket outer peripheral surface. It is an object of the present invention to provide a band coupling / separation device for a rocket that can eliminate the need for covers and can improve aerodynamics.

[Structure of the Invention] (Means for Solving the Problems) The rocket band coupling / separation device according to the present invention has a structure in which the rocket band connecting / separating device is connected to an interstage connecting portion between an upper stage portion and a lower stage portion of the rocket and extends outwards over the entire circumference. A recess is provided, and the Maruman band for tightening the interstage portion coupling portion is housed in the recess, and the ends of the Maruman band are housed in the recess as well as a fork bolt housed in the recess. An eyebolt that engages with the fork bolt and the engaging portions of both bolts are coupled with a puller pin that penetrates in the rocket radial direction, and the inside of the rocket has a separating means that pulls out the puller pin to the rocket center side. The above configuration is used as a means for solving the problem.

(Example) Hereinafter, this invention is demonstrated based on drawing.

1 to 3 are views for explaining an embodiment of the present invention.

That is, reference symbol A in the drawing is the upper stage of the rocket R, reference symbol B
Is a lower part of the rocket R, and includes a first connecting ring 1 fixed to the tail of the upper part A and a second connecting ring 2 fixed to the head of the lower part. , B is formed with an outward concave portion 3 having a substantially trapezoidal cross section over the entire circumference thereof. The both rings 1 and 2 are configured such that the fitting portion 1a formed at the lower end of the first ring 1 is fitted to the inside of the upper end of the second ring 2 in the same manner as a brazing joint, and they are in contact with each other. Facing flanges 1f, 2f
At this time, both of the flanges 1f and 2f are in a state of protruding to the bottom portion of the recess 3.

Further, reference numeral 4 is a Maruman band, and this Maruman band 4 is formed by attaching a plurality of clamps 6 each having a V-shaped groove 6a to one surface of a flexible belt-like body 5 and in a contact state. The V-shaped groove 6a is fitted to both the flanges 1f and 2f. At this time, the concave portion 3 has a depth to accommodate the entire Maruman band 4 inside the outer peripheral surface of the rocket R. In many cases, the Maruman band 4 uses one having a length dimension that extends over the entire circumference of the rocket R, or uses two that have a length dimension that extends over about a half circumference of the rocket R. A fork bolt 7 accommodated in the recess 3 is provided at one of the ends, and an eye bolt 8 similarly accommodated in the recess 3 and engaged with the fork bolt 7 is provided at the other end. .

Both the fork bolt 7 and the eyebolt 8 have holes 7a and 8a having substantially the same diameter, and both holes 7a and 8a are formed.
The a and 8a are engaged in a continuous state and can be freely separated. When mounting the bolts 7 and 8, the band-shaped body 5 is folded at each end of the Maruman band 4, and the ends are fixed, and the inner side of the loop portion formed by the folding. The barrel nuts 9 and 10 are mounted on the barrel nuts 9 and 10, respectively, and the male threads 7b and 8b of the bolts 7 and 8 are screwed into the barrel nuts 9 and 10, respectively. In this embodiment, particularly, as shown in FIG. 2, the flange portion 2f (1f) is cut off at a portion corresponding to the joint portion of the Maruman band 4 to form the flat portion C, and the bolts 7 and 8 are formed. Is disengaged in a tangential direction to the circumference of the rocket R.

Then, inside the rocket corresponding to the connecting portion of the Maruman band 4, a puller pin 11 that penetrates the engaging portions of the bolts 7 and 8 in the rocket radial direction and a separating means that pulls out the puller pin 11 toward the rocket center side are configured. Holder 13 with a working source 12 and a piston 16
Is installed. The holder 13 has a fixing flange 13a that is fixed to the inside of the first ring 1 by using a bolt 14.
And a compression chamber 13b having a circular cross-section with the radial direction of the rocket R as the axial direction, and a mounting portion 13c of the operation source 12 are integrally provided, and the compression chamber 13b is provided at the end of the compression chamber 13b on the outer side of the rocket. , The communication hole 13 inserted into the mounting portion 13c
d is formed. Further, a cap-shaped stopper 15 having a vent hole 15a is screwed onto the end of the compression chamber 13b on the rocket center side.

The puller pin 11 has a diameter corresponding to the holes 7a, 8a of the fork bolt 7 and eyebolt 8 described above, and in this embodiment, the compression chamber 13 is provided at the base end.
The above-mentioned piston 16 slidingly contacting the inner surface of b is integrally provided, penetrates the holder 13 and the wall portion of the rocket R in the radial direction of the rocket R, and projects from the plane portion C into the concave portion 3, and It can slide with the piston 16. The holder 13 has O-rings 17, 1 that come into pressure contact with the inner surface of the first ring 1 and the outer peripheral portion of the puller pin 11.
8 is fitted, and the piston 16 is also fitted with an O-ring 19 which is in pressure contact with the inner surface of the compression chamber 13b. The operation source 12 is composed of a power cartridge 12a loaded with an output medicine and a connector portion 12c to which an ignition cable 12b is connected. An O-ring 2 is attached to a mounting portion 13c of a holder 13.
It is fixed by screwing in through 0, and the ignition cable 12
b is connected to an ignition device (not shown).

Inside the lower step portion B, an appropriate number of separating force giving means 21 for giving a separating force to the upper step portion A are provided. This separating force applying means 21 has, for example, a built-in compression coil spring protruding in the direction of the upper step portion A, and in the illustrated case, when the upper step portion A and the lower step portion B are coupled, the bolt 22 is provided inside the first ring 1. The spring is compressed in the axial direction of the rocket R between itself and the partition wall 23 fixed by, and the repulsive force is always applied to the upper step portion A.

Then, the band coupling / separating device described above engages the fork bolt 7 and the eyebolt 8 in the recess 3 in such a manner that both hole portions 7a, 8a are continuous on the coaxial line.
The ends of the Maruman band 4 are joined by inserting the puller pins 11 from the inside of the rocket R into the two holes 7a and 8a, and at the same time, the Marman band 4 tightens the upper stage A and the lower stage B of the rocket R. is doing. At this time, the piston 16 is located closer to the center of the rocket R than the communication hole 13d, and in some cases, a shear pin protruding from the side of the holder 13 into the compression chamber 13b is provided to suppress the piston 16. There are also things to keep.

Further, in the above band coupling / separation device, when the actuation source 12 is ignited, the high pressure gas generated by the explosion of the output chemical is communicated with the communication hole 13
It flows into the compression chamber 13b through d and the piston 1
6 is pushed toward the center of the rocket R, and at the same time, the puller pin 11 is retracted to the inside of the rocket R and pulled out from the holes 7a and 8a of the bolts 7 and 8 so that the ends of the Maruman band 4 are separated from each other. To separate. Therefore, the upper step portion A and the lower step portion B, which have been released from the tightening by the Maruman band 4, are separated by the action of the separating force applying means.

That is, in the band coupling / separation device of the above-described embodiment, since the entire Maruman band 4 is located inside the outer peripheral surface of the rocket R, it is clear that no cover for protecting from aerodynamic heating is required. . Furthermore, since the actuation source 12 and the piston 16 that constitute the separating means are provided inside the rocket R, the Marman band 4 and the ignition cables 12b and other wiring are not connected, and the end of the Marman band 4 is eliminated. It suffices to provide a structure (fork bolt 7 and eyebolt 8) that is simply connected by the puller pin 11, and the end structure of the band can be made significantly smaller than the conventional structure. Also,
Since the puller pin 11 is pulled out toward the center of the rocket in the above device, there is no influence of the force in the axial direction of the rocket when the separating means is actuated, and compared with, for example, one in which the end of the band is directly coupled with a separation nut. It has an advantage that the impact at the time of separation is extremely small.

[Effect of the Invention] As described above, according to the rocket band coupling / separating device of the present invention, it is possible to eliminate the need for covers for protecting the device from aerodynamic heating.
It is possible to eliminate the protruding part to the outside of the rocket and improve the aerodynamics. Also, by pulling out the puller pin toward the center of the rocket, the impact at the time of separation can be minimized. Moreover, the inertial force when pulling out the puller pin is the moment that acts toward the center of the axle, the so-called aircraft rotating around the axle. Because it is not in the direction, it does not induce unexpected rolling (This phenomenon is more likely to occur as the diameter of the aircraft is larger, so it is effective for large rockets) Have.

[Brief description of drawings]

FIG. 1 is a vertical sectional view for explaining an interstage part of a rocket to which a band coupling / separation device according to an embodiment of the present invention is applied,
2 is a sectional view taken along the line D-D shown in FIG. 1, FIG. 3 is a sectional view taken along the line E-E shown in FIG. 1, and FIG. 4 illustrates a conventional band coupling / separating device. Side sectional view,
FIG. 5 is a sectional view from the bottom side of the device shown in FIG.
The drawing is a sectional view based on the line FF shown in FIG. R ... rocket, 4 ... Maruman band, 7 ... fork bolt, 8 ... eye bolt, 11 ... puller pin, 12 ... actuation source (separating means), 16 ... piston (separating means).

Claims (1)

[Scope of utility model registration request] 1. A Maruman band for tightening the interstage connecting portion is provided in the interstage connecting portion between the upper stage portion and the lower stage portion of the rocket, the recess being outwardly provided around the entire circumference thereof. At the same time, the end portions of the Maruman band are pierced through the fork bolts housed in the recess, the eye bolts housed in the recess and engaged with the fork bolts, and the engaging portions of both bolts in the rocket radial direction. A rocket band coupling / separation device, characterized in that the rocker band coupling / separation device is provided inside the rocket and with a separating means for pulling out the puller pin toward the center of the rocket.