JPS6166850A - Segment coupling rocket motor - Google Patents

Abstract

PURPOSE:To simplify a coupling structure and make a superfluous space useless as well as to improve the charging efficiency of a propellant ever so better, by forming an annular projection and an annular groove, being congruous with each other, on a butting end face of both insulators in adjacent segments, while coupling them together. CONSTITUTION:A rocket motor is divided into plural segments 30 and 40 constituted in the same manner. And, each of these segments 30 and 40 consists of each of short cylinder bodies 31 and 41, insulators 32 and 42 stuck to the former, propellants 33 and 43 charged inside these insulators 32 and 42 and front and rear end face restrictors 34 and 45 of these propellants 33 and 43. At the abovementioned, an annular projection 47 is formed on a rear end face 46 of the insulator 42, while an annular groove 38 being congruous with the projection 47 is formed on a front end face 36 of the insulator 32 to be opposed to the projection. Then, the annular projection 47 is fitted in the annular groove 38, while a bolt 25 and a nut 26 are attached to each of flanges 31a and 41a formed in each of these short cylinder bodies 31 and 41, thus each of segments 30 and 40 is coupled together.

Description

[Detailed Description of the Invention] [Field of Industrial Application] The present invention relates to a particularly large-sized rocket motor formed by connecting a plurality of segments, and more specifically, to a motor case of a rocket that is divided into short cylindrical bodies. This invention relates to a rocket motor in which an insulator is attached to the inner surface of a short cylindrical body, a propellant is loaded inside the insulator, and the motor segments are sequentially abutted and connected.

[Background of the invention]

The main role of the insulator is to intervene between the motor case and the propellant to thermally protect the motor case, and generally uses ablation of the insulator material to suppress the inflow of combustion heat. ing. Therefore, as materials for insulators, materials with good abrasive properties, such as nitrile rubber as a main material, mixed with appropriate aggregates such as asbeth have been conventionally used. Therefore, considering the loss due to ablation, the main body of the insulator has a considerably thick wall, an adhesive medium layer, such as a layer of chloroprene rubber, is interposed between the main body of the insulator and the motor case, and an adhesive layer is interposed between it and the propellant. Due to the addition of a media layer and a layer of natural rubber, the actual thickness of the insulator is considerable, and its weight in large rockets can reach several tons. Since the propulsion hook 4 is held soft by the thick insulator mainly made of rubber, a soft structure is adopted for the joint portion of the segment joint rocket motor.

An example of such a soft structure is disclosed in Japanese Patent Publication No. 53-44606, and this will be schematically explained using FIG. 3.

In the figure, numerals 1 and 2 are the adjacent segments, 3 and 4 are short cylindrical bodies forming outer shells of them, and 5 and 6 are horizontally split propellant blocks into short cylindrical bodies 3 and 4, respectively. In the propellant block 5.6, 7.8 is the inner surface of the short cylinder 3゜4 (the attached insulator, γa
, 7b, and 13a, 8bd are internal combustion type composite propellants filled in the adhesive medium layer and the insulators 7.8, 11 and 12 are end face rest lifters of the propellants. Segment 1 and 2
The bond structure of is as follows.

That is, annular protrusions 7c and 8C are formed inside the ends of the insulators 7 and 8, respectively, and a buffer plate 15 with a 7-lunge made of a rubber material extends from the end surfaces of the propellant blocks 5 and 6 to the outer peripheral surfaces of the annular protrusions. 16, loosely fit an annular sealing member 17 made of rubber material together with a liquid sealant to the outside of the outer circumferential surface of the L#7 flange 15a and 16a to join the segments 1 and 2, and then attach the buffer plate. 15
16 and the sealing member 17 are pressed in the direction of the rocket motor and fastened with bolts 25 and nuts 26.

Therefore, each propellant block 5, 6, etc. is assembled into a series with their peripheral parts elastically and in contact with each other, so that they can resist the inertia force of the rocket and other external forces, and the environmental temperature B
When the propellants 9, 10, etc. contract due to l changes, etc., in this case, both end faces of each & propellant are tried to be shaped into a concave shape, but the buffer plates 15, 16, etc. Since it follows and separates, excessive thermal stress is not generated. At the same time, the annular protrusions 7c, 8c, etc. bend inward due to the above deformation, so that the peeling force generated between them and the short cylindrical bodies 3, 4 is alleviated.

On the other hand, Hiroto Honde developed and proposed it earlier (Japanese Unexamined Patent Publication No. 56
-82834) The insulator is designed to reduce the above-mentioned disappearance rate (ablation rate) by increasing the thermal decomposition temperature, and an example of this is that the above-mentioned asbestos is mixed with 70 needles of in-prene rubber (IR). For example, 40 parts by weight of asbestos is mixed with ethylene propylene rubber (EPDM) Ic.

These insulators have a low ablation rate, so their thickness can be reduced, and since they contain a large amount of inorganic material such as asbestos, they have good adhesion to metals, so they can be easily inserted between the motor case and the motor case. This is intended to improve the filling efficiency of the propellant by omitting the adhesive medium layer and the like.

Since the insulator has higher hardness and tensile strength than the conventional insulator, the propellant contained therein is held relatively rigidly.

Although the above-mentioned soft structure can be used to connect segments using such insulators, the above-mentioned points make the use of such a flexible structure less meaningful, and rather, the loose hook plate and sealing member have a smaller volume than the required volume. In order to occupy the tj, the tj becomes O, which is not suitable for the intention of improving the filling efficiency.

Therefore, the 71st idea of the present invention is to combine the above-mentioned eight insulators into a series.

[Means of the present invention]

Based on the above background, the means of the present invention is to form an annular protrusion having a wedge-shaped cross section on the end face of that insulator in adjacent segments, and to form an annular protrusion that fits the annular protrusion around the other insulator. The insulator is integrated by forming grooves and abutting and bonding these annular projections and the existing grooves.

[Effect]

According to the above means, even if the Ej of the insulator is small, the necessary and sufficient N blood protection can be ensured by the wedge-shaped abutment surface between the annular projection and the annular disease, and the wedge-shaped fitting In the process of mating and mating between the surfaces, the adhesive is removed from between the two surfaces, making it possible to make the adhesive layer extremely thin and to reduce the peeling force that occurs as the insulator contracts. is counteracted by the shearing force of the adhesive layer, so high adhesive strength can be obtained. While the propellant is thus firmly held by the integrated insulator 4C, the deformation is allowed for each segment.

〔Example〕

In FIG. 1, the rocket motor 20 of this embodiment has a body with three seven-arm parts (rear, middle, and front parts) 30.
．． Divided into 40 and father, 21 digit rear segment 30
Km is the connected rear closure, 22 is its inner liner, n is the ronat/sle attached to this closure, 24
is a forward closure fastened to the front segment 50.

Since each segment has almost the same configuration, we will take the middle segment 40 as a representative, and the rear and front seven segments).
For the corresponding parts of 0 and 50, the 7th symbol will be written within 0 below.

In this segment, 41 (31, 51) is a seasonal n-body,
42 (32, 52) is the relatively hard insulator 42a (32a, 52) which is directly attached to the short cylindrical body ve.
a) is an inner surface layer constituting the inner Wj portion of this insulator, and this inner surface R4 is made of natural rubber or the like and serves as the adhesive medium for the propellant.1. It has an appropriate thickness to relieve the stress of the propellant. 43 (33,
53) is an internal combustion type propellant filled in the insulator, 43a (33a, 53a) is its inner hole, and the propellant is a composite type propellant containing polyurethane, polybutadiene, etc. as a binder. . 44 (34,
54) Company name: t# illegal drug l7iI end face restrictor,
It is molded integrally with the insulator from the same material as the insulator 42 (32, 52). 45 (35
, 55) is a rear end face restrictor, the material of which is a mixture of the binder of the propellant and a filler such as carbon black.

Here, the propellant loading process will be explained using segment 4Q as an example. First, l1i is preformed on the inner surface of the short cylindrical body 41.
The insulator 42 with the I end face restrictor M is adhered, and a primer is applied to the inner surface of this molded body. The short cylinder 41 is placed on the base of the loading device with the front end face rest lifter M facing down, and a core corresponding to the inner hole 43a is erected. Using a conventional method, the propellant slurry is poured into a predetermined area and allowed to harden.

The upper end face of the propellant is formed as necessary, and a binder containing mJ filler is poured therein, poured, and applied thickly and hardened to form the front end face rest lifter 45.

For the front segment 50, the forward closure 24 can be attached prior to the above-mentioned loading process, and after the front end face rest lifter 54 is adhered to this closure, the slurry can be cast.

FIG. 2 shows details of the segment 30 and sum combination structure. Reference numerals 36 and 46 denote the 1l11 end face of the insulator 32 and the rear end face of the insulator 42, respectively, and before joining, these end faces are made to protrude from the end faces of the short cylinders 31 and 41 within the range of the clearance compression allowance allowed for the insulator. It is desirable to keep it. 47 above rear end surface 4
An annular protrusion formed near the outer periphery of the annular protrusion 6 has a trapezoidal wedge-shaped cross section, and an annular groove formed between the end faces of the annular protrusion facing the annular protrusion.
70 and 26 are bolts and nuts for fastening, and 31a and 41a are short cylindrical bodies 31 and 41, respectively. The fastening flanges 57 and 48 (FIG. 1) are annular protrusions and annular grooves formed on the end faces of the insulators 52 and 42, respectively, and are formed in the same way as the protrusions 47 and grooves described above.

The rocket motor is assembled as follows.

Apply adhesive to the rear finger face rest lifter 35 of the rear segment (equipment) and the liner n of the rear closure 21 to tie them together, and install them in the assembly tower with the nozzle facing down. The middle seventh segment 40 is brought directly above it, and adhesive is applied to the annular projection 47 and the annular groove 38. In this case, in the next fastening process, the m adhesive
For 611I, the amount of application is controlled so that even if it leaches out, it does not spread between the restrictors M and 45. Next, the segment)
While gradually lowering the bolt 40, it abuts against the rear seven-piece bolt 30, and is fastened with the bolt and nut δ, 26. In this process, the annular protrusion 4T and the annular fII 438,
A snug fit is achieved based on the compression distance while eliminating excess adhesive. In the same manner, the front segment group with the forward closure 24 described above is fastened.

Since the embodiment is as described above, the insulators are
These and the motor case are firmly integrated, and each propellant is stably held by the insulator. When the propellant is about to deform as described above, the end face lifter, 45, and the
The inner surface layer 32a is separated by 55 following the curve.

42a and 52a are interposed between the relatively hard rest lifter main body and exert a buffering effect, so that the internal stress generated in the propellant is alleviated.

Further, in the embodiment, the front end face restrictors 44 and 54 are formed integrally with the insulator, so the structure is simple and the peeling resistance is excellent.
5, 45, and 55 are formed by pouring or bonding using a material similar to that of the propellant binder, so that good bonding can be achieved due to their compatibility without using any adhesive. Overall, the propellant and the rest lifter are completely and firmly integrated, so even if the outer periphery of the propellant is held relatively rigid, concerns such as separation from the propellant can be easily resolved, and , since the number of parts and the bonding process can be reduced, the (J-sensitivity) can be increased accordingly.

〔effect〕

As explained above, even if the present invention is a segment-coupled rocket, the insulator is substantially integrally formed on the inner surface of the motor case, so the coupling structure is simple and no extra space is required. This can further contribute to improving the propellant charging efficiency.

[Brief explanation of the drawing]

FIG. 1 is an overall sectional view of a rocket motor showing one embodiment of the present invention, FIG. 2 is an enlarged sectional view of the main part of FIG. 1, and FIG. K3 is a sectional view of the main part showing a conventional coupling structure. 30, 40, 50... segment, 31, 4
1, 51... short cylinder body, 32, 42, 52...
... Insulator, 47, 57... Annular projection,
38, 48... annular groove.

Claims (1)

[Claims] In a rocket motor in which an insulator is attached to the inner surface of a short cylindrical body and a propellant is loaded inside the insulator, segments are successively abutted and connected. A segment-coupled rocket motor in which a wedge-shaped annular projection is formed, an annular groove that fits the annular projection is formed on the end face of the other insulator, and these annular projections and the existing groove are abutted and bonded.