RU2114370C1 - Rocket launching pack - Google Patents

Abstract

FIELD: rocketry, applicable in transport-launching packs intended for storage, transportation and launching of rockets. SUBSTANCE: pack has a cylindrical body with a releasable cover fastened to it. The inner side of the cover has bulges, the distance between which exceeds the dimension of the rocket nose cone in the plane perpendicular to its longitudinal axis in length equal to the depth of the cavity formed by the bulges jointly with the cover central part. The pack body and cover have grooves facing each other and accommodating an elastic ring with a cut-out and chamfer engageable with the chamfer made in the body groove. A leaf spring is positioned against the cover bulges, one end of this spring is positioned in the cut-out of the elastic spring through the slot made in the cover, its lateral surfaces are engageable with the ring ends, and the other end is rigidly fixed outside the cavity on the cover inner surface that is most distant from the slot. EFFECT: reduced disturbing action on rocket at launching, reliable storage. 4 dwg

Description

 The invention relates to rocket technology and can be used in the construction of transport and launch containers designed for storage, transportation and launch of missiles.

 In many container designs, the opening of the front cover is made by a moving rocket.

 There are various designs of automatically opening containers, for example, a tube for storing and launching missiles [1], containing a tube closed in front by a hood that can break down into a certain number of parts when the head of a rocket hits it, as well as a container for transporting and launching ATGMs [2] ], comprising a housing closed in front by a lid that is pierced by a moving rocket.

 The disadvantage of these structures is the significant disturbance received by the rocket upon exiting the container due to a collision with the lid, which is inevitable when the latter is destroyed.

 In addition, the container does not provide reliable protection of the rocket from mechanical stresses, since it is possible to destroy the lid with an occasional minor mechanical impact, since the lid is made of a material with deliberately set low strength characteristics.

 Also known are designs with automatically resettable covers, for example, device [3], in which the cover is knocked out of the container by a moving rocket.

 The disadvantage of this design is the need for significant effort to undock the lid and the container body and the presence of a rocket hit on the lid, which is inevitable when the lid is separated from the body, which leads to significant disturbing effects on the rocket in the initial phase of flight, causing significant dispersion of the rockets during firing. Reducing the disturbing effect on the rocket is possible by reducing the effort of undocking and reducing the mass of the cover.

 Technical solutions are also known in which the reduction of the disturbing effect on the rocket is achieved by reducing the undocking force. Such designs include, for example, a rocket launching device [4], which is a prototype of the invention and contains an open hollow cylindrical container, a front cover that closes the front opening of the container with the possibility of separation from it under the action of a pressure wave arising inside the container, a hook, one the end of which is pivotally attached to the central part of the front cover, and the other is coupled to the container wall with the possibility of disengagement with it after turning the hook at a certain angle.

 The disadvantage of this technical solution is that a pressure wave arising inside the container is used to open the lid. This requires the use of a sufficiently rigid and strong cover, eliminating the possibility of its deformation and destruction, since deformation can lead to loss of operability of the hinge and, therefore, interaction between the hook and the cover when opening the latter, and low strength - to destruction of the cover and the occurrence of additional disturbances from the expansion of its parts.

 An increase in the rigidity and strength of the lid (for example, by installing additional stiffeners or increasing the wall thickness) leads to an increase in its mass, which, in turn, leads to an increase in the disturbing effect on the rocket. In addition, the presence on the lid of the hook, hinge and elements of their fastening leads to an increase in the mass of the detachable lid, which also leads to an increase in the disturbing effect on the rocket.

 The aim of the invention is to reduce the disturbing effect on the rocket by reducing the mass of the opening cover while maintaining its strength characteristics.

 To achieve this goal, in a known container for launching a rocket containing a cylindrical body with a front resettable lid fixed thereon, protrusions are made on the inside of the lid, the distance between which is larger than the size of the head of the rocket in a plane perpendicular to its longitudinal axis at a length equal to the depth of the cavity formed by protrusions together with the central part of the lid, grooves are made opposite each other on the container body and the lid, into which an elastic ring with a cut and chamfer is installed d, in contact with the chamfer made in the groove of the housing, with a belt spring located opposite the protrusions of the lid, one end of which is placed in the neckline of the elastic ring through the groove made on the lid, contacting the ring ends with its side surfaces, and the other end is rigidly fixed outside the cavity on the inner surface of the lid farthest from the groove.

 Such a constructive solution provides a reduction in the disturbing effect on the rocket from the opening lid due to a decrease in its mass, since fixing the lid along the entire contour of the container body reduces the requirements for its stiffness, which leads to a decrease in the mass of the lid while maintaining its strength characteristics. The location of the protrusions in the Central part of the cover is achieved by reducing the deflection of the tape spring by the head of the rocket, necessary for the complete exit of its loose end from the cutout of the ring. This allows you to reduce the height of the cover and, consequently, the mass. The distance between the protrusions and their height are determined from the need to place the head of the rocket during its interaction through a curved tape spring with a cover.

 Comparison of the claimed technical solution with the prototype made it possible to establish its compliance with the criterion of "novelty." When studying other well-known technical solutions in this technical field, signs that distinguish the claimed solutions from the prototype were not identified, and therefore they provide the claimed technical solution with the criterion of "inventive step".

 In FIG. 1 shows a container with a rocket; in FIG. 2-4 - fastening the lid to the container body: in FIG. 2 - node I in FIG. one; in FIG. 3 - node II in FIG. one; in FIG. 4 is a section AA in FIG. 3.

 The proposed container for launching a rocket comprises a housing 1, a cover 2, a seal 3 located between the housing 1 and the cover 2, and a rocket 4 mounted inside the container (Fig. 1). On the case 1 and the cover 2 opposite each other, grooves "a" and "b" are made, respectively, in which an elastic ring 5 is installed with a notch "c" and a chamfer "g" in contact with the chamfer "d" made in the groove "a" on the housing 1 (Fig. 2-4). On the inner side of the lid 2, protrusions "e" are made, which together with the wall "g" of the lid 2 in its central part form a cavity "and". Opposite the protrusions “e” there is a belt spring 6, one end of which is screwed outside the cavity “and” on the inner surface of the cover 2 with a screw 7 (Fig. 1), and the other end is placed in the groove “k” on the cover 2 (Fig. 3) in the cutout "in" of the ring 5, the ends "l" of which are in contact with the side surfaces "m" of the spring 6 (Fig. 4).

 Opening the lid in the container is as follows.

 When the rocket 4 moves, its nose rests against the belt spring 6 and causes it to bend into the cavity "and" relative to the protrusions "e" on the cover 2. This leads to the displacement of the loose end of the spring 6 in the groove "to" of the cover 2 until it completely leaves the cutout "in" of the ring 5 and the lateral surfaces "m" of the spring 6. Continuing the movement, the rocket 4 through the spring 6 acts on the cover 2, which through the ring 5 acts on the body 1 of the container. Due to the force created by the rocket 4 on the cover 2, and the interaction between the chamfers "g" and "d" on the ring 5 and in the groove "a" of the housing 1, the ring 5 is compressed and removed into the groove "b" on the cover 2, which under the force generated by the rocket 4 and the belt spring 6 is separated from the housing 1 and opens the container for the exit of the rocket 4.

 Thus, in the proposed technical solution, in comparison with the prototype, the disturbing effect on the rocket is reduced by reducing the mass of the opening lid while maintaining its strength characteristics, which is confirmed by experimental development of the design. The audit showed that the container for launching a rocket is operational in combat use and reliably protects the rocket inside it from mechanical and climatic influences during storage and transportation.

Claims (1)

 A missile launch container, comprising a cylindrical body with a front resettable lid fixed on it, characterized in that protrusions are made on the inside of the lid, the distance between which is larger than the size of the rocket’s head in a plane perpendicular to its longitudinal axis, at a length equal to the depth of the cavity, formed by the protrusions together with the central part of the lid, on the container body and the lid are made one opposite the other grooves, in which an elastic ring with a cut and a chamfer is installed, in contact with an apron made in the groove of the housing, with a belt spring located opposite the protrusions of the cover, one end of which is placed in the neckline of the elastic ring through the groove made on the cover, contacting the ends of the ring with its side surfaces, and the second end is rigidly fixed outside the cavity on the inner surface of the cover, most distant from the groove.

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