RU2302600C1 - Two-stage missile in launching pack - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: the two-stage missile in a launching pack has an intermediate fairing, an electric connector located on the missile and coupled to the pack, and a spring device for disconnection of the electric connector blocks. The electric connector is located under the intermediate fairing behind one of the wings in the plane of its symmetry. A through radius slot for the withdrawable part of the blocks with the rear wall of the slot is made of the intermediate fairing above the point of out-let of the electric connector. The missile is provided with a rotary panel consisting of a laminated cover and one end of the lever rigidly coupled to it, whose other end is hinge-fastened on the rear edge of the wing. The cover inner surface is made as the mating outer surface of the intermediate fairing in the point of outlet of the radial slot from it and the equitant outer surface of the missile body in the point of outlet of the electric connector from it.

EFFECT: enhanced reliability of the missile.

5 dwg

Description

The present invention relates to the field of rocket technology and can be used in the construction of two-stage missiles equipped with a device for undocking the electrical communications of the rocket with a transport-launch container (TPK).

A device for connecting a launcher with a missile mounted on it, in which one of the pads of the electrical connector connecting the missile to the launcher, is placed flush in the rocket housing with its outer surface and is equipped with a pyrotechnic device for undocking the pads of the electrical connector before launching the rocket [US patent No. 3249012, publ. 05/03/1966, NKI 89-1.7.].

The disadvantage of this device is its low reliability, because:

- it provides only the undocking of the pads of the electrical connector and does not provide the removal of the undocked pad of the launcher from the path of movement of the glider elements of the rocket moving along the launch tube, which can lead to jamming of the rocket in the TPK pipe and its loss;

- the presence of a special device for undocking the pads of the electrical connector, especially with the use of a pyrotechnic device, and, therefore, the accompanying ignition and electrical circuits, significantly complicates the design.

This drawback is eliminated in the rocket in the launch container selected by the prototype of the present invention, comprising an electrical connector located on the rocket connected to the container by an electric harness, and a device for undocking the electrical connector blocks, in which the undocking device is located in the longitudinal plane of symmetry of the rocket and is made in the form two symmetrically located torsion springs mounted on an axis in the recess of the container body, each of which has one end connected to the body teiner, and the other is made L-shaped, located perpendicular to the longitudinal axis of the rocket between the container body and the rocket, with a shoulder bent in the direction of movement of the rocket and rigidly connected to the electrical connector block, while the recess in the container body is made in the direction of the rocket nose according to the dimensions of the device for undocking with the undocked block of the electrical connector [patent RU No. 2247919 of 03/10/2005, IPC ⁷ F41F 3/055].

Moreover, as can be seen from the description and drawing of the specified device, it is intended for sub-caliber rockets, which, as a rule, are two-stage, that is, equipped with an accelerating engine and, accordingly, a transitional fairing between the stages.

The design of the prototype provided increased reliability by eliminating the possibility of jamming of the undocked electrical connector block in the launch tube by rocket glider elements, mainly an accelerating engine, as well as simplifying the design by combining the uncoupling device for the electrical connector blocks of the undocking and removal of the undocked shoe.

The disadvantage of the described device, however, is its lack of reliability, due to the fact that:

- the hatch on the rocket body to accommodate the onboard electrical connector block is placed in front of the rocket wing, that is, in a place where, as a rule, the maximum bending moment acts on the glider in flight, and this weakening reduces the strength of the rocket body;

- there is no kinematic connection between the rocket body and the L-shaped end of the spring device for undocking the pads of the electrical connector, and the undocking of the blocks when the rocket moves along the TPK occurs only under the action of the elastic force of the shoulders of the L-shaped ends of the springs, which has a significant variation in magnitude;

- on the surface of the rocket body after launch, open contacts of the electrical connector blocks belonging to the rocket appear, which in flight can lead to contamination of them with electrically conductive particles, for example, powder combustion products, and is especially unacceptable for missiles flying at a high flight speed, since this kinetic heating of the surface of the rocket body will lead to carbonization of the electrical insulation between the contacts of the connector pads and it becomes electrically conductive, which causes the contacts to close, resulting in become a failure on-board equipment.

The objective of the invention is to increase the reliability of a two-stage rocket by increasing its strength, introducing a kinematic connection between the rocket and the device for undocking the electrical connector blocks and protecting the contacts of the onboard electrical connector blocks from the effects of kinetic heating from the incident flow at high flight speeds.

The solution to this problem lies in the fact that in a two-stage rocket in a launch container containing a transitional fairing, an electrical connector located on the rocket, connected to the container by an electric harness, and a spring device for undocking the pads of the electrical connector, located in the longitudinal plane of symmetry of the rocket and connected at one end with the container body, and the other, made L-shaped, rigidly connected to the block of the electrical connector, the electrical connector is located under the transitional a leaking behind one of the wings in the plane of its symmetry, while in the transitional fairing above the outlet of the electrical connector, a through radial groove is made for the outlet part of the device for undocking the pads with the back wall of the groove provided with a bevel in the direction of the rear end of the transitional fairing, made with the possibility of interaction with a spring device during undocking, moreover, the rocket is equipped with a rotary shield consisting of a plate cover and rigidly connected to it by one end of the lever, the other end of which It is hinged at the rear edge of the wing, and the inner surface of the lid is formed mating outer surface of the transition fairing in place of exit from the radial groove and an outer surface equidistant rocket body at the site of exit from the electric connector.

The location of the electrical connector under the transitional fairing behind one of the wings of the rocket allows you to make the hatch for the pads onboard connector of the rocket behind the wing, that is, to weaken the body of the rocket in a place where there is a much smaller bending moment.

The implementation in the transitional fairing through radial groove under the outlet part of the device for undocking the pads of the electrical connector ensures the passage of the outlet part of the specified device through the transitional fairing at the start of the rocket.

The implementation of the rear wall of the radial groove with a bevel in the direction of the rear end of the transitional fairing, interacting with the spring device during undocking, provides the kinematic connection of the rocket with the L-shaped end of the spring device for undocking the electrical connector blocks until the end of the undocking.

The implementation of the rocket with a rotary flap, consisting of a plate cover and rigidly connected with it by one end of the lever, the other end of which is pivotally mounted on the rear edge of the wing located in the plane of symmetry of the electrical connector, with the implementation of the inner surface of the cover with the possibility of interaction with the outer surface of the transitional fairing in place the exit of the radial groove protects the radial groove in the transitional fairing and, accordingly, protects the contacts of the undocked connector of the cancer electrical connector you from the effects of kinetic heating of air flow at the initial portion of the flight until the separation stages.

The implementation of the inner surface of the cover of the equidistant outer surface of the rocket at the exit point from the electrical connector provides contact protection on the mid-flight section of the flight.

The invention is illustrated by graphic materials, which show:

- figure 1 is a General view of a two-stage rocket in the launch container;

- figure 2 is a longitudinal section of the device to launch a rocket from TPK;

- figure 3 - the position of the elements of the device at the beginning of the movement of the rocket along the TPK;

- figure 4 - the position of the elements of the device at the start of the flight;

- figure 5 - the position of the elements of the device after the separation of the steps.

The proposed two-stage rocket installed in the TPK 1 (Fig. 1) consists of a marching stage 2 and a detachable engine 3 of a larger caliber, connected by a transitional fairing 4, rigidly connected to the engine 3, and holding the marching stage 2 of the separation mechanism 5.

In the recess of the body of the marching stage 2 behind the wing 6, a socket 7 of an electrical connector is installed.

In the transitional fairing 4, a through radial groove 8 is made, the output of which on the outer surface of the fairing 4 is closed by a rotary flap 9, consisting of a plate cover 10 and rigidly connected to it by one end of the lever 11, the other end of which is pivotally mounted on the rear edge of the wing 6 by the axis 12.

In the prelaunch position (figure 2), a two-stage rocket is electrically connected to the TPK with an electric harness 13 equipped with a plug 14 and a spring undocking device 15 connected to the TPK. The rotary flap 9 is thus set aside.

The radial groove 8 is provided with a bevel 16.

The operation of the device is as follows.

When launched from the container, the rocket, together with the electrical connector, moves forward, overcoming the force of elastic deformation of the shoulder 17 of the spring undocking device 15 until the moment (Fig. 3), at which the parts 7 and 14 of the electrical connector are undocked and the electrical communications of the rocket from the TPK and the fork 14 are undocked with a bundle 13 under the action of the bevel 16 of the radial groove 8 and using the undocking device 15 into the socket 18 TPK.

With the further movement of the rocket under the influence of the starting overload and the incoming air flow on the outer surface of the cover 10 of the rotary flap 9, the latter, turning on the axis 12, closes the exit point of the through radial groove 8 with the cover 10, the inner surface of which is made of the mating outer surface 19 of the transition fairing 4 in place the exit from it of the radial groove 8 and at the same time the equidistant outer surface 20 of the rocket body at the place of exit of the electrical connector, which protects the open after asstykovki socket contacts 7 for starting the flight portion (4).

After triggering the separation mechanism 5 and the separation of the engine 3 together with the transitional fairing 4, the shield 9 (Fig. 5) under the influence of the incoming flow, turning on the axis 12, closes the hole of the hatch 21 in the march stage housing, the supporting edges of which are made in the form of the cover of the shield 9, providing protection for the contacts of the socket 7 during the mid-flight portion of the flight.

Thus, the proposed device improves the reliability of a two-stage rocket by increasing its strength, introducing a kinematic connection between the rocket and the device for undocking the electrical connector blocks and protecting the contacts of the onboard electrical connector blocks from the effects of kinetic heating from the incident flow at high flight speeds.

Claims (1)

A two-stage rocket in the launch container, containing a transitional fairing, an electrical connector placed on the rocket, connected to the container by an electric harness, and a spring device for undocking the pads of the electrical connector, located in the longitudinal plane of symmetry of the rocket and connected at one end to the container body and the other made by -shaped, rigidly connected to the block of the electrical connector, characterized in that the electrical connector is located under the transitional fairing behind one of the wings the plane of its symmetry, while in the transitional fairing above the exit point of the electrical connector, a through radial groove is made for the outlet part of the device for undocking the pads with the rear wall of the groove provided with a bevel in the direction of the rear end of the transitional fairing, made with the possibility of interaction with the spring device when undocking, the rocket is equipped with a rotary shield consisting of a plate cover and one end of the lever rigidly connected to it, the other end of which is pivotally fixed to the rear Romke wing and the inner surface of the lid is formed mating outer surface of the transition fairing in place of exit from the radial groove and an outer surface equidistant rocket body at the site of exit from the electric connector.

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