RU2246093C1 - Two-stage bicaliber rocket - Google Patents

Abstract

FIELD: rocketry, applicable in the construction of two-stage bicaliber rockets provided with a device for separation of the electric lines of the rocket stages.

SUBSTANCE: the assembly of electric connection is fastened at an angle to the rocket longitudinal axis and provided with a rejecting device in the form of a hatch plate door made in the transient fairing, connected to the rejected connector block of the first stage.

EFFECT: enhanced reliability of the rocket.

3 dwg

Description

The present invention relates to the field of rocket technology and can be used in the construction of two-stage bicaliber missiles equipped with a device for undocking the electrical communications of the rocket stages.

Typically, the design of two-stage rockets requires electrical connection between the stages of the rocket, torn at the moment of undocking of the stages. For electrical connection of the stages of the rocket can be used in various electrical connectors used for electrical docking, for example rockets with a launcher or rockets with a launch container.

So, for example, in the device [1], the rocket (projectile) is connected to the launch container by an electric harness, which breaks when the rocket takes off.

The disadvantage of this device in relation to a two-stage rocket is the perturbations acting on the second stage of the rocket when the tow is broken.

The indicated drawback is deprived of the device for the electrical connection of the rocket with the launch container, equipped with electrical connectors with devices for undocking the connector pads at the time of rocket launch or before launch.

So, for example, in the device [2], which is the prototype of the present invention, one of the blocks of the electrical connector connecting the rocket to the launcher is placed radially in the recess of the rocket housing flush with its outer surface, and the response block is docked with it and equipped with a pyrotechnic disconnect device electrical connector pads before launching a rocket.

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

- the described device provides only the undocking of the blocks of the electrical connector and does not allow the removal of the undocked block of the first stage, which with the relative movement of the stages can lead to disturbances of the second stage;

- the presence of a special device for undocking the electrical connector blocks, especially with the use of a pyrotechnic device and, therefore, the associated ignition and electrical circuits, significantly complicates the design and, accordingly, reduces reliability.

In addition, it must be borne in mind that it is most appropriate to place the electrical connector in the volume under the transitional fairing between the steps of the bicaliber rocket, and in this case, the radial undocked section of the electrical connector takes up a significant amount of space, which does not allow full use of the volume under the transitional fairing for rocket equipment elements, those. reduces performance.

The objective of the invention is to eliminate the aforementioned disadvantage of the described rocket device, namely, to increase reliability by simplifying the design and ensuring the removal of the undocked electrical connector block while increasing the net volume under the transitional fairing between the steps.

The problem is solved in that in a two-stage bicaliber rocket with an electric stage docking unit containing an electrical connector fixed in a recess of the second stage housing under the transitional fairing, the electric docking unit is fixed under the flange to the longitudinal axis of the rocket and is equipped with a retraction device in the form of a plate manhole cover made in transitional fairing connected to the outlet block of the electrical connector of the first stage.

The essence of the invention lies in the fact that in this two-stage bicaliber missile, the angular location of the electrical docking unit for the steps provides automatic undocking of the electrical connector blocks during the relative movement of the steps, while the device for removing the undocked block of the first stage is an aerodynamic extractor made in the form of a plate manhole cover located on transitional fairing over the electrical connector and rigidly connected to the outlet block of the electrical connector, which in general scrap simplifies the design and, consequently, increases reliability, and, in addition, this design allows you to place the electrical connector in the narrow front of the transitional fairing and, therefore, make more full use of the volume under the transitional fairing for rocket equipment elements.

The proposed device is illustrated by drawings, which show:

- figure 1 is a longitudinal section of the junction of the stages of the rocket through the electrical connector to the separation of the stages;

- figure 2 - the relative position of the elements of the device after undocking the pads of the electrical connector;

- figure 3 - the relative position of the elements of the device at the end of the separation of steps.

The proposed two-stage bicaliber missile consists of the first (starting) stage 1 (Fig. 1) and the second (marching) stage 2 of a smaller caliber, connected by a transitional fairing 3, rigidly connected to the first stage 1 and held by the separation mechanism 4 under the transitional stage 2. Under the transitional fairing 3 posted node electrical docking stages, containing the outlet block of the electrical connector 5, docked with the mating block 6, located in the inclined recess 7 of the second stage 2.

In the transitional fairing 3, a hatch 8 is made, closed flush with the outer surface of the fairing with a plate cover 9, rigidly connected by a screw 10 to the outlet block 5.

The operation of the device is as follows.

At the end of the operation of the engine of the first stage 1, the separation mechanism 4 is activated and the mechanical connection of stages 1 and 2 is destroyed. Under the influence of the aerodynamic flow, the first stage together with the transition fairing 3 begins to move relative to the second stage 2, undocking the pads 5 and 6. At the same time, the inclined wall 11 recesses 7, acting on the block 5, makes it, together with the cover 9, overcoming the resistance of the incoming flow, rotate relative to the rear wall 12 of the hatch 8 until a positive angle of attack 13 (figure 2), after which the lid 9 together with the block 5 is extracted by the stream to its extreme rear position (figure 3).

Thus, in the proposed technical solution, in comparison with the prototype, reliability is improved by simplifying the design by eliminating the special device for undocking the electrical connector blocks, as well as by ensuring the removal of the uncoupled electrical connector blocks of the first stage, while improving performance.

Sources of information:

1. Application of France No. 2301802, publ. 10/22/1976, class F 42 B 15/04 - analogue.

2. US Patent No. 3249012, publ. 05/03/1966, class 89-1.7 - prototype.

Claims (1)

A two-stage bicaliber rocket with an electric docking unit for steps containing an electrical connector fixed in the recess of the second stage housing under the transitional fairing, characterized in that the electrical docking unit is fixed at an angle to the longitudinal axis of the rocket and equipped with a retraction device in the form of a plate manhole cover made in the transitional fairing connected to the outlet block of the electrical connector of the first stage.

Images