RU2323138C1 - Unit for coupling two parts of rocket - Google Patents

Abstract

FIELD: rocketry; small-caliber rockets and rocket parts.

SUBSTANCE: proposed unit includes two telescopically connected bushes and locking member made in form of split spring-loaded ring of round section. Diameter of ring section is dictated by uncoupling force. Outer bush is provided with trapezoidal groove at bevel angle of 25-30 deg.; inner bush is provided with rectangular groove for placing the split spring-loaded ring in sunken state.

EFFECT: enhanced reliability of coupling without access to joint; automatic uncoupling under action of pressure at preset load during preset period of time; low cost of manufacture of unit.

2 dwg

Description

The invention relates to rocket technology and can be used in the construction of small-caliber rockets to connect the stages and components of the rocket.

A known knot of docking of two parts of the rocket, separated under the action of pressure, containing a fixing element in the form of an annular expandable collet (see patent No. 2127862 - prototype).

The disadvantages of the prototype are the technological complexity of manufacturing and the high cost of the fixing element (ring collet).

The technical task of this invention is to reduce the material consumption, the complexity and cost of manufacturing the fixation element when all the requirements for joining two missile parts without access to the docking place, their reliable connection when exposed to operational loads and undocking in the permitted area of effort and time are met.

The technical result is achieved by the fact that in the junction of the two parts of the rocket containing two telescopically connected bushings with a locking element, the latter is made in the form of a split spring ring of circular cross section, while the outer sleeve is provided with a trapezoidal groove with a bevel angle of 25 ÷ 30 ° and a chamfer, and the inner sleeve is provided with a rectangular groove for accommodating the snap ring in a recessed state.

Figure 1 presents a drawing of the claimed docking station, which indicates the following positions:

1 - outer sleeve, 2 - inner sleeve, 3 - split spring ring.

Figure 2 presents the element of fixation.

Here are also indicated:

α is the bevel angle of the trapezoid groove;

d is the diameter of the wire of the spring ring;

h is the cut width of the spring ring.

A feature of the work of the docking station is as follows. Docking is carried out by axial movement of the inner sleeve to automatically snap the spring ring into the trapezoidal groove with much less force than when undocking, due to the small angle of the entry chamfer.

Undocking occurs automatically when the undocking force is reached (from the action of internal or external pressure).

The magnitude of the undocking force is determined by the choice of the bevel angle α and the wire diameter d. The cut width of the ring h is determined for the ring in a recessed state.

The use of the invention allows to significantly reduce the complexity and metal consumption of the manufacture of the fixation element, simplify the technology and, in general, significantly reduce the cost of the docking station when all the requirements are met.

Claims (1)

The junction of the two parts of the rocket, which are separated under the action of pressure, including two telescopically connected bushings and a fixation element, characterized in that the fixation element is made in the form of a split circular spring ring with a diameter selected on the basis of the required undocking force, while the outer sleeve is equipped with a trapezoid a groove with a bevel angle of 25 ÷ 30 °, and the inner sleeve is provided with a rectangular groove to accommodate a split spring ring in a recessed state.

Images