RU2767228C1 - Method of separating aircraft elements - Google Patents

Abstract

FIELD: aviation; rocket engineering.SUBSTANCE: invention relates to methods of separating structural elements, mainly rocket stages, and can be used in aircraft and rocket engineering. Method of separating elements of aircraft involves making power flanges of mating elements, rod installed in sleeve of retaining inserts, and housing, in which pyrocartridge is installed. At that, the inner cavity of the housing is made in the form of a two-stage cylinder, on one of the stages of which a transition cylinder is rigidly fixed, in which a sleeve is installed with the possibility of movement along the longitudinal axis of the housing, which is a hollow rod, one end of which is made in the form of a piston with a cover, enclosing the transition cylinder and enclosed by the housing, and the other end is made in the form of a piston enveloped by a transition cylinder and a housing. Adapter cylinder thrust against the sleeve piston enveloped by it is provided through a spring, and the cavity between the transition cylinder and the sleeve piston enveloping it is interconnected with the pyrocartridge. At that, the sleeve piston stroke along the transition cylinder has a smaller value than the sleeve piston stroke along the two-stage cylinder of the housing, gas cavities between sleeve pistons communicate via throttling holes made in adapter cylinder. Rod enveloped by the sleeve is made in the form of a tightening bolt with a thrust on the body through a conical bushing. In the body of the tightening bolt there is an annular groove with a conical side wall located on the side opposite to the direction of bolt tightening. Thrust part of the head of the tightening bolt is made in the form of separate retaining inserts, which are partially immersed into the groove of the body of the tightening bolt. Retaining inserts are shaped to the submerged part identical to the shape of the groove of the body of the tightening bolt. At the same time surfaces of interaction of retaining inserts with the sleeve are made conical along the entire length of the sleeve stroke with a taper angle not exceeding the friction angle. Also, the tail part of the tightening bolt body is equipped with a crimping locking gate, which is made in the form of a stepped cylindrical bushing, with provision of support at the end of its movement against the protrusion, which is made in the sleeve, and further squeezing by retaining inserts during return movement of the sleeve.EFFECT: proposed invention — aircraft elements separation method — provides separation pusher functions, which allows improving reliability of aircraft and reducing its weight, and availability of pyro-gas damping of moving elements reduces characteristics of vibration impact.1 cl, 3 dwg

Description

The invention relates to methods for separating structural elements, mainly rocket stages, and can be used in the field of aviation and rocket technology.

The closest technical solution, chosen as a prototype, is a device for separating elements of a spacecraft - patent RU 2144892, containing a housing with a squib installed in it, a sleeve, a rod and liners with support collars, equipped with a membrane rigidly fixed inside the housing, on the shank of which rod, and in the body on the side of the membrane there is a spherical surface, while the distance from the membrane to the beginning, on the side of the rod, of the spherical surface exceeds the width of the support flanges of the stem liners, and the separable elements are fixed on the tail part of the sleeve.

The common essential features of the prototype - a device for separating elements of a spacecraft, coinciding with the essential features of the proposed method are the following: the method includes the manufacture of power flanges of the joined elements, a rod installed in the sleeve of the retaining liners, and a housing in which the squib is installed.

A feature of the well-known prototype system is that this device for separating spacecraft elements implies the presence of separation pushers, which are separate structural elements, the presence of which reduces the reliability of the aircraft and increases its mass, and the deformation of the membrane along the spherical surface of the body in a closed volume increases the vibration impact characteristics .

The present invention - a method of separating the elements of the aircraft provides the functions of the separation pusher, which makes it possible to increase the reliability of the aircraft and reduce its weight, and the presence of pyro-gas damping of the moving elements reduces the characteristics of the vibration impact.

To achieve the above technical result, the method of separating the elements of the aircraft includes the manufacture of power flanges of the joined elements, a rod installed in the sleeve of the retaining liners, and a housing in which a squib is installed, while the internal cavity of the housing is made in the form of a two-stage cylinder, on one of the stages of which it is rigidly a transfer cylinder is fixed, in which a sleeve is installed with the possibility of movement along the longitudinal axis of the body, which is a hollow rod, one end of which is made in the form of a piston with a cover, covering the transfer cylinder and covered by the body, and the other end is made in the form of a piston covered by the transfer cylinder and the body, the stop of the transition cylinder in the sleeve piston covered by it is provided through a spring, the cavity between the transition cylinder and the sleeve piston covering it is connected to the squib, while the piston stroke of the sleeve along the transition cylinder is less important than the stroke of the piston the sleeves on the two-stage cylinder of the body, and the gas cavities between the pistons of the sleeve communicate through the throttle holes, which are made in the transition cylinder, the rod covered by the sleeve is made in the form of a draw bolt, with emphasis on the body through a conical bush, in the body of the draw bolt, an annular groove with a conical with a side wall located on the side opposite to the direction of tightening the bolt, the thrust part of the head of the tightening bolt is made in the form of separate retaining inserts, which are partially immersed in the groove of the tightening bolt body, the retaining inserts are shaped into the immersed part, identical to the shape of the groove of the tightening bolt body, while the surface the interaction of the retaining inserts with the sleeve is made conical along the entire length of the sleeve stroke, with a taper angle not exceeding the angle of friction, also the tail part of the body of the tightening bolt is provided with a crimp locking gate, which is made in the form of a stepped cylindrical sleeve, with ra at the end of its movement into the protrusion, which is performed in the sleeve, and further compression with retaining liners, during the return movement of the sleeve.

A distinctive feature of the proposed method for separating the elements of an aircraft is that the internal cavity of the body is made in the form of a two-stage cylinder, on one of the steps of which a transition cylinder is rigidly fixed, in which a sleeve is installed with the possibility of moving along the longitudinal axis of the body, which is a hollow rod, one the end of which is made in the form of a piston with a cover, enclosing the transition cylinder and covered by the body, and the other end is made in the form of a piston, covered by the transition cylinder and the body, the stop of the transition cylinder in the sleeve piston covered by it is provided through the spring, the cavity between the transition cylinder and the piston covering it sleeves communicate with the squib, while the piston stroke of the sleeve along the transition cylinder is less important than the stroke of the pistons of the sleeve along the two-stage cylinder of the body, and the gas cavities between the pistons of the sleeve communicate through the throttle holes that are made in the transition cylinder the core, the rod covered by the sleeve is made in the form of a draw bolt, with emphasis on the body through the conical bushing, in the body of the draw bolt an annular groove is made with a conical side wall located on the side opposite to the bolt tightening direction, the thrust part of the head of the draw bolt is made in the form of separate retaining liners, which are partially immersed in the groove of the body of the draw bolt, the holding liners are shaped into the immersed part, identical to the shape of the groove of the body of the draw bolt, while the surfaces of interaction of the holding liners with the sleeve are tapered along the entire stroke length of the sleeve, with a taper angle not exceeding the friction angle, also the tail part of the draw bolt body is provided with a crimp locking gate, which is made in the form of a stepped cylindrical bushing, with a stop at the end of its movement in the protrusion, which is made in the sleeve, and further compression by holding liners, during the return movement of the sleeve.

Due to the presence of these distinguishing features in combination with the known ones, the following is achieved: the presence of pyro-gas damping of moving elements reduces the characteristics of vibration impact, and the absence of compartment pushers as separate structural elements makes it possible to reduce the number of actuators with an increase in the reliability of the aircraft and a decrease in its weight.

This method can be implemented as a docking unit for rocket stages, compartments, warheads and other payloads that need to be separated during the flight.

The invention is illustrated in Fig.1...3:

Figure 1 shows a method for separating the elements of an aircraft in a holding configuration.

Figure 2, shows a method of separating the elements of the aircraft in a undocked configuration.

In Fig.3, sec. A-A (figure 1), holding inserts are presented.

The method of separating the elements of the aircraft shown in figure 1...3 includes the manufacture of power flanges 1 and 2 (figure 1) of the joined elements, the rod 3 (figure 1, figure 3) installed in the sleeve 4 (figure 1, figure .3) retaining inserts 5 (Fig.1, Fig.3), and housing 6 (Fig.1, Fig.3), in which the squib 7 (Fig.1) is installed, while the internal cavity of the housing is made in the form of a two-stage cylinder , on one of the steps of which a transition cylinder 8 (Fig.1) is rigidly fixed, in which a sleeve is installed with the possibility of moving along the longitudinal axis of the housing, which is a hollow rod, one end of which is made in the form of a piston 9 (Fig.1) with a cover 10 (figure 1), covering the transition cylinder and covered by the body, and the other end is made in the form of a piston 11 (figure 1), covered by the transition cylinder and the body, the stop of the transition cylinder in the sleeve piston covered by it is provided through the spring 12 (fig.1 ), the cavity 13 (figure 1) between the transition cylinder and covering its piston liners communicate with the squib, while the stroke 1 (figure 1) of the piston of the sleeve along the transition cylinder is less important than the stroke L (figure 1) of the pistons of the sleeve along the two-stage cylinder of the housing, and the gas cavities between the pistons of the sleeve communicate through the throttle holes 14 (figure 1), which are performed in the transition cylinder, the rod covered by the sleeve is made in the form of a tightening bolt, with emphasis on the body through the conical sleeve 15 (figure 1), an annular groove 16 is made in the body of the tightening bolt (figure 1) with With a conical side wall located on the side opposite to the direction of tightening the bolt, the thrust part of the head of the tightening bolt is made in the form of separate retaining inserts, which are partially immersed in the groove of the tightening bolt body, the retaining inserts are shaped into the immersed part, identical to the shape of the groove of the tightening bolt body, while surfaces 17 (figure 1) of the interaction of the retaining liners with the sleeve are conical along the entire stroke length L of the sleeve, with an angle of value not exceeding the angle of friction, also the tail part of the body of the tightening bolt is provided with a crimp locking gate 18 (figure 1), which is made in the form of a stepped cylindrical sleeve, with a stop at the end of its movement in the protrusion 19 (figure 1), which is performed in sleeve, and further compression with retaining liners, during the return movement of the sleeve.

The method of separating the elements of the aircraft works as follows: when an electrical signal is applied to the squib, in the cavity between the transition cylinder and the sleeve piston surrounding it, an excess gas pressure occurs, which sets the sleeve in motion, thereby removing the rod tightening torque. When the sleeve is moved to stroke 1, the excess gas pressure also sets in motion the stem, with a compression locking valve installed on it, as a result of which the flanges of the joined elements are separated, while the retaining liners move smoothly along the conical surface of the sleeve and the stem. When the sleeve is moved to stroke L, the joint is finally released, the stem extends beyond the body, and the crimp locking gate at the end of its stroke abuts against the protrusion and is crimped by the retaining liners along the outer diameter during the reverse movement of the sleeve. Throttle holes serve to connect the gas cavities between the pistons of the sleeve, providing its gas damping.

Claims (1)

A method for separating the elements of an aircraft, including the manufacture of power flanges of the joined elements, a rod installed in the sleeve of the retaining liners, and a housing in which a squib is installed, characterized in that the internal cavity of the housing is made in the form of a two-stage cylinder, on one of the stages of which a transition is rigidly fixed a cylinder in which a sleeve is installed with the possibility of movement along the longitudinal axis of the body, which is a hollow rod, one end of which is made in the form of a piston with a cover, covering the transition cylinder and covered by the body, and the other end is made in the form of a piston covered by the transition cylinder and the body , the stop of the transfer cylinder in the sleeve piston covered by it is provided through a spring, the cavity between the transfer cylinder and the sleeve piston covering it is connected to the squib, while the stroke of the sleeve piston in the transfer cylinder is less important than the stroke of the sleeve pistons in a two-stage cylinder the inside of the body, and the gas cavities between the pistons of the sleeve communicate through the throttle holes, which are made in the transition cylinder, the rod covered by the sleeve is made in the form of a draw bolt with emphasis on the body through a conical bush, an annular groove is made in the body of the draw bolt with a conical side wall located with on the side opposite to the direction of tightening the bolt, the thrust part of the head of the tightening bolt is made in the form of separate retaining inserts, which are partially immersed in the groove of the tightening bolt body, the retaining inserts are shaped into the immersed part, identical to the shape of the groove of the tightening bolt body, while the interaction surfaces of the retaining inserts with the sleeve the sleeves are made tapered along the entire stroke length with a taper angle not exceeding the friction angle, and the tail part of the body of the tightening bolt is also equipped with a crimp locking gate, which is made in the form of a stepped cylindrical sleeve, with a stop at the end of its movement into the protrusion, which which is performed in the sleeve, and further compression by holding liners during the return movement of the sleeve.

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