RU2500591C1 - Aircraft compartment separation system - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering. Proposed system comprises fastener consisting of explosive bolts and guide pins, separator composed of air driven separation mechanism composed of gas cylinder, air pusher with rod with its lengthwise axis aligned with separable part lengthwise axis. Air cylinder rod is connected with piston by means of hinge and furnished with push yoke connected with said rod by hinge and equipped with at least two adjustable thrusts for contact with separable compartment spaced apart in symmetry about its centre of gravity. Said compartment has seat for yoke thrusts.

EFFECT: decreased shock load at compartment, higher reliability of separation, lower weight.

3 cl, 5 dwg

Description

The invention relates to aerospace engineering and is intended to separate from the aircraft (LA) compartment in a given direction.

The known separation system of the head of the aircraft, adopted for the prototype, which includes a fastening device consisting of explosive bolts and guide pins and a separation device in the form of a pneumatic separation mechanism with a central pusher ("Flight Theory and Ballistic Missile Design" I.N. Pentsak , "Engineering", Moscow, 1974, pp. 233 and 235). The pneumatic separation mechanism consists of an electro-pneumatic valve (starting device), a gas cylinder, holding studs and a pneumatic pusher. The rod of the pneumatic pusher abuts against the heel on the warhead, and its longitudinal axis coincides with the longitudinal axis of the warhead and rocket.

The essential features of the proposed system, which coincide with the features of the prototype, are the following: a fastening device consisting of bursting bolts and guide pins and a separation device in the form of a pneumatic separation mechanism consisting of a gas cylinder, a pyro valve (starting device), a pneumatic pusher with a rod, a longitudinal axis which coincides with the longitudinal axis of the detachable part.

The disadvantages of this prototype system are the following: when the head is attached to the body, there may be a gap between the pneumatic pusher rod and the thrust fifth on the head, which increases the shock load on the head, the presence of a central pneumatic pusher limits its use for separating various types of head parts (e.g. having a centrally located nozzle). In addition, after the operation of the explosive bolts and the descent of the head part from the guide pins, on the stroke length of the pneumatic cylinder rod due to the influence of external disturbances on the detachable head part, it is possible that it deviates from the specified separation direction. At the same time, the pneumatic cylinder rod is loaded with transverse forces from the side of the detachable head, which requires reinforcing the design of the rod, pneumatic cylinder and the separation device as a whole and, as a result, increasing the mass of the separation device. In addition, there is no adjustment of the stock exhibit in a given direction.

The technical result aimed at achieving the proposed separation system is to reduce the shock load on the detachable compartment (by improving the fixing conditions), the possibility of using different types of compartments (for example, having a centrally located nozzle) to separate from the aircraft, and increasing the reliability of separation from the aircraft compartment in a given direction, reducing the mass of the compartment separation device.

To solve this problem, in the separation system of the aircraft compartment, containing a fastening device consisting of bursting bolts and guide pins and a separation device in the form of a pneumatic separation mechanism consisting of a cylinder with gas, a pneumatic pusher with a rod, the longitudinal axis of which coincides with the longitudinal axis of the detachable part, the rod of the pneumatic cylinder is connected to the piston by means of a swivel, for example spherical, and is equipped with a pushing fork connected to the rod by means of a swivel and having no enee two adjustable stops in the form of hemispheres for contact with the discharge compartment, spaced symmetrically about its center of mass, and in the discharge compartment are sockets to accommodate hemispherical abutments plugs, sockets and are shaped conical recesses.

The distinguishing features of the proposed aircraft compartment separation system are as follows: the pneumatic cylinder rod is connected to the piston by means of a swivel, for example, spherical, the rod is equipped with a pushing fork connected to the rod by a swivel, the pushing fork has at least two adjustable stops in the form of hemispheres for contact with the detachable compartment, symmetrically spaced relative to its center of mass, and in the compartment there are slots for accommodating the hemispheres of the fork stops in the form of conical recesses.

Due to the presence of these distinctive features, together with the known ones, the following technical result is achieved: the shock load on the detachable compartment is reduced (due to improved fixing conditions), it becomes possible to use different types of compartments (for example, having a centrally located nozzle) to separate from the aircraft, and the reliability of separation is increased from the aircraft compartment in a given direction, the mass of the compartment separation device is reduced.

The proposed technical solution can find application in aerospace technology for predominantly unmanned aircraft with booster and detachable compartments.

The separation system of the aircraft compartment is presented in figure 1 ... 5.

Figure 1 presents a diagram of a system for separating an aircraft compartment. The aforementioned system for separating the compartment 1 from the aircraft 2 consists of a fastening device containing explosive bolts 3 and guide pins 4 and a separation device containing a gas cylinder 5, a pyro valve (starting device) 6, a pneumatic pusher 7 with a rod 8 and a piston 9, a longitudinal axis the pneumatic pusher 7 coincides with the longitudinal axis of the detachable compartment 1, the rod 8 of the pneumatic pusher 7 is connected to the piston 9 by means of a swivel 10, for example, spherical, and is equipped with a pushing fork 11 connected to the rod by means of a hinge with Connections 12 and having at least two adjustable stops 13 in the form of hemispheres for contact with a detachable compartment 1, spaced symmetrically relative to its center of mass, and in the compartment there are sockets 14 for accommodating hemispheres of the fork stops.

Figure 2, figure 3, figure 4 and figure 5 presents a General view of the separation system of the compartment. A detachable compartment 1 is fixed to the body of the aircraft 2 by means of bursting bolts 3 and guide rods 4 (conventionally shown in one plane). Adjustable stops 13 located on the plug 11 are installed in the nests 14. The thrust surfaces of the adjustable stops 13 are in the form of hemispheres, and the nests 14 are in the form of conical recesses, which compensates for manufacturing and technological inaccuracies in the installation of the detachable compartment 1 and the separation device in the aircraft body 2. The rod 8 is connected to the piston 9 by means of a spherical swivel joint 10 and is held in the swivel socket by a latch 15 (Fig. 5). After securing the detachable compartment 1 to the body of the aircraft 2 by means of bursting bolts 3 and guide pins 4, the adjustable stops 13 are tightened with a predetermined tightening torque to eliminate gaps between the stops 13 and the detachable compartment 1 and backlash in the connection of the pushing fork 11 with the rod 8 of the pneumatic pusher 7 and the pneumatic pusher 7 with piston 9.

Proposed in figure 1-5, the separation system of the compartment of the aircraft operates as follows. After the explosive bolts 3 are triggered, the detachable compartment 1 is released from mechanical connection with the aircraft 2. At the same time, a command is issued to the pyrovalve 6, which opens and gives access to the compressed gas from the cylinder 5 to the pneumatic pusher 7. Under the action of compressed gas, the pneumatic pusher 7 is activated and the rod 8 through the stops 13 the fork 11 pushes the detachable compartment 1 from the aircraft 2. At the initial moment, the detachable compartment moves along the guide pins 4, after leaving the guide pins, the detachable compartment is held on the stops 13 of the pushing fork 11 in the conical sockets 14, than provides separation of the compartment in a given direction. Moreover, due to the presence of a swivel joint 10 of the rod 8 with the piston 9, transverse loads from the influence of external disturbances on the rod 8 are eliminated.

Claims (3)

1. The separation system of the compartment of the aircraft, comprising a fastening device consisting of bursting bolts and guide pins, and a separation device in the form of a pneumatic separation mechanism consisting of a gas cylinder, a pneumatic pusher with a rod, the longitudinal axis of which coincides with the longitudinal axis of the detachable part, characterized the fact that the rod of the pneumatic cylinder is connected to the piston by means of a swivel, for example spherical, and is equipped with a pushing fork connected to the rod by means of a swivel and having at least two adjustable stops for contact with a detachable compartment, spaced symmetrically with respect to its center of mass, and in the compartment there are slots for accommodating the fork stops. 2. The system according to claim 1, characterized in that the thrust surfaces of the adjustable stops are in the form of hemispheres, and the nests have the shape of conical recesses. 3. The system according to claim 1, characterized in that in the articulation of the rod with the piston there is an emphasis preventing the loss of the rod.

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