RU2239780C1 - Missile with normal aerodynamic configuration - Google Patents

Abstract

FIELD: rocketry, in particular, guided missiles, may be used in missiles of various types and classes with lattice control surfaces.

SUBSTANCE: the shaft of the missile control actuator is made in the form of a sleeve with a pyrotechnical source of pressure installed in its inner cavity, the tail piece of the control actuator shaft is installed outside it. Made in the tail piece are the cavity of the air cylinder and a passage of the end of the rod of the air cylinder piston, provided with a lever with journals made on it for engagement with the end surface of the root section of the lattice control surface. Stops are provided on the root section of the control surface, they are engaged with the lever journals in the folded position of the control surface. Besides, the spring-loaded members of the mechanism fixing the control surface in the unfolded position are made in the form of flat V-shaped springs. The rod of the air cylinder piston is made double-ended.

EFFECT: enhanced controllability of the missile.

5 cl, 6 dwg

Description

The invention relates to rocket technology, in particular to guided missiles, and can be used in various types and classes of missiles with trellised rudders.

A rocket with a normal aerodynamic design is known, which contains a propulsion system, guidance and control system equipment, fixed wings and movable lattice rudders of a control system located on the housing uniformly relative to its longitudinal axis, as well as mechanisms for opening the wheels and fixing them in the open and folded provisions. This rocket is described in the magazine “Wings of the Motherland” No. 8, 1993 (color insert and p.26). In addition, a known rocket with a normal aerodynamic design with fixed wings and movable rudders evenly located on the body relative to the longitudinal axis. The rudders are equipped with opening and fixing mechanisms. The rocket has a pyrotechnic pressure accumulator, lattice rudders are equipped with pins for fixing in the folded position, each rudder opening mechanism is made in the form of a pneumatic cylinder, and each rudder fixing mechanism in the open position is made in the form of spring-loaded rods, and in the folded position - in the form of gripping scissors (RF patent No. 2085825, F 24 B 15/00).

The last technical solution is taken as a prototype.

Along with the advantages of the above missiles, which include:

- a decrease in the overall dimensions of the rocket in connection with the use of small-sized and low-energy-intensive drives for controlling lattice rudders;

- providing high flight tactical data of the rocket due to the presence of mechanisms for opening the rudders and their fixation in the folded and open positions;

- minimum dimensions during transportation and storage of missiles;

there are drawbacks due to the fact that the steering mechanism does not have a mechanical connection with the steering wheel that accompanies the steering wheel throughout the entire deployment process, namely:

- with an unfavorable combination of external loads, there is a probability of either a long opening time or an incomplete opening of the trellised rudders;

- with a favorable combination of external loads (large opening forces), the effect of rebounds from the locking mechanism is possible, which can also lead to an increase in the opening time of the trellised rudder.

Both situations separately or combined negatively affect the controllability of the rocket in the initial phase of autonomous flight.

When creating the invention, the task was to increase the controllability of the rocket by eliminating the influence of external loads on the process of opening and fixing the trellised rudders.

The problem is achieved in that in a known rocket with a normal aerodynamic design, containing a propulsion system, guidance and control system equipment, fixed wings and movable trellised rudders with their control drives located on the body uniformly relative to its longitudinal axis, as well as mechanisms disclosure and their fixation in the open and folded positions, each opening mechanism includes a pneumatic cylinder, the piston cavity of which is communicated by a pyrotechnic channel a pressure source, and two rollers fixed in front of the rudder shaft end of the steering wheel and included in the mounting holes in the root part of the rudder, and each steering lock mechanism in the open position is made in the form of spring-loaded elements installed in the rear part of the rudder shaft shaft interaction with the corresponding mounting recesses in the root part of the trellis, the difference is that the drive shaft is made in the form of a glass, in the inner cavity of which a pyrotechnic a source of pressure, outside of which the shaft end of the rudder drive shaft is located in its bottom part, in the shank there is a pneumatic cylinder cavity closed by a cover and an opening for the outlet of the end of the piston rod of the pneumatic cylinder equipped with a lever with which it can interact with the end face of the root part of the lattice rudder pins, and in the root part of the steering wheel there are stops interacting with the trunnions of the lever in the folded position.

In addition, the spring-loaded elements of the steering lock mechanism in the open position are made in the form of V-shaped springs, and the mounting recesses in the root of the steering wheel have a reciprocal shape.

The piston rod of the pneumatic cylinder is double-end, a hole is made in the cover of the pneumatic cylinder for the outlet of the 2nd end of the rod interacting with the U-shaped stop fixed on the rocket body for locking the steering wheel shaft.

The emphasis on the root of the rudder is made with a length that ensures the formation of a gap between the rocket body and the corresponding rudder.

In the inner cavity of the steering wheel drive shaft there is a microswitch of signals forming the commands for opening the trellised rudders and sizing the drive shaft.

This embodiment of the rocket provides reliable disclosure of trellis rudders regardless of the external loads.

Figure 1 shows a General view of the rocket; figure 2 is a General view of the disclosure mechanism of the rudders in the context; 3 - steering wheel opening mechanism (view A of FIG. 2); figure 4 is a kinematic diagram of the mechanism when the steering wheel is folded; figure 5 is a kinematic diagram of the mechanism in the process of disclosure; figure 6 is a kinematic diagram of the mechanism with the steering wheel open.

A rocket with a normal aerodynamic design (Fig. 1) comprises a housing 1 and a propulsion system placed therein, guidance and control equipment (not shown), four fixed wings 2 and four guided lattice rudders 3 of the control system located on the housing 1 uniformly relative to it longitudinal axis and in the folded position.

The missile has mechanisms for opening the rudders and their fixation in the open and folded position, as well as a device for sizing the rudder drive shaft (the drive is not shown).

The shaft 4 (figure 2) of the steering wheel drive 3, which at the same time is the housing of the steering wheel opening mechanism 3, is made in the form of a cup, on the outside of which a shank 5 is located on its bottom.

Each lattice steering wheel 3 is connected to the drive by means of two rollers 6 fixed in front of the shank 5. The ends of the rollers 6 are placed in the mounting holes of the root part of the rudder 3. The rollers 6 are the axis of rotation of the rudder 3 when it is opened. In the root part of the steering wheel 3 there are two stops 7 designed to fix the steering wheel 3 in the folded position, and the contact surfaces 8 involved in the process of opening the steering wheel. The emphasis 7 is made with a length that ensures the formation of a gap between the body of the rocket 1 (Fig. 1) and the corresponding trellis rudder 3. On the inner surfaces of the root part of the rudder 3 there are two rectangular grooves 9 for fixing the rudder 3 in the open position.

A pyrotechnic pressure source 10 is installed in the internal cavity of the shaft 4. A cavity of the pneumatic cylinder 11 is made in the shank 5, connected to the pressure source by the channel 12. In the cavity of the pneumatic cylinder 11 there is a piston 13 with a double-end rod 14, one end of which is rigidly fixed to the lever 15. The lever 15 has two trunnions 16, which, interacting with the stops 7, hold the trellised steering wheel 3 in the folded position. The pneumatic cylinder 11 is closed hermetically by a cover 17, in which a hole for the outlet of the second end of the rod 14 is hermetically sealed. The portion of the rod 14 protruding beyond the cover 17, interacting with the U-shaped stop 18 mounted on the housing 1 (Fig. 1), arrests the shaft 4 (Fig. .2) steering wheel drive 3.

A switch 19 is installed in the inner cavity of the drive shaft 4. The switch consists of a movable part 20 protruding in the cavity of the pneumatic cylinder 11 at the end of the piston 13 stroke, in contact with which it presses the microswitch button 21. In the shank 5 (Fig. 3) from the sides niches are made in which two V-shaped spring clips 22 are mounted for fixing the steering wheel 3 in the open position. The spring 23 holds the piston 13 in its original position. An emphasis 24 is fixed on the shank 5 above the lever 15.

The disclosure of the trellis rudders of 3 missiles is carried out both automatically in the beginning of an autonomous flight, and manually during routine maintenance.

When starting a rocket trellised rudders 3 are in the folded position. The propulsion system and control guidance systems operate in the usual mode for this class of missiles. The disclosure of the trellised rudders is carried out after the pyrotechnic pressure source 10 is triggered (Fig. 2) at the signal of the rocket control system.

In the initial position (figure 4, the steering wheel 3 in the folded position), the piston 13 is held by a spring 23, which prevents spontaneous opening of the trellised steering wheel and the actuation of the drive shaft, while the pins 16 of the lever 15 are under the stops 7.

Under excessive pressure of the gas, the source of which is a pyrotechnic source of pressure 10 entering the porsche cavity of the pneumatic cylinder 11, the piston 13 begins to move. In this case, the pins 16 (Fig. 5) come out from under the stops 7 of the rudder 3, freeing it for rotation in the rollers 6. Further movement of the piston 13 due to the action of the pins 16 on the contact surfaces 8 of the root part of the rudder 3 leads to its full disclosure of rotation on 90 °.

After full disclosure of the steering wheel 3 using spring clips 22 (Fig.3) is fixed in the open position.

After the steering wheel 3 is fully opened, the residual piston stroke 13 is selected (Fig. 6), which leads to the actuation of the drive shaft 4 by way of the output of the second end of the rod 14 from the stop 18.

After sizing (Fig.6) of the drive shaft 4 under the influence of the moving part 20 of the switch 19, the button of the microswitch 21 is activated, generating a signal about the opening of the steering wheel 3 and sizing of the drive shaft 4, while the lever 15 is installed on the stopper 24, preventing the piston 13 from returning to the original position under the influence of the spring 23 in the event of a pressure drop in the pneumatic cylinder 11.

Claims (5)

1. A rocket with a normal aerodynamic design, comprising a propulsion system, guidance and control system equipment, fixed wings and movable lattice rudders with control drives located on the housing evenly relative to its longitudinal axis, as well as mechanisms for opening the wheels and their fixation in the open and folded positions, wherein each opening mechanism includes a pneumatic cylinder, the piston cavity of which is communicated by a channel with a pyrotechnic pressure source, and fixed in front part of the shaft of the steering wheel shaft, two rollers included in the mounting holes in the root of the steering wheel, and each steering lock mechanism in the open position is made in the form of spring-loaded elements installed in the rear of the shaft shaft of the steering wheel drive with the possibility of interaction with the corresponding mounting recesses in the root part steering wheel, characterized in that the drive shaft is made in the form of a cup, in the inner cavity of which a pyrotechnic pressure source is installed, outside of which x the ostovik of the rudder drive shaft, the shank of the pneumatic cylinder closed by a cover and the hole for the outlet of the end of the piston rod of the pneumatic cylinder equipped with a lever with the possibility of interaction with the pins with the pins on the root part of the lattice steering wheel are provided in the shank, while there are stops on the root of the steering wheel interacting with trunnions of the lever in the folded position of the steering wheel. 2. The rocket according to claim 1, characterized in that the spring-loaded elements of the steering lock mechanism in the open position are made in the form of flat V-shaped springs located in the side recesses of the shank, and the mounting recesses in the root of the steering wheel have a shape corresponding to them. 3. The rocket according to claim 2, characterized in that the piston rod of the pneumatic cylinder is double-end, a through hole is made in the cover of the pneumatic cylinder to exit the 2nd end of the rod, interacting with a U-shaped stop mounted on the rocket body. 4. The rocket according to claim 3, characterized in that the stops on the root of each trellised rudder are made in length, providing a gap between the rocket body and the corresponding trellised rudder. 5. The rocket according to claim 4, characterized in that in the inner cavity of the drive shaft there is a switch of signals forming commands for opening the trellised rudders and sizing the drive shaft.

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