RU2169341C1 - Antiaircraft missile - Google Patents

Abstract

FIELD: rocketry. SUBSTANCE: the antiaircraft missile consists of a sustainer stage, whose body shell is joined to the nose fairing, functional units, staging mechanism and a zero stage. Part of the functional units is made in the form of weight simulators of control actuator units with control surfaces installed on the frames in succession one after another, and a warhead in the form of a steel tube with a made thread and weights radially positioned on it. The rest part of the functional units incorporates a power unit with an inertia switch and a flare. The control surfaces of the control actuator are installed in parallel with the missile longitudinal axis and locked, and the weights of the warhead simulator are installed for movement on the tube. EFFECT: provision of determination of the missile ballistic characteristic and its dispersion at firing to a simulated point in the stage of development work. 2 dwg

Description

 The present invention relates to the field of rocketry and can be used to determine ballistic characteristics at the stage of development.

 Known anti-aircraft guided missile [1] complex "Shell-C1", made according to a two-stage scheme, with a bicaliber body and a detachable starting engine.

 A missile consists of a launch and a march stage connected by a separation mechanism. The marching stage consists of combat equipment, including a warhead, contact and non-contact fuses with a head fairing, and functional blocks containing a steering gear, gyroscopic coordinator, electronic equipment, a high-frequency unit and a radiation unit.

 For all its merits, this missile cannot be used to develop a new missile design, since it has only its geometry, its structural elements, and ballistic characteristics inherent only to it.

 Known anti-aircraft guided missile [2], consisting of a launch stage and a marching stage with functional units and combat equipment, connected by a separation mechanism, in which the marching stage body is made in the form of a thin-walled steel shell connected to the head fairing, while the functional blocks and combat equipment interconnected in the axial direction and placed inside the shell, and part of the shell around the combat equipment is made in the form of an additional mass of damaging elements of the warhead.

 However, this design of an anti-aircraft missile, with all its advantages, cannot be used to develop a new missile design in the same way as its counterpart [1].

 The objective of the invention is to eliminate the above disadvantages, namely the determination of the ballistic characteristics of the rocket and its dispersion (miss) when firing at a simulated point at the mining stage.

 This task is achieved by the fact that in an anti-aircraft missile consisting of a marching stage, the shell of which is connected to the head fairing, functional blocks, a separation mechanism and a launching stage, part of the functional blocks are made in the form of weight simulators of steering drive blocks mounted on frames in a certain sequence with rudders and warheads in the form of a steel pipe with an external thread and radially located loads, where the rest of the functional blocks contains a power unit with inertia th contactor and tracer, with the handlebars steering the drive unit mounted parallel to the longitudinal axis of the rocket is non-rotatably and cargo warhead simulator axially movable.

 The essence of the invention lies in the fact that this anti-aircraft missile design allows you to determine the ballistic characteristics of the missile at an early stage of its development, as well as to determine the dispersion (miss) when firing at a simulated point.

The drawings show the proposed design of an anti-aircraft missile (Fig. 1) and its marching stage (Fig. 2), where:
1 - starting stage;
2 - march stage;
3 - separation mechanism;
4 - shell shell;
5 - head fairing;
6 - frames;
7 - a simulator of a block of a steering drive;
8 - steering wheels;
9 - pipe simulator with thread;
10 - cargo simulator;
11 - power supply;
12 - inertial contactor;
13 - tracer.

 The device, assembly sequence and operation of the anti-aircraft missile are as follows: first, the launch stage 1 is assembled, which consists of an engine with a charge and a stabilizer, then the march stage 2 is assembled, while the steering simulators 7 mounted on the frames 6 axially mounted and mounted on the frames 6 with rudders 8 and a warhead, consisting of a steel pipe 9 with an external thread and loads 10 radially located on it, a power supply 11 with an inertial closure 12 and a tracer 13, they install (push) a thin-walled the shell of the hull 4 of the marching stage 2, which, landing, sits on the steering gear unit 7. The head fairing is mounted on the assembled marching stage 5. The assembled marching and starting stages are interconnected by means of the separation mechanism 3. When assembling the marching stage, 2 steering wheels 8 of the steering wheel simulator 7 set (stop) parallel to the longitudinal axis of the rocket to ensure the flight of the rocket along a specific ballistic trajectory.

 If the rudders 8 of the simulator of the block of the steering drive 7 are not stopped, then the rocket, spinning, flies along a spiral ballistic trajectory, while the rudders fall on the stop, which is unacceptable. For a stable flight of the rocket, the correct centering of the marching stage is necessary, which is performed by the loads 10 of the warhead simulator due to axial movement in the desired direction.

 During the flight of an anti-aircraft missile in the initial section, at the moment the engine starts to start the launch stage, the axial overloads acting on the rocket change, the inertial contactor 12, including the power supply 11, from which the mechanism for separating stages 3 is triggered, the impulse for switching on is ignited (ignition ) tracer 13. A detachable launch stage with a separation mechanism performs longitudinal movement without the possibility of impact with the end of the stern of the march stage 2, which ensures separation of the stages of the rocket running stream without disturbance to the march stage 2, while the march stage continues to fly with a burning tracer. A tracer installed and burning in the stern of the marching stage allows ground surveillance services to record from several points the entire flight path by glow, and when firing a rocket at a simulated point, it allows to determine the dispersion (miss), which is necessary at the stages of testing new rocket designs.

Sources of information
1. Magazine of the military-industrial complex "Military Parade" March - April 1995, photo of a rocket p. 45 Article "Carapace covering objects" p. 151 - 153 - analogue.

 2. Patent of Russia N 2133446 from 07/27/99, BI N 20, 1999 - prototype.

Claims (1)

 An anti-aircraft missile containing a marching stage in the form of a shell shell connected to the head fairing, in which the functional blocks are placed, a launch stage, a stage separation mechanism, characterized in that some of the functional blocks are made in the form of weight simulators of steering blocks mounted sequentially one after another drive with rudders and warhead in the form of a steel pipe with external thread and loads radially located on it, the rest of the functional blocks include a power supply with with a tertiary lock and tracer, while the rudders are mounted on the march stage housing parallel to the longitudinal axis of the rocket and are locked, and the loads of the warhead simulator are mounted with the possibility of axial movement through the pipe.

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