RU2206057C1 - Homing antiaircraft rocket - Google Patents

Abstract

FIELD: antiaircraft defense. SUBSTANCE: guidance system of rocket comes in the form of photoelectron multipliers with limited field of vision coupled by means of intermediate relays to corresponding electromagnets. Mobile cores of electromagnets are linked to vanes produced in the form of vanes-wing flaps spring-loaded with regard to rocket body. Explosive charge is manufactured in the form of ground bomb without fragmentation stuffing. EFFECT: expanded technical potential of rocket and capability to lock on various targets. 1 cl, 3 dwg

Description

 The invention relates to military equipment and can be used directly in air defense to engage moving enemy air targets. The invention relates to tactical defensive weapons: land-air, air-air, sea-air. The invention can be used for the defense of both strategic objects, and directly at the front line with an easy mobile installation, and also, as a special case, with one’s hand; in the conduct of air combat - air-to-air; from ships for air targets.

 The design of the rocket allows you to destroy the target, but is not intended to destroy people in the aircraft, which manifests humanity to the enemy.

 Known methods: RF patent 2059961, US 5323337 and others, in which the guidance of the rocket on the target is carried out using complex radio-technical guidance tools. The complexity of the devices both on the ground and on the missiles themselves; or pointing a missile at a target using a laser beam. These are very expensive devices. The high cost of the designs is not the last negative quality of the device, but also the fact that the radio frequency of the missile control cannot protect itself from the interference of random or intentional extraneous radio frequencies that lead the missile away from the target / NATO missiles launched in Yugoslavia and missiles fell in Bulgaria /.

 Stationary guidance devices are very expensive and bulky, self-masking and can be hit by the enemy, and the remaining missiles will not be able to be used, since there are no means of guidance.

 The patent of the Russian Federation 2111445 is adopted as a prototype. This is an individual-use anti-aircraft missile containing a thermal homing head with a bearing angle sensor and a signal converter, a propulsion system, a hardware compartment with a steering drive, an onboard power supply and an airborne connector for electrical communication of the missile circuits with a launching device and a compartment for a high-explosive fragmentation warhead, in the housing of which an explosive charge, a current-eddy and shock sensor, and an executive b fuse lock, laser non-contact target sensor, mode memory unit and driver for controlled delay of an explosive detonation pulse, while the output of a non-contact target sensor is connected to the actuator fuse via a driver for controlled delay pulse of an explosive charge, the control circuit of which is connected to a sensor via a signal converter angle of the bearing by the thermal homing head, and through the mode memory block - with an onboard connector for input from the starting device to the prelaunch Mand delay control pulse detonation explosive depending on the size of the target and the conditions of its interception "in Dogon" or "forward".

The prototype is pleased with its technical limitations of using a rocket under certain battle conditions, namely:
- a thermal homing head that is not able to direct a missile at combat gliders, balloons and other aircraft operating without heat generation;
- high-explosive fragmentation charge is designed for damage to the aircraft and people in it from a distance / uncertainty about a direct hit /, which is not always effective for eliminating an air target, increases the weight of the rocket, fuel supply;
- cannot be used from the battle formations of the ground forces and, therefore, cannot protect the leading edge from raids by enemy bomber and assault aircraft;
- Cannot be used to combat stealth aircraft.

Statement of the technical problem of the proposed rocket:
- that the missile to the aerial target, detected visually, came out using its own autonomous independent guidance system;
- that the rocket hit the target by directly hitting the target;
- so that the rocket instantly explodes on contact with the target;
- so that it could hit invisible planes;
- so that the rocket does not depend on ground guidance devices;
- to prevent extraneous electromagnetic fields from affecting the rocket;
- so that the rocket could hit the target at night;
- to be able to fire from the battle lines of the defense line;
- That the rocket possesses simplicity of design and inexpensive.

 The rationale for the invention. None of the analogues and the prototype have the totality of the listed features set in the technical task.

 A homing anti-aircraft missile (Figs. 1, 2) contains a housing 1, a guidance system that includes four photoelectronic multipliers 2, four steering wheel fenders 3, four night vision devices 4, four viewing limiters 5 for photoelectronic multipliers 2, four electromagnets with a moving core 6, four return springs 7 and an onboard electric power supply 8, an explosive charge made in the form of a high-explosive mine 9 without fragmentation filling, an instantaneous impact fuse 10, a propulsion system in the form of a marching engine A 11, the switch main engine 12, four intermediate relay 13 (Figure 3) and four tail feather stabilizer 14.

 When using the inventive homing anti-aircraft missile, all the results set by the technical task are achieved.

 Description of the invention. When enemy aircraft appear, the missile is visually aimed at the target. The marching engine switch 12 turns on the marching engine 11, which gives further acceleration to the rocket. The target moves and goes beyond the axis of the missile flight path, falls into the "field of view" of one of the four photomultiplier tubes 2. The control current in the circuit of this photomultiplier tube 2 changes. Through an intermediate relay 13, a power current is supplied to an electromagnet with a movable core 6, which is rigidly connected to the corresponding wheel-wing liner 3.

 The fender wheel 3 departs under the action of an electromagnet with a movable core 6 from the housing 1. This creates a cavity between the housing 1 and the fender wheel 3, the air volume is more rarefied than other places in the housing 1. Such a local rarefaction of air behind the fender wheel 3 favorably affects the speed of execution of the command missile, which is very important when pursuing a fast flying target. Like a caterpillar transport, holding the movement of one caterpillar, a turn is made at full speed. Such actions of the guidance system are able to quickly change the course of the rocket, no matter how the course of the target changes.

 The photoelectronic multiplier 2 and the entire chain to the steering wheel-wing wheel 3 allows you to keep the target in the axis of symmetry of the rocket’s flight all the time.

 The shadow target has moved away from the photomultiplier tube 2, there is no current on the winding of the intermediate relay 13. The executive current on the electromagnet with the movable core 6 is turned off, the return spring 7 returns the steering wheel to the fender 3. The rocket moves linearly on the target, supported by four feather tail stabilizers 14.

Similar actions occur when the shadow from the target falls on some other photomultiplier tube 2. In order to have a more directed movement of the rocket, each photomultiplier tube 2 is equipped with a viewing limiter 5, which covers it with a horizontal view of 270 ^o .

Thus, each photomultiplier tube "sees" only that part of the sky with a 90 ^o sector, which is located on its side. And if the target appears, then he leaves the shadow, substituting the center of the rocket under the shadow.

 On approaching the target, what happens is that the shadow from the target can cover two or even all four photomultiplier tubes 2. In this position, this means that the target is in the center of the missile’s flight path and will be hit at close range.

 To hit the target at night, the rocket can be equipped with night vision devices 4.

 The proposed homing anti-aircraft missile is industrially applicable.

The advantages of the proposed rocket are obvious:
- the launch facility may be of various designs, including the possibility of launching by hand;
- mobile;
- does not need ground-based guidance and tracking means;
- it is not affected by extraneous electromagnetic fields;
- she does not need a thermal cable from the working engines of the target. It can hit non-motorized flying targets like gliders, balls, etc .;
- invisible planes cannot escape from it;
- simplicity of design and maintenance;
- lightweight due to fuel reduction, lack of fragmentation filling and sophisticated guidance equipment.

Claims (2)

 1. A homing anti-aircraft missile with a guidance system, an onboard electrical power supply, rudders, a propulsion system, an instant action fuse and an explosive charge, characterized in that the missile guidance system is made in the form of photoelectronic multipliers with viewing limiters connected by means of intermediate relays to the corresponding electromagnets, the movable cores of which are connected to the rudders made in the form of rudder-wing liners, spring-loaded relative to the rocket body, etc. This explosive charge is formed as a land mine filling without fragmentation.  2. The rocket according to claim 1, characterized in that it is equipped with night vision devices.

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