RU3817U1 - ANTI-AREA MANAGED ANTI-UTILIZED ROCKET - Google Patents

Description

Individual anti-aircraft guided missile

The proposal relates to rocket technology and is intended for use in portable anti-aircraft missile systems (MANPADS) for hitting jet, turboprop and propeller-driven manned and unmanned aerial vehicles in oncoming and catch-up courses with visual visibility of the target.

Famous MANPADS Stinger (USA), designed to intercept modern and promising aircraft and front-line helicopters 1.

The guided missile of the complex consists of a guidance system compartment, a warhead compartment (warhead), a dual-mode marching solid propellant engine, tail unit and a launch accelerator.

The guidance system compartment includes a thermal homing head (GOS), consisting of a target coordinator and electronic equipment, a steering drive unit and a power source.

GOS monitors the target by infrared radiation and gives the operator detection signals at the stage of target acquisition, as well as control signals during the flight of the rocket. Electronics

MPK6 F42B 15/00

converts the mismatch signal from the thermal GOS into commands for controlling the electric drive of the rocket rudders. Guidance missiles is carried out by the method of proportional navigation.

The steering gear compartment consists of an electronic module and four folding aerodynamic surfaces, two of which serve as rudders. The electric steering wheel control commands are recounted taking into account the position of the rocket body rotating in flight around the longitudinal axis.

The warhead compartment contains an explosive charge and a contact fuse. One of the three modes of warhead detonation delay ensures its operation inside the aircraft structure, which significantly increases the damage ability of the complex. However, due to the complexity of matching the fuse delays with the warhead passage times inside the target structure in a wide range of missile and target meeting conditions, the probability of hitting the target is significantly reduced. In addition, there is a decrease in the likelihood of defeat for small targets due to misses.

Known SATCP MANPADS missile Mistral (France), containing a thermal seeker with a multi-element sensor, high-explosive fragmentation warheads with contact and laser proximity sensors of an explosive device, electronic control and guidance equipment, electric steering gear, thermal battery, solid propellant propulsion system 1. In comparison with the launch Stinger missile, SATCP missile has higher flight performance and, accordingly, large overall weight and weight parameters (length 1.84 m, diameter 0.09 m, weight 17.6 kg).

Thanks to a more sensitive thermal GOS, the SATCP missile provides the capture of an aircraft with one jet engine at a distance of 6 km and a light helicopter at a distance of 4 km, regardless of the detection angle. The warhead of the rocket has a mass of 3 kg and provides a satisfactory damaging effect with a miss of up to 1 meter, characteristic of missiles with a thermal seeker. The laser non-contact fuse, except for the main purpose, is used to prevent premature operation when meeting with false targets (trees, water surface, etc.).

The process of aiming and launching a SATCP missile from a shoulder is practically impossible. Therefore, the rocket is launched not from the shoulder, but from the tripod, which together with the electronic unit and the sighting device is an integral part of the complex.

All Mistral MANPADS equipment is divided into two packages of 20 kg each: one contains a SATCP missile in a container, and the other contains a launcher with an electronic launch and aiming unit.

Therefore, the calculation of the complex should consist of two people, which excludes the individuality of using the complex and the missile, limits the tactics of using MANPADS, and, as a result, reduces the likelihood of the combat mission of the unit equipped with it.

An increase in the probability of hitting an air target is achieved by increasing the mass of explosive warhead missiles and the number of damaging elements. However, inconsistency during small misses formed by the warhead of the battlefield with the parameters of the target (size, meeting conditions and speed of its flight) reduces the likelihood of defeat, especially when firing at highly maneuverable, small-sized high-speed targets.

Known anti-aircraft guided missile for personal use 9M39, which is part of MANPADS 9K38, which is in service with the army of the Russian Federation 2, and consists of a head compartment, a steering compartment, a warhead compartment, a propulsion system and a wing unit.

The head compartment contains a thermal seeker with a target bearing angle sensor giving a signal proportional to the mismatch angle between the longitudinal axis of the rocket and the optical axis of the tracking coordinator, and an electronic unit for generating a single-channel control signal.

The rocket propulsion system consists of solid-propellant starting and dual-mode marching engines.

In the hardware compartment of the rocket there is a steering gear with rudders, an onboard power supply, an onboard connector for the electrical connection of the rocket circuits with the launch tube and the launch device.

An explosive charge with a detonator and an explosive device including an executive unit with electric igniters, a main target sensor in the form of a pulsed vortex magnetoelectric generator and a backup shock sensor are placed in the case of a high-explosive fragmentation warhead compartment.

The introduction of a magnetoelectric generator makes it possible to increase the penetration of warheads into the target structure and, accordingly, the probability of its destruction.

Depending on the conditions for intercepting the target, the operator sets the required launching device when launching the rocket

switch appropriate guidance mode (catch-up or towards).

The 9M39 missile has a low weight (10.5 kg) and, together with the launch tube - the container and the launch device, is transported and launched (from the shoulder) by one operator, i.e. is a dual-use individual missile.

However, when shooting at a small, high-speed maneuverable air target, misses are possible, which reduces the likelihood of their destruction.

The technical result of using the proposal is to increase the likelihood of hitting air targets in a wide range of their parameters: target size, flight speed and the mode of interception (after or after).

This is achieved by the fact that in an anti-aircraft guided missile containing a thermal seeker with a target bearing angle sensor, a hardware compartment with a steering gear, an on-board power supply and an airborne connector for electrical communication of the missile circuits with a launching device, a propulsion system, a high-explosive fragmentation warhead with an explosive charge , and a fuse with shock and vortex target sensors and an executive unit, laser non-contact target sensor (NDC) placed in the casing of the warhead compartment, a mode memory block and a controlled pulse delay driver n explosive charge. In this case, the output of the non-contact target sensor is connected to the executive

to the unit through a controlled delay driver, the control circuit of which is connected via a signal converter to the sensor of the bearing of the thermal seeker, and through the mode memory block, with an on-board connector for inputting pre-launch commands to control the delay of the explosive charge detonation pulse, depending on the size of the target and the conditions for its interception (after or towards).

The essence of the proposal is presented in the drawings, where: in Fig. 1 is a general view of an anti-aircraft guided missile; figure 2 is a structural diagram of the pulse formation of undermining warhead; Fig. 3 is a structural diagram of a driver delay control shaper.

The individual anti-aircraft guided missile (Fig. 1) contains a homing heat head 1 with a bearing angle sensor 2 formed by the bearing coil of the GSN tracking coordinator, a hardware compartment 3 with a steering gear 4, an onboard power supply 5 and an airborne connector 6, a high-explosive fragmentation warhead 7 compartment , in the case of which there is a fuse 8 and a charge of В В 9, solid propellant marching 10 and starting 11 engines, wing unit 12.

The fuse (Figure 2) includes shock 13 and eddy current 14 target sensors connected to the Executive unit 15, the laser NDC 16 connected to the Executive unit 15 through the shaper controlled delay 17 pulses of detonation of explosive charge,

a mode memory block 18 included in the delay control circuit of the shaper 17. The chain of passage of the pre-start delay control commands to the memory block 18 from the switches of the starting device 19 K1 (target dimension) and K2 (interception mode - catch-up or towards) contains an onboard connector 6.

In the delay control circuit of the shaper 17, a sensor 2 of the target angle of the target of the thermal seeker is automatically connected through the signal converter 20 to automatically adjust the delay time depending on the angles of approach to the target.

The shaper of the controlled delay of the explosive detonation pulse (Fig. 3) consists of a capacitor 21 connected to the resistors (R1R8) 22 through a multiplexer 23, a comparator 24 connected to the executive unit 15.

The table shows the options for generating a time delay depending on the combination of switches K1 and K2 on the rocket launcher and the signal of the bearing sensor 2 of the thermal GSN1.

Table)

Shooting a rocket is as follows. Before launch, the anti-aircraft gunner (operator) puts the missile in the launch device into the firing position. When the target appears, determining its type and selecting the start mode, it sets the switches K1 and K2 on the starting device 19 to the corresponding positions. In this case, the electric signals from the starting device 19 through the onboard connector 6 are fed to the rocket in the mode memory unit 18, made on a standard element base. After capturing the target of the thermal seeker 1, the rocket is launched, which is carried out by the shoulder anti-aircraft gunner.

At the initial stage of the rocket’s flight, up to the firing range of the fuse 8, an electric signal close to a sinusoidal shape from the coil of the bearing sensor 2 is converted into a digital code in the converter 20 and fed to the input of the multiplexer 23 of the controlled delay driver 17, which simultaneously receives a signal from mode memory 18.,) Note: Information related to the description of the example

The specific implementation of the controlled delay driver, including (Fig. H), is intended for state patent examination to justify the criteria of the invention, industrial applicability and is not subject to publication, as it represents the Know-How of the enterprise-developer. Thus, the multiplexer 23, at the control input of which one of the eight voltage levels is formed (see table), includes the corresponding resistor 22 of the timing RC circuit, i.e. Specifies a specific amount of delay.

The non-contact laser sensor of the target 16, consisting of a twelve-beam laser emitter, a photodetector, a lens system and a signal processing unit, which is turned on beyond the firing distance of the fuse 8, having detected the target, gives a command to charge from the on-board power supply of the capacitor 21, through the circuit is one of the resistors 22, thereby forming the delay time of the pulse to detonate the warhead. The voltage from the capacitor 21 is supplied to the comparator 24, which, when the unlocking threshold is reached, supplies voltage to the actuator unit 15 of the fuse 8, which provides an explosive charge 9.

The value of the selected delay allows the missile to get as close to the target as possible after it is detected by the laser NDC and undermine the explosive charge 9 with the maximum damaging effect on the miss, and in the case of a direct hit of the missile at the target, provide explosive charge V 9 from the signals from shock 13 and eddy current 14 sensors inside the design of the aircraft with the maximum damaging effect. This ensures a high probability of hitting air targets, regardless of the size, speed of the target and interception mode.

From the calculations it follows that the probability of hitting the proposed missile when firing at various targets is 1.5-2 times higher than the probability of hitting the class.

Sources of information:

1. Anti-aircraft missile and missile-cannon systems of the capitalist countries (review based on foreign press materials) under the general editorship of Academician E.A. Fedoseyev.

Scientific Information Center (77) 1986 p. 72-78, 162-166.

2. Portable 9K38 SAM (prototype). MOT and operation manual, design bureau of mechanical engineering. Military Publishing House, Moscow, 1987

0S // # i & famous rockets similar

Claims (1)

An individual anti-aircraft guided missile containing a thermal homing head with a target bearing angle sensor and a signal converter, a propulsion system, an equipment compartment with a steering gear, an onboard power supply and an airborne connector for electrical communication of the missile circuits with a launch device and a high-explosive fragmentation warhead compartment, in the case of which contains the explosive charge, eddy current and shock sensors of the target and the fuse actuator, characterized in that it contains the b of the warhead, a non-contact target sensor, a mode memory unit and a driver for controlled delay of an explosive charge detonation pulse, while the output of a non-contact target sensor is connected to the fuse actuator through a controlled delay driver, the control circuit of which is connected through a signal converter to the angle sensor of the thermal homing head, and through the mode memory block - with an onboard connector for inputting pre-launch control commands for the delay delay of the explosive charge detonation pulse from the starting device awn on the size of the purpose and conditions of its interception ( "in pursuit" or "forward").