RU2651457C1 - Air target simulator - Google Patents

Abstract

FIELD: air target simulation means.

SUBSTANCE: invention relates to air target simulation means, in particular to mobile simulators of air targets for testing technical characteristics, monitoring the technical condition of anti-aircraft complexes with infrared guidance systems and for training the calculation of anti-aircraft complexes when conducting combat training. Simulator of air targets contains starting engine (1) with stabilizers (2) providing rotation of the simulator, electronic delay board (3) for switching tracers, Tracers compartment (8), marching engine (6), head compartment (7) with ballistic tip. Tracers (9), (10) are located without going beyond the caliber of the simulator of air targets. Nozzles (13) of propulsion engine (6) are placed at an angle to maintain stable rotation of the simulator around the longitudinal axis.

EFFECT: provides the level of infrared radiation necessary to capture anti-aircraft missiles with thermal homing heads on the oncoming and catch-up course on the entire flight path.

1 cl, 1 dwg

Description

The invention relates to means of simulating air targets, in particular to mobile simulators of air targets (IVC), and can be used to refine technical characteristics, monitor the technical condition of anti-aircraft systems with infrared guidance systems, as well as to train the calculations of the said systems when conducting combat training firing.

Known anti-aircraft target missile (see patent RU No. 2222767, IPC F42B 8/12, F42B 15/10, publ. 01/27/2004), consisting of a propulsion system with a stabilizer, a radio-transparent head compartment with a fairing and a corner reflector microwave- energy and tracers, in the head edema in front of the corner reflector of microwave energy, a cartridge block of heat-resistant composite material in the form of thick-walled disks is installed and fixed in the inner cavity of which tracers are placed, while in the body of the head compartment coaxial to the tracers are made diametrical gas-water holes arranged relative to each other, the axes of which are perpendicular to the longitudinal axis of the target rocket, and the working end surfaces of the tracers are located in the gas-water holes of the head compartment housing, and a direct current source with an electronic delay unit for sequential activation of the tracers is installed in the fairing cavity.

The disadvantages of the target are that, due to the eccentricity of the center of mass of the IVC arising from sequential single combustion of tracers radially located in the head compartment, it will be diverted from the calculated trajectory in both horizontal and vertical planes, which requires increased safety measures and leads to the need the expansion of the danger zone, which cannot be provided at a number of military air defense training ranges and combined-arms training grounds, and, accordingly, to limiting the conditions for the use of a military information center; tracers provide only illumination of the ITC flight path in the optical wavelength range and do not create a sufficient level of infrared radiation for capture by anti-aircraft missiles with thermal homing heads.

A known simulator of air targets adopted for the prototype (see patent RU No. 2442947, IPC F41J 9/08, F42B 8/12, F42B 15/10, publ. 02/20/2012), consisting of a rocket engine with stabilizers and a head part . The head part includes tracers of the front and rear groups located in it, a current source, an electronic delay unit for activating tracers. The simulator is equipped with a tail unit of rotation around the longitudinal axis, made in the form of flat feathers. The feathers are mounted radially on the engine for stabilizers, at an angle to the longitudinal axis. Tracers of the rear group are mounted on the engine and are oriented backwards by working ends. Tracers of the rear group are activated from the launcher at the start of the simulator. The tracers of the front group are located in the head part, oriented forward by the working ends. The front group tracers are switched on via the delay unit from the on-board current source. The tracers of each group are located symmetrically relative to the longitudinal axis of the simulator of air targets.

The disadvantages of the prototype are that the tracers of the front group, located in the head part, are oriented forward by the working ends. Tracers can attenuate from the incoming air flow, which leads to an insufficient level of infrared radiation to capture anti-aircraft missiles with thermal homing heads in the opposite direction, as well as blowing out burning particles of the tracer composition, which continue to burn during the flight, which leads to the removal of anti-aircraft missiles with thermal heads homing.

The proposed invention solves the problem: expanding the technical capabilities of the simulator of air targets, improving security, reducing cost.

The technical result obtained by the implementation of the invention is to provide the level of infrared radiation necessary for the capture of anti-aircraft missiles with thermal homing heads in the oncoming and catch-up course on the entire flight path.

The specified technical result is achieved in that in an airborne simulator containing a starting engine with stabilizers providing rotation of the simulator, an electronic delay switch for tracers, a tracer compartment, a marching engine, a head compartment with a ballistic tip, the new thing is that the tracers are located without going beyond the caliber of the simulator of air targets, the nozzles of the mid-flight engine are placed at a certain angle to maintain stable rotation of the simulator around the longitudinal axis.

The simulator can be equipped with a shell heated to a temperature of infrared radiation.

The location of the tracers without going beyond the caliber of the air target simulator allows them to remain in the aerodynamic shadow of the main engine, which provides a sufficient level of infrared radiation for capture by anti-aircraft missiles with thermal homing heads and eliminates their attenuation from the oncoming air stream.

Placing the nozzles of the main engine at a certain angle allows you to maintain a stable rotation of the simulator around the longitudinal axis.

The simulator can be equipped with a shell heated to a temperature of infrared radiation to simulate a nozzle of a turbojet engine.

Technical solutions with features distinguishing the claimed solutions from the prototype are not known and do not follow explicitly from the prior art. This suggests that the proposed solutions are new and have an inventive step.

The essence of the invention is illustrated in the drawing, which shows a General view of a variant of the proposed ITC outside the container.

The air targets simulator contains a starting engine 1 with stabilizers 2, an electronic delay board 3 for turning on the tracers, a delay board 4 for turning on the main engine and a power source 5, the main engine 6, the head compartment 7, the tracer compartment 8, which includes tracers oriented backwards with the working ends 9 and forward 10, the reflectors 11 and 12. The nozzles 13 of the main engine 6 are placed at a certain angle to maintain stable rotation of the simulator around the longitudinal axis.

The ITC flight path is set by setting elevation angles and course on the launcher.

The start-up signal of the IVC is fed to the electric igniter of the on-board power source 5. After the battery has entered the mode, the signal is supplied to the electric igniter of the starting engine 1. The target leaves the container and flies along the ballistic path, tracers 9 light up from the signal supplied from the delay board 4 to turn on the main engine 6, the reflector 11 provides a predetermined level of infrared radiation in the rear hemisphere. At this moment, the ITC can be fired by anti-aircraft missiles with thermal homing “catch-up”. After a sufficient time has elapsed to achieve safe removal of the target from the launcher, the signal from the electronic delay board 3 sets fire to the tracers 10, the reflector 12 provides a given level of infrared radiation in the front hemisphere, and the target can be fired by anti-aircraft missiles with thermal homing heads " towards ”.

Claims (2)

1. An air target simulator, comprising a starting engine with stabilizers providing rotation of the simulator, an electronic delay switch for activating tracers, a tracer compartment, a marching engine, a head compartment with a ballistic tip, characterized in that the tracers are located without going beyond the caliber of an air target simulator, a march nozzle The engine is angled to maintain stable rotation of the simulator around its longitudinal axis. 2. The simulator according to claim 1, characterized in that it is provided with a shell heated to a temperature of infrared radiation.

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