RU2247310C1 - Method for launching of guided missile and complex of armament for its realization - Google Patents

Abstract

FIELD: armament, in particular, missile complexes.

SUBSTANCE: the method consists in firing of the missile from the launching tube and subsequent starting of the jet engine by thermogasdynamic action by igniter combustion products on the inserted charge of solid fuel. At starting of the engine subjected to the action by combustion products is only the part of the charge end face surface that is limited by the cavity communicating with the engine combustion chamber. Action is effected by means of thermogasdynamic jets directed at an angle to the charge end face, and the time of action is provided according to a definite dependence. The combustion products from the charge end face surface are moved in the charge axis and turned before the inlet to the engine nozzle axis and turned before the inlet to the engine nozzle unit, at the same time they are transferred in the radial and tangential directions. A complex of armament for realization of the given method is also claimed.

EFFECT: enhanced reliability of the armament complex.

3 cl, 2 dwg

Description

The invention relates to military equipment, and in particular to methods of launching rockets of artillery and missile systems of weapons.

A known method of launching a rocket, adopted as a prototype [1], including the ejection of a projectile from the launch tube and the subsequent inclusion of its rocket engine by thermogasdynamic effects of the products of ignition of the igniter on the charge of solid fuel. The thermogasdynamic effect of the igniter combustion products on the solid fuel charge is carried out after eliminating the gap between the solid fuel charge and the combustion chamber of the rocket engine in the direction of the resulting thermogasdynamic force of the combustion products. This eliminates the destruction of charge at the time of engine start and improves the reliability of the complex.

However, the application of the method is possible only for shells with a homing head, in the rocket engine of which a face combustion charge and an igniter are used, which is located in the central nozzle of the engine, which makes it possible to reduce shock loads on the projectile nodes in a wide temperature range of application. In weapon systems with a command control system with optical communication channels, in which the projectile should always be on the line of sight of the target, the application of this method is not possible, since with a central location of the nozzle of the rocket engine, the products of charge combustion are ejected onto the line of sight and weaken the passage of system commands management. At the same time, with increasing range, the signal attenuation increases, which leads to loss of control. The increase in range due to the use of the end-combustion charge at the central location of the nozzle of the rocket engine leads to the need to increase the mass of the igniter, which, as a rule, has optically opaque combustion products. As a result, at the moment the engine is turned on, the control system signal may weaken below the minimum acceptable level, which also leads to loss of control. Normal operation of the control system can be ensured by performing an engine with side inclined nozzles remote from the radiation receiver.

The method is implemented by an armament complex [1], including a launch tube installed in it with a throwing means a projectile with a rocket engine equipped with an auxiliary charge of solid fuel, an igniter and a rocket engine start device. An engine with a plug-in end-combustion charge, having the highest possible volumetric filling coefficient, provides a maximum projectile range to a missile. However, when the charge is burning, the inner surface of the armor coating opens, with which the intensive release of optically opaque decomposition products of the armor coating begins. As a result, there is a significant attenuation of the signal in the optical complex-projectile communication line. The use of slowly burning fuels with optically transparent combustion products in the end-combustion charge does not provide the required engine thrust, and the nozzle arrangement of the igniter device does not provide reliable ignition of the end-charge, since the residence time of the igniter combustion products in the engine combustion chamber is less than the time required to warm the fuel by the required thickness, which ensures its stable combustion.

The objective of the invention is to increase the reliability of the complex with optical control channels of the projectile in a wide temperature range of application.

The solution to this problem is achieved by the method of launching a guided missile, including firing a projectile from the launch tube and then turning on the rocket engine by thermo-gasdynamic action of the igniter combustion products on the solid fuel input charge, in which when the engine is turned on, only part of the charge end surface is exposed to the ignition products, which limit the cavity communicated with the combustion chamber of the engine; by means of thermogasdynamic jets directed at an angle to the end surface of the charge, and the exposure time is ensured from the condition

Where

τ is the time of exposure to the surface of the charge;

λ is the thermal conductivity of the fuel;

C is the specific heat of fuel;

ρ is the fuel density;

u is the burning rate of the fuel,

while the combustion products from the end surface of the charge are moved along the axis of the charge and deployed before entering the nozzle block of the engine, while simultaneously passing them in the radial and tangential directions.

The proposed method is implemented by an armament complex, including a launch tube with a guided projectile with a throwing means and a rocket engine containing a solid solid fuel charge, an igniter and a launch device, in which the solid fuel charge is made in the form of a cylindrical channel checker with a partially armored outer surface and inclined longitudinal grooves made on the outer surface at the front end, while between the rear end of the charge and the combustion chamber is made communicating The symmetrical cavity with it, into which gas-water channels are led out at an angle to the end surface of the charge from the high-pressure chamber formed at the rear end of the charge and containing the igniter, and the engine nozzles are placed in the longitudinal grooves of the solid fuel charge.

, установленное расчетно-экспериментальным путем, является оптимальным временем воздействия, в течении которого формируется достаточная для устойчивого горения топлива глубина прогретого слоя, что повышает надежность воспламенения заряда. В следствии того, что продукты сгорания с поверхности, подвергаемой воздействию струй, перемещают вдоль оси заряда и перед входом в сопловой блок двигателя разворачивают, перепуская их одновременно в радиальном и тангенциальном направлении, а сопла двигателя размещены в продольных пазах заряда, реализуется турбулентный режим течения высокотемпературных продуктов сгорания у поверхности топлива, что значительно повышает надежность воспламенения заряда при отрицательных температурах и позволяет вскрывать заглушки соплового блока до момента воспламенения всей поверхности заряда твердого топлива, что дает возможность снизить внешнетраекторные возмущения снаряда в момент включения двигателя и повысить тем самым точность стрельбы.When thermogasdynamic effects of the igniter combustion products on a part of the surface of the solid fuel charge in a limited cavity communicating with the engine combustion chamber, by jets directed at an angle to the end surface of the charge, the erosion-free mode of combustion of the charge is ensured, thereby eliminating an uncalculated arbitrary increase in pressure in the combustion chamber of the engine in the moment of its inclusion, caused by the effect of erosive combustion of fuel, which occurs when a longitudinal generatrix of a charge is exposed. Exposure time

established by calculation and experimental means is the optimal exposure time, during which the depth of the heated layer sufficient for stable combustion of the fuel is formed, which increases the reliability of the ignition of the charge. Due to the fact that the combustion products from the surface exposed to the jets are moved along the axis of the charge and deployed before entering the nozzle block of the engine, passing them simultaneously in the radial and tangential directions, and the nozzles of the engine are placed in the longitudinal grooves of the charge, a turbulent flow regime of high temperature combustion products near the fuel surface, which significantly increases the reliability of ignition of the charge at low temperatures and allows you to open the nozzle block plugs up to m The ignition of the entire surface of the charge of solid fuel, which makes it possible to reduce the external trajectory perturbations of the projectile at the time of engine start and thereby increase the accuracy of firing.

The implementation of the charge of solid fuel in the form of a cylindrical channel block with a partially armored outer surface and inclined longitudinal grooves on the outer surface at the front end provides a developed combustion surface, and, as a result, the possibility of using slow-burning fuels with optically transparent combustion products. In addition, due to partial reservation of the outer surface and the presence of longitudinal grooves, an optimal mode of change in engine thrust over time is ensured.

The placement of the igniter in the high-pressure chamber eliminates the influence of processes taking place in the combustion chamber of the engine on it, and further increases the reliability of the ignition of the charge.

The invention is illustrated by drawings. Figure 1, 2 presents a diagram explaining the method of starting and the design of the projectile and engine that implements the specified method.

Guided projectile 3 consists of the main functional blocks and a rocket engine (figure 2) containing a combustion chamber 8, a nozzle block 9 with sealing plugs. A solid rocket fuel charge 10 is placed in the combustion chamber, made in the form of a cylindrical channel checker with a partially armored outer surface 11 and inclined longitudinal grooves 12 made on the outer surface at the front end 13. A symmetrical cavity 14 is made between the rear end of the charge 10 and the combustion chamber, communicating with the combustion chamber. In the cavity, at an angle to the end surface of the charge 10, gas-gas channels 15 are removed from the high-pressure chamber formed at the rear end of the charge. Ignition of the charge 10 is carried out by the igniter 16, placed in a high pressure chamber. The igniter is ignited by an electric igniter 17 located at the bottom of the engine 18.

The proposed method is implemented as follows.

Missile 3 is ejected from the launch tube 1 (transport and launch container or the barrel of an artillery gun) installed on the base 2 (gun carriage, turret of the combat vehicle) using a propelling charge 4 or a rocket engine, giving the projectile 3 initial speed (Fig. 1). On the trajectory 7, the rocket engine is turned on and further accelerates the projectile 3, the flight of which is carried out along the line of sight 6 of the optical channel of the control system 5. At the moment the engine is turned on, the part of the surface of the charge of solid fuel 10 in the limited cavity 14 communicating with the camera is subjected to thermo-gas-dynamic effects of the igniter 16 combustion engine 8, while the impact is exerted by jets directed at an angle to the end surface of the charge.

The products of combustion of the igniter 16 and the charge from the surface exposed to the jets are moved along the axis of charge 10 (Fig. 2) and deployed before entering the nozzle block 9 of the engine, passing them simultaneously in the radial and tangential directions. The sealing plugs of the nozzle block are opened until the entire surface of the solid fuel charge is ignited.

The number of nozzles, the design parameters of the charge of solid rocket fuel, an igniter and gas ducts are determined in each case by calculation and are specified as a result of experimental testing of the projectile.

Thus, the proposed method for launching a guided projectile and an armament complex for its implementation allows to increase the reliability of armament complexes with optical control channels in a wide temperature range of application.

Sources of information

1. Patent RU No. 2167385 dated March 6, 2000; Published on May 20, 2001, bull. No. 14 is a prototype.

Claims (2)

1. A method of launching a guided missile projectile, including firing a projectile from a launch tube and then turning on the rocket engine by thermogasdynamic action of the igniter combustion products on the solid fuel input charge, characterized in that when the engine is turned on, only part of the charge end surface is exposed to combustion products, which is limited communicated with the combustion chamber of the engine cavity, the effect is produced by thermodynamic jets, directing at an angle to the end surface of the charge, and the exposure time is provided from the condition

where τ is the time of exposure to the surface of the charge; λ is the thermal conductivity of the fuel; C is the specific heat of fuel; ρ is the fuel density; u is the burning rate of the fuel, while the combustion products from the end surface of the charge are moved along the axis of the charge and deployed before entering the nozzle block of the engine, simultaneously passing them in the radial and tangential directions. 2. An armament complex including a launch tube with a guided projectile placed in it with a throwing device and a rocket engine containing a plug-in charge of solid fuel, an igniter and a launch device, characterized in that the charge of solid fuel is made in the form of a cylindrical channel checker with a partially armored outer surface and inclined longitudinal grooves made on the outer surface at the front end, while symmetrically communicating with it is made between the rear end of the charge and the combustion chamber I cavity into which the high pressure chamber formed at the rear end and comprising an igniter charge, withdrawn at an angle to the end surface charge gazovodnye channels, and nozzle motor housed in longitudinal grooves of the charge of solid fuel.

Images