RU193992U1 - PORTABLE FUEL CORRECTIVE MISSION ENGINE - Google Patents

Abstract

The utility model relates to the field of military equipment, in particular to rocket and artillery weapons, and can be used in the development and creation of a paste-type corrective rocket engine (RDPT). The technical result of the utility model is to increase the efficiency of a paste-type corrective rocket engine due to the possibility changes in the thrust of the corrective engine throughout its operation with the required accuracy, and, if necessary, zeroing the thrust (due to the use of scabbard -screw mechanism with a linear stepper motor with a sliding stem) to provide the desired level of accuracy donavedeniya or retargeting missiles (CU) according to the changed coordinates (at changed its target location) to the final trajectory, which generally increases the combat effectiveness missile.

Description

The utility model relates to the field of military equipment, in particular to missile and artillery weapons, and can be used to increase the technical capabilities for retrieving (retargeting) missiles belonging to the class of high-precision weapons, as well as for performing maneuvers when overcoming enemy missile defense.

Known development of control propellant rocket engines do not fully meet the requirements. So, the figure 1 shows a dual-mode rocket engine, which includes: body 1, nozzle block 2, nozzle block cover 3, die 4, sustainer charge 5, igniter 6, afterburner charge 7, longitudinal through channels with paste-like fuel 8, pulsed gas generator 9 [1]. Presented in figure 1, a dual-mode rocket engine operates as follows. When the igniter 6 is ignited, the surface of the channel and the end of the sustainer charge 5. The engine operation in the sustainer mode is ensured by the combustion of the sustainer charge. If it is necessary to transfer the engine to afterburning operation, afterburning charge is activated 7. The afterburning charge is activated by ejecting pasty fuel from charge channels 8 into the engine chamber. The paste-like fuel is emitted by compressed gas generated during the operation of the pulsed gas generator 9. The pulsed gas generator 9 is equipped with independent, different in weight, samples of a pyrotechnic composition. This allows you to obtain the required, depending on the size of the free volume of the combustion chamber, the size of the droplets of the paste-like fuel. Changing the size of the droplets is carried out by changing the difference in the chamber pressure and the discharge pressure. The use of the engine in question allows us to obtain a constant, independent of the free volume of the combustion chamber, transition time from marching to afterburner operation. And an increase in the number of afterburner sections will allow to increase the number of correcting impulses or to implement discrete control of the amount of thrust and operating time in afterburner mode due to their parallel or sequential use.

However, along with the advantages, such an engine has a significant drawback, it is dual-mode, with programmed thrust change, which does not provide real-time flight control and does not allow to obtain the required thrust level.

The figure 2 shows the control propellant rocket engine (RAPT) with a spinneret block, which includes: gas reducers 10-11, cylinder 12, electro-pneumatic valves (EPC) 13-14, gas lines 15-16, flow tubes 17, flow tube spring 18, rear bottom 19, piston 20, pasty fuel 21, engine housing 22, front wall 23, flow tube cavity 24, combustion chamber with nozzle 25, igniter 26, flow tube piston 27 [1, 2]. The principle of operation of such an engine is as follows. When the engine is started, a command signal is supplied to EPA 13, which allows compressed gas to enter the piston space through the gas line 16. Under pressure, the piston 20 begins to displace the paste-like fuel 21 through the openings in the front wall of the tank 23 and the flow tubes 17 into the combustion chamber 25. Ignition paste fuel is produced by an igniter 26, which is a powder charge. The combustion of the powder suspension provides the necessary pressure and ignition temperature of the paste-like fuel (PT). An increase in the length of the column of burning paste-like fuel provides an increase in the combustion area, and, consequently, an increase in pressure in the combustion chamber. The length of the PT column increases until the speed of the paste-like fuel is aligned along the axis of the feed channel and the combustion rate of the PT along the axis of the paste-like fuel column, while the engine enters marching mode. It should be borne in mind that a significant length of a PT column is not permissible due to the fact that for large values of transverse overload, a deviation of the axis of the PT column from the axis of the channel can occur. This can lead to the burning of the walls of the combustion chamber and, even, the breakdown of the column of the burning PT from the cut of the feed channel.

The transition to the afterburner mode of operation is performed through the pulse mode. In this case, a command signal is supplied to EPA 13 and compressed gas enters the cavity of the flow tubes 17 through the highway 15. Compressed gas acts on the pistons of the flow tubes 27, overcoming the force of the springs 18, and moves the flow tube forward. As a result of this, an annular gap is formed and the column of paste-like fuel is ejected, while the energy of the compressed gas produces its crushing into droplets. The compressed gas supply system along the line 15 is organized so that it is possible to use a different number of flow tubes working to spread paste-like fuel.

The disadvantages of such an engine is that it has a complex fuel consumption control system due to the use of pneumatic nozzles in the spinneret block, which significantly increases its passive mass and reduces reliability.

The prototype of the developed utility model is “Jet engine”, utility model No. 42269, the scheme of which is shown in Figure 3 [3], is useful. This utility model includes a housing 28, a fuel chamber 29, a rear wall of a tank 30, a housing of a tank 31, a powder pressure accumulator (PAD) 32, an electro-pneumatic valve 33, a pressure regulator 34, igniters 35-36, a piston 37, a paste fuel 38 , nozzle block 39, nozzle block 40, storage chamber 41.

The principle of operation of such an engine is as follows.

As sources of the working fluid, a powder pressure accumulator (PAD) 32 is used. When the engine is started, a command signal is supplied to the igniter 35. The pressure on the piston 37 is supplied by gases coming from the powder pressure accumulator and pressure regulator 34, which receives a signal for the required pressure from a control system to create a certain traction. Under pressure, the piston 37 begins to displace the pasty fuel 38 through the openings in the front wall of the tank and the nozzle block 40 into the combustion chamber. Ignition PT produced igniter 36, which is a powder charge. The combustion of the powder suspension provides the necessary pressure and ignition temperature of the paste-like fuel. An increase in the length of the column of burning paste-like fuel provides an increase in the combustion area, and, consequently, an increase in pressure in the combustion chamber. The length of the PT column increases until the speed of the paste-like fuel is aligned along the axis of the feed channel and the combustion rate of the PT along the axis of the paste-like fuel column, while the engine enters marching mode. Due to the engine control system, pressure regulator 34, and EPA 33, the necessary pressure in the accumulation chamber 41 is maintained, which makes it possible for the proposed engine to be multi-mode, with the possibility of a smooth change in traction.

However, along with the advantages of such an engine, it has significant drawbacks, like the RDPT shown in Figure 2, it has a complex fuel consumption control system due to the use of a powder pressure accumulator with a pressure regulator, which does not provide the required accuracy of homing (retargeting) missiles (warheads) . Another significant drawback of this utility model is the impossibility of zeroing the engine thrust, which may be required when the missile is finally aimed at the target.

To eliminate these drawbacks, a utility model is shown, shown in figure 6. The composition of the utility model includes: an engine block 44, a fuel chamber with a paste-like fuel 45, a block of nozzles 46, a piston 47, a tank case 48, a nozzle block 49, an igniter 50, a scissor mechanism 51, a communication channel with an onboard missile control system 52 (shown schematically), a linear stepper motor with a retractable rod 53.

The figure 4 shows the scissor mechanism. The simplest scissor mechanism consists of a system of levers, hinges and a drive that creates linear movement. As the drive, a hydraulic cylinder or a mechanical transmission with an electric drive is used (in the proposed corrective rocket engine using paste-like fuel, a linear stepper motor with a sliding rod is used).

One of the elevator supports is pivotally fixed to the base, the other has the ability to move along the base. The remaining levers are hinged according to the principle of scissors. A lifting table (piston 47) is pivotally attached to the upper levers. As a result of the impact of the drive, the distance between the supports 43 and the height 42 changes. Given that the length of the levers is a constant value, with a decrease of 43, the height 42 will increase the load (piston) will linearly move.

One of the main advantages of the scissor mechanism is the self-leveling of the horizon (piston 47) due to the construction. In addition, this design is highly reliable and very compact.

Figure 5 shows an example of a linear stepper motor with a sliding rod. The main advantages of a linear stepper motor with an extended stem are:

- ensuring accurate movement, screw pitch error of not more than 0.015 mm;

- screw efficiency reaches 85%;

- high power;

- does not require an additional power system (power is supplied from the on-board missile control system via communication channel 52).

The principle of operation of the proposed correction engine for paste fuel is as follows.

At the command of the onboard missile control system, a signal is transmitted through the communication channel 52 to a linear stepper motor with a retractable rod 53, which drives the scissor mechanism 51. Under the action of the scissor mechanism 51, the piston 47 begins to displace the pasty fuel from the fuel chamber 45 through the block of nozzles 46 into combustion chamber. The ignition of paste-like fuel (PT) is produced by the igniter 50, which is a powder charge. The combustion of the powder suspension provides the necessary pressure and ignition temperature of the paste-like fuel. The increase in the length of the column of burning paste-like fuel provides an increase in the combustion area and pressure in the combustion chamber. The length of the PT column increases until the speed of the paste-like fuel is aligned along the axis of the feed channel and the combustion rate of the PT along the axis of the paste-like fuel column, while the engine enters marching mode. Due to the on-board control system commands transmitted via the communication channel 52 to the linear stepper motor with a retractable rod 53, the necessary pressure on the piston 47 is maintained to displace the required amount of paste-like fuel, and, as a result, the thrust of the correction motor is regulated, providing the proposed engine with multimode and if necessary, zeroing traction.

The technical result of the utility model is to increase the efficiency of the corrective propellant rocket engine, due to the possibility of changing the thrust of the corrective engine throughout its operation with the required accuracy, and if necessary, zeroing the thrust, which provides the required level of accuracy of missile retargeting or re-targeting (warhead) by changed coordinates (at a target that has changed its location) on the final section of the trajectory, which generally increases the combat effectiveness of the missile armed i.

List of references

1. Avdienko, A.A. and others. Design of propulsion systems for solid and paste-like fuels. Saratov, Saratov branch of VAU, 2001 .-- 170 p.

2. Kartashov, Yu.I., Fomenko, VV, Zakharenko, V.G. Paste rocket fuels, gunpowder and special compounds (formulations, products, bibliography). - St. Petersburg: Review of the work of FSUE "RSC" Applied Chemistry for 1966-2003 ", 2003. - 63 p.

3. Elisov, A.V. and others. "Jet engine". Utility Model Patent No. 42269. - M .: 2004.

Claims (1)

A paste-like corrective rocket engine (PT), comprising an engine block, a paste-type fuel chamber, a nozzle block, a piston, a tank block, a nozzle block, an igniter, a scissor mechanism, a communication channel with an onboard missile control system, a linear stepper motor with a sliding rod .

Images