Method of launching guided ballistic missile

Abstract

FIELD: rocket and space equipment.SUBSTANCE: methods for launching a guided ballistic missile. To do this, launch is performed from a container tilted 2.5–5.5° from the vertical towards the cabin, with the rotation angle of the main engine nozzle limited to 1.5° in the first second of flight.EFFECT: gas-dynamic impact on the launcher is reduced.1 cl, 3 dwg

Description

[0001] The invention relates to rocket and space military equipment and can be used to launch missiles from a transport and launch container (TLC).

[0002] A known method for reducing the jet effect on a self-propelled launcher (PU) of a rocket first-stage propulsion system (PSPS), consists in selecting the characteristics of a powder pressure accumulator that pushes the rocket out of the transport and launch container in such a way as to increase the launch altitude of the propulsion system at a level sufficient to minimize or completely eliminate the gas-dynamic impact on the structural elements of the launcher (Physical principles of launch: a tutorial / A.P. Mashtakov, R.V. Krasilnikov; Baltic State Tech. University - St. Petersburg, 2018, pp. 73-76).

[0003] The disadvantage of this method is the increase in the mass of the propellant pressure accumulator that pushes the rocket, as well as the corresponding increase in pressure in the bottom volume of the rocket, which leads to the need for additional strengthening of the container walls and the tail section of the rocket, which in turn leads to an increase in their mass.

[0004] A self-propelled launcher (patent RU 2386918 C1, IPC F41F 3 / 04, published April 20, 2010) is known, comprising a vehicle chassis and a transport and launch unit, including a body, a launch device, and support systems. The launch device described in this patent, designed for vertical mortar launch of missiles, lacks devices for reducing the gas-dynamic impact of the rocket jet on the launcher.

[0005] The disadvantage of such a launcher is the direct destructive effect of the gas-dynamic jet on the structure of the launcher and the TPK.

[0006] A method is known for reducing the gas-dynamic impact on the ground of the launch site and the launcher of the jet stream of a launching missile at angles close to the vertical angle, and a device for implementing it (patent RU 2481540 C1, IPC F41F 3 / 04, published 04.09.2012), which consists in the directed removal from the launcher of the jet stream of the launching missile by the jet of an additional jet engine installed directly on the launcher.

[0007] The disadvantage of this solution is a significant increase in the weight and complexity of the launcher design, due to the need to carry additional elements in the form of a jet engine, as well as its fastening, lifting and lowering elements.

[0008] The technical problem solved by the proposed invention is the reduction of the gas-dynamic impact on the design of the launcher and the transport and launch vehicle of the jet stream of a launching guided ballistic missile when it is launched from the transport and launch vehicle.

[0009] The implementation of the essence of the invention is achieved in that the rocket is launched from a transport and launch container tilted from the vertical towards the launcher cabin at an angle of 2.5° to 5.5°, while the angular deviation of the rotary control nozzle during the first second of engine operation is limited to a maximum value of 1.5°.

[0010] Technical illustrations:

[0011] Fig. 1 - The location of the rocket and launcher at the moment of activation of the control unit during launch from a vertically located transport and launch vehicle;

[0012] Fig. 2 - The location of the missile and launcher at the moment of activation of the control unit during launch from a TPK tilted from the vertical;

[0013] Fig. 3 - Comparison of the height of the impact of the gas jet axis on the launcher when launched from a vertical and inclined TPK.

[0014] Based on the results of statistical modeling (numerical solution of the system of differential equations of rocket motion), during the launch of a rocket (1) from a vertically located TPK (2), taking into account such disturbing factors as: wind direction and speed, deviation of the mass-inertial and aerodynamic characteristics of the rocket, deviation of the point of application of the thrust force of the first stage propulsion system, deviation of the TPK verticalization angle, due to design and technological tolerances, the relative position of the rocket and the launcher (3) is possible (Fig. 1).

[0015] Thus, immediately at the moment of switching on the control unit, the nozzle axis, and therefore the gas jet from the control unit, will be directed in the most unfavorable direction - towards the control unit.

[0016] The proposed method is implemented as follows.

[0017] The rocket (1) is launched from the TPK (2), tilted towards the launcher cabin (3) at an angle of 2.5° to 5.5° from the vertical (Fig. 2), while the angular deviation of the rotary control nozzle during the first second of engine operation is limited to a maximum value of 1.5°.

[0018] The deviation of the TPK from the vertical is ensured by adjusting the supply of liquid to the two-stage telescopic lifting hydraulic cylinder (4) using automatic throttle devices (5) connected to the hydraulic cylinder (Fig. 1, 2).

[0019] The limitation on the angular deviation of the rotary control nozzle is ensured by the formation of a control program at the initial section of the trajectory, implemented by the rocket control system.

[0020] Due to the deviation of the longitudinal axis of the TPK from the vertical, after the center of mass of the rocket leaves the TPK section, a moment from gravity will appear, creating an increment in the angular velocity of the rocket in the Ox plane. с at сAs a result, the rocket will take the position shown in Fig. 2. The limitation on the angular deviation of the rotary control nozzle during the first second of engine operation is aimed at maintaining the specified position during the operation of the cruise propulsion system, while simultaneously preventing the rocket from losing control.

[0021] This position ensures that the axis of the gas jet of the remote control does not hit the control unit.

[0022] The statistical modeling of the proposed method, taking into account the disturbing factors used in modeling the launch from a vertical TPK, showed that the further (after the activation of the propulsion system) movement of the rocket leads to the rocket taking the position shown in the right part of Fig. 3, in which the axis of the propulsion system nozzle is also directed directly at the launcher.

[0023] However, this position will occur later than the position shown in the left part of Fig. 3 (the axis of the propulsion system nozzle hits the launcher when launching from a vertical TLC) and the distance between the exit of the propulsion system nozzle and the exit of the TLC will be approximately 20% greater than the similar distance for the case of a rocket launch from a vertical TLC.

[0024] This allows for a reduction in the gas-dynamic impact of the jet stream of the first stage propulsion system of the launching rocket during its launch from the transport and launch vehicle to the launcher, expressed in a reduction of the specific heat flux by up to 50%, acting on the launcher structure, without increasing the mass of the components of the missile system.

[0025] The relevance of the invention is due to the reduction of damage received by the launcher from the impact of the jet stream of the launching rocket, which leads to a reduction in the volume of necessary repair work, as well as to ensuring the possibility of multiple use of the launcher and elements of the missile system.

Claims

A method for launching a guided ballistic missile, the sustainer engine of which has a rotating control nozzle, characterized in that the missile is launched from a transport and launch container tilted from the vertical toward the launcher cabin at an angle of 2.5° to 5.5°, wherein the angular deviation of the rotating control nozzle during the first second of engine operation is limited to a maximum value of 1.5°.

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