RU2534838C1 - Cruise missile - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to rocketry, particularly to cruise missile with launch-and-accelerate stage (LNC) and midflight power plant (MFP) with supersonic ramjet (SSRJ). Cruise missile comprises MFS with head air intake with central body, SSRJ and LNC. SSRJ comprises conical diffuser, fuel manifolds, combustion stabilisers, NC jointed with conical diffuser, supersonic nozzle at NC outlet and control system. LNC with jet engine is arranged in NC of missile engine and in air channel to be uncoupled and ejected. Fuel manifolds and combustion stabilisers of MFP can fold and are secured at conical diffuser arranged at NC inlet. Nozzle case is composed of two coupled cylindrical and ogival shells. Note here that nozzle critical section is adjusted with help of nozzle hydraulic drive.

EFFECT: decreased weight and sizes of cruise missile, higher in-flight thrust.

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Description

The proposed technical solution relates to rocket technology and describes the design of a cruise missile with a marching propulsion system with a supersonic ramjet engine (SPVRD) and a launch-booster stage (SRS) with a jet engine.

Known cruise missile (RF patent No. 2117907, 1998), with a combined propulsion system SPRD. The design of the known rocket is made in such a way that the air intake is made head-on with the central body, the air channel is located symmetrically along the longitudinal axis of the rocket, while the CPC is placed in the combustion chamber of the SPVRD and the air channel and fastened to the central body. After the acceleration of the rocket due to the accelerating engine, the CPC is separated from the rocket and ejected through the nozzle. To achieve the required rocket acceleration speeds, a certain supply of CPC fuel is required, which determines the dimensions of the CPC. To output the booster stage, the diameter of the critical section of the nozzle must be larger than the diameter of the CPC, which negatively affects the dimensions and efficiency of the march stage.

The aim of the proposed technical solution is to eliminate these drawbacks: reducing the mass and dimensions of the cruise missile and increasing the efficiency of the march stage in flight.

This goal is achieved by the fact that a cruise missile containing a marching stage with a frontal air intake with a central body connected by an air channel to the combustion chamber of the marching system, a supersonic ramjet engine including a conical diffuser, fuel manifolds, combustion stabilizers, a combustion chamber docked with a conical diffuser, a supersonic nozzle located at the outlet of the combustion chamber, and a control system, a starting and starting stage with a jet engine, accommodates what is known in the combustion chamber of the marching stage engine and the air channel with the possibility of undocking and ejection, differs in that the fuel collectors and combustion stabilizers of the marching power plant are made folding and mounted on a conical diffuser located at the entrance to the combustion chamber by means of rotation axes and connected through the system rods with the corresponding hydraulic drive for opening the fuel collectors and combustion stabilizers, mounted on the flange of the conical diffuser, the nozzle body is made of two docked cylindrical and chewing shells, while the critical sectional area of the nozzle is controlled by a nozzle hydraulic drive mounted on the housing by means of a rocking chair and made in the form of a group of cylinders with a piston connected by a common collector and to enable the rotation of subsonic valves kinematically connected to the synchronization ring and corresponding subsonic shutters fastened with fingers and traction, ensuring mutual movement, with the corresponding supersonic shutters, fixed On the output part of the nozzle body rotatably and forming, together with subsonic flaps, a channel for the expiration of combustion products, the main propulsion system is equipped with a control system made in the form of belts of air pressure receivers located on the central body of the air intake, corresponding air pressure signaling devices transmitting an electrical signal on-board automation unit located in the central body of the air intake, nozzle control unit, mounted on a cone di fuser and a nozzle connected with hydraulic manifolds with a hydraulic drive; and a turbopump hydraulic unit connected with a fuel tank by collectors and a nozzle control unit.

The implementation in the proposed march stage of the fuel collectors and stabilizers of combustion folding allows a more rational use of the internal cavity of the combustion chamber (KS) for the location of the CDS, which is directly related to the mass and overall parameters of the cruise missile. In addition, folding manifolds and combustion stabilizers more fully block the air channel of the combustion chamber inlet, providing optimal organization of the fuel-air mixture, which significantly increases the completeness of combustion and, as a result, the efficiency of the marching power plant

The use of an all-mode nozzle with an adjustable critical cross-sectional area allows you to place a large-volume CDS, reducing one of the overall dimensions of the CDS, the power plant and the rocket as a whole.

The nozzle is part of an engine control system that, by adjusting the critical sectional area of the nozzle, maintains the required level of full pressure recovery in the air intake of the power plant, which during marching flight allows maintaining the most economical modes and ensuring a given level of anti-surge stocks.

Figure 1 presents a diagram of the proposed cruise missile in the initial (static) state, in the working position, the cruise missile is presented in figure 2 with conventionally shown CPC. The operating position of the fuel manifolds and combustion stabilizers is shown in Fig.3. Figure 4 shows an all-mode nozzle with an adjustable critical cross-sectional area in working condition. A schematic representation of the control system of the marching power plant, which allows you to change the critical sectional area of the nozzle, is presented in Fig.5.

The scheme of the proposed cruise missile is shown in figure 1.

SPVRD - 1

СРС-2

Adjustable nozzle - 3

Fuel collectors - 4

Combustion stabilizers - 5

Combustion chamber SPVRD - 6

Frontal axisymmetric air intake - 7

Central body - 8

Air channel - 9

Fuel tank - 10

Release Mechanism - 11

Pylons - 12

The missile has a normal aerodynamic design, consists of SPVRD (1) and SRS (2). The input device contains a frontal axisymmetric air intake (7) with a central body (8), rigidly fastened through pylons (12), an air channel (9) for supplying air to the SPVRD combustion chamber (6), around which the rocket fuel tank (10) is located.

СРС (2) is located both in the SPVRD combustion chamber (6) and in the air channel (8).

Folding fuel manifolds (4) and combustion stabilizers (5) are located at the entrance to the SPVRD combustion chamber (6). The products of combustion from the combustion chamber of the SPVRD are thrown out through an adjustable supersonic nozzle (3).

In the starting position, the CPC (2) is located inside the air channel and is fastened to the central body (8) using a special uncoupling mechanism (11).

After the end of the work of the CDS (2), it is undocked from the central body (8) and, under the influence of the pressure of the incoming air flow, is separated from the rocket. After the output of the CPC, the fuel collectors (4) open and the critical section of the adjustable nozzle (3) is set to the working position. The SPVRD starts (1) and the march flight begins.

The scheme of the cruise missile in the working position is shown in figure 2 (CPC shown conditionally).

The layout of the fuel manifolds and combustion stabilizers in the open position of figure 3.

Conical Diffuser - 13

Hydraulic actuator for opening fuel collectors and combustion stabilizers - 14

Traction System - 15

Axis of rotation - 16

Fuel collectors (4) and combustion stabilizers (5) of the main propulsion system are mounted on a conical diffuser (13) located at the entrance to the combustion chamber using rotation axes (16) and are connected through a traction system (15) with a hydraulic drive for opening the fuel collectors and combustion stabilizers (14). The opening hydraulic drive is fixedly mounted on the flange of the conical diffuser and, through a piping system with pyro valves, is connected to a turbo pump hydraulic unit. After disconnecting and exiting the CPC, the pyro valves are blown up and high pressure is supplied from the hydraulic unit of the turbopump into the cylinder cavity of the hydraulic drive for opening the fuel manifolds and combustion stabilizers (14) for their installation in the working position.

The design of the supersonic nozzle in the working position is shown in figure 4.

Nozzle Housing - 17

Hydraulic nozzle - 18

Thrust - 19

Earring - 20

Thrust - 21

Fingers - 22

Pusher - 23

Sync Ring - 24

Subsonic Sash - 25

Supersonic sash - 26

Axis of rotation - 27

Subsonic (25) and supersonic (26) flaps are mounted on the nozzle body (17) with the possibility of rotation relative to the axis of the bosses at the ends of the flaps. Between each other, the shutters are fastened with the help of traction (21) and fingers (22). The hydraulic drive of the nozzle (18) through the earring (20) and the axis of rotation is fastened with a subsonic sash (25) and through the axis of rotation and thrust (19) with the nozzle body. The rod (19) is fastened to the synchronization ring (24) by means of a pusher (23).

The control pressure from the control system enters certain cylinder cavities of the nozzle hydraulic drive (18), which leads to a change in its geometry and movement of the thrust (19) around the axis of rotation (27). The rod (19) through the pusher (23) transfers the force to the synchronization ring (24), providing synchronous movement of all the cylinders of the hydraulic nozzle (18). Through the earring (20) and the axis of rotation, the force from the movement of the hydraulic drive of the nozzle (18) is transmitted to the subsonic sash (25), which drives the supersonic sash (26) through the thrust (21) and fingers (22). Depending on which cavity of the hydraulic cylinder of the nozzle (18) the control pressure enters, the nozzle closes or opens.

The regulation scheme of the marching power plant, providing a change in the critical section area of the nozzle is shown in Fig. 5.

Air Pressure Receivers - 28

Air Pressure Alarm - 29

On-board automation unit - 30

Nozzle control unit - 31

Turbo pump unit - 32

Seal jump - 33

The control system contains belts of air pressure receivers (28) located on the central body of the air intake, air pressure signaling devices (29) and an on-board automation unit (30) located in the central body of the air intake in the instrument compartment, a nozzle control unit (31) installed in the aggregate compartment marching power plant, a turbo pump unit (32) and an all-mode supersonic adjustable nozzle (3) located at the outlet of the combustion chamber of the marching power plant.

Maintaining a given level of pressure recovery is carried out by maintaining the position of the closing shock wave of the seal (33) in the area between the zones of the air pressure receivers (28), which are connected by air lines to the air pressure signaling devices (29). When air pressure alarms are triggered, the corresponding electrical signals are sent to the on-board automation unit (30), and from it to the nozzle control unit (31), which controls the fluid supply to the hydraulic drive of the adjustable nozzle (3). The pressure of the working fluid necessary for the operation of the nozzle and the nozzle control unit is provided by a turbopump hydraulic unit (32), which takes fuel from the fuel tank (10). The spent working fluid is returned to the fuel tank (10). The operation of the turbopump is provided by part of the air taken from the air channel of the rocket and entering the air turbine, and then released through special louvers into the atmosphere.

Thus, the proposed cruise missile, equipped with a missile defense system located both in the control system and in the air channel and fastened to the central body of the air intake, allows due to the design of the main propulsion system with the air defense system and the frontal axisymmetric air intake, which has the following original technical solutions:

adjustable supersonic jet nozzle, the maximum diameter of which allows you to place a CDS in the combustion chamber of the engine of the largest volume;

an emerging system of fuel collectors and combustion stabilizers, which allows more efficient placement of CPC in the product’s air channel;

adjustable supersonic jet nozzle in conjunction with a system for regulating the critical nozzle cross-sectional area allows maintaining the most economical modes during marching flight;

significantly reduce the dimensions and mass of the rocket, as well as increase the traction and economic characteristics of the propulsion system and the rocket as a whole.

Claims (1)

A cruise missile containing a march stage with a frontal air intake with a central body connected by an air channel to the combustion chamber of the marching system, a supersonic ramjet engine including a conical diffuser, fuel manifolds, combustion stabilizers, a combustion chamber docked with a conical diffuser, a supersonic nozzle, located at the outlet of the combustion chamber, and a control system, a starting and starting stage with a jet engine, located in the combustion chamber of the engine a neck stage and an air channel with the possibility of undocking and ejection, characterized in that the fuel manifolds and combustion stabilizers of the marching power plant are made folding and mounted on a conical diffuser located at the entrance to the combustion chamber, by means of rotation axes and connected through a traction system with a corresponding hydraulic drive of opening fuel collectors and combustion stabilizers mounted on the conical diffuser flange, the nozzle body is made of two joined cylindrical and mastic holes, while the critical sectional area of the nozzle is adjusted using a hydraulic nozzle mounted on the housing by means of a rocking chair and made in the form of a group of cylinders with a piston connected by a common collector and to enable rotation of the subsonic valves, kinematically connected to the synchronization ring and the corresponding subsonic valves, fastened with the help of fingers and traction, ensuring mutual movement with the corresponding supersonic flaps fixed to the output part of the nozzle body and with the possibility of rotation and forming, together with subsonic flaps, a channel for the expiration of combustion products, the main propulsion system is equipped with a control system made in the form of belts of air pressure receivers located on the central body of the air intake, corresponding air pressure signaling devices that transmit an electrical signal to the on-board automation unit, located in the central body of the air intake, nozzle control unit, mounted on the cone of the diffuser and hydraulically connected by manifolds with a hydraulic nozzle, and a turbopump, associated with the collectors of the fuel tank and nozzle control unit.

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