RU25931U1 - WINGED ROCKET - Google Patents

Description

The utility model relates to the field of missile weapons, in particular to low-flying homing cruise missiles (CR), designed to destroy surface ships and transports from the composition of naval attack groups, landing formations, convoys and single ships.

Known KR ZM-54E, providing an increased firing range and adopted for the prototype, consisting of sequentially docked devices and separation of the launch stage with a solid fuel engine, march subsonic stage containing aerodynamic surfaces to control the position of the KR in flight and a turbojet engine, and a supersonic combat stage, containing a nose fairing, aerodynamic control surfaces of the combat stage in autonomous flight, a flight control system and guidance to the target, b Oy part and solid-fuel engine A.B.Shirokorad Weapons of the domestic fleet, Minsk-Harvest, Moscow-ACT, 2001 p. 539-542.

Coinciding features with the well-known KR prototype are: KR contains a solid-fuel starting engine docked with docking and separation devices, a marching subsonic stage containing aerodynamic control surfaces for the position of the RC in flight and a turbojet engine, and a supersonic combat stage containing a nose fairing, aerodynamic combat control surfaces in autonomous flight, flight control system and guidance on the target, warhead and solid fuel engine.

The subsonic marching speed of the KR prototype with a turbojet engine allows on the marching section to have a minimum fuel consumption of one kilometer, and, accordingly, increases the maximum firing range, and the supersonic combat stage provides low vulnerability when flying in the zone of near intense opposition at a distance of less than the target 20 km, however, the improvement of enemy fire and information countermeasures systems leads to a gradual decrease in the probability of hitting a target of a known missile defense and, accordingly, to increase the outfit of the Kyrgyz Republic, necessary to hit the target, as well as the number of carriers of the Kyrgyz Republic (aircraft, ships), necessary when conducting military operations.

The task to which the proposed device is aimed is to increase the probability of hitting a target with a cruise missile.

To solve this problem in the Kyrgyz Republic, consisting of docked and separated docking devices for the starting solid propellant engine, a marching subsonic stage containing aerodynamic surfaces for controlling the position of the RC in flight and a turbojet engine, and

a supersonic warhead containing a nose cone, aerodynamic control surfaces of the warhead in autonomous flight, a flight control and guidance system for the target, warhead and solid propellant engine, a supersonic warhead is located in the cavity of the marching step, which contains its own nose cone, flight control system and guidance on the target, warhead and additional solid fuel engine. In this case, the turbojet engine can be located both inside and outside the march stage housing.

In addition, to reduce the mass of the march stage in autonomous flight, a turbojet engine can be docked with it through a docking and separation device.

Distinctive features of the Kyrgyz Republic is that the supersonic combat stage is located in the cavity of the marching stage, equipped with its own nose cone, flight control and targeting system, warhead and an additional solid fuel engine.

Additionally, the turbojet engine can be docked with the march stage by means of a docking and separation device.

Due to the presence of these distinctive features in combination with the well-known, the following technical result is achieved - the likelihood of overcoming the enemy air defense by a cruise missile and hitting a target is significantly increased, and after separation of the turbojet engine from the marching stage in autonomous flight, its mass is reduced.

As a result of a search by sources of patent and scientific and technical information, no solutions containing similar features were found. Thus, we can conclude that the proposed Kyrgyz Republic is not known from the prior art and, therefore, meet the eligibility criterion - “new.

The proposed technical solution can find application in the field of missile weapons, especially for hitting naval targets with low-flying cruise missiles, which allows us to conclude that the criterion “industrial applicability.

Figure 1 shows the design of the RC according to claim 1 and claim 2 of the formula.

Presented in FIG. 1, the CR contains a starting solid-fuel engine 1 docked by the docking and separation device 2 with a marching subsonic stage 3, docked by the docking and separation device 4 with a supersonic combat stage 5.

The supersonic combat stage 5 is located in the cavity of the marching subsonic stage 3 and contains a nose fairing 6, aerodynamic control surfaces for the position 7 of the combat stage 5 in autonomous flight, the flight control system 8 of the combat stage 5 and its guidance to the target, the warhead 9 and the solid-fuel engine 10.

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stage 3 in flight, flight control system 13 of march stage 3 and its guidance on the target, warhead 14, turbojet engine 15 with fuel tank 16 and fuel supply system 17 and solid fuel engine 18. Turbojet engine 15 may be located outside of march stage 3 (option And in Fig. 1), moving out of the transport position in the case of the march stage 3 beyond its contours into the external air flow using the device 19.

Additionally, the turbojet engine 15 of the march stage 3 can be docked with the march stage 3 using the docking device and the compartment 20.

KR according to claim 1 and claim 2 of the utility model formula works as follows.

The missile launch control system of a warship equipped with missiles according to any one of claims 1 to 2, moving at an arbitrary rate, having received data on the location of the target and its speed, enters the coordinate data into the flight control and guidance system 13 for the march stage 3 target meeting points with the target necessary for the angle of rotation of the CR in the autonomous flight for approaching the meeting point with the target, after which the solid propellant engine 1 is launched. The CR, initially having the speed of the carrier ship at the starting point, begins to move autonomously ie, from the comfort of home launcher, moving at an angle to the horizon 0 defined launcher. After accelerating the accelerator to a speed that ensures effective control of aerodynamic surfaces 12, the flight control system and pointing 13 at the target of the marching stage 3 provides a decrease in the acceleration and rotation through the angle fr to move toward the target on the marching section. At the launch site, after the accelerator accelerates to the necessary subsonic speed sufficient to start the turbojet engine 15 of march stage 3, the docking and separation devices 2 are activated and the starting solid propellant engine 1 is separated and the turbojet engine 15 is launched, into which fuel is supplied from the tank 16 by fuel supply systems 17. On the marching section, the flight of the aircraft to the target at an altitude of H 1 (L-20 m, which ensures the secrecy of the RS from the target detection systems, is carried out. At a distance to target 3 (L-40 km, determined by the radius of the homing head of the flight control system and guidance 13 to the target is turned on by the homing head, which scans the space with the radar beam within the ghc ms angle To search for the target After capturing the target by the homing head of the flight control system and pointing 13 at the target of the march stage 3, it provides flight of the Kyrgyz Republic to the zone of intensive counteraction by air defense means of the target at a distance of-10-20 km. Before the beginning of this zone, a docking and separation unit 4 is activated and mid-flight 3 and combat 5 stages are separated, after which the flight control and guidance 13 system on the mid-flight target provides its controlled flight to the target, and the flight control and guidance system 8

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combat stage 5 on the target provides its controlled flight to the target. After the separation of the combat 5 and the marching 3 stages, solid-fuel engines 10 and 18 are activated, which provide the afterdrive of the combat stage 5 and the marching stage 3 to supersonic flight speeds and maintaining these speeds when they fly to the target.

In the configuration variant of the RC with the location of the turbojet engine 15 inside the mid-flight stage housing 3 with the extension device 19, before starting the mid-flight turbojet engine 15, it can be extended beyond the contours of the mid-flight stage 3 to the operating position by activating the device 19 (see option A in FIG. 1).

In addition, before starting the solid propellant engine 18 of the march stage 3, the separation device 20 of the turbojet engine 15 can be activated, while the mass of the solid propellant engine 18, which is expended in accelerating the march stage 3 of the turbojet engine 15 to supersonic flight speed and maintaining the supersonic speed during the flight of the march stage 3, is saved. to the goal.

Given that the probability of overcoming air defense by marching stage 3 as a result of its overclocking to supersonic speed at the target will slightly differ from the probability of overcoming air defense by combat stage 5, which, according to the calculations, can carry warhead 9 with a mass comparable to the mass of warhead 14. placed in the march stage 3, the total probability of hitting the target of the proposed RC and the method of its application increases by at least 1.5-K2 times and, accordingly, the required outfit of the RC and h layers of carriers (airplanes, ships), necessary for the conduct of hostilities can be reduced not less than 1 times.

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Claims (2)

1. A cruise missile, consisting of a docking and separation unit for a solid-fuel starting engine, a marching subsonic stage containing aerodynamic control surfaces for the position of the aircraft in flight and a turbojet engine, and a supersonic combat stage containing a nose fairing, aerodynamic control surfaces for a combat stage in autonomous flight, flight control system and guidance on the target, warhead and solid-fuel engine, characterized in that the supersonic combat stage times placed in the cavity of the march stage, which contains its own nose cone, flight control system and guidance to the target, warhead and additional solid fuel engine. 2. The cruise missile according to claim 1, characterized in that the marching stage is docked with a turbojet engine by means of a compartment docking device.