RU172805U1 - ROCKET - TARGET INDICATOR FOR RADAR AND RADIO TECHNICAL EXPLORATION - Google Patents

Abstract

This utility model relates to the field of unmanned aerial vehicles, in particular missiles, and can be used to ensure the destruction of a target at the required flight range of an anti-ship missile (RCC) under various flight conditions. Target missile for radar and electronic reconnaissance consists of a housing with four steering surfaces placed on the housing. The housing contains: a two-channel active-passive homing head, an inertial control system, an interface module, a telemetry information transmission system, an emergency self-liquidation system and an engine, while the two-channel active-passive homing head includes a target recognition unit and a target identification unit, which allows Based on the received radio technical characteristics, determine the class of the object. The technical result achieved by using the proposed utility model is to increase the effectiveness of combat use by increasing the range of detection of targets, the possibility of identifying them and choosing a given target. 2 ill.

Description

The proposed utility model relates to the field of unmanned aerial vehicles, in particular missiles, and can be used to ensure the destruction of a target at the required flight range of an anti-ship missile (RCC) under various flight conditions.

The prior art device for guiding a projectile or missile containing the first and second systems located on the launcher, the first to determine the coordinates of the target before the launch of the rocket, the second to calculate from this data the flight path to the target and the third system located on the shell , to guide the projectile during the flight along the calculated trajectory to the target location (Patent RU No. 2295102, publ. 10.03.2007, IPC F41G 7/20). The second system includes a transmitter, and the third - a receiver that receives signals from the second system and transfers them to the processor that controls the flight.

The disadvantage of this device is the inability to launch missiles at targets located outside the radar target detection zone.

The objective of the proposed utility model is to eliminate the aforementioned drawback, the creation of a target missile for radar and radio reconnaissance.

In modern conditions for the use of anti-ship missiles (RCC), there are limitations on the firing range due to the ability of the radar of the ship. Target designation (CC) can be obtained only in the area of direct radar visibility of the radar, which is about 40 km. When using anti-ship missiles at a longer range, it is necessary to obtain target designation (CC) from external sources, such as ship-mounted remote observation posts, aircraft-remote observation posts, and space-based means for obtaining data on the remote control, which is complex and expensive. When conducting an attack at the maximum range of RCC application, it is proposed to use a target-pointing missile for radar and radio reconnaissance (Rocket-TsU) to obtain operational data on the TsU.

The technical result achieved by using the proposed utility model is to increase the effectiveness of combat use by increasing the range of detection of targets, the possibility of identifying them and choosing a given target.

The problem is solved due to the fact that the target missile for radar and radio reconnaissance is made in the form of a body with four steering surfaces located on the body and placed in the body of a two-channel active-passive homing head, an inertial control system, an interface module, a telemetry information transmission system, emergency self-destruction system and engine, while the group of outputs of the two-channel active-passive homing head is connected to the first group inputs of the inertial control system, the second group of outputs of the inertial control system is connected to the group of inputs of the telemetry information transmission system, the third group of inputs and outputs of the inertial control system is connected to the first group of inputs and outputs of the interface module, the second group of inputs and outputs of the interface module is connected to the missile side connector, the third group of outputs of the interface module is connected to the group of inputs of the emergency self-liquidation module, the fourth group of inputs and outputs of the inertial control system with It is connected to the group of engine inputs and outputs, the fifth group of outputs of the inertial control system is connected to the steering surfaces, while the two-channel active-passive homing head includes a target recognition unit and a target identification unit, which allows to determine the class of the object based on the received radio technical characteristics.

The essence of the utility model is illustrated in FIG. 1 and FIG. 2.

In FIG. 1 is a structural diagram of an embodiment of an anti-ship target missile for radar and radio reconnaissance; in Fig.2 is a graphical representation of the results of the two-channel active-passive homing when searching in continuous mode.

In FIG. 1 marked:

1 - rocket body;

2 - two-channel active-passive homing head;

3 - inertial control system;

4 - interface module;

5 - a telemetry information transmission system;

6 - emergency self-destruction module;

7 - engine;

8 - steering surfaces;

9 - board port anti-ship missiles.

The proposed device, the circuit of which is presented in FIG. 1, in the general case, contains: a rocket body 1, in which a two-channel active-passive homing head (GOS) 2, an inertial control system (ISU) 3, an interface module 4, a telemetry information transmission system (TMI) 5, an emergency self-liquidation module 6 are located and engine 7. On the housing are steering surfaces 8 (in the proposed embodiment, four steering surfaces). The group of outputs of the two-channel active-passive homing head 2 is connected to the first group of inputs of the inertial control system 3, the second group of outputs of the inertial control system 3 is connected to the group of inputs of the transmission system TMI 5, the third group of inputs and outputs of the inertial control system 3 is connected to the first group of inputs - the outputs of the interface module 4, the second group of inputs and outputs of the interface module 4 is connected to the rocket connector 9, the third group of outputs of the interface module 4 is connected to the group of inputs of the emergency module self-liquidation 6, the fourth group of inputs / outputs of the inertial control system 3 is connected to the group of inputs / outputs of the engine 7, the fifth group of outputs of the inertial control system 3 is connected to the steering surfaces 8. The GPS 2 includes a target recognition unit and a target identification unit.

The proposed device provides software implementation of the possibility of obtaining the sign "Rocket-TsU" and the formation of the flight path. The shooting ship should have a TMI reception system, such as a mobile receiving radar station (MPRS), which allows receiving and processing TMI in real time. As part of the ammunition of the shooting ship, it is necessary to provide for the presence of 1 - 2 Rocket-TsU (for ammunition 8-16 anti-ship missiles).

Let us consider the operation of the device by the example of the operation of the embodiment of the device shown in FIG. one.

The TsU-missile is launched from a shooting ship in the direction of the alleged grouping of a likely enemy along a formed path consisting of two sections.

In the first section (≈22 km), Rocket-TsU performs a flight at a marching altitude of Nm ≈ 12 m, providing a maximum range of target detection for GOS 2. GOS 2 is turned on at a distance that allows you to observe the background-target situation (FSO) in the area, starting at 40 km from the shooting ship.

Further, throughout the flight, the seeker 2 continues to continuously scan the FTC and detect targets. GOS 2 alternates operating modes: active and passive; in active mode, GOS 2 emits signals of a certain power at a certain frequency, and then, receiving reflected signals from detected targets, determines their type (large, small) using the target recognition unit. In passive mode, the GPS 2 receives signals, analyzes the radio technical characteristics of these signals f, T, τ (carrier frequency, pulse repetition period, pulse duration), based on the received data in the target identification unit, identifies the type of detected radar station (radar) of the detected targets ( observation station, sighting station and others).

The transmission system TMI 5 transmits via radio channel to the MPRS data on the target situation for the formation of the flight mission salvo.

Upon reaching the maximum range D * of the radio horizon between the MPRS of the shooting ship and the Rocket-TsU flying at an altitude of 12 m, i.e. at a distance, when the Rocket-TsU begins to leave the visibility range of the MPRS, it begins to adjust its trajectory (implements a flight at altitude, providing a radio horizon of the MPRS) with the aim of the possibility of further transmission of data about the TsU.

Thus, the flight of the Rocket-TsU is carried out at altitude in accordance with the formula

where D is the current range from the firing ship to the 3M-24ECU rocket, km;

D * - the maximum range of the radio horizon between the MPRS of the shooting ship and the 3M-24ETSU missile flying at an altitude of 12 m, km:

Upon reaching the elimination time specified in the emergency self-liquidation module 6, or the complete development of fuel, the rocket - TS self-destructs.

In FIG. Figure 2 shows an option for detecting two targets: target 1, having the characteristics of signals f1, T1, τ1, and target 2, having the characteristics of signals f2, T2, τ2. Based on real-time data from the missile launcher received in real time from the Rocket-missile launcher at the MPRS, the commander of the shooting ship decides on the choice of the target for the attack, its belonging to the grouping of the likely enemy, the choice of the firing method and the beginning of a missile attack. Allowed time for making a decision is 6-7 minutes.

The use of the Rocket-TsU allows the launch of anti-ship missiles to attack targets located not only in the range of the radar of the ship, but also in the reach of the anti-ship missiles. During hostilities, if preliminary intelligence is available on the location of the likely enemy’s groupings (it is allowed to have them with an accuracy of 30 km), the use of the Missile - TSU will provide information on the TsU data with an accuracy of 3 km with a valid aging time of 6-30 minutes depending on range of anti-ship missiles, which is a prerequisite for ensuring the effective use of ammunition anti-ship missiles of a shooting ship.

The presented diagram and description of the device allow, using the existing element base, to manufacture the device, which characterizes the proposed utility model as industrially applicable.

Claims (1)

1. Target missile for radar and radio reconnaissance, made in the form of a body with four steering surfaces located on the body and placed in the body of a two-channel active-passive homing head, an inertial control system, an interface module, a telemetry information transmission system, emergency self-destruction system and an engine while the group of outputs of the two-channel active-passive homing head is connected to the first group of inputs of the inertial control system, in the third group of outputs of the inertial control system is connected to the group of inputs of the telemetry information transmission system, the third group of inputs and outputs of the inertial control system is connected to the first group of inputs and outputs of the interface module, the second group of inputs and outputs of the interface module is connected to the missile side connector, the third group of outputs of the interface module connected to the group of inputs of the emergency self-liquidation module, the fourth group of inputs and outputs of the inertial control system is connected to the group of inputs and outputs of the engine I, the fifth group of inertial control system output connected to the control surfaces, the two-channel active-passive homing head includes a target identification and target identification unit allowing based on the received radio characteristic to determine the class of the object.

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