RU166336U1 - ROCKET - TARGET INDICATOR FOR RADAR EXPLORATION - Google Patents

Abstract

Target-guided missile for radar reconnaissance, made in the form of a hull, with four steering surfaces located on the hull and housed in the hull by an active homing radar head, an inertial control system, an interface module, a telemetry information transmission system, an emergency self-liquidation system and an engine, while the group of outputs active radar homing head is connected to the first group of inputs of the inertial control system, the second group of outputs is inertial th 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 inputs of the emergency self-destruction 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, the fifth group of outputs is inertial A new control system is connected to the steering surfaces, while the active radar homing head includes a target recognition unit.

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 above drawback, the creation of a target missile for radar reconnaissance.

In modern conditions for the use of anti-ship missiles (ASM) 3M-24E, there are limitations on the firing range, due to the possibility 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 missile - target designator for radar 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 missile target for radar reconnaissance consists of a body with four steering surfaces located on the body and placed in the body: an active homing radar head, an inertial control system, an interface module, a telemetry information transmission system, an emergency self-liquidation system and engine, while the group of outputs of the active radar homing head is connected to the first group of inputs of the inertial control system the second group of inputs 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 the interface module is connected to the group of inputs of the emergency self-destruction 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 tor, the fifth group of inertial control system output connected to the control surfaces, the active radar seeker includes a target identification unit.

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 reconnaissance; in Fig.2 is a graphical representation of the results of the active radar homing when searching in continuous mode.

In FIG. 1 marked:

1 - rocket body;

2 - active radar homing;

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, comprises: a rocket body 1, in which an active radar homing head (GOS) 2, an inertial control system (IMS) 3, an interface module 4, a telemetry information transmission system 5, an emergency self-destruction module 6, and an engine 7 are located. the housing has steering surfaces 8 (in the proposed embodiment, four steering surfaces). The group of outputs of the seeker 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 telemetry information transmission system 5, the third group of inputs and outputs of the inertial control system 3 is connected to the first group of inputs and outputs of the interface module 4 , the second group of inputs and outputs of the interface module 4 is connected to the onboard connector of the rocket 9, the third group of outputs of the interface module 4 is connected to the group of inputs of the emergency self-destruction module 6, the fourth the 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 active radar homing 2 includes a target recognition 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 RCC).

The TMI 5 transmission system may be an ORBITA-IV telemetry information transmission system.

The system of emergency self-destruction 6 may be a system of emergency liquidation A3-M2.

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

A missile - a missile launcher 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), the Rocket - TsU performs a flight at a marching height 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 (FSC) in the area, starting at 40 km from the shooting ship.

Further, throughout the flight, GOS 2 continuously continues to scan the FTC and detect targets. GOS 2 emits signals of a certain power at a certain frequency, and then, receiving signals reflected from the detected targets, using the target recognition unit, it can determine their type (large, small). 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 (realizes a flight at altitude, providing a radio horizon of the MPRS) with the aim of the possibility of further transmitting data about the TsU.

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

Where:

D, [km] - current range from the firing ship to the 3M-24ETSU rocket,

D ∗, [km] is the limiting range of the radio horizon between the MPRS of the shooting ship and the 3M-24ETSU missile flying at an altitude of 12 m:

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

In FIG. Figure 2 shows the option of detecting two targets: target 1 large and goal 2 small. Based on real-time data from the missile-control system from the Rocket-missile to the MPRS, the commander of the shooting ship makes a decision on choosing the target for the attack, its belonging to the grouping of the probable enemy, choosing the firing method and launching a missile attack. Allowed time for a decision is 6-7 minutes.

The use of the Rocket - TsU allows the launch of anti-ship missiles to attack targets that are not only in the range of the radar of the ship, but also within the reach of the anti-ship missiles. During military operations, 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 Rocket-TsU will allow the TsU to receive data with an accuracy of 3 km with a valid aging time of 6-30 minutes depending on the range of use RCC, which is a prerequisite for ensuring the effectiveness of the ammunition of the RCC of a shooting ship.

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

Claims (1)

Target-guided missile for radar reconnaissance, made in the form of a hull, with four steering surfaces located on the hull and housed in the hull by an active homing radar head, an inertial control system, an interface module, a telemetry information transmission system, an emergency self-liquidation system and an engine, while the group of outputs active radar homing head is connected to the first group of inputs of the inertial control system, the second group of outputs is inertial th 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 inputs of the emergency self-destruction module, the fourth group of inputs / outputs of the inertial control system is connected to the group of inputs / outputs of the engine, the fifth group of outputs is inertial A new control system is connected to the steering surfaces, while the active radar homing head includes a target recognition unit.

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