LT6371B - Air target for a rocket with infrared targeting system - Google Patents

Abstract

Self-propelled air target for a rocket having an infrared targeting system. Said target comprises a hull, control surfaces, a rocket engine and an exhaust pipe cover and is provided with a heat-exchanger with multiple edges on the exhaust pipe. Such heat-exchanger with multiple edges increases efficiency of heat dissipation from the rocket engine into surrounding thus improving target visibility in infrared radiation spectrum.

Description

Field of the Invention

FIELD OF THE INVENTION relates to moving air targets, especially self-propelled infra-red air targets.

Description of the Related Art

Self-propelled aerial targets are used for missile exploration or military training. One type of such missile is specially designed to be detected by its infrared trace.

U.S. Pat. US 6,600,165 B1 is the nearest analog disclosed. The target described comprises an airplane or rocket body and nose, wings and / or control surfaces, a system for supplying fuel and an oxidizer to a combustion chamber containing the combustion gas, and for supplying the combustion gas to a propulsion nozzle and an infrared emitter. The target has at least one tube connecting the combustion chamber or driving nozzle to the nose, wings and / or target control surface, or to an outer member attached thereto. The main disadvantage of this target is the high cost of the airframe body with the necessary controls and systems.

The present invention seeks to improve the functional-performance characteristics of infra-red rocket missile targets by improving their infrared radar visibility, simplifying design and reducing the cost of such a target.

Brief Description of the Invention

In order to improve the functional-performance characteristics of rocket targets for infra-red missiles, the outer surface of the target nozzle is provided with a ribbed heat exchanger that radiates more efficiently the thermal energy generated during rocket motor operation. This improves the target's visibility in the infrared range.

Brief description of the drawings

Other features and advantages of the invention are described in the detailed description of the invention with reference to the following drawings:

Fig. 1 illustrates a rocket target with a universal transport and launching device;

Fig. 2 is a cross-sectional view of a rocket target;

Fig. 3 is a cross-sectional view of the propulsion portion of a rocket target;

Fig. 4 is a rear view of the propulsion portion of a rocket target.

Before referring to the detailed description of the invention, with reference to the drawings of exemplary embodiments of the invention, it is to be noted that identical elements are denoted by the same numerals throughout the drawings.

Detailed Description of the Invention

It should be understood that many specific details are set forth to provide a full and comprehensible description of an exemplary embodiment of the invention. However, it will be apparent to one skilled in the art that the details of the embodiments of the invention do not limit the scope of the invention, which may be practiced without such specific guidance. The well-known techniques, procedures, and ingredients have not been described in detail to avoid the confusion of exemplifying embodiments of the invention. Furthermore, this description is not to be construed as limiting the examples provided, but merely as an implementation thereof.

According to an embodiment of the invention, the rocket target (1) according to the invention comprises a housing (3), an engine (4), an impeller (5), a heat exchanger (6) and an aerodynamic hood (7).

A propulsion system comprising a combustion engine (4), a heat exchanger (6), and an aerodynamic enclosure is located at the rear of the missile target. The heat exchanger (6) is formed as the outer surface of the nozzle of the rocket target (1). The edges of the heat exchanger (6) are shaped in such a way that they radiate more effectively the thermal energy generated by the operation of the rocket motor into the environment.

The rocket target (1) is transported to launch from the universal transport-launching device (2).

The present invention is intended to be used as a self-propelled aerial target in various military exercises or missile tests.

Although many features and advantages have been enumerated in the description of the invention, together with the structural details and features of the invention, the description is exemplary of the invention. Changes may be made to the details, in particular the shape, size and layout of the materials, without departing from the principles of the invention, in accordance with the most widely understood meanings of the terms used herein.

Claims (1)

1. A self-propelled rocket air target comprising a housing (3), control surfaces (5), a rocket motor (4), and a combustion exhaust manifold cover (7), further comprising a heat exchanger (6) mounted on the combustion exhaust outlet of the device. covering many edges.