RU2090820C1 - Missile transport-launching pack - Google Patents

Abstract

FIELD: missile weaponry. SUBSTANCE: pack has a front cover of non-metal material and a metallized interior surface. Installed in the pack behind the front cover are a disk and diaphragm of radioabsorbing material, destructed together with the front cover by the shock wave produced by the gas generator. The rear bottom is rigidly attached to the pack shell. EFFECT: improved design.

Description

 The invention relates to the field of weapons, mainly to the construction of transport and launch containers of missiles.

Known transport-launch containers of box-shaped construction, which includes a metal shell of square cross-section, a set of external frames, front and rear covers. Moreover, the front and rear covers are covered with metal foil to protect against exposure to the rocket electromagnetic radiation coming from the outer space [1]
Also known are transport and launch containers of a cylindrical structure, including a metal shell of circular cross section, front and rear covers, a gas generator that generates a shock wave to discard the covers before launching the rocket [2]
The problem to be solved by the claimed invention is directed to reducing the level of reflections of the microwave signal inside the container and increasing the protection against exposure to the rocket of electromagnetic radiation coming from outside.

 The fact is that the missile transport and launch container (TPK) is designed to store, transport and launch the missile. Storage time without opening the container can be 10-20 years. With such long-term storage, a periodic check of the functioning of the rocket equipment is necessary. If the missile has an active homing head (AGSN), it becomes necessary to check the AGSN with the inclusion of radiation. Known TPK designs are not very suitable for testing rocket equipment with radiation on. Firstly, a high level of reflections in the TPK leads to the occurrence of a standing wave and, as a result, to the occurrence of spurious currents in the chains of the squibs, which can lead to unauthorized operation of the squibs. Secondly, the reflected microwave energy falls back into the AGSN antenna system and can damage the AGSN receiver circuit.

 To solve this problem, the TPK design is proposed, presented in the following figures: FIG. 1 rocket in a transport and launch container, FIG. 2 simplified equivalent circuit TPK.

 1) Radio engineering design.

 When checking the equipment of the rocket, the AGSN antenna 1 generates radiation directed along the axis of the TPK towards the front cover 2, the microwave energy passes through the radio-transparent fairing 3, falls on the radio-absorbing diaphragm 4 and on the radio-absorbing disk 5. The dielectric characteristics of the materials of the diaphragm and disk and the design dimensions are chosen so that the reflection coefficient in the frequency range of the AGSN is -8 -10 dB. The internal metallization of the front cover 6 provides protection against exposure to a rocket of electromagnetic radiation (shielding) coming from the external environment, and in addition enhances the effect of radar absorbing material. Part of the microwave energy due to reflections in the TPK flows in the direction of the metal bottom 7 and its cylindrical socket 12. Reflecting from the bottom, the microwave signal again falls on the radar absorbing diaphragm 4.

 The radar absorbing diaphragm 4 and the radar absorbing disk 5 also weaken the leaking microwave signals from the outer space from the side of the cover 2, thereby increasing the protection against the effects of electromagnetic radiation from the outer space on the rocket.

 2) Mechanical construction.

 When the rocket starts, an electric signal is supplied to the igniter on the gas generator of opening the cover 11. The gas generator opening the lid creates pressure inside the TPK. With a rapid increase in pressure in the TPK, a shock wave is formed. The front of the shock wave, reaching the radar absorbing diaphragm 4, the radar absorbing disk 5 and the front cover 2, destroys them into small fragments that scatter outside the container. After that, the rocket is ejected from the TPK using catapults 10. In FIG. 1 the following designations are also adopted: 8 - metal shell of circular cross section, 9 outer frame.

 The equivalent circuit of the radio engineering design of the TPK with the rocket can be arbitrarily depicted as a segment of the coaxial line agreed at the end of FIG. 2 Here, the rocket plays the role of the inner conductor 13, the transport and launch container acts as the outer shell of the coaxial line 14, the radar absorbing diaphragm and the radar absorbing disk play the role of the radar absorbing coordinated load 15, and the metallization of the inner surface of the lid and the rear bottom act as shielding short circuits 16. Physically, that the microwave field excited in such a segment of the coaxial line will be absorbed by the matched load.

 Sources of information.

 1. Technical translation of the ICB "Fakel" N 1102 / K, 1976, "The cost of manufacturing TPK missiles SAM-D." Source: Conference Materials of the American Institute of Astronautics and Aeronautics, 1975.

 2. US patent N 4455917 from 06/26/84, F 41 F 3/04, "Device for throwing off the end caps of the rocket container using a shock wave."

Claims (1)

 A transport and launch rocket container containing a metal shell of circular cross section, a front cover, a rear bottom, a generator for opening the front cover, characterized in that the front cover is made of non-metallic material with metallization of the inner surface, a disk made of radar absorbing material is installed inside the container behind the front cover and the diaphragm, which are destroyed together with the front cover by the shock wave when starting the gas generator, the rear bottom is rigidly attached to the container shell.

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