A system for evaluating aircraft/watercraft/battle-vehicle survivability equipment comprising: (1) a Static Pyrotechnic Unit (SPTU) and a support stand; (2) a system of Short Range Simulating Rocket (SRSR) and a rocket launching apparatus; and (3) a control system that activates said Static Pyrotech
A system for evaluating aircraft/watercraft/battle-vehicle survivability equipment comprising: (1) a Static Pyrotechnic Unit (SPTU) and a support stand; (2) a system of Short Range Simulating Rocket (SRSR) and a rocket launching apparatus; and (3) a control system that activates said Static Pyrotechnic Unit in (1) and said system SRSR in (2). When the Static pyrotechnic Unit is ignited, the resulting flash has an IR wavelength and multi spectral emission, intensity and time duration that simulate the initial flash created by a shoulder missile. When the Short Range Simulating Rocket is fired, the resulting radiation has an IR wavelength and multi spectral emission, intensity and time duration that simulates the radiation trail emitted from a fired shoulder missile. The flash created by the Static pyrotechnic Unit, and the trail emission of the Short Range Simulating Rocket are detected by the target survivability detection equipment, enabling the target to take protective measures.
대표청구항▼
1. A system for evaluating aircraft/watercraft/battle-vehicle survivability equipment comprising the following: (1) a Static Pyrotechnic Unit (SPTU) and a support stand on which said Static pyrotechnic Unit is positioned, said support stand comprising a base and insulating board connected by a teles
1. A system for evaluating aircraft/watercraft/battle-vehicle survivability equipment comprising the following: (1) a Static Pyrotechnic Unit (SPTU) and a support stand on which said Static pyrotechnic Unit is positioned, said support stand comprising a base and insulating board connected by a telescopic pole, said insulating board has wires for igniting the SPTU, and said SPTU is coated with a flammable material/compound for electrical ignition;(2) a system of Short Range Simulating Rocket (SRSR) and a rocket launching apparatus, said Short Range Simulating Rocket comprising a front section which comprises a pyrotechnic flare material, a back section which comprises a propellant, a rocket engine, and stabilizing fins, and in between the front section and the back section, there is a safety mechanism that enables/disables the activation of the SRSR, said launching apparatus comprising a tripod that can change azimuth and elevation and pedestal on top of which a launch tube is mounted; and(3) a control system that sets the timing of and activates said Static Pyrotechnic Unit in (1) and said system SRSR in (2),wherein, when the Static pyrotechnic Unit is ignited, the resulting flash is characterized by having an IR wavelength and multi spectral emission, intensity and time duration that simulates the initial flash created by a fired shoulder missile,wherein, when the Short Range Simulating Rocket is fired, the resulting radiation is characterized by having an IR wavelength and multi spectral emission, intensity and time duration that simulates the radiation trail emitted from a fired shoulder missile;wherein, the flash created by the Static pyrotechnic Unit, and the trail emission of the Short Range Simulating Rocket are detected by the target (aircraft/watercraft/battle-vehicle) survivability detection equipment and their trajectory and emission characteristics are determined, enabling the target to take protective measures. 2. The system in accordance with claim 1, wherein the Static pyrotechnic Unit comprises an electrical ignition system. 3. The system in accordance with claim 1, wherein said flammable material/compound comprises Magnesium, Teflon, and Viton or a combination thereof. 4. The system in accordance with claim 1, wherein the coating material/compound having a thickness of up to 1.5 mm determines the flash duration of the Static pyrotechnic Unit. 5. The system in accordance with claim 1, wherein the surface area of the Static pyrotechnic Unit comprises ribs or fins. 6. The system in accordance with claim 1, wherein the surface area, of the Static pyrotechnic Unit determines the intensity of the flash. 7. The system in accordance with claim 1, wherein the length of the Static pyrotechnic Unit determines the intensity of the flash. 8. The system in accordance with claim 1, wherein the shape of the Static pyrotechnic Unit determines the intensity of the flash. 9. The system in accordance with claim 1, wherein said insulating board is made from silica. 10. The system in accordance with claim 1, wherein said telescopic pole is made from metal. 11. The system in accordance with claim 1, wherein the pyrotechnic material of the Short Range Simulating Rocket has a ribbed structure. 12. The system in accordance with claim 1, wherein the pyrotechnic material of the Short Range Simulating Rocket comprises a (pellet) flare assembly. 13. The system in accordance with claim 1, wherein the Short Range Simulating Rocket is programmed to follow a ballistic trajectory based on preset direction, range, height, acceleration and speed for maximum safety. 14. A method for evaluating aircraft/watercraft/battle-vehicle survivability equipment comprising: providing the system of claim 1;determining the distance/range of the aircraft/watercraft/battle-vehicle being tested to assure that it is in the safe range for the test;igniting the Static pyrotechnic Unit; andactivating and launching the Short Range Simulating Rocket to test the aircraft/watercraft/battle-vehicle being tested within a predetermined time.
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이 특허에 인용된 특허 (7)
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