Countermeasures radiation source for missile decoys

Abstract

A missile decoy countermeasures radiation source that provides a controlled radiation source that emulates jet aircraft engines, wherein the radiation generating elements utilizes specific catalysts, dopings and fuel additives burned within a reticulated ceramic matrix. Further a variable speed multi-element rotating blade structure is incorporated to provide the chopping of the radiation. The reticulated ceramic burner is doped such that radiation spectral lines are highest in those bands that are of interest to anti-aircraft missile seekers. The outermost surface of the decoy body is fabricated from reticulated ceramics that are transparent to the select lines of radiant energy, is breathable and a smooth, providing an aerodynamic surface for fast moving aircraft. Further the injection of specific catalysts, dopings and fuel additives provide for real-time spectral management and the injection of oxidizers allows for high altitude operations.

1 . A countermeasures missile decoy radiation source wherein: 
 a. A burner is created from reticulated silicon-carbide ceramics, and;    b. At least two layers of dopants are deposited within the ceramic matrix with the innermost doping zone being a mixture of Platinum and Zirconium. The second doping zone being Samarium or Thorium/Thorium-Cerium Oxides or their complexes and other catalysts, and;    c. The preferred fuel is Jet fuel [JP4-JP8], and;    d. The fuel may contain additives of finely divided Aluminum, Magnesium, Boron or nanoenergenic particles and;    e. Fuel flow can be controlled to manage radiation output, and;    f. An outer metallic cylinder with periphery slots is spun around the ceramic burner to provide programmatic chopping of the radiation, and;    g. The speed of the chopping element is controlled by electro-mechanical means.    h. A microcomputer is used to manage fuel flow, chopper speed, dopants mixing, igniter control and inlet port geometry.    
   
   
       2 . A missile decoy countermeasures radiation source as described in  claim 1;  wherein the ceramics are, but not limited to; Aluminum Oxides, Zirconium Silicates, Titanium Oxides, Rhenium Boride, Oxides, Carbides or Nitrides.  
   
   
       3 . A missile decoy countermeasures radiation source as described in claims  1  and  2 ; wherein one or more of the dopants are Barium HexaAluminate, Palladium, Cerium, Zirconium Oxides, Phosphates, Thorium/Thorium-Cerium Oxides or their complexes and other catalysts.  
   
   
       4 . A missile decoy countermeasures radiation source as described in claims  1 ,  2  and  3 ; wherein an outer porous ceramic tube [ 155 ] encases the burner and chopper assembly [See  FIG. 3 ] to provide an aerodynamic surface for high-speed use. Further the ceramic tube is transparent to the radiation bands of interest.  
   
   
       5 . A missile decoy countermeasures radiation source as described in claims  1  through  4 ; wherein the microcomputer manages the injection of dopants into the fuel.  
   
   
       6 . A missile decoy countermeasures radiation source as described in claims  1  through  5 ; wherein the microcomputer or Digital Signal Processor reads an Ultraviolet Sensor and an array of IR Spectral Sensors to manages the injection of dopants into the fuel.  
   
   
       7 . A missile decoy countermeasures radiation source as described in claims  1  through  6 ; wherein the fuel is supplied from the aircraft or helicopter via flexible tubing within the tether, providing decoy operations for an extended period of time.  
   
   
       8 . A missile decoy countermeasures radiation source as described in claims  1  through  7 ; wherein Oxidizers are programmatically added to the fuel providing decoy operations at high altitudes.