Supersonic aircraft with spike for controlling and reducing sonic boom

Abstract

Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region therebetween and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.

1 . A method for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed, comprising the steps of: 
 providing said aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of said aerospace vehicle, said first spike having a leading end portion tapering to a predetermined cross-section, a first section having a first cross-sectional area, and a first transition region between said predetermined cross-section and said first section; and    configuring said first transition region so as to reduce the coalescence of shock waves produced by said first spike during normal supersonic flight of said aerospace vehicle.    
   
   
       2 . The method of  claim 1  wherein said leading end portion tapers toward a point.  
   
   
       3 . The method of  claim 1  wherein said step of configuring said first transition region comprises locating said first transition region in a predetermined location relative to said fuselage.  
   
   
       4 . The method of  claim 1  wherein said step of configuring said first transition region comprises shaping said first transition region with a predetermined contour.  
   
   
       5 . The method of  claim 1  further comprising the step of providing said aerospace vehicle with a second spike extending from the rear thereof substantially opposite the direction of normal flight of said aerospace vehicle.  
   
   
       6 . A method for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed, comprising the steps of: 
 providing said aerospace vehicle with a spike extending from the tail thereof substantially opposite the direction of normal flight of said aerospace vehicle, said spike having a leading end portion tapering to a predetermined cross-section, a first section having a first cross-sectional area, and a first transition region between said predetermined cross-section and said first section; and    configuring said first transition region so as to reduce the coalescence of shock waves produced by said spike during normal supersonic flight of said aerospace vehicle.