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.

Abstract: A trailer hitch alignment and signaling device for guiding a tow vehicle with a trailer hitch ball into position for coupling a trailer with a trailer tongue extending outwardly from the body of the trailer and a coupler for connection to the hitch ball at the outer end of the tongue, includes a mounting bracket to be connected to the trailer tongue; a Y-shaped guide with a leg and two arms connected to the leg at a diverging angle, the guide pivotally connected to the mounting bracket and rotatable between a first position with the arms below and on either side of the coupler and a second position with the arms of the guide stowed between the mounting bracket and the trailer body; and a signaling assembly for signaling that the tow vehicle is in correct position for connecting the trailer coupler to the hitch ball.

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.