Abstract: A solid fuel rocket burn rate control employing electrical energy preheating of the fuel grain at a plurality of locations dispersed over the grain burn face cross-section as a thrust control arrangement. The electrical energy of the preheating is generated by electrical battery cells which are dispersed across the grain cross-section and are triggered from an inert state into energy generation by burn face heat. The preheating situs moves continually in response to movement of the grain burn face; this is achieved through the use of high temperature electrical battery cell materials responding to the approach of the grain burn face by increased chemical activity and decreased electrical resistance. Preferably, the preheating is directly accomplished by the heat from electrical and other losses in the battery cells.

Abstract: Gas generator apparatus usable with a ducted rocket propellant having a high exponent burn rate, a burn rate that is burn chamber pressure sensitive to a greater degree than are normally used propellants. The gas generator includes elementary pressure regulating elements and apparatus for damping movement of the pressure regulating elements to remove oscillatory components of motion therefrom. Burn rate operating point determination and the stability characteristics thereof are described along with the effects of variations in propellant burn rate exponent and regulating element parameters.

Abstract: A propulsion system having an afterburning turbojet with the fuel supplied at the inlet to the turbojet compressor. The turbojet combustor has a bypass with a flow control connected at the inlets to the combustor and the bypass to control the amount of fuel-air mixture from the compressor that enters the combustor.

Abstract: An intermittent burning ramjet engine having a rough wall combustor with fuel supplied to a fuel injector upstream of the combustor. The fuel is cyclically ignited at a predetermined frequency. A resonator tuned to a frequency less than one-tenth of the combustor frequency is positioned between the combustor and the ramjet inlet.

Abstract: A solid boron fuel burning ramjet engine having a cylindrical primary burner located within a ramjet combustion chamber. A portion of the air bypasses the primary burner to provide secondary burning at the outlet of the primary burner. Solid boron fuel pellets are ground to powder in a wire brush fuel mill with the fuel then being carried to the primary burner by air which is passed through the fuel mill.