초록 ▼

All-internal compression inlets for supersonic aircraft, with variable geometry systems and shock stability bleed systems provide high performance, large operability margins, i.e. terminal shock stability that reduces the probability of inlet unstart, and contribute little or nothing to the overall

All-internal compression inlets for supersonic aircraft, with variable geometry systems and shock stability bleed systems provide high performance, large operability margins, i.e. terminal shock stability that reduces the probability of inlet unstart, and contribute little or nothing to the overall sonic boom signature of the aircraft. These inlets have very high internal area contraction or compression and very low external surface angles. All shocks from the internal inlet surfaces are captured and reflected inside the inlet duct, and all of the external nacelle surfaces are substantially aligned with the external airflow. The inlet shock stability system consists of bleed regions that duct bleed airflows to variable area exits with passive or active exit area controls. This reduces the risk of inlet unstarts by removing airflow through a large open throat bleed region to compensate for reductions in diffuser (engine) corrected airflow demand. Because the stability bleed is not removed until the inlet terminal shock moves upstream over the bleed region, the necessary normal shock operability margin is provided without compromising inlet performance (total pressure recovery, and distortion).

대표청구항 ▼

We claim: 1. A supersonic inlet for use with an aircraft, said supersonic inlet comprising: an internal duct having an opening for receiving airflow and a throat section, said inlet further comprising one or more external surfaces wherein said one or more entire external surfaces are aligned with t

We claim: 1. A supersonic inlet for use with an aircraft, said supersonic inlet comprising: an internal duct having an opening for receiving airflow and a throat section, said inlet further comprising one or more external surfaces wherein said one or more entire external surfaces are aligned with the flow of the aircraft, said opening of said internal duct further comprised of a first and second leading edge, wherein said leading edges are staggered in location; and said throat section of the inlet further incorporating a shock stability bleed system, wherein a portion of said airflow is removed from said internal duct so that a shock wave is maintained within said throat section. 2. A supersonic inlet for use with an aircraft, said supersonic inlet comprising: an internal duct having an opening for receiving airflow and a throat section, said inlet having one or more external surfaces aligned with the airflow of said aircraft, a centerbody positioned within said duct, and having a leading edge, the external surfaces being aligned with the airflow of the aircraft from the leading edge to an associated engine; said opening of said internal duct further comprised of a leading edge, wherein said leading edge of said duct is staggered in location with respect to the leading edge of the centerbody; and said throat section of the inlet further includes a shock stability bleed system, wherein a portion of said airflow is removed from said internal duct so that a shock wave i maintained within said throat section. 3. The inlet of claim 1 wherein all of the external surfaces are aligned with the airflow of the aircraft. 4. The inlet of claim 1 wherein one or more of the external surfaces are aligned with the airflow of the aircraft at all operating conditions. 5. The inlet of claim 1 wherein said internal duct comprises one or more movable compression surfaces. 6. The inlet of claim 1 wherein said one or more external compression surfaces are fixed in location. 7. The inlet of claim 2 wherein all of the external surfaces are aligned with the airflow of the aircraft. 8. The inlet of claim 2 wherein one or more of the external surfaces are aligned with the airflow of the aircraft at all operating conditions. 9. The inlet of claim 2 wherein said internal duct comprises one or more movable compression surfaces. 10. The inlet of claim 2 wherein said one or more external compression surfaces are fixed in location. 11. A low boom supersonic inlet for use with an aircraft engine, the supersonic inlet comprising: one or more internal surfaces forming an internal duct to provide airflow to the aircraft engine and having an opening for receiving airflow; and one or more external surfaces that are entirely aligned with the flow of air to the inlet whereby the inlet external shock waves that contribute to the sonic boom signature of the aircraft have been substantially reduced. 12. The low sonic boom supersonic inlet of claim 11 wherein said internal surfaces provide supersonic compression and are movable into two or more positions. 13. The low sonic boom supersonic inlet of claim 11 wherein said internal surfaces extend from the leading edge to the engine entrance, said internal surfaces comprising one or more compression surfaces for providing supersonic compression of the air to the inlet throat and subsonic diffusion of the air to the engine entrance. 14. The low sonic boom supersonic inlet of claim 11 wherein said internal duct further comprises a throat section having a shock stability bleed system comprised of one or more bleed passageways wherein a portion of said airflow is removed from said internal duct through said one or more bleed passageways so that an airflow shock wave is maintained within said throat region. 15. The low sonic boom supersonic inlet of claim 11 wherein all of the compression surfaces are located within said internal duct. 16. The low sonic boom supersonic inlet of claim 15 wherein excess air not required by the engine is ducted out of the inlet through an overboard bypass system. 17. The low sonic boom supersonic inlet of claim 11 wherein said internal duct has a rectangular cross-sectional shape. 18. The low sonic boom supersonic inlet of claim 11 wherein said internal duct has a elliptical cross-sectional shape. 19. The low sonic boom supersonic inlet of claim 1 wherein said internal duct has a rectangular cross-sectional shape. 20. The low sonic boom supersonic inlet of claim 1 wherein said internal duct has a elliptical cross-sectional shape. 21. The low sonic boom supersonic inlet of claim 2 wherein said internal duct has a rectangular cross-sectional shape. 22. The low sonic boom supersonic inlet of claim 2 wherein said internal duct has a elliptical cross-sectional shape. 23. The low sonic boom supersonic inlet of claim 1 wherein said shock stability bleed system further comprises bleed passages having a variable area exit. 24. The low sonic boom supersonic inlet of claim 1 wherein said throat section of said inlet further comprises one or more movable internal sidewalls in the throat section for varying the throat area. 25. The low sonic boom supersonic inlet of claim 1 wherein the interior surfaces of the internal duct have continuous surfaces from the opening to the exit of the inlet.