초록 ▼

Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward porti

Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following x0) a region just ahead of the lip x1) substantially to said lip. A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.

대표청구항 ▼

We claim: 1. A supersonic aircraft jet engine installation having an inlet cowl assembly comprising: a) said cowl assembly having three separate generally tubular sections, b) said sections including a first forward inlet section that is forwardly translatable, a second bypass section that is forwa

We claim: 1. A supersonic aircraft jet engine installation having an inlet cowl assembly comprising: a) said cowl assembly having three separate generally tubular sections, b) said sections including a first forward inlet section that is forwardly translatable, a second bypass section that is forwardly translatable with respect to the first section, and a third section fixed to an engine structure, the forward inlet section having a forward position everywhere openly spaced entirely forwardly of the second section. 2. The cowl assembly of claim 1, wherein a side air intake is opened for bypassing of air into the engine when said inlet section is in said forward position. 3. The cowl assembly of claim 2 wherein said side air intake extends circumferentially. 4. The cowl assembly of claim 3 wherein the second section has an arcuately blunted leading edge exposed for efficient entrainment of additional intake air at low aircraft speeds, in response to first section translation forwardly relative to the second section. 5. The cowl assembly of claim 4 wherein the first and second sections have simultaneously forwardly translated positions, relative to the third section, whereby a circumferential opening between the second and third sections is increased to allow excess inlet air to bypass to the exterior. 6. The cowl assembly of claim 5 wherein the first section has a tilt position relative to the second section as the first and second sections are translated forwardly. 7. The cowl assembly of claim 3 wherein the first and second sections have simultaneously forwardly translated positions, relative to the third section, whereby an opening between the second and third sections is increased to allow excess inlet air to bypass to the exterior. 8. The cowl assembly of claim 7 wherein the first section has a tilt position relative to the second section as the first and second sections are translated forwardly. 9. The combination of claim 7 wherein circumferential openings are opened with co-existence when the first section is translated forwardly relative to the second section, and the second section is translated forwardly relative to the third section. 10. The combination of claim 7 including actuator means holding the first and second sections in relatively fixed closed positions when the second section is translated forwardly relative and the third section. 11. The combination of claim 2 wherein the aircraft has a wing, the first jet engine nacelle having a forward portion lapping the wing, and wherein the fuselage has reduced cross sections along fuselage length at zones closest to the first jet engine nacelle forwardmost portion. 12. The combination of claim 11 wherein the reduced cross sections of the fuselage relative to both the first jet engine nacelle and the wing section closest to the fuselage define an area ruled configuration or configurations. 13. The combination of claim 1, wherein c) said cowl assembly has forward and rearward separable in line air intake sections, d) said in line air intake sections have primary relatively closed positions, e) said in line air intake sections have secondary relatively separated positions to provide an air passing gap therebetween, f) and means for controlling relative tilt of the in line air intake sections to controllably vary the geometry of said air passing gap. 14. The combination of claim 13 wherein said f) means includes an actuator operatively connected to the forward section to vary tilt thereof relative to the rearward section. 15. A supersonic aircraft jet engine installation having an inlet cowl assembly comprising: a) said cowl assembly having two separate generally tubular sections, b) said sections including a first inlet section that is forwardly translatable, and a second section fixed to an engine structure, c) there being a gap between said first and second sections, the gap characterized in that a bypass function is provided when the sections are in close proximity to each other, and a low speed auxiliary air function is provided when the two sections are separated by a wider gap. 16. The cowl assembly of claim 15 wherein means is provided for controlling bodily translation of said forward section, thereby to control said gap.