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Ramjet for a supersonic and hypersonic aircraft

Imported: 24 Feb '17 | Published: 06 Jan '04

Marc Bouchez, François Falempin, Vadim Levine

USPTO - Utility Patents

Abstract

According to the invention, the wall (

5) is mounted movably as one so as to be able to slide longitudinally in translation, bringing the joint line (

14) closer to the fuel injector (

9) so as progressively to modify the geometries of the oxidant inlet (

16) and of the combustion chamber (

15), said geometries passing progressively from a first state (I) in which, for a Mach number lying between 1.5 and 3, said oxidant inlet (

16) constricts said oxidant flow only slightly and the combustion chamber (

15) is long and divergent, to a second state (III) in which, for a Mach number lying between 8 and 12, said oxidant inlet (

16) strongly constricts said oxidant flow and said combustion chamber (

15) is shorter and exhibits a constant cross section.

Description

The figures of the attached drawing will give a good understanding of how the invention can be produced. In these figures, identical references designate similar elements.

FIG. 1 shows, in a diagrammatic view in perspective, with partial cutaway, an examplary embodiment of the ramjet in accordance with the present invention.

FIG. 2 is a diagrammatic view in transverse section along the line II—II of FIG.

1.

FIG. 3 is a partial diagrammatic side view along the line III—III of FIG.

2.

FIG. 4 is a diagram, in diagrammatic longitudinal view, illustrating the main elements of the ramjet in accordance with the present invention.

FIG.

5 and FIG. 6 respectively illustrate the relative positions of the main elements of said ramjet, at the front end and at the rear end thereof, for operation at Mach 3.

FIG.

7 and FIG. 8 correspond respectively to FIGS. 5 and 6, for operation of the ramjet at Mach 6.

FIG.

9 and FIG. 10 correspond respectively to FIGS. 5 and 6, for operation of the ramjet at Mach 8.

FIG. 11 is a diagram indicating an altimetric-trajectory example, as a function of the flight Mach number, for the ramjet in accordance with the present invention.

FIG. 12 is a diagram indicating the specific impulse as a function of the flight Mach number, for said ramjet.

Claims

1. A ramjet for a supersonic and hypersonic aircraft, including an elongate body which consists of:

said walls of said body delimiting between them:

wherein:

2. The ramjet as claimed in claim 1, wherein the translation of said lower wall is rectilinear.

3. The ramjet as claimed in claim 1, wherein the translation of said lower wall is curvilinear.

4. The ramjet as claimed in claim 1, wherein the said lower wall is shorter than said upper wall.

5. The ramjet as claimed in claim 1, wherein the ridge of said upper wall exhibits the shape of a bevel so as, with said second face, to define a minimum inlet cross section for the flow of oxidant.