Shapeable Inlet Manifold for Hypersonic Scramjet

• US 20190331024A1
• Filed: 01/12/2018
• Published: 10/31/2019
• Est. Priority Date: 01/12/2017
• Status: Active Application

• Current Assignee: The Government Of The United States Of America, As Represented By The Secretary Of The Navy
• Original Assignee: The Government Of The United States Of America, As Represented By The Secretary Of The Navy
• Inventors: Maxwell, Jesse R., Goodwin, Gabriel B.
• Application Number:
  US15/869,932
• Publication Number:
  US 20190331024A1
• Time in Patent Office: Days
• CPC Class Codes: F02C 7/042 having variable geometry
• CPC Class Codes: F02K 7/10 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
• CPC Class Codes: F02K 7/14 with external combustion, e.g. scram-jet engines

Abstract

A shapeable inlet manifold for a hypersonic scramjet includes an inlet lower cowling; a mount surface; and an inlet stream surface movably coupled to the mount surface, wherein the inlet lower cowling and the inlet stream surface define an opening of the shapeable inlet manifold allowing fluid flow therethrough. The inlet stream surface has first and second dispositions relative to the lower cowling defining first and second shapes of the opening, thereby providing respective first and second flow characteristics through the inlet manifold during flight.

Claims

1. A shapeable inlet manifold for a hypersonic scramjet comprising:

an inlet lower cowling;

a mount surface;

an inlet stream surface movably coupled to the mount surface, wherein the inlet lower cowling and the inlet stream surface define an opening of the shapeable inlet manifold allowing fluid flow therethrough;

wherein the inlet stream surface is configured to have a first disposition relative to the inlet lower cowling defining a first inlet shape of the opening and a second disposition relative to the inlet lower cowling different from the first disposition defining a second inlet shape of the opening, thereby providing respective first and second flow characteristics through the inlet manifold during flight.

2. The shapeable inlet manifold of claim 1, further comprising an electronic controller configured to control the inlet stream surface to maintain leading edge shock attachment at the inlet, thereby providing optimum aerodynamic performance as a waverider as flight Mach number changes.

3. The shapeable inlet manifold of claim 1, wherein the electronic controller is configured to perform the steps of:

measuring a flight Mach number;

comparing the measured Mach number to a current Mach-number-specified-by-position;

adjusting the inlet stream surface of the shapeable inlet manifold towards a desired disposition based on the comparing;

iteratively ensuring that the flight Mach number matches the Mach-number-specified-by-position by correcting the disposition of the inner stream surface until a difference between the Mach numbers is within a predetermined tolerance.

4. The shapeable inlet manifold of claim 1, wherein a change from the first disposition to the second disposition includes a change in location of the inlet stream surface with respect to the inlet lower cowling.

5. The shapeable inlet manifold of claim 1, wherein a change from the first disposition to the second disposition includes a change in shape of the inlet stream surface.

6. The shapeable inlet manifold of claim 1, further comprising one or more actuators attached to the mount surface and to the inlet stream surface and configured to actuate the inlet stream surface from the first disposition to the second disposition.

7. The shapeable inlet manifold of claim 6, wherein the one or more actuators are linear actuators.

8. The shapeable inlet manifold of claim 1, wherein the inlet stream surface is a continuous flexible surface.

9. The shapeable inlet manifold of claim 1, wherein the inlet stream surface comprises a plurality of rigid tiles.

10. The shapeable inlet manifold of claim 1, wherein the inlet stream surface is configured to change from the first disposition to the second disposition via temperature-based shaping based on differences in local stiffness.

11. A method of controlling the shape of a shapeable inlet manifold for a hypersonic scramjet, the method comprising:

measuring a flight Mach number;

comparing the measured Mach number to a current Mach-number-specified-by-position;

adjusting an inner stream surface of the shapeable inlet manifold towards a desired disposition based on the comparing;

iteratively ensuring that the flight Mach number matches the Mach-number-specified-by-position by correcting the disposition of the inner stream surface until a difference between the Mach numbers is within a predetermined tolerance.