Metallic nosecone with unitary assembly

Patent metadata

Field	Value
Publication number	US-9835425-B2
Application number	US-201514826668-A
Country	US
Kind code	B2
Filing date	Aug 14, 2015
Priority date	Aug 14, 2015
Publication date	Dec 5, 2017
Grant date	Dec 5, 2017

Abstract

A nosecone is provided and includes a ring that includes an angled surface, a nosecone tip, a double-walled shroud portion including inner and outer dome elements, a first end that interfaces with and is constrained by the nosecone tip and a second end that is connectable to the ring to define with the angled surface a sliding, resistive interface and a shim disposable in the double walled shroud portion to pre-load the sliding, resistive interface and to provide for separation distance between the inner and outer dome elements.

First claim

What is claimed is:

1. A nosecone, comprising:
a ring including an angled surface;
a nosecone tip;
a double-walled shroud portion including inner and outer dome elements, a first end that interfaces with and is constrained by the nosecone tip and a second end that is connectable to the ring to define with the angled surface a sliding, resistive interface; and
a shim disposable in between the inner and outer dome elements of the double walled shroud portion proximate to the nosecone tip to pre-load the sliding, resistive interface and to provide for separation distance between the inner and outer dome elements.

2. The nosecone according to claim 1 , wherein the nosecone tip, the shroud portion and the shim comprise titanium.

3. The nosecone according to claim 1 , wherein the angled surface is annular and increases in diameter with increasing distance from the nosecone tip.

4. The nosecone according to claim 1 , wherein the nosecone tip comprises a blunt curvature.

5. The nosecone according to claim 1 , wherein interior and exterior facing surfaces of the inner and outer dome elements each have a tailorable emissivity.

6. The nosecone according to claim 1 , wherein the shim comprises an annular ring having substantially uniform axial and radial thicknesses.

7. A nosecone, comprising:
a ring including an angled surface;
a nosecone tip including first and second transverse surfaces;
an inner dome element including a first end to interface with the first surface of the nosecone tip and a second end connectable to the ring;
an outer dome element disposable about the inner dome element and including a first end to be constrained by the second surface of the nosecone tip and a second end formed to define with the angled surface a sliding, resistive interface; and
a shim disposable between the respective first ends of the inner and outer dome elements to pre-load the sliding, resistive interface and to provide for separation distance between the inner and outer dome elements.

8. The nosecone according to claim 7 , wherein the nosecone tip, the inner and outer dome elements and the shim comprise similar metallic materials and the ring comprises aluminum and an exterior thermal protection coating.

9. The nosecone according to claim 7 , wherein the nosecone tip, the inner and outer dome elements and the shim comprise titanium.

10. The nosecone according to claim 7 , wherein the angled surface is annular and increases in diameter with increasing distance from the nosecone tip.

11. The nosecone according to claim 7 , wherein the nosecone tip comprises a blunt curvature.

12. The nosecone according to claim 7 , wherein the first surface of the nosecone tip comprises an annular, radially outwardly facing surface and the second surface of the nosecone tip comprises an annular, axially facing surface.

13. The nosecone according to claim 7 , wherein:
the first end of the inner dome element comprises an annular, radially inwardly facing surface to complement the first surface of the nosecone tip and an annular, axially facing surface to abut with the shim, and
the first end of the outer dome element comprises opposing annular, axially facing surfaces to abut with the shim and the second surface of the nosecone tip.

14. The nosecone according to claim 7 , wherein:
the second end of the inner dome element is configured to be welded to the ring, and
the second end of the outer dome element comprises an annular, angled surface to complement the angled surface of the ring.

15. The nosecone according to claim 7 , wherein the shim comprises an annular ring having substantially uniform axial and radial thicknesses.

16. The nosecone according to claim 7 , wherein the shim is integrally formed with at least one of the inner and outer dome elements.

17. A ballistic or rocket powered aircraft, comprising:
a fuselage; and
a nosecone configured for ejection from the fuselage, the nosecone comprising:
a ring including an angled surface and being attachable to and partially detachable from the fuselage;
a nosecone tip including first and second transverse surfaces;
an inner dome element including a first end to interface with the first surface of the nosecone tip and a second end connectable to the ring;
an outer dome element disposable about the inner dome element and including a first end to be constrained by the second surface of the nosecone tip and a second end formed to define with the angled surface a sliding, resistive interface; and
a shim disposable between the respective first ends of the inner and outer dome elements to pre-load the sliding, resistive interface and to provide for separation distance between the inner and outer dome elements.

18. The ballistic or rocket powered aircraft according to claim 17 , wherein the nosecone tip, the inner and outer dome elements and the shim comprise titanium and the ring comprises:
an upper anvil titanium portion; and
a lower anvil titanium portion from which the upper anvil titanium portion is detachable.

19. The ballistic or rocket powered aircraft according to claim 18 , wherein the inner dome element is welded to the upper anvil titanium portion.

20. The ballistic or rocket powered aircraft according to claim 18 , further comprising:
fasteners by which the inner dome element is fastened to the lower anvil titanium portion; and
pressure relief doors arranged with the fasteners.

Assignees

• Raytheon Co

Inventors

• Rodriguez Stephanie G
• Kuhar Todd
• Penhollow Thomas H
• Greer Brian B
• Hahn Mark A
• Reed Regina P
• Cordova Richard M
• Dickerson Patrick G
• Preston Kenneth G
• Ramos Rick A
• Hink Brady A
• Johnson Gary H

Classifications

• F42B10/46 Primary

  Streamlined nose cones; Windshields; Radomes {(F42B12/105 takes precedence)} · CPC title

• B64C1/40

  Sound or heat insulation {, e.g. using insulation blankets} · CPC title

• B64C1/0009

  Aerodynamic aspects · CPC title

• F42B15/36

  Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means · CPC title

• B64C30/00

  Supersonic type aircraft · CPC title