Thermal protection device, in particular for an aerospace vehicle

• US 5,489,074 A
• Filed: 03/31/1994
• Issued: 02/06/1996
• Est. Priority Date: 04/01/1993
• Status: Expired due to Fees

• Current Assignee: Societe Nationale D'Etude Et De Construction De Moteurs D'Aviation
• Original Assignee: Societe Europeenne de Propulsion
• Inventors: Lacombe, Alain, Tual, Michel, Arnold, Thibault
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/220,807
• Time in Patent Office: 677 Days
• Field of Search: 244/158 A, 244/160, 244/121, 244/131, 244/132, 52/506, 52/513, 403/408.1, 403/356, 403/357
• US Class Current: 244/159.1
• CPC Class Codes: B64G 1/58 Thermal protection, e.g. heat shields
• CPC Class Codes: F16C 11/06 Ball-joints; Other joints having more than one degree of angular freedom, i.e. universal joints universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts F16D3/16
• CPC Class Codes: F16C 11/069 with at least one separate part to retain the ball member in the socket; Quick-release systems
• CPC Class Codes: F16C 2202/24 Insulating
• CPC Class Codes: F16C 2326/47 Cosmonautic vehicles, i.e. bearings adapted for use in outer-space in general B64G
• CPC Class Codes: Y10T 403/7022 Resilient
• CPC Class Codes: Y10T 403/75 having a joining piece extending through aligned openings in plural members

Abstract

The thermal protection device is made up of a plurality of juxtaposed unit modules each comprising a fairing element provided with fixing tabs and thermal insulation integrated in the fairing element. The gap between neighboring fairing elements is limited to the minimum width necessary for accommodating thermal expansion thereof. The connection means which releasably connect the fixing tab to a primary structure to be protected comprise a ball fixed to the fixing tab in adjustable manner and capable of being locked in a corresponding socket of a retaining part fixed to the primary structure. The ball is locked in its socket by means of a bolt capable of being released by action exerted against a resilient return force.

Claims

1. A thermal protection device, in particular for an aircraft or a space vehicle, the device comprising a plurality of juxtaposed unit modules each comprising a fairing element provided with fixing tabs, thermal insulation integrated in the fairing elements, and rigid connection means for releasably connecting the fixing tabs to a primary structure that is to be protected,

wherein the gap between neighboring fairing elements is limited to a value substantially equal to the minimum value necessary for accommodating thermal expansion of the fairing elements, and the rigid connection means for connecting a fixing tab of a module to the primary structure comprise a ball fixed to the fixing tabs in adjustable manner and capable of being locked inside a corresponding socket of a retaining part fixed to the primary structure, the ball being locked in its socket by means of a bolt capable of being released by action exerted against a resilient return force.

2. A device according to claim 1, wherein the locking bolt is movable in a direction substantially perpendicular to the direction of the resilient return force, which force acts on a keeper having a face that forms a self-locking ramp against which the locking bolt bears.

3. A device according to claim 2, wherein the locking bolt is released by applying traction on said keeper from outside the thermal protection device through a gap between neighboring unit modules.

4. A device according to claim 3, wherein the traction is exerted by means of a wire permanently fixed to said keeper and extending through said gap.

5. A device according to claim 2, wherein the locking bolt is released by applying thrust on said keeper from outside the thermal protection device through a gap between neighboring unit modules.

6. A device according to claim 2, wherein the locking bolt is released by acting on said keeper from inside the primary structure.

7. A device according to claim 1, wherein the ball is fixed to the fixing tab in a manner that is adjustable by screwing a part carrying the ball in or out, thereby enabling the distance between the fixing tab and the ball to be varied so as to adjust the position of the fairing element as a function of the desired aerodynamic shape independently of dimensional faults in the fairing elements, in the primary structure, and in the connection means.

8. A device according to claim 1, wherein each fairing element is in the form of an open box having an outside face and flanks perpendicular to said outside face.

9. A device according to claim 1, wherein each fairing element has a polygonal outside face and the fixing tabs are situated in the middles of the sides of the fairing elements.

10. A device according to claim 1, wherein each fairing element has a quadrangular outside face and the fixing tabs are situated in the corners of the fairing elements and extend away from the outside face, being perpendicular to planes that are normal to the outside face and that contain the diagonals thereof.