Methods of forming flexible structures for a rocket motor assembly, related flexible structures, and related assemblies including the flexible structures

Patent metadata

Field	Value
Publication number	US-10072613-B2
Application number	US-201514629297-A
Country	US
Kind code	B2
Filing date	Feb 23, 2015
Priority date	Feb 23, 2015
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

A method of forming a flexible structure for a rocket motor assembly comprises forming a polysiloxane composition comprising at least two different silicone materials. A preliminary structure is formed from the polysiloxane composition. The preliminary structure is cured to crosslink at least a portion of different polysiloxane chains of the preliminary structure. A flexible structure for a rocket motor assembly, a flexible assembly for a rocket motor assembly, a moveable thrust nozzle assembly for a rocket motor assembly, and a rocket motor assembly are also described.

First claim

What is claimed is:

1. A flexible assembly for a rocket motor assembly, comprising:
a first substrate;
a second substrate overlying the first substrate; and
a lamination comprising an alternating sequence of flexible structures and rigid structures extending between the first substrate and the second substrate, at least one of the flexible structures comprising a cured polysiloxane composition comprising crosslinked polysiloxane chains of at least two different silicone materials.

2. The flexible assembly of claim 1 , wherein each of the flexible structures has a shear modulus substantially equivalent to that of each other of the flexible structures.

3. The flexible assembly of claim 1 , wherein at least one of the flexible structures has a different shear modulus than at least one other of the flexible structures.

4. The flexible assembly of claim 1 , wherein each of the flexible structures independently has a shear modulus less than 26 psi.

5. The flexible assembly of claim 1 , wherein each of the flexible structures comprises the cured polysiloxane composition.

6. The flexible assembly of claim 1 , wherein at least one other of the flexible structures comprises another cured polysiloxane composition comprising crosslinked polysiloxane chains of at least two other different silicone materials.

7. A moveable thrust nozzle assembly for a rocket motor assembly, comprising:
a fixed housing; and
at least one flexible assembly coupled to and circumscribing a portion of the fixed housing and comprising:
a first substrate;
a second substrate overlying the first substrate; and
a lamination comprising an alternating sequence of flexible structures and rigid structures extending between the first substrate and the second substrate, at least one of the flexible structures comprising a substantially homogeneous, cured polysiloxane composition comprising crosslinked polysiloxane chains of at least two different silicone materials.

8. The moveable thrust nozzle assembly of claim 7 , wherein each of the flexible structures of the lamination independently has a shear modulus less than 26 psi.

9. The moveable thrust nozzle assembly of claim 8 , wherein each of the flexible structures of the lamination has a shear modulus substantially equivalent to that of each other of the flexible structures.

10. The moveable thrust nozzle assembly of claim 9 , wherein each of the flexible structures of the lamination comprises the cured polysiloxane composition.

11. A rocket motor assembly, comprising:
at least one stage comprising:
a vessel containing a propellant structure; and
a moveable thrust nozzle assembly connected to an end of the vessel and comprising:
a fixed housing; and
a flexible assembly coupled to and circumscribing a portion of the fixed housing and comprising:
a first substrate;
a second substrate overlying the first substrate; and
a lamination comprising an alternating sequence of flexible structures and rigid structures extending between the first substrate and the second substrate, at least one of the flexible structures comprising a substantially homogeneous, cured polysiloxane composition comprising crosslinked polysiloxane chains of at least two different silicone materials.

12. The rocket motor assembly of claim 11 , further comprising:
at least one additional stage comprising:
another vessel containing another propellant structure; and
another moveable thrust nozzle assembly connected to an end of the another vessel and comprising:
another fixed housing; and
another flexible assembly coupled to and circumscribing a portion of the another fixed housing and comprising:
another first substrate;
another second substrate overlying the another first substrate; and
another lamination comprising another alternating sequence of additional flexible structures and additional rigid structures extending between the another first substrate and the another second substrate, at least one of the additional flexible structures comprising another substantially homogeneous, cured polysiloxane composition comprising additional crosslinked polysiloxane chains of at least two different silicone materials.

13. The rocket motor assembly of claim 12 , wherein each of the flexible structures of the flexible assembly and each of the additional flexible structures of the another flexible assembly independently has a shear modulus less than 26 psi.

14. The rocket motor assembly of claim 13 , wherein each of the flexible structures of the flexible assembly has a shear modulus substantially equivalent to that of each of the additional flexible structures of the another flexible assembly.

15. The rocket motor assembly of claim 13 , wherein at least one of the flexible structures of the flexible assembly has a different shear modulus than at least one of the additional flexible structures of the another flexible assembly.

16. A flexible assembly for a rocket motor assembly, comprising:
a first substrate;
a second substrate overlying the first substrate; and
a lamination comprising an alternating sequence of flexible structures and rigid structures extending between the first substrate and the second substrate, at least one of the flexible structures comprising a substantially homogeneous, cured polysiloxane composition comprising crosslinked polysiloxane chains of at least two different silicone materials.

Assignees

• Orbital Atk Inc

Inventors

• Gajiwala Himansu M
• Hall Steven B

Classifications

• B32B2307/542

  Shear strength · CPC title

• B32B2307/546

  Flexural strength; Flexion stiffness · CPC title

• C08G77/12

  containing silicon bound to hydrogen · CPC title

• B32B2250/24

  All layers being polymeric · CPC title

• B32B3/266

  characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12 · CPC title