High performance space motor solid propellants

• US 5,798,480 A
• Filed: 08/02/1990
• Issued: 08/25/1998
• Est. Priority Date: 08/02/1990
• Status: Expired due to Term

• Current Assignee: Northrop Grumman Innovation Systems, Inc. (Northrop Grumman Corporation)
• Original Assignee: Cordant Technologies, Inc. (Howmet Aerospace, Inc.)
• Inventors: Willer, Rodney L., McGrath, David K.
• Primary Examiner(s): Miller, Edward A.
• Application Number:
  US07/561,973
• Time in Patent Office: 2,945 Days
• Field of Search: 149/19.4, 149/19.6
• US Class Current: 149/19.4
• CPC Class Codes: C06B 45/105 The resin being a polymer bearing energetic groups or containing a soluble organic explosive

Abstract

A family of high performance, space motor, solid propellants based on polyglycidyl nitrate elastomer binder, ammonium perchlorate oxidizer and beryllium or beryllium hydride fuel which do not require the presence of plasticizers. A high performance, space motor, solid propellant based on a polyglycidyl nitrate elastomer binder, ammonium perchlorate or hydroxy ammonium perchlorate and beryllium or beryllium hydride optimizes performance at low solids levels.

Claims

1. A high energy, space motor, solid propellant having a theoretical specific impulse, at 1,000 psi and expansion ratio of 50:

1, of at least about 350 lb-sec/lb and comprising an isocyanate cured polyglycidyl nitrate binder and from about 40 to about 75% by weight high energy particulate solids comprising oxidizer particulates selected from the ammonium perchlorate and hydroxy ammonium perchlorate and fuel particulates selected from beryllium and beryllium hydride and wherein the polyglycidyl nitrate is an isocyanate curable polyglycidyl nitrate polymer having a functionality of nearly 2.0 or more and a hydroxyl equivalent weight of from about 1000 to about 1700 and has less than about 2 to 5% by weight cyclic oligomer present in the polyglycidyl nitrate.

2. A high energy, solid propellant of claim 1 wherein the particulate solids comprise from about 40 to 60% by weight.

14. The propellant of claim 1, wherein said specific impulse is above 380.

3. A high energy, space motor, plasticizer-free, solid propellant comprising an isocyanate cured polyglycidyl nitrate binder and from about 40 to about 75% by weight high energy particulate solids comprising oxidizer particulates selected from ammonium perchlorate and hydroxy ammonium perchlorate and fuel particulates selected from beryllium and beryllium hydride, wherein the polyglycidyl nitrate is an isocyanate curable polyglycidyl nitrate polymer having a functionality of nearly 2.0 or more and a hydroxyl equivalent weight of from about 1000 to about 7000 and has less than about 2 to 5% by weight cyclic oligomer present in the polyglycidyl nitrate.

4. A high energy, space motor, plasticizer-free, solid propellant of claim 3 wherein the particulate solids comprise from about 40 to 60% by weight.

5. A high energy, space motor, plasticizer-free, solid propellant of claim 3 wherein the oxidizer particulates comprise ammonium perchlorate.

6. A high energy, space motor, plasticizer-free, solid propellant of claim 5 wherein the fuel particulates also comprise beryllium.

7. A high energy, space motor, plasticizer-free, solid propellant of claim 3 wherein the oxidizer particulates comprise ammonium perchlorate and the fuel particulates comprise beryllium.

8. A high energy, space motor, plasticizer-free, solid propellant of claim 3 wherein the oxidizer particulates comprise ammonium perchlorate and the fuel particulates comprise beryllium hydride.

9. A high energy, space motor, plasticizer-free, solid propellant of claim 7 wherein the particulates additionally comprise cyclotetramethylene tetranitramine, diaminoglyoxime and mixtures thereof.

10. A high energy, space motor, plasticizer-free, solid propellant of claim 8 wherein the particulate solids additionally comprise cyclotetramethylene tetranitramine, diaminoglyoxime and mixtures thereof.

11. A high energy, space motor, plasticizer-free, solid propellant of claim 3 wherein the propellant includes additional components selected from bonding agent, burn rate modifier, nitrate ester stabilizer and urethane cure catalyst.

12. A high energy, space motor, solid propellant having a theoretical specific impulse at 1,000 psi and expansion ratio of 50:

1 of at least about 380 lb-sec/lb and comprising about 15 to about 60% by weight of an isocyanate cured polyglycidyl nitrate binder and from about 40 to about 85% by weight of particulate solids and wherein the particulate solids comprise oxidizer particulates selected from ammonium perchlorate or hydroxy ammonium perchlorate and fuel particulates selected from beryllium and beryllium hydride and wherein the polyglycidyl nitrate is an isocyanate curable polyglycidyl nitrate polymer having a functionality of nearly 2.0 or more and a hydroxyl equivalent weight of from about 1000 to about 1700 and has less than about 2 to 5% by weight cyclic oligomer present in the polyglycidyl nitrate.

13. The propellant of claim 12, wherein the binder is present in an amount of about 25 to 60% by weight and said particulate solids are present in an amount of about 40 to 75% by weight.