FUEL SYSTEMS AND OXIDIZERS

• US 3,705,495 A
• Filed: 01/21/1963
• Issued: 12/12/1972
• Est. Priority Date: 01/21/1963
• Status: Expired due to Term

• Current Assignee: Leonard Greiner, Welby G. Courtney
• Original Assignee: Leonard Greiner, Welby G. Courtney
• Inventors: Greiner, Leonard, Courtney, Welby G.
• Primary Examiner(s): Padgett, Benjamin R.
• Application Number:
  US04/253,523
• Time in Patent Office: 3,613 Days
• Field of Search: 60/35.4,214-216,219 149/74,75,109 23/152
• US Class Current: 60/214
• CPC Class Codes: C06B 27/00 Compositions containing a metal, boron, silicon, selenium or tellurium or mixtures, intercompounds or hydrides thereof, and hydrocarbons or halogenated hydrocarbons
• CPC Class Codes: C06B 47/02 the components comprising a binary propellant
• CPC Class Codes: C06B 47/14 comprising a solid component and an aqueous phase
• CPC Class Codes: Y10S 149/12 High energy fuel compounds

Abstract

7. A method of producing thrust which comprises reacting in a combustion chamber an oxidizer comprising a liquid composition consisting essentially of from about 59 percent to about 77 percent by weight of perchloric acid, from 0 to about 15 percent by weight of HNO3 and the remainder water, the amount of water being sufficient to form dihydrated perchloric acid with at least about 95 percent of the perchloric acid and a fuel selected from the group consisting of light metals, metal hydrides, and mixtures thereof.

Claims

1. A method of producing thrust which comprises reacting in a combustion chamber an oxidizer comprising substantially dihydrated perchloric acid and a fuel selected from the group consisting of light metals, metal hydrides and mixtures thereof.

2. A method of producing thrust which comprises reacting in a combustion chamber an oxidizer comprising substantially dihydrated perchloric acid and a fuel consisting predominantly of a light metal.

3. A method of producing thrust which comprises reacting in a combustion chamber an oxidizer comprising substantially dihydrated perchloric acid and a fuel consisting predominantly of a metal hydride.

4. A method of producing thrust which comprises reacting in a combustion chamber an oxidizer comprising substantially dihydrated perchloric acid and a fuel consisting predominantly of Zr.

5. A method of producing thrust which comprises reacting in a combustion chamber an oxidizer comprising substantially dihydrated perchloric acid and a fuel consisting predominantly of ZrH2.

6. A method of producing thrust which comprises reacting in a combustion chamber an oxidizer comprising substantially dihydrated perchloric acid and a fuel consisting predominantly of AlH3.

7. A METHOD OF PRODUCING THRUST WHICH COMPRISES REACTING IN A COMBUSTION CHAMBER AN OXIDIZER COMPRISING A LIQUID COMPOSITION CONSITING ESSENTIALLY OF FROM ABOUT 59 PERCENT TO ABOUT 77 PERCENT BY WEIGHT OF PERCHLORIC ACID, FROM 0 TO ABOUT 15 PERCENT BY WEIGHT OF HNO3 AND THE REMAINDER WATER, THE AMOUNT OF WATER BEING SUFFICIENT TO FORM DIHYDRATED PERCHLORIC ACID WITH AT LEAST ABOUT 95 PERCENT OF THE PERCHLORIC ACID AND A FUEL SELECTED FROM THE GROUP CONSISTING OF LIGHT METALS. METAL HYDRIDES, AND MIXTUES THEREOF.

8. A method of producing thrust which comprises reacting in a combustion chamber an oxidizer comprising about 90 percent by weight of dihydrated perchloric acid, about 8 percent by weight of nitric acid and about 2% by weight of water and a fuel selected from the group consisting of light metals, metal hydrides, and mixtures thereof.

9. A method of producing thrust which comprises reacting in a combustion chamber an oxidizer comprising about 84.2 percent by weight of dihydrated perchloric acid, about 10.5% by weight of nitric acid and about 5.3 percent by weight of water and a fuel selected from the group consisting of light metals, metal hydrides, and mixtures thereof.

10. In a rocket propellant system a liquid oxidizer consisting essentially of from about 59 percent to about 77 percent by weight of perchloric acid, from 0 to about 15 percent by weight of HNO3 and the remainder water, the amount of water being sufficient to form dihydrated perchloric acid with at least about 95 percent of the perchloric acid.

11. In a rocket propellant system a liquid oxidizer consisting essentially of about 90 percent by weight dihydrated perchloric acid, about 8 percent by weight nitric acid and about 2 percent by weight water.

12. In a rocket propellant system a liquid oxidizer consisting essentially of about 93 percent by weight dihydrated perchloric acid, about 6 percent by weight nitric acid and about 1 percent by weight water.

13. In a rocket propellant system a liquid oxidizer consisting essentially of about 84.2 percent by weight dihydrated perchloric acid, about 10.5 percent by weight nitric acid, and about 5.3 percent by weight water.