# US 5,341,639 A · Fullerene rocket fuels

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- Number: US 5,341,639 A
- Document ID: US5341639A
- Status: Granted
- Kind: A
- Application number: 08/005,729
- Filed: 1993-01-19
- Granted: 1994-08-30
- Earliest claimed: 1993-01-19
- Assignees: The United States of America as represented by the Secretary of the Army
- Inventors: William D. Stephens
- Web page: https://patentgrep.com/patent/US5341639A

## CPC

- F02K 9/08: using solid propellants (F02K9/72 takes precedence; using semi-solid or pulverulent propellants F02K9/70)
- C10L 5/00: Solid fuels (produced by solidifying fluid fuels C10L7/00; peat briquettes C10F7/06)
- F02K 7/18: Composite ram-jet/rocket engines
- Y10S 977/948: Energy storage/generating using nanostructure, e.g. fuel cell, battery
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- C10L: FUELS NOT OTHERWISE PROVIDED FOR; NATURAL GAS; SYNTHETIC NATURAL GAS OBTAINED BY PROCESSES NOT COVERED BY SUBCLASSES C10G OR C10K; LIQUIFIED PETROLEUM GAS; USE OF ADDITIVES TO FUELS OR FIRES; FIRE-LIGHTERS
- Y10S: TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS

## Abstract

Solid fuel gas generator compositions for use in ducted rockets, in which fullerenes or substituted fullerenes are used. Fullerene compounds in which easily oxidizable groups, oxidizing groups, or salts of oxidizing acids are attached to the spherical carbon skeleton of the fullerene.

## Claims

### Claim 1

In the method of operation of a ducted rocket comprising a primary combustor containing a solid fuel gas generator for supplying hot fuel gases and partial decomposition products for combining with oxygen acquired from air during flight for producing complete combustion products in a secondary combustor and discharging combustion gases through a nozzle to provide thrust for said ducted rocket, the improvement in said method of operation of said ducted rocket for achieving high efficiency in the operation of said ducted rocket comprising incorporating into a solid fuel gas generator composition a solid fuel selected from the group consisting of fullerenes having a cage structure and derivatives of fullerenes having a cage structure.

### Claim 2 (depends on 1)

The method for achieving high efficiency in the operation of said ducted rocket as defined in claim 1 wherein said solid fuel gas generator is comprised of an energetic binder selected from a polymeric hydrocarbon and an oxygenated polymer having oxidizing groups selected from nitro, nitrate, nitramine, perchlorate, and azide attached thereto, and wherein said solid fuel fullerenes having a cage structure has a C.sub.60 cage structure and wherein said derivatives of solid fuel fullerenes having a cage structure has a C.sub.60 cage structure.

### Claim 3 (depends on 2)

The method for achieving high efficiency in the operation of said ducted rocked as defined in claim 2 where said solid fuel fullerenes having a C.sub.60 cage structure has an attached easily oxidizable group selected from the group consisting of alkyl, alkylene, acetylenic, alcohol, amine, hydrazine, mercaptan, sulfide, disulfide, and aldehyde groups, said solid fuel fullerenes having a C.sub.60 cage structure with said attached easily oxidizable group being solid fuel fullerenes derivatives.

### Claim 4 (depends on 3)

The method for achieving high efficiency in the operation of said ducted rocket as defined in claim 3 wherein said solid fuel fullerenes derivatives are salts of fullerenes amine derivatives compounded with an oxidizing acid selected from nitric acid and perchloric acid.

### Claim 5 (depends on 2)

The method for achieving high efficiency in the operation of said ducted rocket as defined in claim 2 wherein said solid fuel fullerenes having a C.sub.60 cage structure has an oxidizing group attached directly to said solid fuel fullerenes C.sub.60 cage structure.

### Claim 6 (depends on 2)

The method for achieving high efficiency in the operation of said ducted rocket as defined in claim 2 wherein said solid fuel fullerenes having a C.sub.60 cage structure has an oxidizing group attached through an intermediate group to said fullerenes C.sub.60 cage structure.