US3691769A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Multi-component propellant jet propulsion
Assignee: RTX Corp
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Filing: 1964-01-16
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Granted: 1972-09-19
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Expires: 1984-01-16
Abstract
Abstract In the method of supplying a multi-component propellant including metal, oxidizer and hydrogen to the combustion chamber of a multi-component propellant rocket motor, the improvement which comprises stably suspending finely divided hollow particles of the metal in a liquid oxidizer to form a suspension of hollow particles of the metal in the liquid oxidizer, the hollow particles of said metal having a specific gravity approximately equal to the specific gravity of the liquid oxidizer; such that such suspension is stable and capable of withstanding the gravitational fields and acceleration forces to which the rocket engine system is subjected.
Inventors
- 👤 Joseph R Keilbach
- 👤 Vito J Sarli
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 13:25
CPC Classifications
C; C06; C06B; C06B45/00; C06B45/02
Claims Analysis
Total Claims: 18
Claim 1
Independent Claim
92 words
In the method of supplying a multi-component propellant including metal, oxidizer and hydrogEn to the combustion chamber of a multi-component propellant rocket motor, the improvement which comprises stably suspending finely divided particles of metal in a liquid oxidizer to form a slurry capable of retaining the metal particles in suspension under the gravitational fields and acceleration forces to which the rocket engine system is subjected, said particles of metal being provided with a coating which is inert to the liquid oxidizer and feeding the resulting metal-liquid oxidizer slurry to the combustion chamber.
Claim 2
Dependent Claim
92 words
In the method of supplying a multi-component propellant including metal, oxidizer and hydrogEn to the combustion chamber of a multi-component propellant rocket motor, the improvement which comprises stably suspending finely divided particles of metal in a liquid oxidizer to form a slurry capable of retaining the metal particles in suspension under the gravitational fields and acceleration forces to which the rocket engine system is subjected, said particles of metal being provided with a coating which is inert to the liquid oxidizer and feeding the resulting metal-liquid oxidizer slurry to the combustion chamber.
Claim 3
Dependent Claim
28 words
The improvement of claim 1 wherein the liquid oxidizer of the slurry is a member selected from the group consisting of liquid oxygen, nitrogen tetroxide and hydrogen peroxide.
Claim 4
Dependent Claim
30 words
The improvement of claim 1 wherein the liquid oxidizer of the slurry is liquid oxygen, and wherein the metal-liquid oxygen slurry and hydrogen are fed to the combustion chamber separately.
Claim 5
Dependent Claim
43 words
The improvement of claim 1 wherein the liquid oxidizer of the slurry is a member selected from the group consisting of nitrogen tetroxide, and hydrogen peroxide, and wherein the liquid oxidizer, the slurry, and liquid hydrogen are separately fed to the combustion chamber.
Claim 6
Dependent Claim
38 words
The improvement of claim 1 wherein the slurry comprises a small amount of a material capable of gelling the liquid oxidizer, said material serving to maintain the finely divided particles of the metal fuel suspended in the oxidizer.
Claim 7
Dependent Claim
56 words
The improvement of claim 1 wherein the liquid oxidizer of the slurry is liquid nitrogen tetroxide, and wherein the slurry comprises a small amount of finely divided aluminum oxide, the aluminum oxide serving to gel the liquid nitrogen tetroxide to thereby maintain the finely divided particles of the metal fuel suspended in the liquid nitrogen tetroxide.
Claim 8
Dependent Claim
43 words
The improvement of claim 1 wherein the particles of metal fuel suspended in the liquid oxidizer have a specific gravity approximately equal to the specific gravity of the liquid oxidizer, thereby insuring stability of suspension of the metal particles in the liquid oxidizer.
Claim 9
Dependent Claim
36 words
The improvement of claim 8 wherein the hollow metal particles are coated with an inert material capable of dissipating at the combustion temperature of the tripropellant system to release the metal particles to the combustion chamber.
Claim 10
Dependent Claim
10 words
The improvement of claim 8 wherein the metal is beryllium.
Claim 11
Dependent Claim
10 words
The improvement of claim 1 wherein the metal is aluminum.
Claim 12
Dependent Claim
53 words
The improvement of claim 1 wherein the total oxygen fed to the combustion chamber is approximately equal, stoichiometrically, to the amount of metal fed to the chamber, and wherein the amount of hydrogen fed to the combustion chamber is between about 20 and 32 per cent by weight of the total tripropellant fuel.
Claim 13
Dependent Claim
76 words
For use as a component of a multi-component jet engine propellant system comprising beryllium/oxygen/hydrogen, a stable slurry of a liquid oxidizer and finely divided beryllium particles, said particles of beryllium comprising hollow spheres which have a specific gravity approximately equal to the specific gravity of the liquid oxidizer such that the slurry is capable of retaining the beryllium particles in suspension under the high gravitational fields and acceleration forces to which the jet engine is subjected.
Claim 14
Dependent Claim
76 words
For use as a component of a multi-component jet engine propellant system comprising beryllium/oxygen/hydrogen, a stable slurry of a liquid oxidizer and finely divided beryllium particles, said particles of beryllium comprising hollow spheres which have a specific gravity approximately equal to the specific gravity of the liquid oxidizer such that the slurry is capable of retaining the beryllium particles in suspension under the high gravitational fields and acceleration forces to which the jet engine is subjected.
Claim 15
Dependent Claim
12 words
The slurry of claim 13 including a gellant for the liquid oxidizer.
Claim 16
Dependent Claim
39 words
The compoSition of matter of claim 13 wherein the beryllium particles are coated with a thin film of an inert material which is capable of being dissipated at the combustion temperature of the fuel to release the metal particles.
Claim 17
Dependent Claim
27 words
The composition of claim 13 wherein the liquid oxidizer is a member selected from the group consisting of liquid oxygen, nitrogen tetroxide, hydrogen peroxide, and mixtures thereof.
Claim 18
Dependent Claim
27 words
The method of claim 8 wherein the liquid oxidizer is a member selected from the group consisting of liquid oxygen, nitrogen tetroxide, hydrogen peroxide and mixtures thereof.
References Cited (Backward Citations)
No citation records indexed.
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-09-19 | 1976-03-20 | 1976-09-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-09-19 | 1980-03-20 | 1980-09-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-09-19 | 1984-03-20 | 1984-09-19 | $7700.00 | Window Closed / Lapsed |