Stable-combustion oxidizer for hybrid rockets

• US 6,073,437 A
• Filed: 02/20/1998
• Issued: 06/13/2000
• Est. Priority Date: 10/13/1994
• Status: Expired due to Term

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Jones, H. Stephen
• Primary Examiner(s): KIM, TAE JUN
• Application Number:
  US09/027,170
• Time in Patent Office: 844 Days
• Field of Search: 60/251, 60/256, 60/257, 60/258, 60/259, 60/260, 60/726, 60/39.48, 60/39.823, 60/204, 60/220, 60/250, 60/39.827
• US Class Current: 60/204
• CPC Class Codes: F02K 9/50 using pressurised fluid to pressurise the propellants
• CPC Class Codes: F02K 9/72 using liquid and solid propellants, i.e. hybrid rocket-engine plants
• CPC Class Codes: F02K 9/94 Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants
• CPC Class Codes: G01B 11/24 for measuring contours or curvatures
• CPC Class Codes: G01B 11/245 using a plurality of fixed, simultaneously operating transducers G01B11/2408 - G01B11/2425, G01B11/255 take precedence

Abstract

A hybrid heater vaporization system (280, 380) including hybrid heaters (250, 350) can be used to vaporize liquid oxygen as it enters a motor (200, 300) to improve the combustion characteristics of a hybrid rocket (11). The motor (200, 300) preferably includes hybrid fuel both in a substantially cylindrical portion (216, 316) in the substantially cylindrical portion of the motor and a substantially multi-toroidal shaped portion (217, 316) in the forward end of the motor (200, 300). The vaporization system (280, 380) of the present invention finally makes hybrid rockets (11) practical for aerospace applications.

Claims

1. A method of improving combustion of a rocket comprising a first fluid propellant component and a second propellant component, wherein the second propellant component is in a casing, wherein the first fluid propellant component enters the casing in a stream, and wherein the rocket has a burn of a duration characterized by the burning of said propellant components, comprising the following steps:

(a) providing a first oxygen-driven hybrid heater having an exhaust stream having combustion products when ignited;

(b) positioning the hybrid heater such that the exhaust stream of combustion products of the hybrid heater are directed into the casing of the second propellant component when the hybrid heater is ignited and intersects the stream of the first fluid propellant component within the casing substantially throughout the burning of said propellant components;

(c) providing a sufficient quantity of oxygen to enable the hybrid heater to burn during substantially the entire duration of the rocket burn; and

(d) igniting the hybrid heater and supplying the sufficient quantity of oxygen to the hybrid heater such that the hybrid heater burns during substantially the entire duration of the rocket burn.

2. The method of claim 1, wherein the fluid propellant component is liquid oxygen.

3. The method of claim 2, wherein:

there are a plurality of hybrid heater, and the exhaust of each heater intersect the stream of the fluid propellant component.

4. A method of improving combustion of a hybrid rocket by gasifying liquid oxygen as it enters in a stream a casing containing hybrid fuel, before it contacts the hybrid fuel, comprising:

(a) positioning at least one oxygen-driven hybrid heater having an exhaust stream when ignited such that its exhaust stream intersects and mixes directly with the liquid oxygen stream within the casing as the liquid oxygen stream enters the casing, substantially throughout a duration of burning of the hybrid fuel and oxygen within the casing;

(b) providing O2 to the hybrid heater;

(c) igniting the hybrid heater.

5. The method of claim 4, wherein:

there are a plurality of hybrid heaters, and the exhaust streams of each heater intersect the stream of the liquid oxygen.

6. A method of pressurizing a rocket comprising a first liquid fuel component and a second fuel component with pressurization means to force the first liquid fuel component into contact with the second fuel component, comprising the following steps:

(i) storing an inert gas initially at a cryogenic temperature;

(ii) heating the inert gas with a hybrid heater having combustion products when ignited by mixing the combustion products of the hybrid heater with the gas;

(iii) introducing the heated inert gas into a container containing the first liquid fuel component; and

(iv) introducing the first liquid fuel component from said container to another hybrid heater.

7. A method of igniting a rocket comprising a first liquid fuel component and a second fuel component, wherein the second fuel component is in a casing, comprising the following steps:

(i) providing a hybrid heater having combustion products when ignited;

(ii) connecting the hybrid heater to the casing;

(iii) positioning the hybrid heater such that the combustion products of the hybrid heater enter the casing of the second fuel component when the hybrid heater is ignited and said combustion products directly mix with a stream of the first liquid fuel component within the casing substantially throughout a duration of burn of the fuel components in the casing; and

(iv) producing a spark to ignite the hybrid heater, which in turn ignites the rocket.

8. The method of claim 7, further comprising the steps of:

immersing in an oxygen-containing environment a spark-producing means which produces sparks when electricity is supplied thereto;

supplying electricity to the spark-producing means to produce the spark.

9. The method of claim 8, wherein:

the spark-producing means is a carbon arc.

10. A method of igniting a rocket comprising a first liquid fuel component and a second fuel component, wherein the second fuel component is in a casing, comprising the following steps:

providing a hybrid heater having combustion products when ignited;

connecting the hybrid heater to the casing;

positioning the hybrid heater such that the combustion products of the hybrid heater enter the casing of the second fuel component when the hybrid heater is ignited;

immersing in an inert-gas environment a spark-producing means which produces no sparks when in an inert-gas environment; and

causing oxygen to contact the spark-producing means to produce a spark to ignite the hybrid heater, which in turn ignites the rocket.

11. The method of claim 10, wherein:

the spark-producing means is a carbon arc.