Granted Patent B2

US 7,404,288 · App. 11/261,433 · Granted Jul 29, 2008

Abstract

Claims (24)

1. A hybrid rocket system, comprising:

a motor case having a proximal end and a distal end, the motor case defining an interior volume including a combustion chamber at the proximal end, wherein the motor case is configured to hold solid rocket fuel, the motor case having a first nozzle at the distal end;

a fuel tank coupled to the proximal end of the motor case, the fuel tank defining an internal volume configured to hold a fluid oxidizer;

a partition interposed between the motor case and the fuel tank, wherein at least one access passageway extends through the partition, the access passageway providing exterior access to the interior volume of the motor case or the internal volume of the fuel tank while the hybrid rocket motor is coupled to the fuel tank, wherein the ratio of solid rocket fuel weight to oxidizer weight is maintained within a predetermined range of values and wherein the system operates at a substantially constant specific impulse through the range of values;

a conduit fluidly coupling the supply of oxidizer to a second nozzle, wherein the conduit provides a pathway for oxidizer to flow in a downstream direction from the supply of oxidizer toward and into the second nozzle;

a pressure regulator coupled to the conduit and interposed between the supply of oxidizer and the second nozzle, wherein the pressure regulator regulates the pressure of oxidizer at a location downstream of the pressure regulator and upstream of the second nozzle to a set point pressure at or below a first pressure, wherein the first pressure comprises the pressure required to maintain the oxidizer in a gas state to ensure that the any oxidizer flowing through the conduit is in a gas state prior to entering the second nozzle;

wherein the at least one access passageway comprises a motor case access passageway, the motor case access passageway having a first opening in communication with the interior volume of the motor case and a second opening in an external wall of the partition.

2. The system of claim 1 , wherein the oxidizer comprises Nitrous Oxide and the solid rocket fuel comprises hydroxyl terminated polybutadiene and wherein the oxidizer to fuel ratio is in the range of around 4 to round 12.

3. The system of claim 1 , wherein the Nitrous Oxide is stored in the fuel tank at a temperature of around −95 degrees Fahrenheit.

4. The system of claim 1 , wherein the at least one access passageway comprises a fuel tank access passageway, the fuel tank access passageway having a first opening in communication with the internal volume of the fuel tank and a second opening in an external wall of the partition.

5. The system of claim 1 , further comprising an injector configured to inject fluid oxidizer from the fuel tank into the motor case, wherein the injector is entirely positioned within the fuel tank on a first side of the bulkhead partition.

6. The system of claim 1 , wherein the first pressure is the vapor pressure of the oxidizer at a given temperature.

7. A hybrid rocket system, comprising:

a motor case having a proximal end and a distal end, the motor case defining an interior volume including a combustion chamber at the proximal end, wherein the motor case is configured to hold solid rocket fuel, the motor case having a first nozzle at the distal end;

a fuel tank coupled to the proximal end of the motor case, the fuel tank defining an internal volume configured to hold a fluid oxidizer;

a partition interposed between the motor case and the fuel tank, wherein at least one access passageway extends through the partition, the access passageway providing exterior access to the interior volume of the motor case or the internal volume of the fuel tank while the hybrid rocket motor is coupled to the fuel tank, wherein the ratio of solid rocket fuel weight to oxidizer weight is maintained within a predetermined range of values and wherein the system operates at a substantially constant specific impulse through the range of values;

a conduit fluidly coupling the supply of oxidizer to a second nozzle, wherein the conduit provides a pathway for oxidizer to flow in a downstream direction from the supply of oxidizer toward and into the nozzle;

a pressure regulator coupled to the conduit and interposed between the supply of oxidizer and the nozzle, wherein the pressure regulator regulates the pressure of oxidizer at a location downstream of the pressure regulator and upstream of the second nozzle to a set point pressure at or below a first pressure, wherein the first pressure comprises the pressure required to maintain the oxidizer in a gas state to ensure that the any oxidizer flowing through the conduit is in a gas state prior to entering the second nozzle; and

an injector configured to inject fluid oxidizer from the fuel tank into the motor case, wherein the injector is entirely positioned within the fuel tank on a first side of the partition.

8. A hybrid rocket system, comprising:

a motor case having a proximal end and a distal end, the motor case defining an interior volume including a combustion chamber at the proximal end, wherein the motor case is configured to hold solid rocket fuel, the motor case having a first nozzle at the distal end;

a fuel tank coupled to the proximal end of the motor case, the fuel tank defining an internal volume configured to hold a fluid oxidizer;

a partition interposed between the motor case and the fuel tank; and

an injector configured to inject fluid oxidizer from the fuel tank into the motor case, wherein the injector is entirely positioned within the fuel tank on a first side of the partition.

Assignments (8)