An anti-torque thruster system implemented onboard an aircraft comprising a propulsion means coupled to the aircraft, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the aircraft, a fuel storage container coupled to the propulsion means via a fuel delivery con
An anti-torque thruster system implemented onboard an aircraft comprising a propulsion means coupled to the aircraft, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the aircraft, a fuel storage container coupled to the propulsion means via a fuel delivery conduit, wherein the fuel storage container is capable of storing an appropriate fuel for the propulsion means, a valve means disposed between the fuel storage container and the propulsion means, wherein the valve means may be useable to regulate the flow of fuel from the fuel storage container to the propulsion means, and a controller for controlling the valve means to regulate the flow of fuel from the fuel storage container to the propulsion means, wherein the controller is capable of receiving input from at least one input device.
대표청구항▼
What is claimed is: 1. An anti-torque thruster system implemented onboard a helicopter comprising: a propulsion means coupled to the helicopter, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the helicopter, and wherein the propulsion means is in addition to
What is claimed is: 1. An anti-torque thruster system implemented onboard a helicopter comprising: a propulsion means coupled to the helicopter, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the helicopter, and wherein the propulsion means is in addition to and of a different type from the helicopter's main anti-torque system; a fuel storage container coupled to the propulsion means via a fuel delivery conduit, wherein the fuel storage container is capable of storing an appropriate fuel for the propulsion means; a valve means disposed between the fuel storage container and the propulsion means, wherein the valve means may be useable to regulate the flow of fuel from the fuel storage container to the propulsion means; and a controller for controlling the valve means to regulate the flow of fuel from the fuel storage container to the propulsion means, wherein the controller is capable of receiving input from at least one input device. 2. The anti-torque thruster system of claim 1, wherein the propulsion means includes a primary propulsion means and a secondary propulsion means. 3. The anti-torque thruster system of claim 2, wherein the primary propulsion means is capable of providing at least some anti-torque thrust and the secondary propulsion means is capable of providing at least some additional anti-torque thrust. 4. The anti-torque thruster system of claim 1, wherein the propulsion means is coupled to the helicopter during the initial manufacture of the helicopter. 5. The anti-torque thruster system of claim 1, wherein the propulsion means is coupled to the helicopter as a bolt-on product. 6. The anti-torque thruster system of claim 1, wherein the propulsion means is located along a main fuselage. 7. The anti-torque thruster system of claim 1, wherein the propulsion means is located along a junction between a main fuselage and a tail boom. 8. The anti-torque thruster system of claim 1, wherein the propulsion means is connected to a tail boom of the helicopter. 9. The anti-torque thruster system of claim 1, wherein the propulsion means comprises at least one rocket. 10. The anti-torque thruster system of claim 1, wherein the propulsion means utilizes a liquid-propellant. 11. The anti-torque thruster system of claim 1, wherein the propulsion means comprises at least one hydrogen peroxide fueled rocket. 12. The anti-torque thruster system of claim 11, wherein the rocket is fueled by approximately 85% to 98% hydrogen peroxide. 13. The anti-torque thruster system of claim 1, wherein fuel storage container includes a pressurizing means. 14. The anti-torque thruster system of claim 1, wherein the fuel delivery conduit includes a pressurizing means. 15. The anti-torque thruster system of claim 1, wherein the propulsion means utilizes a solid propellant. 16. The anti-torque thruster system of claim 1, wherein the propulsion means includes a rotatable nozzle. 17. The anti-torque thruster system of claim 1, wherein the controller is coupled to at least one control switch, wherein the at least one control switch is capable of providing a receivable input to the controller to activate the controller. 18. The anti-torque thruster system of claim 17, wherein the control switch is coupled to at least one anti-torque pedal of the helicopter. 19. The anti-torque thruster system of claim 1, wherein the controller is coupled to at least one sensor, wherein the at least one sensor is capable of providing a receivable input to the controller. 20. The anti-torque thruster system of claim 19, wherein the at least one sensor comprises at least one of a tail rotor sensor, a main rotor sensor, an anti-vibratory sensor, a spin sensor, a strobe, a tachometer, and/or a gyroscope. 21. An anti-torque thruster system implemented onboard a helicopter comprising: at least one propulsion means coupled to the helicopter, wherein each propulsion means is capable of providing a measure of anti-torque thrust to the helicopter, and wherein the propulsion means is in addition to and of a different type from the helicopter's main anti-torque system; at least one fuel storage container coupled to at least one propulsion means via at least one fuel delivery conduit, wherein each fuel storage container is capable of storing an appropriate fuel for the at least one propulsion means; at least one valve means disposed between each fuel storage container and each propulsion means, wherein each valve means may be useable to regulate the flow of fuel from the fuel storage container to the coupled propulsion means; and at least one controller for controlling each valve means to regulate the flow of fuel from each fuel storage container to the coupled propulsion means, wherein the controller is capable of receiving input from at least one input device. 22. A method for using an anti-torque thruster system onboard a helicopter, comprising: providing at least one propulsion means coupled to the helicopter, wherein each propulsion means is capable of providing a measure of anti-torque thrust to the helicopter, and wherein each propulsion means is in addition to and of a different type from the helicopter's main anti-torque system; providing at least one fuel storage container coupled to at least one propulsion means via at least one fuel delivery conduit, wherein each fuel storage container is capable of storing an appropriate fuel for the at least one propulsion means; providing at least one valve means disposed between each fuel storage container and each propulsion means, wherein each valve means may be useable to regulate the flow of fuel from the fuel storage container to the coupled propulsion means; providing at least one controller for controlling each valve means to regulate the flow of fuel from each fuel storage container to the coupled propulsion means, wherein the controller is capable of receiving input from at least one input device; receiving certain flight information; receiving certain helicopter specific information; comparing the received flight information with the received helicopter specific information to determine whether any of the received flight information exceeds any parameters of the received helicopter specific information; activating, if the compared flight information exceeds the parameters of the received helicopter specific information, the propulsion means to provide at least a measure of anti-torque thrust to the helicopter. 23. The method of claim 22, wherein the flight information comprises at least some data regarding at least one of the functionality of a tail rotor, a main rotor, rotation of the helicopter, and/or pilot input. 24. The method of claim 22, wherein the helicopter specific information comprises at least some data regarding at least one of a helicopter's main rotor torque and performance, tail rotor torque and performance, torque parameters, engine type, aerodynamics, structural limitations, mechanical limitations, performance limitations, acceptable rotation parameters, safety limitations, and/or an equivalent.
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