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, andor 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, andor 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, andor an equivalent.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A method of amplifying specific fragments of a target DNA or RNA with the aid of a polymerase chain reaction in real time, the method comprising:
(a) providing a first oligonucleotide primer that comprises a donor fluorescent dye and a second oligonucleotide primer that comprises an acceptor fluorescent dye, wherein the first and second oligonucleotide primers are designed to anneal to partially overlapping portions of a target nucleic acid, wherein such overlap is not more than one nucleotide;
(b) allowing the primers to anneal to the target nucleic acid at partially overlapping positions;
(c) carrying out a polymerase chain reaction which allows for a fluorescent resonance transfer of energy between the donor dye and the acceptor dye;
(d) detecting an increase of fluorescent emission of the acceptor dye; and
(e) correlating the increase in the emission of the acceptor dye with the accumulation of the specific fragment of DNA or RNA.
2. The method of claim 1, wherein the first oligonucleotide primer is a forward primer, and the second oligonucleotide primer is a reverse primer.
3. A method of amplifying specific fragments of a target DNA or RNA with the aid of a polymerase chain reaction in real time, the method comprising:
(a) providing a first oligonucleotide primer that comprises a fluorescent dye and a second oligonucleotide primer that comprises a universal quencher, wherein the first and second oligonucleotide primers are designed to anneal to partially overlapping portions of a target nucleic acid, wherein such overlap is not more than one nucleotide;
(b) allowing the primers to anneal to the target nucleic acid at partially overlapping positions;
(c) carrying out a polymerase chain reaction which allows for a quenching effect between the fluorescent dye and the universal quencher;
(d) detecting a reduction in emission of the fluorescent dye; and
(e) correlating the decrease in the emission of the fluorescent dye with the accumulation of the specific fragment of DNA or RNA.
4. The method of claim 3, wherein the first oligonucleotide primer is a forward primer, and the second oligonucleotide primer is a reverse primer.