Thrust requirements for helicopter tail rotors?

Question

I'm researching what would be involved in generating temporary thrust for helicopter tail rotors for a system to be implemented in case of tail rotor failure or damage. I'm looking for specific links to find information on what amount of thrust..percentage wise or general amounts..are needed for operation of a military helicopter like a Blackhawk or any other smaller models. I'm interested in developing an emergency thrust device or system for loss of tail rotor function in combat or civilian use. I envision a jet propulsion system built into the tail and properly armored that is controlled by computer to alter it's amount of thrust as necessary depending on inputs from the pilot for course correction. Or a system of thrust vectoring of the primary engine exhaust. Such a system would provide emergency backup manuevering in the event of tail rotor loss or malfunction to provide ample time for evasion and descent in a controlled manner for both civilian and military helicopters.

Answer 1

That system was already developed, and even manufactured as a primary tail thrust system eliminating the tail rotor entirely. It is called the NOTAR.

Answer 2

The thrust has to match the counter force generated by the primary rotors! The tail rotors are there to prevent the aircraft from rotating on it's axis! Alternatives have already been tried through the years but go ahead and try something new! Try designing a primary that doesn't require a tail rotor in the first place! Learn everything you can about how the aircraft functions! Hopefully this will give you a few new ideas! Come up with something incredibly simple and reliable! Copy nature because it has had billions of years to try millions of differing configurations!