This paper deals with the instability of a hovering helicopter with controls fixed The generalized simple stabilization system, which is composed of rods, springs, dampers and masses and uses the rotor shaft to generate gyroscopic forces, has been analysed Special cases of a Second Order System have been considered and show that good stability can be achieved, thus overcoming the limitations of First Order Systems

In this essay the projected design for a spring tab rotor system is discussed for a particular size of rotor The size of rotor discussed is one designed to lift a comfortable 2,000 lb all up weight, for a single rotor helicopter

The behaviour of the rotor system collectively and the tab particularly is discussed under various conditions with respect to performance, vibration, weight, etc

Some possible applications are considered, and suggestions for simple helicopter configurations to which the rotor system might apply are put forward

Finally there is a technical appendix, in which the assumptions made and the formulae used to get results are stated In some cases where necessary the formulae have been derived

Graphs are presented to demonstrate the necessary parameters and the behaviour of the system