Abstract X-wing aircraft employ a rigid rotor-wing utilizing symmetrical circulationirfoils. The rotor is driven mechanically, and lift is achieved by modulation of air circulation about the base airfoils. This is accomplished by blowing compressed air through trailing edge openings in the rotor blades, and controlling the amount of air being ejected through those openings. By cyclically modulating the amount of ejected airflow, cyclic lift control is obtained. Likewise, by collectively controlling the ejected airflow collective lift control is obtained. One reason for the lack of popularity of circulation control rotor systems is concern over a loss or air pressure resulting from a damaged rotor blade. The damage to a rotor blade, such as ballistic damage, can cause the entire plenum pressure to be vented through that damaged blade. The result is a loss of pneumatic control, not only of that blade, but control of all rotor blades. It is this problem, the prevention of blade pressure loss, which is solved by this venture.
In (1) a circulation control rotor system for a helicopter having (a) air ejection slots and circulation control air passageways in its rotor blades for achieving cyclic control by ejected airflow around each rotor blade, (b) a stationary airflow plenum in its hub having ports therein for airflow therefrom, (c) rotating air ducts having input ends in alignment with the plenum ports, and opposite ends connected to the rotor blade air passageway for conducting plenum airflow from the ports to the rotor blade ejection slots, and (d) a series of control valves in the plenum airflow ports for governing airflow to the rotating air ducts as the ducts pass each valve in sequence azimuthally around the hub, (2) means for preventing loss of plenum pressure in the event of a blade air pressure loss including means sensing air pressure in the rotating air duct for each blade, and means comparing the sensed rotating air duct pressure with pressure at the control valves, the means for preventing loss of plenum pressure further including a closure means disposed in each rotating air duct, capable when activated of cutting off airflow into the rotating duct, and means activating said closure means in response to a comparing means signal from the means for comparing.
Claim 2
Dependent Claim
210 words
In (1) a circulation control rotor system for a helicopter having (a) air ejection slots and circulation control air passageways in its rotor blades for achieving cyclic control by ejected airflow around each rotor blade, (b) a stationary airflow plenum in its hub having ports therein for airflow therefrom, (c) rotating air ducts having input ends in alignment with the plenum ports, and opposite ends connected to the rotor blade air passageway for conducting plenum airflow from the ports to the rotor blade ejection slots, and (d) a series of control valves in the plenum airflow ports for governing airflow to the rotating air ducts as the ducts pass each valve in sequence azimuthally around the hub, (2) means for preventing loss of plenum pressure in the event of a blade air pressure loss including means sensing air pressure in the rotating air duct for each blade, and means comparing the sensed rotating air duct pressure with pressure at the control valves, the means for preventing loss of plenum pressure further including a closure means disposed in each rotating air duct, capable when activated of cutting off airflow into the rotating duct, and means activating said closure means in response to a comparing means signal from the means for comparing.
Claim 3
Dependent Claim
18 words
The means for preventing plenum pressure loss of claim 1 wherein pressure sensing means includes a pressure transducer.
Claim 4
Dependent Claim
28 words
The means for preventing plenum pressure loss of claim 1 wherein the closure means are valves, and the valve activating means includes a hydraulic or electrohydraulic servo unit.