Abstract: A main helicopter rotor on which a rotary tubular shaft supports, at its top end, an annular hub integral with the tubular shaft itself. The assembly consisting of the tubular shaft and the hub is closed off at the top by a bell connected in removable manner to the hub and enclosing an oscillating plate assembly supported on a fixed shaft extending inside the aforementioned tubular shaft. A rotary ring on the oscillating plate assembly is connected to blade pitch change levers via respective rocker arms connected in articulated manner to the aforementioned rotary ring via respective pins extending radially in relation to the aforementioned bell and accessible via respective radial holes formed through the same.

Abstract: A control and actuating system for adjusting the cyclic pitch of the blades of a helicopter automatically and independently in response to the blade gyrating angular position and to the helicopter forward velocity. This action is also independent of the control and adjustment of the collective pitch. The actuation of the blade pitch is performed by means of cams and followers. A hydraulic force-amplifying system is used between the follower/cam assemblies and the blade pitch actuator so as to isolate the follower/cam assemblies from the load carrying components of the system. The displacement signals generated by two cams are combined into a single linear displacement signal which causes a corresponding rotational movement of the blade. The axial position of one cam is determined by the pilot's action and the axial position of the other cam is defined by the helicopter forward speed.

Abstract: Links (48-50) tangential to the rotorshaft (30) and connected to the inner swashplate ring (38) center the swashplate and restrain it from rotating (in the case of a stationary inner ring) by attachment to gearbox lugs (34-36), or drive it in unison with the rotorshaft (in the case of a rotating inner ring) by attachment to rotorshaft flanges. Spherical (rod-end) bearings (52-54, 56-58) so that the links can accommodate collective and cyclic swashplate attitude changes by moving out of plane.Links (70-72) tangential to the outer swashplate ring (64) and connected thereto and to the airframe (74) perform a similar function in restraining, centering and allowing for collective/cyclic movement of a stationary outer swashplate ring.

Abstract: A swashplate control system (10) has a first gimbal ring (26) pivotally mounted at (32) along a longitudinal axis. A second gimbal ring (24) is pivotally attached at (28) to the first gimbal ring (26) along a lateral axis. A longitudinal cyclic actuator (14) pivots the first gimbal ring (26) along the longitudinal axis. A lateral cyclic actuator (16) pivots the second gimbal ring (24) along the lateral axis. The lateral cyclic actuator (16) is mounted on the first gimbal ring (26). A swashplate (12) is rotatably mounted on the second gimbal ring (24).

Abstract: A helicopter blade positioning mechanism provides collective and cyclic pitch angle adjustment of the blades independently. This mechanism is all enclosed within the blade driving axle. The pitch angle of each blade is adjusted collectively and cyclicly by direct action on and within the blade hub. No other linkage is required between the blade and the blade pitch actuation means. The cyclic pitch adjustment of each blade is obtained either by a rotation imparted to the whole blade body or by twisting the blade, depending upon the mechanism configuration used. In both cases, the cyclic pitch variations are superimposed on the collective pitch setting, vary sinusoidally as the blades gyrate around their vertical axis of gyration, one full pitch variation cycle for each full gyration of the blades. This mechanism plays the role and replaces the well known swash-plate/linkage arrangement used on most helicopters.

Abstract: Apparatus for controlling both collective and cyclic pitch of blades of a helicopter rotor comprises a non-rotating plate which is connected via a fixed caliper and servo controls to a fixed housing and to which is attached the internal ring of a ball race bearing. The external ring of the bearing carries a rotating plate, which is connected by means of rotating caliper or links to each of the rotors and by means of pitch rods to control levers for adjusting the pitch of the blades. The non-rotating plate is fixed to external armatures of laminated joint pieces which are mounted slidingly up and down a guide base. The collective pitch is controlled by sliding the assembly of non-rotating plate and joint pieces up or down the guide base while the cyclic pitch is controlled by inclining the assembly relative to the main rotor shaft. This inclination involves deformations in the laminated joints.

Abstract: A device comprising cyclic plates driven by flexible blades for controlling a helicopter rotor. The device comprises upper flexible curved blades pivotably mounted on the rotor shaft, above the rotary plate, and pivotably mounted by a ball joint on the rotary plate, so as to cause it to rotate with the rotor shaft and at least one lower flexible curved blade, pivoting on an element of the structure of the helicopter and pivotably mounted by a ball joint on the non rotary plate, so as to secure it against rotation. The transverse stiffness of the blades ensures centering of the plates whereas the longitudinal flexibility of the blades and their end pivot point allow the blades to follow the axial translational and tilting movements imparted to the plates by pilot controls pivotably mounted to the non rotary plate, and transmitted to levers controlling the angle of attack of the rotor blades by means of links pivotably mounted to the rotary plate.

Abstract: Centering and stabilizing against rotation of a helicopter swashplate stationary ring are provided by spokes that are attached between the airframe and the stationary ring. When the swashplate tilts for cyclic control, the spokes bend and twist. When the swashplate translates for collective control, the spokes are required to lengthen and skew with respect to the swashplate. An elastomeric bearing having a cylindrical component to allow for skew and a shear pad to allow for lengthening attaches each spoke to the swashplate. The invention eliminates the need for the ball joint, standpipe and scissors associated with traditional swashplate centering techniques.

Abstract: A rotor system for a helicopter having a power shaft carrying at least one pair of diametrically opposite frames for rocking motion about an axis radially of said shaft. Sets of lift blades carried by the frames, respectively, for rocking motion about radial axes. A first pitch control means for rocking the frames and blades sets periodically. A second control means for rocking the blade sets simultaneously and equally relative to the frames. A third control means, including servomechanisms, for independently rocking the individual blades of said sets in different directions and extents relative to each other.

Abstract: A compact, rugged, streamline, stiff, pitch control system is devised in a helicopter by concentrically nesting a cyclic pitch control tube and collective pitch control tube within the drive shaft and stationary mast of a helicopter rotor system. The collective pitch control tube terminates in an upper inclined flange which engages a stationary swashplate by means of a bearing member disposed in an inclined bearing raceway in the stationary swashplate. The stationary swashplate in turn is rotatably coupled through a universal joint to the cyclic pitch control tube. Relative rotation of the cyclic pitch control tube with respect to the collective pitch control tube adjusts the stationary swashplate to a selected inclination with respect to the longitudinal axis of the control tubes and of the helicopter mast. A rotating swashplate is rotatably coupled to the stationary swashplate and transmits the angular orientation of the stationary swashplate to the pitch case of each rotor blade as appropriate.

Abstract: A device for controlling the cyclic and collective pitch of a helicopter rotor in which a fixed ring of an oscillating plate is maintained regularly fixed and is guided in its oscillations with respect to a drive shaft by a plurality of variable configuration supports uniformly distributed about the said drive shaft and connected to the said fixed ring by means of cylindrical pivots at least one of which is eccentric with respect to an axis rotation of an associated supported fork, which is perpendicular thereto.

Abstract: In a helicopter having a power shaft with a main axis and bearings for supporting an even number of blades for pivoting about their longitudinal axes, arms mounted on the respective blades for pivoting them in the same and opposite directions for cyclic and total pitch control, respectively, a featured control lever mounted intermediate its ends on a first pivot which lies in a first plane in which the main axis lies, with the control lever having movability of first and second kinds bodily with its pivot axis in the first plane and rockable about its pivot axis, respectively, links connecting the ends of the control lever with the free ends of the arms for pivoting the blades in first and second directions on movements of the control lever of the first and second kinds, respectively, an axially immovable control shaft turning with the power shaft, a swashplate mounted on the control shaft for universal movement on the latter, a first operating connection between the swashplate and first pivot, and including

Abstract: The pitches of the several blades in a helicopter rotor assembly are controlled by individual blade control subsystems. Those blade control subsystems respond to the output signals from accelerometers mounted on the blades. The signals from the accelerometers are used to control the pitch of the blades on which the accelerometers are mounted as well as the pitch of other blades. By appropriate orientation of any accelerometer and filtering within a particular feedback subsystem, each subsystem is designed to correct particular modes of blade motion to the exclusion of other modes of motion by varying lift.

Abstract: A rotatable bladed device for vehicles, such as especially a helicopter rotor, which has its blade pitch controlled by a setup which includes a swash plate setup controlled by a set of hydraulic actuators and the particular swash plate setup position and attitude in turn controls the blade pitch by a plurality of rods pivoted together at one end at one particular point movable longitudinally of the rotor axis, one of which rods has its other end pivoted at a point on the pitch arm by which it controls pitch and another of which rods is also pivoted at a point fixed by the rotational position at any particular time of the rotor hub.

Abstract: A helicopter rotor (10, 29) includes a rotor hub (11, 30) supporting a plurality of rotor blades, and a pitch control means comprising a universal joint (21, 45) adapted to permit both tilting and axial vertical movements of the control means to change the pitch of the rotor blades both cyclically and collectively. The universal joint has three radially extending pins (22) each supporting a radially slidable and rotatable bearing (23) having a spherical external surface (25), the bearings being located in generally axially extending tracks (26) having a circular cross-sectional shape for rolling engagement by the bearings.Axial movements are permitted by rolling of the bearings along the tracks and tilting movements by a combination of rolling and a sliding movement of the bearings along the pins.Several embodiments are described and illustrated.

Abstract: A redundant swashplate control system includes five or more actuators coupled to the swashplate. A feedback network independently controls each actuator to track a commanded position and a reference ram differential pressure that it related to the ram differential pressures sensed from all of the actuators.

Abstract: A rotor shaft for helicopters in which a main rotatable shaft is tubular and supports in its interior a shaft (25) which is angularly fixed relative to the helicopter body and disposed coaxially to said main shaft; a swivel plate assembly being coupled to said fixed inner shaft and being disposed, together with at least part of a plurality of kinematic linkages connecting said swivel plate to the rotor blades and a plurality of actuator means controlling the position of said swivel plate, inside the space lying between said main shaft and said inner shaft.

Abstract: A flight control system is provided for a helicopter furnishing safety feres, and providing back up control in the event of failure of controls of the rotary head swashplate of a helicopter. The swashplate is regulated by a series of actuators which are angularly positioned at particular settings around the swashplate. In the event of a control system failure, a supplemental system controls the selected settings for the swashplate, rotary head, and spar root and blade assemblies of the helicopter.

Abstract: An integrated transmission and helicopter rotor head is disclosed. Lift and bending moments generated by the rotating hub are carried by non-rotating support structure. The rotating rotor shaft is adapted to carry only torque loads. Partial gear reduction takes place above the rotor shaft, thereby reducing its torque loading. The invention includes a planet gear assembly wherein the ring gear is connected to the rotating hub, while the rotor drive shaft causes rotation of the sun gear. The hub swashplate is located above the hub with its control rods passing through the planet gear assembly.

Abstract: In a helicopter rotor, a blade control linkage is externally supported on the rotor hub and connected to the root end of a torque tube to provide torsion inputs to the blade by twisting the flexible spar member, which is enveloped by the torque tube and joined to the torque tube at a predetermined blade radial location. The linkage forms a parallelogram with the torque tube, and short vertical ball joint mounted links incline in two directions to accommodate blade lead/lag and flapping motions without introducing pitch coupling.

Abstract: A helicopter having a mast 50 which drives a rotor and which is driven from a transmission 16 has a swashplate 10 individually linked to pitch horns on each rotor blade. At least four control channels 11-15 are coupled to the swashplate. Three channels may control the attitude and position of the swashplate. The control channels 11-15 are actuated in response to pilot commands transmitted by means including mechanical, optical or electrical systems. A separate power unit 21-25, 31-35 supplies each control channel. Each power unit is directly driven by the transmission 16. Means 11c-15c applies control of the swashplate 10 from among the control channels 11-15.

Abstract: A cycloidal fluid flow engine suitable for turbine and propeller operation, employing blades of aircraft type wing and tail configuration, pitch controllable through the full range of advance ratios by reciprocating control surfaces, guided by an adjustable inclined bearing device on each blade hub, or one such device centrally located on the mainshaft housing.

Abstract: A compensating linkage for the rotor control system on rotary wing aircraft is disclosed. The main rotor and transmission are isolated from the airframe structure by elastic suspension. The compensating linkage prevents unwanted signal inputs to the rotor control system caused by relative motion of the airframe structure and the main rotor and transmission.

Abstract: A helicopter mast is driven by a transmission with a swashplate individually linked to pitch horns on each rotor blade. At least four actuators are coupled to the swashplate, three of which normally control the attitude and position of the swashplate. A separate power unit is provided for each actuator, each power unit being independently driven from the transmission. Means are then provided to shift control of the swashplate from one of the three actuators to a fourth actuator upon any one becoming disabled.

Abstract: End bearing assemblies are provided for articulating links, especially for articulating control links associated with helicopter rotor mechanisms. The end bearing assemblies comprise at least two elastomeric bearing sections connected by a load-transmitting member and arranged to react to loadings and accommodate motions along and about at least one of three mutually orthogonal axes.

Abstract: This invention is concerned with helicopter rotor control systems which hitherto have tended to comprise complex assemblies which are costly to manufacture and maintain and which are vulnerable to external damage.A helicopter rotor is disclosed in which each of a plurality of radially extending rotor blades is attached to the outer end of an individual spindle 19 having its inner end protruding into the interior of a hollow rotor hub structure 12 and supported by bearing means 21 arranged to permit rotational movement of the spindle 19 about its axis. A pitch control lever 22 is attached to the inner end of each spindle 19 and is articulated, through a universal joint, to the upper end of an individual connecting rod 38, 39, 40 and 41, the lower ends of the connecting rods being attached to a common housing 42 having independently rotatable means for connection to helicopter flying controls.

Abstract: A blade control method and means for helicopter rotors which increases heopter speed by mixing two/rev. control motion with one/rev. cyclic and collective motion through mechanical summation is provided. Both rotary and vertical motions are imparted to an inner control shaft and these motions are combined to impart vertical oscillatory motions to the rotor head which motions increase the thrust developed by the helicopter rotor.

Abstract: An aircraft comprising a generally annular wing structure surrounding a circular central structure to form an annular air duct, a pair of fuselages extending longitudinally at opposite sides of the aircraft, and rotor blades extending radially across the air duct from the central structure and rotatable relative to the central structure around the duct for inducing airflow through the duct to effect a lift on the aircraft. The annular wing structure consists of forward and rear wings forming air foils, the forward wing having a generally semicircular trailing edge and the rear wing having a generally semicircular leading edge.

Abstract: A helicopter rotor assembly comprises a rotor including a rotor boss and a rotor cup in, and coaxial with, said boss, a plurality of rotor blades each having an integral rigid spindle connecting the blade to the rotor with the spindle axes intersecting at the axis of rotation of the rotor and with the blades being inclined upwardly from the rotor. Articulated joints connect the spindles with the boss and further articulated joints connect the spindles with the cup. The blades are rotatable about the spindle axes and control means is provided for lifting and lowering the rotor boss relative to the cup to vary the inclination of the blades.

Abstract: An aircraft flight control including a linkage system having a walking beam to which control inputs are imparted and from which a control output is taken and having anti-jamming and over-control abatement provisions.

Abstract: The invention covers a mechanism for turning a horizontal axis rotor windmill into the direction of the wind, either under the instruction of a small pilot vane, or automatically without the use of such vane. This is accomplished by cyclically controlling the pitch of the rotor blades during revolution whereby to decrease the gyro forces on the rotor when yawing, as well as to take advantage of the force of the wind on the blade to assist turning the axis into the wind. The mechanism of the present invention automatically and cyclically alters the pitch of the blades as the yaw angle of the wind changes so as to present a cyclically different angle of attack between the blades and the wind, thus utilizing the force of the wind to cause the turning of the axis of the rotor into the wind.

Abstract: An analog mixer for a helicopter rotor control system mounted for tilting motion about a variable tilt axis and connected to the rotor control swashplate to cause synchronous tilting and including means to impart tilt generating control inputs to the analog mixer, and means to vary the position of the analog mixer tilt axis as a function of helicopter speed to thereby vary the phase angle of the helicopter rotor without imparting control inputs to the rotor control swashplate.

Abstract: The control system includes a sensing mechanism by which a true pure signal from flapping bending activity resulting from an external load force on a rotor blade in a rotor system is generated and fed back to a gyroscope which then precesses to return a correcting feathering motion to the rotor blade through a swashplate. Such generation is developed by the sensing mechanism which comprises a cantilevered beam or spring system secured at its one end to a fixed hub arm about which the blade feathers and having its other end operatively connected to the gyroscope. The gyroscope is positioned outside of a high force blade feathering loop and is independently sized from the rotor to which it is coupled. The system also provides for pilot command input to produce a control feathering motion to a pair of blades independently of the sensing means.

Abstract: Various modifications are disclosed of the composite aircraft, which is the subject of U.S. Pat. No. 3,856,236 by this same inventor. The control console is supported from the center of the upper rotating balloon sphere instead of its south pole to reduce the periodic motion of the console about its point of attachment to the sphere. The console is supported from the center of an inner framework through a tapered indentation in the bottom of the sphere. A lift command control system determines the angle of attack of each wing about the periphery of the sphere to provide the force required to generate movement of the sphere in a preselected direction. If the wing experiences a gust, the force reaction compels the wing to seek a different angle of attack to keep the new force in balance with the command force exerted by the control on the wing to automatically provide gust control. A pneumatic lift command control system is illustrated.