Abstract: A shaft deflection controller includes an input driveshaft adapted for inputting power from an engine. The input driveshaft includes an axis of rotation and a spur pinion at an end of the input driveshaft. The axis of rotation of the input driveshaft changes, relative to a frame, with deflections of the input driveshaft. Two face gears are adapted for meshing with the spur pinion of the input driveshaft. A flexible shaft stabilizing mount includes an inner sleeve portion and a mounting flange. The inner sleeve portion includes a base portion connecting the inner sleeve portion to the mounting flange and a plurality of cage spring members. The mounting flange is connected to and concentric with the inner sleeve portion. The flexible shaft stabilizing mount controls the deflection of the input driveshaft by applying forces onto the input driveshaft, which tend to resist changes in the alignment of the axis of rotation of the input driveshaft. The flexible shaft stabilizing mount is connected to a rigid frame.

Abstract: A mechanical procedure is performed using a sequence of instructions generated from a relational data base. The data base includes at least one unit operation file containing data associated with the performance of a single unit operation, indications of prior operations that must be performed, and any support files that are required by each unit operation file. There is a generic instruction file containing a plurality of generic instructions. A sequence of unit operations to perform the mechanical procedure is first defined, using the information in the unit operation files. After this arranging of the unit operations, a series of task-specific instructions is generated for each of the unit operations by selecting and completing a series of generic instructions using information in each pertinent unit operation file.

Abstract: A precision grinding apparatus includes a grinding worm for precision grinding a case-hardened face gear. A shaper is first placed into contact with a face gear, to thereby shape a surface of the face gear into a plurality of face gear teeth. The shaper is then removed, and the face gear is case hardened. The grinding worm is disposed in a normal orientation to the case-hardened face gear and includes a spiral tooth extending along a perimeter of the grinding worm. The spiral tooth of the grinding worm is adapted to contact and precision grind the case-hardened gear. A dressing tool includes a protrusion for contacting the spiral tooth of the grinding worm, as the spiral tooth contacts and precision grinds the case-hardened face gear. The dressing tool thus maintains the shape of the grinding worm to within a desired tolerance range.

Abstract: A coupler/decoupler is suitable for connecting one mechanical system to another and, upon application of sufficient force, resettably disengaging the first mechanical system from the second. In particular, the coupler/decoupler couples the pilot's or co-pilot's controls to the primary flight control system in a helicopter. In the event that the primary flight control system jams, applying a selected force to the controls causes the coupler/decoupler to disengage the primary flight control system, allowing the control to move again. In addition, the coupler/decoupler is configured to transmit a signal when the primary flight control system is disengaged, which activates a backup flight control system.

Abstract: A pressurized porous surface near the leading edge of a rotorcraft blade, is designed to be used as an active control device which alleviates the aerodynamics of blade vortex interactions (BVI) and thus the impulsive BVI noise levels and signature. The pressurized porous surface can be actuated on an azimuth-dependent deployment schedule or actuated continuously. The pressurized porous surface is supplied with either positively pressurized air, negatively pressurized air, or a combination of both, when actuated. The pressurized porous surface targets the local blade aerodynamics, rather than the vortex strength or blade/vortex separation distance.

Abstract: A securing system includes a primary structure and a first strip of hook and loop fasteners adapted to be secured thereon. A secondary structure includes a plurality of apertures disposed therein. The plurality of apertures fit over the first strip of hook and loop fasteners when the secondary structure is placed onto the primary structure. A second strip of hook and loop fasteners is adapted for fitting over the plurality of apertures of the secondary structure and for contacting portions of the first strip of hook and loop fasteners through the plurality of apertures. The contacting of the first and second strips of hook and loop fasteners secures the primary structure to the secondary structure.

Abstract: An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a trailing edge flap located near the tip of each of the rotorcraft's rotor blades. The flap may be actuated in any conventional way, and is scheduled to be actuated to a deflected position during rotation of the rotor blade through predetermined regions of the rotor azimuth, and is further scheduled to be actuated to a retracted position through the remaining regions of the rotor azimuth. Through the careful azimuth-dependent deployment and retraction of the flap over the rotor disk, blade tip vortices which are the primary source for BVI noise are (a) made weaker and (b) pushed farther away from the rotor disk (that is, larger blade-vortex separation distances are achieved).

Abstract: A system is disclosed for controlling the external flow passing along the external surface of an aircraft such as the tailboom of a helicopter. A fan blows air into a cavity within a surface, and the air exits the surface through one or more axially oriented slots. A ramp structure is positioned within the cavity and upstream of each slot, and a set of fence structures are mounted in each slot and spaced from each other as well as from the ramp structure. The ramp and fence structures trip the airflow which then couples to the downstream side of the ramp and fence structures, thus eliminating the axial airflow component adjacent to the slot, and exits the slot in a direction normal to the axis. The airflow exits the slot in a direction tangential to the external surface and generally parallel with the external flow, resulting in deflection of the external flow and generating lift which is used to augment antitorque control in the helicopter implementation described.

Abstract: There is provided a renewable energy source ejector rack for retaining and releasing stores (bombs or the like) on an aircraft, which has on-board pressurization capability, employs a single pressurization system for two or more release mechanisms, and uses air or other clean non-pyrotechnic pressurized gases both as the energy source and energy transfer medium. The aircraft contains a miniature compressor and purification system. Ambient air is filtered, dried and stored as an energy medium. Since the compressor system is onboard, the pressure can be constantly maintained regardless of temperature change. Using purified air eliminates the excessive cleaning burden imposed when using state-of-the-art pyrotechnics, and eliminates the sealing problems associated with hydraulics.

Abstract: A hybrid resistance card (R-Card) is manufactured using a two-step process wherein an electrically conductive ink layer and an electrically resistive ink layer are printed onto a surface, which may be either a substrate or the part on which the R-Card is to be used. The conductive ink layer is selectively applied in a pattern of shapes to electrically short out portions of the resistive ink layer, thereby permitting the R-Card to have a predetermined resistive taper across its width according to a desired resistivity curve. The resistive ink layer comprises grid-like lines bordering and separating the conductive shapes. The resistive taper is substantially continuous along the length of the R-Card, at least linearly, though if the card is designed to cover an entire part, it is substantially continuous along a plurality of directions on the card, with the tapers being designed to round into one another.

Abstract: A dual-mode high speed rotorcraft is disclosed which combines the efficiency of a helicopter with the high-speed capability of a fixed wing aircraft. The rotorcraft includes a rotor for propulsion during low-speed flight and hover, which is stopped and locked to function as a fixed wing during a high-speed flight. Also included are a canard and a high-lift tail, which together function to provide substantially all of the lift for the rotorcraft during the transition between low and high-speed flight, so that the rotor may be unloaded while starting and stopping.

Abstract: An engine control system for a helicopter having at least one engine is provided, including an electronic engine control unit for each engine and further including a manually operated system for backing up each electronic engine control unit in the event of a failure thereof or for permitting optional manual engine operation. The engine control system includes at least one collective pitch stick and at least one twist grip rotatably mounted on the collective pitch stick. Each twist grip includes a normal (NORM) position within the range of the operating arc which is coincident with a detent. The system includes means for electronically actuating the detent to retract when the twist grip is rotated out of the NORM position into a manual operating mode, so that the electronic disablement of the detent permits an operator to smoothly operate the twist grip through the operating arc when the engine control system is in a manual control mode.

Abstract: A dual polarization antenna for use on an aircraft, preferably a helicopter or the like, permits practical and reliable high frequency radio communications in a severe non line of sight, nap of the earth flight environment. The antenna comprises both a horizontally polarized component and a vertically polarized component. The horizontally and vertically polarized components are formed of an integral element, which has a bend therein so that the two components have an angular orientation with respect to one another. The horizontally polarized component is oriented in a generally horizontal direction and the vertically polarized component is oriented in a generally vertical direction. Ideally, the horizontally and vertically polarized components are oriented as orthogonally to one another as possible, depending upon the airframe application.

Abstract: A closed loop fully self-contained actuation system for converting a mechanical input motion into a mechanical output motion, which actuates a device such as a flight control surface on an aircraft, comprises an input actuator including a first fluid pressurizing means responsive to the mechanical input motion, and an output actuator including a second fluid pressurizing means, as well as a flexible fluid line extending between the first and second fluid pressurizing means to provide fluid communication therebetween. The second fluid pressurizing means is responsive to fluid flow through the fluid line, thereby initialing the output motion. The system is advantageous because it requires no hydraulic pumps, no accumulators, no reservoirs, and no dynamic seals or mechanical joints, permitting great reliability. The actuation system may be easily folded in conjunction with the apparatus on which it is employed, for compact storage.

Abstract: A main rotor head is disclosed, which is adapted for mounting on a main rotor mast of a helicopter. A main rotor mast nut is threaded onto the main rotor mast in order to fasten the main rotor head to the mast. The key feature of the invention is a nut retention means, which comprises a cup-shaped round annular disk and closely surrounds the nut, preventing separation of the main rotor head from the main rotor mast should the nut fail during flight.

Abstract: An apparatus for removing the metal wire braid shielding from jacketed electrical wire. It uses a male/female die set and avoids moving the wire braid while cutting. A carousel is provided which readily accommodates different wire sizes.

Abstract: A linkage is provided between various components within the feed mechanism of an automated gun which allows a feed cover, which includes some of the components of the feed mechanism, to be opened relative to other elements within the feed mechanism in order to allow access or changing of ammunition within the feed mechanism without unlinking the various feed mechanism components. Feed mechanism components within the gun are linked to other feed mechanism components within the rotatable feed cover by means of a ball and bracket combination. The feed cover rotates about a pivot pin on a predetermined axis. The bracket, through which the motive power supplied to the components of the feed mechanism and the feed cover is disposed to lie on and is rotatable about the predetermined axis defined by the pivot pin.

Abstract: An improved flexure member in a helicopter rotary system is devised wherein the flexure member is made of wound monofilamentary resin impregnated material comprising a fiber matrix and is formed in a flat strap disposed through a rotary hub of the rotor system and integrally extends from the flat strap to form a transition member and then to a cruciform flexure member having an X-shaped cross section. The cruciform member then extends and attaches to an outboard fitting adapted for coupling to the root of a rotor blade. In one embodiment the fiber matrix is wound around cylindrical lugs which forms the outboard fitting in combination with the integral extension of the cruciform member. The cruciform member is particularly characterized by including a woven X-shaped reinforcing fabric disposed within the X-shaped member about which fabric the monofilamentary layers are formed thereby forming each leg of the X-shaped cruciform.