Abstract: Single shaft, air breathing auxiliary power units having a single stage centrifugal load compressor driven by a gas turbine engine. The latter has a single stage centrifugal compressor and a single stage radial inflow turbine mounted in back-to-back relationship on the same shaft as the load compressor. Control systems for these auxiliary power units feature turbine exhaust gas temperature and turbine speed responsive fuel flow control; a bypass valve control which causes air to be dumped overboard when the pneumatic load demand drops to prevent load compressor surge; and an inlet guide vane control.

Abstract: An aircraft performance instrument which provides a first indicator which represents the line of level flight of the aircraft and a second indicator representative of the maximum permissible angle of attack of the aircraft.

Abstract: A heat exchanger core including a heat conducting tube. A plurality of spines are mounted on the tube in opposed groups and are separated by spine free areas, one of which faces the direction of air flow and the other of which faces away from the direction of air flow.

Abstract: This invention is directed to a method of working the free end of heat exchanger tubes, and particularly the formation of braze cups, with the heat exchanger tubes in situ relative to the heat exchanger core with the method including the step of utilizing centering tooling positioned about a tube expansion rod to assure that the braze cup is centered relative to its respective tube axis.

Abstract: The present invention is directed to a power control for an automatic transmission which consists of two valves, the first of which is a characteristic valve providing a pressure differential linearly proportional to an input speed signal provided by a prime mover driven fixed displacement pump, and a second valve which is modulated by the pressure differential generated by the first valve and by a pressure feedback proportional to the torque transmitted by the transmission. The power control provides a series of linear control curves proportional to input speed and is useful as either an automotive type control or an anti-stall control, or a combination of both.

Abstract: A displacement control for a variable displacement hydraulic motor wherein the control is a summing pressure compensator control which is responsive to the pressures of a plurality of loads so that the average, weighted average, or total pressures of the loads can be sensed to generate a control signal for increasing the displacement of at least one motor when the plurality of pressures have a sum or average above a predetermined level. The summing pressure compensator control can also include an overpressure sensing device which is responsive to the pressure of one load, or the highest pressure of more than one load, to also provide a control signal to increase motor displacement. The increase in motor displacement limits the pressure of the motor system.

Abstract: The invention provides independent guidance and monitoring integrated into an MLS landing system and a scaled-down MLS take-off or missed approach guidance system useable at small airports. An added fixed beam precision guidance system is integrated into the MLS time sequence format. The fixed beam guidance system is based upon the concept of using paired fixed overlapping beams, sequentially radiated by different fixed antennas (80 and 81), oriented to left and right of a prescribed guidance path. The paired beams overlap at the prescribed guidance path in such a manner that an aircraft departing or making a missed approach on such path will intercept equal signal intensities to indicate an on-course condition.

Abstract: A dual pressure source, or selectively alternative high pressure source, control system for a variable displacement hydraulic unit servo mechanism wherein normal control of the unit is provided by the low pressure source, such as a transmission charge pump, and wherein a high pressure source of control fluid with a restrictive orifice is provided to initiate servo movement, especially under conditions generating high internal friction. The flow restrictive orifice generates a pressure drop in a high pressure control line once the servo mechanism starts to move, inducing flow through such line. Thus, the control system provides a momentary source of high pressure fluid but permits control rate changes which are substantially independent of the hydraulic unit working pressure. Preferably, the high pressure source is a shuttle selected highest pressure of a transmission main loop incorporating the hydraulic unit.

Abstract: This invention relates to a jam tolerant rotary actuation system having multiple flight control surfaces. The actuation system includes in combination an actuation mechanism for each flight control surface. Each actuation mechanism is releaseably coupled to a main drive line shaft. The main drive line shaft is mechanically, serially coupled to each actuation mechanism to thereby establish an actuation assembly.A power drive unit is provided and is drivingly coupled to either end of the actuation assembly to thereby create an actuation system that will respond to the jamming of one of the flight control surfaces by the release of the actuation mechanism associated with the jammed surface from the main drive line shaft and the actuation of the remaining surfaces by the power drive unit.

Abstract: The invention is directed to a rotational speed sensing switch which provides a variable linear displacement of an output member in response to a varying speed rotational input. The switch includes a sensing means, which includes a rotatable rolling element-and-ramp assembly, acting in cooperation with a signaling means which includes an axially movable actuating disc, an output member comprising a switch rod, and a biasing means. The aforementioned improvement over the prior art comprises a regulating means included within the sensing means.

Abstract: In a single-frequency precision guidance landing system, the use of a DME interrogator in the aircraft and a DME receiver at the ground installation, each tuned to the same DME channel frequency, to uniquely interrogate a selected ground station and hence identify it by virtue of its replies being synchronous in the aircraft with the interrogations, the interrogations and the replies also being used to obtain range to the ground installation. This technique uses airborne already-installed DME interrogators for selective interrogation of a desired landing installation, thereby to eliminate any need to add additional special purpose equipment to the aircraft to accomplish the desired uniqueness of interrogation and ground installation identification achieved by this invention.

Abstract: A lubricant delivering coupling adapted to interconnect a power transfer unit and a load having a rotary input. The coupling is comprised of a pair of concentrically disposed inner and outer hollow members. The outer member is in a torque transmitting relationship between the power transfer unit and the load. The inner hollow member is secured at both ends to an inner surface of the outer member and is adapted to receive lubricant from a lubricant source within the transfer device for delivery to and through the hollow inner member.The inner and outer members each have intermediate the respective ends thereof a shear section. Upon overloading of the outer member and the shearing failure thereof, the inner member continues to twist until rupture at the inner member shear section.

Abstract: This invention relates to a unidirectional high gain brake arrangement that includes in combination a shaft mounted for rotation within a housing. The shaft is rotatable in either direction. A brake is selectively releasably coupled to the housing and to the shaft. The brake has a first member. An intermittent motion device is respectively coupled through the first member to the housing and through a one-way clutch to the shaft. The brake also has a second member that is mechanically coupled to the first brake member and to the housing. The intermittent motion device causes the brake to be activated by movement imparted to the first brake member after a preset number of revolutions of the shaft in one direction. The brake is released by rotation of the shaft in an opposite direction whereby torque transmitted through the one-way clutch to the first brake member is removed.

Abstract: An independent test sight is described for a pilot's head-up display (HUD). In one embodiment, the independent test site comprises a collimator assembly and an aligned periscope assembly. The collimator assembly comprises a source of light, a reticle, and a lens for projecting the image of the reticle. The periscope assembly comprises a rhomboid prism housed within the chassis of the HUD in such a manner that it can be pivoted from a stowed position to an erect position where it projects a reticle pattern in the field of view of the HUD combiner.

Abstract: The invention provides independent guidance and monitoring to be integrated into an MLS landing system and also provides a scaled-down MLS landing guidance system useable at small airports. In both cases an added fixed beam precision guidance system is integrated into the MLS time sequence format. The fixed beam guidance system is based upon the concept of using paired fixed overlapping beams, sequentially radiated by different fixed antennas. One pair is oriented to left and right of the centerline of the runway, and the other pair is oriented above and below the desired glideslope. The first set of paired beams overlap at the centerline of the runway in such a manner that an aircraft approaching exactly on centerline will intercept equal signal intensities to indicate an on-course approach.

Abstract: The invention is directed to a unitary cage assembly annularly positioning a plurality of rollers in a pair of roller bearings supporting a cradle swashplate. By utilizing the unitary cage assembly, a parallel relationship between the rollers is assured and, furthermore, only a single locating mechanism for the unitary cage assembly is required.

Abstract: The present invention is directed to a compact, lightweight and inexpensive hydrostatic transmission which in the preferred form has a variable displacement and reversible pump placed in side-by-side relationship with a fluid motor and wherein the transmission has a multisection housing with a uniform width center section forming both the pump chamber and the motor chamber. The fluid capacity of the pump and the fluid capacity of the motor are proportional to their widths and the ratio of the fluid capacity remains constant as various width center sections are used.

Abstract: In order to facilitate the installation of transducers such as accelerometers in a larger system, each transducer is provided with a memory circuit which is physically attached to the transducer and contains data reflecting the operating characteristics of that particular transducer. The data stored in the memory can be in the form of coefficients for polynomial equations that describe the operation of the transducer as the function of a variable such as temperature. Provision is made for transmitting this data along with the signal output from the transducer to the larger system.

Abstract: This invention relates to a motor control circuit for a permanent magnet motor having a rotor and motor windings. A motor winding transformer circuit is coupled to motor windings and provides an output signal representative of the magnitude and direction of the real current present in the motor windings. A rotor speed/position sensing circuit provides an output signal representative of the motor speed and direction.

Abstract: In order to provide timely aircraft performance data from an aircraft flight data recorder in a useful format, a flight data display system is provided: with a data storage unit; an interface circuit for reformatting flight data from the flight data recorder; a central processor for converting selected portions of the reformatted data into engineering units and storing the converted data into the storage unit; and a video display unit including a keyboard for selecting the desired portions of the reformatted flight data for display on the video display unit. The video display unit provides for the multicolor display of flight data in either graphical form or in a cockpit instrument form on a cathode ray tube.