Abstract: This invention is a machine component, specifically a bolt, incorporating a means of indicating the clearance the component has with an associated operating part. The device is in the form of a hollow bolt, within which is a slidable, but frictionally restrained, pin which protrudes from the head of the bolt. The device finds particular usefulness in mechanisms which, in the position in which the clearance is critical, are unaccessible for direct measurement.

Abstract: This invention is a piston-cylinder hydraulic snubbing device to arrest or resist motion. The invention may be utilized as a snubbing device alone, or it may be incorporated into a hydraulically actuated piston-cylinder assembly. The principal feature is that an orifice, through which hydraulic fluid is forced, is in the form of a gap between the ends of a piston ring, which gap is varied by engagement of the ring with a tapered bore in the cylinder.

Abstract: A logic controlled APR system including arming logic, engine failure detection circuits, and test circuit means for testing system operating condition without engine operation. The logic controlled APR system detects an engine failure in a multi-engine aircraft and provides solenoid controlled increased fuel flow to the remaining normally operating engines, and includes a disarm mode in the event of an RTO (rejected take-off).

Abstract: This invention relates to apparatus for accurately determining the characteristics of turbo-powered simulators. The apparatus provides for the determination of the air flow through the turbine of the simulator, the air flow through the fan section, and the thrust produced, all with high accuracy. The data thus accumulated, together with the data on temperatures and pressures both inside and outside the simulated engine, enable the engineer to determine other desired characteristics. The apparatus is free of certain disadvantages of conventional equipment in that it substantially eliminates tare forces in thrust measurement, it eliminates the necessity of accounting for inlet momentum, it minimizes distortion of inlet flow, and it enables simple and accurate measurement of the air flow through the engine simulator.

Abstract: A system for generating an optimum vertical speed command and controlling the aircraft to this command by allowing the aircraft to assume an optimum trimmed condition for the thrust energy available which system utilizes the aircraft autopilot system.

Abstract: A system for processing signals representative of airspeed error and inertial longitudinal acceleration of an aircraft to provide an output signal representative of windshear induced acceleration which is filtered to remove the high frequency components and which may be utilized to indicate the presence of windshear to a pilot who can then respond by resetting the thrust to maintain airspeed, or alternatively the output signal is utilized to correct the inertial damping signal of an airspeed control system under windshear conditions.

Abstract: A process of forming an interference fit between a rivet and the perimeter of an aperture through which the rivet shank is inserted finds particular application in the aircraft industry where sheets of component materials are joined together as a sheet assembly by a plurality of rivets. The process utilizes a high energy impact gun which forms a button on one end of a rivet shank, the other end of the rivet shank protruding a predetermined distance from a sheet surface and prevented from longitudinal movement by a bucking bar. The impact gun is then activated against the other end to rapidly form a second button. The rivet shank is radially expanded during the riveting process to thereby swell against the perimeter of the rivet hole for compression stressing which serves to stress relieve the area adjacent to the hole during cyclic loading of a sheet assembly.

Abstract: A system for utilizing electrical energy to induce eddy currents in an electrically conductive article, e.g., the metallic member of a hot melt type fastener. An ultrasonic frequency generator circuit utilizing a single SCR and having a maximum power output of about 1 kilowatt includes in circuit therewith a coupling coil for providing directly a high concentrated magnetic field which induces eddy currents in the electrically conductive article for rapid heating.

Abstract: A cryogenic fuel tank of a cylindrical design having toroidal surface ends, is suspended in aircraft structure through a central front mount member; and the rear of the tank is supported by rod elements which extend: from a mounting ring about the tank, to mount points rearwardly within the interior of the fuselage. The central front mount member has a baffles attached thereto, so as to prevent undue sloshing of the liquid within the tank. The front end of the tank suspension absorbs radial and axial loads, but no bending moments; and the aft linkage suspension arrangement takes primarily radial and torsional loads. Also the aft suspension provides for unrestrained axial and radial contraction and expansion of the outer shell of the tank.

Abstract: A rate-limited, signal magnitude limited, non-linearized lag circuit for processing glide slope error signals to reject noise and reduce aircraft response to hardover signals due to ground transmitter malfunctions or other anomalies. A feature of an embodiment includes a logic circuit connected to the lag circuit for preventing aircraft deviation due to hardover signals.

Abstract: A variable camber apparatus for the leading edge of an airfoil that is operable for lift variation at high airspeeds of a jet aircraft such as for maneuvering of fighter aircraft. The cambering apparatus comprises an upper surface flexible skin panel which is supported along its inner edge by a wing spar assembly and along its outermost edge, by an airfoil edge forming structure. A hinged rib member, through a kinematic linkage mechanism associated between itself and the structure at the outermost edge of the airfoil section, bends and torsionally twists the airfoil edge forming structure about a relative spanwise axis.

Abstract: Air breathing gas turbine engine design concepts, and methods and apparatus for providing variable engine cycles are disclosed. The preferred engine embodiments involve two flow control valve systems for internal management of air, each of which have the capacity to cross-over or invert adjacent annular flow patterns, and at least one of which is capable of switching from inverted to straight through flow.