Abstract: A link (10) exchanges data between a master (MC) and slave (SC) computer. Each computer has control lines (26A, 42) and incompatible information lines (26B, 26C, CA1-15, CX1-21). The master computer (MC) includes a master interface (28) connected to the information and control lines (26) of the master computer (MC). The master interface (28) has separate intercommunication lines (LA/B) and intermediate (34) lines. This master interface (28) is able to provide an intermediate signal on its intermediate lines (34) in response to signals provided by the master computer (MC) on its control lines (26A). The link (10) includes a computing subsystem (30) and a slave interface (38). The computing subsystem (30) is connected to the intercommunication (LA/B) and intermediate (34) lines of the master interface (28). The computing subsystem (30) has command lines (36) for providing thereon a command signal in response to the intermediate signal.

Abstract: A proportional fuel fuel control (11) regulates the fuel flow (Wf) from a hydromechanical unit (36) based upon an error signal (E) representing the difference between a demanded speed signal (Nd) and an actual speed signal (Nh). The demanded speed signal (Nd) is generated by an integrator (32) as the time integral of the least of a plurality of acceleration terms (Aa, Ab, Ac, Ad) selected by a select low gate (38). The demanded acceleration term (Aa) is generated by junction (26) as the difference between the demanded signal (Nd) and a scheduled speed signal (Ngs). Stress acceleration terms (Ac, Ad) are generated by junctions (48, 50) and scheduling means (42, 44) which form stress limiter circuits. A stall acceleration term (Ab) is generated by a junction (46) and a scheduling means (40) which forms a stall prevention feature.

Abstract: A variable displacement vane pump includes a rotor (10) rotatably mounted in a casing (32). The casing (32) has a pair of relatively rotatable complementary cams (18,20). Each cam (18,20) has a surface shaped to provide an annular curvilinear track. The pump also has a first (14) and second (16) plurality of vanes slidably mounted upon the rotor (10). Each of the vanes (14,16) is sized and positioned to engage a corresponding cam (18,20). These vanes (14,16) are constrained in a radial direction by the cams (18,20) as the rotor (10) rotates. The vanes of the first (14) plurality engage one (18) of the cams, the other one (20) of the cams being engaged by the vanes of the second plurality (16).

Abstract: Apparatus is operable gyroscopically to determine direction and to determine north. This apparatus includes a case (34), a gimbal (20) and a central gyro (10). The gimbal (20) is rotatably mounted in the case for rotating azimuthally. The central gyro (10) has transverse to its spin axis (16), a single degree of rotational freedom. This central gyro (10) is mounted in the gimbal (20) to rotate about its spin axis (16) and shift the degree of freedom between a vertical (12) and a horizontal (18) axis. The central gyro (10) has a transducer (28) and a torquer (26). The transducer (28) can sense motion about the single degree of freedom and can provide a deflection signal signifying this motion. The torquer (26) is connected to the transducer (28) and can respond to its deflection signal for applying a torque to the central gyro (10) tending to affect motion about the single degree of freedom, when this freedom is oriented along the vertical axis (12).

Abstract: An acceleration limit reset circuit (38, 40, 42, 44) is disclosed for a closed loop fuel control (11) of a gas turbine engine (10). The closed loop control includes a comparator circuit (28) which compares an acceleration term Ngs-Nd to a limit value Al and if the scheduled acceleration (Ngs-Nd) is in excess of the limit, regulates the rate of change of the engine speed to the limited value Al. The acceleration limit Al is scheduled by an accel/decel limiter circuit (30) as substantially equivalent to the surge line of the engine. The acceleration limit reset circuit (38, 40, 42, 44) is provided for modifying the acceleration limit Al during special operating conditions of the engine (10) by a signal RRS.

Abstract: A variable displacement vane pump has a ported casing (10), a rotor (28) and a first (32a) and second (32b) plurality of vanes. The ported casing (10) has a pair of relatively rotatable, complementary cams (18, 20). Each cam has a surface shaped to provide a curvilinear annular track (18a, 20a). The rotor (28) is rotatably mounted in the casing (10). The vanes (32a, 32b) are slidably mounted upon the rotor (28). Each of the vanes (32a, 32b) are sized and positioned to engage a corresponding one of the pair of cams (18, 20). The vanes of the first plurality (32a) of vanes engage one of the cams (18), the other cam (20) being engaged by the vanes of the second pluarlity (32b). Thus constructed, the vanes (32a, 32b) can move in pairs in a closed path within the casing (10). The vanes (32 a, 32b) of each pair can ride on different ones of the cams (18, 20). By rotating the cams (18, 20) with respect to each other, the phasing of the vanes (32a, 32b) in each pair can be altered.

Abstract: An acceleration limit reset circuit (38, 40, 42, 44) is disclosed for a closed loop fuel control (11) of a gas turbine engine (10). The closed loop control includes a comparator circuit (28) which compares an acceleration term Ngs-Nd to a limit value Al and if the scheduled acceleration (Ngs-Nd) is in excess of the limit, regulates the rate of change of the engine speed to the limited value Al. The acceleration limit Al is scheduled by an accel/decel limiter circuit (30) as substantially equivalent to the surge line of the engine. The acceleration limit reset circuit (38, 40, 42, 44) is provided for modifying the acceleration limit Al during special operating conditions of the engine (10) by a signal RRS.

Abstract: A steerable artillery projectile utilizing electro-optical circuitry to home on a laser designated target where the rear end of the projectile is displaceably coupled to the front end thereof which contains the electro-optical circuitry and munitions is disclosed. The displaceably coupled rear end of the projectile has a plurality of compartments equispaced around its longitudinal axis and each compartment has a gas cartridge which can be activated by the electro-optical circuitry. In flight, a selected gas cartridge may be discharged by the electro-optical circuitry causing the longitudinal axis of the rear end of the projectile to momentarily move out of line with the longitudinal axis of the front end of the projectile resulting in a modification of the flight path of the projectile to home on the laser designated target.

Abstract: A buffer can exchange data between a computer having a plurality of lines and a device. One of these lines, a halt line, can transmit a halt signal when the computer has halted. The buffer includes a plurality of transmitters and a plurality of controlled receivers. A halt transmitter is included among the plurality of transmitters. The transmitters are separately connected to predetermined respective ones of the plurality of lines for transmitting their signals to the device. The halt transmitter is connected to the halt line for transmitting the halt signal to the device. The receivers are connected between the device and given respective ones of the plurality of lines for coupling to them signals from the device. Each one of a predetermined set from the plurality of receivers has a receive terminal commonly connected to the halt line for enabling operation of this predetermined set in response to the halt signal.

Abstract: A Color Separator for a Map Display Video Generator utilizing a Fresnel lens to expand a multicolor light signal output from a point of light scanned map film to a stationary area that entirely fills an input end of a bundle of optical fibers the other end of which bundle is divided into three smaller bundles. The light output from each smaller bundle is first passed through a colored filter to thereby separate the light into the primary colors red, green and blue. The separated light is then converted to an electrical signal by photomultipliers and used to generate a color video signal applied to a color cathode ray tube display to display the map thereon.

Abstract: A fuel control system (11) for a gas turbine engine (10) is disclosed. The proportional control regulates the fuel flow Wf from a hydromechanical unit (36) based upon an error signal E representing the difference between a demanded speed signal Nd and an actual speed signal Ng. The demanded speed signal Nd is generated by an integrator (32) as the time integral of the difference between the demanded signal Nd and a scheduled speed signal Ngs. Additionally, the difference signal is limited between an upper limit Al and a lower limit Dl prior to the integration by a comparator (28) and limited circuit (30).

Abstract: A fuel control apparatus (34) for a gas turbine engine (10). The fuel control apparatus (34) meters fuel flow Wf according to an electrical signal (Wf/Pc, E) indicative of the desired fuel/air ratio of the engine as scheduled from the power lever angle (PLA) by a closed loop acceleration based electronic governor (26). The apparatus (34) mechanically multiplies the electrical signal (Wf/Pc, E) by the compressor discharge pressure (Pc) of the engine (10) to yield the fuel flow (Wf).

Abstract: An unbalanced current detector for a three phase electrical system of the type including a current transformer (4, 6, 8) for each phase (.phi.A, .phi.B, .phi.C) and a burden resistor (16) which receives a rectified output of the current transformer is disclosed. The harmonic content of a rectified ripple voltage developed across the burden resistor (16) is applied to a filter (20) for extracting desired frequencies and rejecting other frequencies, and the filter output is applied to a level detecting and amplifying circuit (54) the output of which is applied to an indicator (77) to indicate an unbalanced current condition.

Abstract: A fuel control apparatus (34) for a gas turbine engine (10). The fuel control apparatus (34) meters fuel flow Wf according to an electrical signal (Wf/Pc, E) indicative of the desired fuel/air ratio of the engine as scheduled from the power lever angle (PLA) by a closed loop acceleration based electronic governor (26). The apparatus (34) mechanically multiplies the electrical signal (Wf/Pc, E) by the compressor discharge pressure (Pc) of the engine (10) to yield the fuel flow (Wf).

Abstract: A puzzle in the form of a multi-colored regular solid is disclosed. Plates corresponding to the adjacent faces of the regular solid are disposed on said faces and divided into a plurality of triangles of different colors, and which triangles have adjacent edges. The plates are coupled in pairs and the pairs are rotatable relative to their respective faces. The object of the puzzle is to rotate the pairs of plates so that none of the adjacent edges of the triangles are of the same color.

Abstract: In this method, a unit (24) is tested by a test instrument (22) with the aid of a master (MC), an intermediate (30) and a slave (SL) computer. The latter connects to the test instrument (22) for sensing its measurements. The method includes the step of dispatching one of a plurality of instruction signals to the intermediate computer (30) from the master computer (MC). Another step is issuing to the slave computer (SL), when it is not halted, a signal to halt from the intermediate computer (30) after receipt by the intermediate computer (30) of one of the instruction signals. Another step is transmitting from the intermediate (30) to the slave (SL) computer, after the latter has halted, that one of a plurality of command signals corresponding to the currently dispatched one of the instruction signals.

Abstract: A control system directs an aircraft along a predetermined curvilinear descent path (10). The aircraft carries a plurality of sensors, for example, an altitude sensor. The system has a longitudinal device (64) responsive to at least one of these sensors for providing a longitudinal signal related to longitudinal displacement of the aircraft. The system also has a height device (26) responsive to the longitudinal signal for producing a height signal functionally related to the altitude required to follow the path. Also, a command subsystem (36) responds to the height signal and a given one of the sensors to produce an error signal bearing a predetermined relation to the extent of deviation from the descent path. In one embodiment dispersion otherwise occurring during a flare maneuver is reduced by definitely directing the aircraft onto a specific path such as a circular arc. Such a control system may employ an aircraft motion monitoring system (FIG.

Abstract: An actuator for rotating an output member, having an epicyclic transmission adapted to rotate the output member in response to the motion of a rotor which contains a plurality of radial projections which interact with a stator or non-rotating portion of the actuator to produce a rotating tangential force vector directed substantially perpendicular to the radial projections.