Abstract: A solution to reduce the ratcheting sound that occurs at the start of braking when an operation pedal is operated by foot. Because a mounting seat as a flat part and base plate are provided between a ratchet member and support axial center S of an operation pedal, there is a possibility that the ratchet member's vibration will propagate to the adjacent mounting seat and base plate, amplifying the ratchet sound. However, the adjacent mounting seat and base plate are provided with beads, having cross-sections that bend convexly in a direction substantially orthogonal to the vibration waveform of the ratchet sound produced by a pole coming into contact with serrations when the mounting seat and base plate maintain a flat plate shape; i.e., in a circumferential direction about support axial center S. Therefore, rigidity against the vibration is increased, propagation of vibration is minimized, and ratchet sound is effectively reduced.

Abstract: Methods, apparatuses, and systems for two-way satellite communication and an asymmetric-aperture antenna for two-way satellite communication are disclosed. In one embodiment, a beam pattern for an asymmetric-aperture antenna is offset in a narrow beamwidth direction, and the offset beam pattern is directed by a mechanical gimbal, with the beam pattern offset made to reduce interference with an adjacent satellite. In additional embodiments, operational areas near the equator are identified for a given offset beam pattern, or a beam pattern offset may be adjusted over time to compensate for movement of the asymmetric-aperture antenna when attached to an airplane, boat, or other mobile vehicle.

Abstract: A bicycle component positioning device includes a fixed member, an operating member and a positioning mechanism. The operating member has an input portion and an output portion. The positioning mechanism is operatively disposed between the operating member and the fixed member. The positioning mechanism includes a positioning member that is movable between a first position in which the positioning member is engaged with the fixed member and a second position in which the positioning member is disengaged from the fixed member. The positioning member is held in engagement with the fixed member in the first position by the input portion when the input portion is in an operating position. The positioning member is movable from the first position to the second position upon movement of the input portion from at least one of the operating positions.

Abstract: A mechanically operated proportional flow control valve (8) which a valve spool (9) is described, which is moveable between two end limits limiting a regulating range. A device (20, 22) is described for selectively limiting the regulating range of the valve (8). This device can be used to block “locked-in” positions (F1, RH1) of the spool (9) at the end limits of the regulating range. The device includes a locking bar 20 which has locking formations (28, 29) which engage a pin (22) on a lever (11) connected with the spool (9).

Abstract: A prosthetic foot having an adjustable height heel includes a frame portion with an ankle link pivotally supported on the frame portion at a first pivot axis. A detent rod is pivotally connected to the ankle at a second pivot axis, and a detent member is pivotally affixed to the frame portion at a third pivot axis. The detent member is selectively operable to receive and releasably retain a length of the detent rod therein so that the length of the detent rod extending between the second and third pivot axes may be selectably adjusted. When the length of the rod is so adjusted, the angular relationship of the frame portion and the ankle link is changed thereby changing the heel height of the foot. The detent mechanism may be activated by various means including fluidic means, mechanical means, electromechanical means, and the like.

Abstract: Adjusting arrangement for a steering column tube of a steering system of a motor vehicle having a swivellably disposed clamping lever which, in a released position, unblocks or, in a locked position, blocks a longitudinal or vertical displacement of the steering column tube, and has an actuating device for the manual releasing or locking of the clamping lever, which actuating device has a grip arrangement which, in a vehicle-fixed mounted condition, is accessible from a driver seat position. A guide rail arrangement is positioned on the steering column tube and is aligned in the longitudinal direction of the steering column tube. An adjusting slide block is displaceably held on the guide rail arrangement. The slide block is moved by the grip arrangement and is connected with the clamping lever.

Abstract: A machine tool operated by gyroscopic precession is disclosed. The machine tool is provided with a rotatable member disposed for rotation in a single plane, the member mounted to a base. A gyroscopic mass supported by a gimbal is mounted to the rotatable member so that the spin axis of the gyroscopic mass, in a null position, is parallel to a plane of rotation of the rotatable member. A sensor is provided for sensing position of the rotatable member, the sensor providing a control input to a computer, which in turn develops a drive signal for driving an actuator coupled to the gimbal. When the actuator is activated by the drive signal, the gimbal is displaced, precessing the gyroscopic mass and generating a force used to rotate the rotatable member.

Abstract: A feedback system for use in controlling control moment gyroscopes that are used in positioning a spacecraft where the relative rate of rotation is determined from the difference between the rotation rate of the gimbals of the CMGs and the rotation rate of the frame about the gimbal axis. The inertial reference units on the spacecraft are utilized as the source of measured rates of rotation of the three spacecraft axes with respect to a predetermined axis and these are converted to the rates of rotation of the frame about the individual CMG gimbal axes.

Abstract: A stable positioning system for a suspended payload. A stabilizer, control unit and positioner are located above a suspended payload. The stabilizer includes a plurality of flywheels within a casing. The axis of rotation of each flywheel is aligned with one of three orthogonal axes. A central bevel gear translates the output of a high r.p.m. motor to the various flywheels. Four flywheels are arranged into two counterrotating pairs along one horizontal axis. Two flywheels counterrotate about the other axis and a single flywheel rotates about the vertical axis. The mass and arrangement of flywheels provides gyroscopic stability while neutralizing potential precessional moments.

Abstract: A triaxial gyroscopic stabilizer for a movie or television camera has a camera in a cardan suspension unit, two three-stage gyroscopes, controlled linkages for adjusting course, banking and pitch, booster-converters, a set of accelerometers, a pitch angle sensor, an integrator, a system shut-off unit, a memory unit, low frequency filters, two computing units, a summator and course and pitch control levers. The cardan suspension unit has an external frame, a middle frame and a platform; the outer frame has the form of a half-fork bracket with an axis of rotation aligned along the course axis; the middle frame has the form of a fork bracket with an axis of rotation aligned along the course axis; the middle frame has the form of a fork bracket with an axis of rotation aligned along the axis of pitch. The first of the two three-stage gyroscopes is mounted on the platform, while the second is mounted on the middle frame.

Abstract: A propulsion and positioning system for a vehicle comprises a first gyroscope mounted for precession about an axis remote from the center of said gyroscope. A support structure connects the gyroscope to the vehicle. Gyroscopes are used to cause the first gyroscope to follow a path which involves at least one precession-dominated portion and at least one translation-dominated portion, wherein in the precession-dominated portion, the mass of the first gyroscope is transferred and associated movement of the mass of the remainder of the system in a given direction occurs, and, in the translation-dominated portion, the mass of the first gyroscope moves with an associated second movement of the mass of the remainder of the system in substantially the opposite direction, wherein the movement owing to the translation-dominated portion and is larger than the movement owing to the precession-dominated portion of the motion, hence moving the system.

Abstract: A new circuit is connected to the pan servo amplifier 38 of a camera remote pan head 44 for the purpose of eliminating the need for manual backpan. The circuit comprises a tachometer 20 mounted on the pan arm of a camera crane or jib arm 28 and connected to switch 32 and potentiometers 34 and 36. The switch and potentiometers select between three options for operation: an off position, a one to one reverse correspondence between the panning movement of the crane arm 28 and the panning movement of the pan head 44, and a variable reverse correspondence between the panning movement of the crane arm 28 and the panning movement of the remote pan head 44.The output is summed to a servo amplifier 38 which drives the remote head pan motor/tachometer 40. A number of means for alternative implementation are also suggested.

Abstract: A reactionless momentum compensated payload positioner adapted to be mounted on a supporting body for providing momentum compensation of an oscillatory and scanning payload and for suppressing reactions in the supporting body to the torques that occur as an aiming angle of the payload is changed. The payload positioner includes a gimbal assembly having at least two axis of rotation including an elevation axis and an azimuth axis. A pair of reactionless drive module are provided for rotating the payload about both axes. Each reactionless drive module includes a housing, a main drive shaft connected to the payload, a DC electric motor for rotating the drive shaft, and a flywheel. The main drive shaft is freely rotatably suspended within the housing by main bearings and the flywheel is freely rotatably mounted to the main drive shaft by bearings. ?In operation, the flywheel counter rotates with respect to the main drive shaft.

Abstract: A prime mover for a rotatable member supported for rotation in a single plane on a stationary base is provided wherein reaction torque applied to the base due to powering such rotation is greatly reduced. At least one gyroscopic mass in a gimbal support is mounted to the rotatable member, with an axis of rotation of the gyroscopic mass being generally parallel to the plane of movement of the member. A force is applied, as by a solenoid, to the gimbal in a direction normal to the plane of rotation so as to cause precession of the gyroscopic mass, thereby rotating the rotatable member. Applications of the invention include robotics and machine tools, where the rotatable member may be a swinging arm robot having a tool affixed to an end thereof, or a rotary table to which a workpiece is mounted.

Abstract: An antenna having a central axis is supported on a supporting member which in turn is supported on an azimuth gimbal. The antenna and the supporting member are rotatable around an elevation axis perpendicular to the central axis gimbal is supported on a base and is rotatable around an azimuth axis perpendicular to the elevation axis. A first gyro having an input axis parallel to the elevation axis is secured to the supporting member, and a second gyro having an input axis perpendicular to both the central axis and the elevation angle axis is secured to the supporting member. An accelerometer is provided for outputting a signal representative of an inclination angle of the central axis relative to a horizontal plane. An azimuth transmitter is provided for outputting a signal representative of a rotation angle of the azimuth gimbal around the azimuth axis.

Abstract: A gyro platform assembly for determining a drift rate of a sensing axis of first gyro, the sensing axis being fixedly aligned to a carrousel axis. The first gyro is on a plane of a first platform. The first platform is connected to a vehicle along the carrousel axis. The first platform has the plane and an opening. A second platform is connected to the first platform within the opening. The second gyro is on a surface of the second platform. The second platform is carrouselable around a carrousel axis that is perpendicular to the carrousel axis of the first platform. The second gyro has a sensing axis that is adjustibly aligned with the sensing axis of the first gyro. When the vehicle rotates, each sensing axis experiences the same rotation rate. Each sensing axis produces a signal that is the result of the rotation rate of the vehicle, and a sensing axis drift rate. The second platform is carrouseled 180 degrees and the sensing axis of its gyro produces another signal.

Abstract: A three axis, single degree of freedom gyroscope based rate sensing platform has restraining torque developed for the platform from a feedback loop that includes electronics that decouples individual gyroscope outputs from the rate inputs that correspond to axes other than the input axis for that gyroscope and provides an enhanced frequency response. The outputs from the various gyroscopes are processed in a compensator that estimates the platform rates on independent axes using either a Kalman filter estimator or a matrix inverse of the matrix equation of motion between platform input rate and gyroscope output. High bandwidth performance is obtained by an increased stiffness and prefiltering of the gyro torque inputs.

Abstract: A fault-tolerant air data and inertial navigation reference system utilizes skewed axis inertial sensors and fault-tolerant redundant electronics to provide higher redundancy with fewer parts. Parallelly operating processor circuits each receive the individual outputs of six skewed-axis gyros and six skewed-axis accelerometers. Each processor independently processes parity equations using the outputs to identify malfunctioning sensors. Further, the output of each processor is transmitted to three parallelly operating voter circuits. The voters are operable to discard a processor if its output does not agree with the majority. The voter outputs are similarly fed back to the processor circuits, which compare these outputs, and discard any voter whose output disagrees with the majority, thus providing a completely integrated system.

Abstract: A stabilization system for space platforms, satellites and the like. One arrangement for demonstration purposes incorporates a frame and a pair of motor/flywheel units which are pivotably mounted to the frame. These units are retained in positions of alignment with the frame axis and energized briefly to develop a torque for rotating the frame. Retraction of a retaining pin permits the units to pivot by 90 degrees, immediately generating precession forces which abruptly stop the frame at the desired angular orientation.

Abstract: A gyroscopically stabilized apparatus for aiming an instrument at a target object. An external yoke is attached to the ends of a hub assembly which supports the gyro and camera platforms for rotation about pan, tilt and roll axes. The yoke is associated with an externally located vibration damping system interposed between the yoke and the support arm attached to the helicopter or other transporting vehicle. This makes possible a greater degree of helicopter pitch and roll without having any support structure impact the gyro and camera. In one embodiment the platforms are associated with separately rotatable hemispheres joined to provide a spherical fairing. In another embodiment the hemispheres are attached together for common rotation about pan and tilt axes.

Abstract: In the present invention the inertial measurement unit system comprises a basic strapdown inertial measurement unit and an isolated fourth gyro strapped to a rotatable platform which is commanded to rotate at a rate equal to the spin rate of the vehicle body but in an opposition direction. The rotatable platform is controlled substantially by a control signal to cause the rotatable platform to turn at a rate substantially equal to the roll of the vehicle body but in an opposite direction. A signal processing means operates on (i) the output of an inertial navigational system computer representative of the rate of rotation of the inertial measurement unit along the roll axis, (ii), the output of the isolation gyro, and (iii) an output of a counter which counts the complete revolutions of the rotatable platform. In turn, an error signal is provided which is related to the rotation measurement error of the first rotation signal.

Abstract: A stabilized platform for mounting a camera or other sensor is suspended from a support post by a universal or Cardan joint with two torque motors powering its axes. Below this universal joint is a rotational joint also powered by a torque motor. A gyro stabilizer assembly comprising three orthogonally arranged gyroscopes is mounted on the platform. Position sensors detect the precession angles of the three gyroscopes and provide inputs to servo control loops which deliver drive signals to the torque motors. The platform including the gyro stabilizer assembly and the payload of camera or other sensor is configured such that the center of gravity is precisely located at the intersection of the three motor driven axes so as to eliminate unwanted torquing moments as a result of vehicle accelerations.

Abstract: A stabilised mount (e.g. for an antenna) has two gyroscopic rotors mounted in such a way that they can pivot about orthogonal axes. Rewinding of the antenna (to avoid undue twisting of the electrical cables) is liable to cause a voilent destabilisation of the mount because of the gyroscopic action of the rotors. To prevent this destabilisation the rotors are locked against the aforementioned pivoting action during the rewinding procedure.

Abstract: A gyroscope mounting structure for use in a spacecraft attitude control system has ten control moment gyroscopes. The structure has a truss for supporting the gyroscopes. The truss has an axis of symmetry. Five front gyroscopes are axially spaced from five rear gyroscopes along the axis of symmetry. The front gyroscopes and the rear gyroscopes are peripherally spaced about the axis of symmetry at equal angular spacings. Each gyroscope has a gimbal axis which is disposed at substantially the same acute angle to the axis of symmetry. Each gimbal axis is disposed parallel to an adjacent reference line which passes through a common intersection point on the axis of symmetry. The truss has a front frame, a rear frame and chords connecting the frames. The truss has five front struts interspaced between the five front gyroscopes for support thereof. The truss also has five rear struts interspaced between the five rear gyroscopes for support thereof.

Abstract: An inertial sensor arrangement comprises two electrically restrained gyros with three mutually orthogonal input axes. After A/D-conversion pick-off signals are supplied to a digital computer which forms part of the restraining loop of the gyros and provides digital output signals. The output signals are applied to a D/A-converter which supplies corresponding currents to the torquer of the gyros. Thereby integrating quantization errors are avoided. The cross-coupling behavior and gyro errors can be compensated in the computer. The inertial sensor arrangement can be measured as an entirety. The gyro parameters measured thereby are memorized in an EEPROM and are taken into account in the computer.

Abstract: A brake actuator for an all-terrain vehicle, the actuator including a housing and a cover, a hand-operated lever arm pivotally mounted in the housing and projecting outwardly from the housing through said cover, the lever arm being operatively connected to the brake cables for the wheels, a locking segment mounted for pivotal movement in the housing, a ratchet-type cam surface on the segment, the segment being biased to move into locking engagement with the lever arm, the ratchet-type cam surface being spaced at progressively greater distances from the pivot axis to block the lever arm at increasing distances from the brakes.

Abstract: An attitude displacement measurement apparatus including a base, primary bearing means retained by the base, auxiliary bearing means mounted for rotation on the primary bearing means on a given axis with respect to the base, a first rotor mounted for rotation on the auxiliary bearing means on the given axis, a second rotor mounted for rotation on the auxiliary bearing means on the given axis, a first drive mechanism coupled to the first rotor and operable to produce rotation thereof on the auxiliary bearing means in one sense on the given axis, and a second drive mechanism coupled to the second rotor and operable to produce rotation thereof on said auxiliary bearing means on the given axis in a sense opposite to the one sense.

Abstract: A stabilized platform which is suitable for stabilizing the bore-sight of a communications antenna or the like, is provided with a pendulous mounting which holds the structure erect. A pair of gyroscopes give active control of the attitude of the platform, and are coupled to the platform via a gear arrangement. When the platform is rotated rapidly (to unravel feed cables or to permit overhead tracking of the antenna) the gyroscopes experience a much lesser degree of movement which is determined by the gearing ratio, such that the gyroscopes are not destabilized.

Abstract: A foot operated vehicle parking brake mechanism comprises a brake pedal lever and a brake cable actuator pivotal about a common axis, the brake pedal lever being operable upon depression to displace the cable actuator to a cable tensioning position in which the vehicle brake is set. The cable actuator and pedal lever are independently releaseably retained in the cable tensioning and depressed positions and, respectively, against the bias of the tensioned cable and a pedal lever biasing spring. A manually operable release mechanism operates to release the pedal lever from its depressed position and, during return of the pedal lever to its retracted position, the pedal lever operates to release the cable actuator for return to its released position.

Abstract: A pivotable steering column is adjustable to any of a number of angular positions defined by the teeth of two elements of a first locking device. A manual lever can be raised to disable the first lock and allow selection of a different steering wheel inclination. The steering wheel can be moved to its uppermost position by lowering the manual lever once. In this case, the first lock maintains engagement of the teeth of the aforementioned two element, and a powerful spring pulls the steering column upward to the uppermost position irrespective of the first lock. A second lock then becomes wedged between the pivotable and stationary parts of the steering column, thus holding the former in the uppermost position. Lowering the manual lever a second time disengages the second lock, allowing the steering column tilt cown from the uppermost position. Thus, the steering column returns to an originally set driving position defined by locking engagement of the first lock.

Abstract: A seat suspension is disclosed in which a movable frame to be mounted onto a seat cushion for an automobile so as to be resiliently movable relative to a base frame mounted onto the floor surface of the automobile. The movable and base frames are connected with each other such that the movable frame can be moved elastically and vertically by means of two links mounted crosswise and pivotally and a spring constantly biasing these two links. Between the movable and base frames, there is provided a lock mechanism which is arranged to lock the movable frame at a desired height level. The lock mechanism includes a lock piece which is provided in either the base frame or the movable frame and has a plurality of engagement recesses in a vertical direction, and a lock pin which is provided in the other frame and is adapted to be engaged within the engagement recesses of the lock piece.

Abstract: A monolithic two axis gimbal suspension system for a tuned inertial instrument includes flexure hinges which are formed monolithically integral therein to define the pivot axis of the suspension system, each monolithically integral flexure hinge having aligned pairs of skew, crossed bridges integral with the relatively rotatable gimbals of the suspension system. The suspension system is used in a dry tuned gyroscope to suspend the gyro rotor from the gyro spin shaft. A method for making the monolithic suspension system comprises electro discharge machining of a monolithic workpiece mounted on a movable mandrel. Monolithically integral flexure hinges comprising skew, crossed bridges formed therein, interconnect gimbal portions which are formed in the workpiece. Construction of an improved tuned gyroscope employing the monolithic suspension system in a single compartment housing is described.

Abstract: In a stabilized gyrocompass having meridian seeking gyroscopic means and slaved horizontal gryoscopic means disposed upon a common platform, a signal representative of the angle which develops between the meridian seeking gyro and the platform in response to the dynamic effects of the vehicle is generated. The generated angle is proportional to the northerly inertial velocity term and is used to control the platform in azimuth, thereby providing a dynamically correct stabilized gyrocompass without the use of accelerometers or gravity sensors which are conventional in the art.

Abstract: Destabilization of a gyro-stabilized platform (such as employed for mounting an antenna on-board a ship) resulting from uncompensated yaw or rotation of the platform in azimuth from a fixed reference orientation is prevented by employing a pair of counter-rotating gyros for each stabilized axis and caging gyros having a spin direction opposite to the direction of rotation of the platform.

Abstract: A two-gyro four-gimbal attitude sensing system having gimbal lock avoidance is provided with continuous azimuth information, rather than roll information, relative to the magnetic cardinal headings while in near vertical attitudes, thereby to allow recovery from vertical on a desired heading. The system is comprised of means (48) for stabilizing an outer roll gimbal (14) that is common to a vertical gyro (12) and a directional gyro (10) with respect to the aircraft platform (50) which is being angularly displaced about an axis substantially parallel to the outer roll gyro axis, and means (38) for producing a signal indicative of the magnitude of such displacement (62, 64) as an indication of aircraft heading. Means are provided to cause stabilization of the outer roll gimbal (14) whenever the pitch angle of the aircraft passes through a threshold prior to entering vertical flight and destabilization of the outer roll gimbal (14) upon passing through the threshold when departing vertical flight.

Abstract: A torque converter is disclosed which comprises a gimbal assembly having a gyroscope mounted for rotation within one of the rings thereof. The spin axle of the gyroscope and the entire gimbal assembly are adapted to rotate about the precessional axis of the gyroscope. The gimbal ring is further adapted to oscillate about a torque axis that is perpendicular to the precessional axis to set up gyroscopic forces in the converter. The spin axis of the gyroscope is independently connected to the output gear of a differential drive unit and the input gear of the unit is connected to the drive shaft of the engine. A planetary gear section is interposed between the input and output gears of the drive unit that is adapted to turn the loaded output shaft of the converter. Oscillating means rock the gimbal ring about the torque axis at some fixed multiple of the engine speed while the entire gimbal assembly is turned about the precessional axis at some fixed multiple of the load speed.

Abstract: A mounting for an adjustable steering hand wheel for motor vehicles with an outer column immovably secured at the vehicle body and with a bearing housing pivotally secured at the upper end of the outer column by way of a pivot joint; a steering shaft extends through the outer column which is connected with a steering shaft section non-rotatably connected with the steering hand wheel and rotatably supported in the bearing housing by way of a shaft joint, whereby the bearing housing is provided with an arm extending along the outer column; an adjustable form-locking detent means pairing is arranged between the end of the arm and the outer column whose one part consists of a detent row and whose other part consists of a locking member cooperating with the detent row and adapted to be lifted radially out of the detent row, whereby one of the two parts of the detent means pairing is arranged at the end of the arm and the other part at a corresponding place at the outer column corresponding to the end area of the a

Abstract: An inertial platform carries at least one dynamically-tuned free-rotor gyro and is mounted in a three-axis gimbal system. Accelerometers are carried on the platform with their sensitive axes aligned with the two sensitive axes of the gyro. During alignment of the platform, and while the gyro motor is being run up to speed, the output of the gyro pick-off on each axis is combined with the output of the accelerometer on the other axis and applied through a resolver to the appropriate gimbal torque motor.

Abstract: Six sensors are oriented to position their input axes on the surface of a cone. The cone angle is optimized to permit the use of sensors with identical range capacity despite the fact that the maximum input along each of the orthogonal axes differs.The optimization of cone angle minimizes the average total error amplification due to skewing and change of sensor maximum rate capability to provide data closely approximating that derived from a non skewed, orthogonal, sensor array. The sensors may be gyroscope or accelerometer which are packaged in assemblies of two identical sensors each.

Abstract: An inertial measuring unit which precesses about the direction of apparent acceleration as a consequence of the introduction of a mass unbalance to each of the gyroscopes in the inertial measuring unit. The mass unbalances and the rotational moments of inertia of the gyroscopes are carefully controlled so that all gyroscopes within the inertial measuring unit precess at the same rate about any apparent acceleration. The precession of gyroscopes causes certain of the gyroscope errors to be averaged about zero thus reducing the error in the inertial measuring unit. The effect of precession upon the spatial orientation of the inertial measuring unit is compensated for by sensing the apparent acceleration and computationally compensating for the precession due to such acceleration.

Abstract: The azimuth shaft of an internally gimballed, gyro-stabilized platform assembly is maintained rigid by keeping the uniquely structured inertial instrument-mounting components neutrally buoyant in a flotation liquid that is captive within a spherical shaped outermost gimbal member. Unlike the prior art, this internally gimballed, gyro-stabilized platform assembly can be used for precision, and high-"g", applications.

Abstract: An adjustment mechanism for snow deflectors is disclosed which is connected between a discharge chute and pivotal deflector to permit an operator to orient and secure the deflector at a desired angular position without leaving his station. The angular adjustment of the deflector is controlled by the operator pulling on a flexible cable which is connected at one end to the deflector. The adjustment mechanism includes a ratchet block which is pivotally secured at one of its ends to the chute and a shouldered pin which is fixed to the deflector. The shouldered pin extends into the ratchet block for locking engagement therewith. The deflector and ratchet block pivot in response to the operator pulling the flexible cable which permits the shouldered pin to engage a selected one of several locking teeth along a toothed slot in the ratchet block thereby securing the deflector at various selected angular deflecting positions.

Abstract: A caging system for non-closed-loop gyro systems used in gyro stabilized platforms using fluid dashpots in place of automatic caging gyro brakes, torquers, or solenoids. A fluid dashpot is mounted on the gyro stabilized platform for each gyro of the platform with the linear motion of the dashpot along an axis normal to the median general rotational plane of the respective gyro of the platform. Movement of a dashpot linear movement member is greatly accentuated by the dashpot to gyro assembly interconnected linkage as roll component or pitch component amplitude exceeds designed operational gimbal roll and pitch ranges of respectively roll and pitch gyros of the platform.

Abstract: A gyrocompass comprises a gyroscopic element having a stabilizing gyro with a relatively heavy rotor rigidly secured to a driving shaft and a control gyro with a rotor of lower inertia mounted on the same driving shaft as a free rotor gyro. A case enclosing the gyroscopic element and a drive motor is mounted in a vehicle with the spin axis in the north south plane in gimbals with a nominally vertical outer axis and an inner or tilt axis in the east-west plane. The stabilizing gyro is slaved to the control gyro by means of signals from pick-offs associated with the latter so as to zeroise misalignment, and the tilt gimbal is pendulous to provide a gravity reference, so that the azimuth misalignment signal between the gyros generates an opposing tilt torquer current which is a measure of the gyro tilt angle.

Abstract: A redundant inertial reference system is provided with four gyroscope units, with the spin axes of the gyroscopes in the units being oriented, respectively, perpendicular to the four faces of an equilateral tetrahedron. Incidentally, a tetrahedron is a four sided body, and an equilateral tetrahedron is a four sided body having equilateral triangles for the four sides. With the four gyroscopes mounted perpendicular to the four sides of an equilateral tetrahedron, each of the gyroscopes is located symmetrically with respect to the others, with an angle of approximately 109.4 degrees between the spin axes of the gyroscopes. The system is particularly applicable to strapdown type inertial guidance systems and can provide three dimensional orientation information even if two of the gyros fail. The system uses four gyro units, a minimum number which can accomplish a foregoing function, with the four gyro units arranged substantially symmetrically with respect to one another.

Abstract: Disclosed herein is an engine including a timer plate which is operable to concurrently adjust the engine spark and the setting of the engine throttle valve, a rotatable starter mechanism, and a starter interlock for preventing engine starting when the timer plate is at a predetermined advanced speed setting. The starter interlock includes a resilient, unitary blocking element having a cam follower portion and a pawl portion which is movable between a normal nonoperating position and an operating position to prevent rotation of the engine starter mechanism and further includes a projection on the timer plate which is located to selectively engage the blocking element cam follower portion and move the pawl portion to the operating position when the timer plate is moved to the predetermined advanced speed setting.

Abstract: A slat and modulatable flap control system for an aircraft having slats in the leading edge of the wing and having flaps in the trailing edge of the wing. A detent pin on a control handle, and any one of four detent slots on a detent crank, can be engaged to selectively, and automatically, set the flaps and the slats (because of the cooperative action of other constituent components of the control system) in optimum positional relationship for takeoff/"go-around," cruising, approach, and landing of aircraft. The control system is ideally suited for aircraft used in "short takeoff-and-landing" situations.

Abstract: An inertial platform having four gimbals, an intermediate one of which is capable of only limited movement, has pickoffs and torque motors on each gimbal axis. Part of the intermediate gimbal and an adjacent gimbal are removable, these parts being joined by a gimbal bearing.

Abstract: A seat back member is pivotally connected to a seat cushion member. First and second rows of successively stepped teeth are arranged in opposed rows on one of the members. First and second latch bars are pivotally mounted on the other member and one of the latch bars is engageable with the stepped teeth of one row to block forward pivoting movement of the seat back and ratchet over the teeth during rearward pivoting movement of the seat back. The other latch bar is engageable with the stepped teeth of the other row to block rearward pivoting movement of the seat back and ratchet over the teeth during forward pivoting movement of the seat back. A spring urges both latch bars to their normal positions engaging their respectively associated teeth. A release handle is operable to disengage a selected one of the latch bars from its associated teeth to permit motion of the seat back in the direction normally blocked by that latch bar.

Abstract: A system providing economical redundant strap-down inertial measurement capability in a space navigation system. By appropriate orientation of two-degree-of-freedom dry tuned rotor gyros, the system is able to achieve complete redundancy utilizing only three gyro units. With this orientation, both orthogonal and skewed rate data are available. Not only are the necessary computations materially simplified, but this system also provides the necessary conditions for failure detection and isolation.