Abstract: The geological gyrocompass is an accurate, portable instrument useful for geologic mapping and surveying which employs an aircraft gyrocompass, strike reference bars, a pair of sights and leveling devices for horizontally leveling the instrument. A clinometer graduated in degrees indicates the dip of the surface being measured.

Abstract: A vertical shaft system for gyroscopic theodolites with two degrees of freedom for ensuring the vertical alignment of the azimuth determining pendulum system in the apparatus, wherein perforated stones are arranged in two axial points on the housing and on the azimuth determining pendulum system of the apparatus, and wires clamped on both ends are threaded through the perforated stones and tensioned by tensioning elements, furthermore perforated guiding stones are formed for alignment of the tensioned wires, and surfaces of rotation are formed in the vicinity of the axial points between the housing and azimuth determining pendulum system with an air gap about the wires.

Abstract: A stabilized sighting device for use on a carrier comprises an outer unit mounted for rotation about a bearing axis which may be parallel to the yaw axis of the carrier. An intermediate unit is mounted for rotation on the outer unit about an elevation axis and a sight unit provided with a gyro is mounted on the intermediate unit for rotation within a predetermined angular range about an inner axis located in a plane perpendicular to the elevation axis. First and second motors are provided for driving the intermediate unit and the sight unit about the intermediate and inner axes, respectively and are controlled by first and second servo loop circuits receiving signals from the gyroscope. A detector delivers a signal representative of the deviation of the inner unit from the canonical position and a position reproducing loop controlled by the detector actuates a motor driving the outer unit. The configuration of the outer gimbal is preferably reversed for decreasing the perturbating torques.

Abstract: A portable gyroscopic compass surveying device includes means for rapidly aligning the apparatus with respect to geographic north, the north finder itself being operated apart from the associated theodolite on its own low mount. The transfer of the azimuth reference data is accomplished optically by sighting the theodolite telescope on a retro-reflector associated with the north finder. Because the north finder is physically separated from the theodolite, sightings may be made by the theodolite operator while the undisturbed north seeking operation is in process, significantly shortening the total time of operation at each station.

Abstract: A gyroscopic azimuth aiming concept adapted to aim a navigable body such as a drone or missile before its launching and defining an aiming method and system, and a suspension system to pendulously and removably suspend a gyroscope unit from the navigable body such that the gyroscope unit is isolated against pitch and roll displacements to be sensitive only to azimuth deviation of the navigable body. The aiming system and suspension system include a suspension assembly having an upper end removably connectable to the navigable body, a lower end, cables pendulously suspending the lower end from the upper end, and an anchoring base with an upright pivot to laterally restrain the lower end while allowing horizontal pendulous rotation and pivoting thereof, and a gyroscope unit is pendulously suspended to the lower end and its input axis is approximately aligned in the East direction to measure its azimuth deviation from the East direction by the effect of the earth rotation thereon.

Abstract: A miniature automatically self-aligning azimuth reference employs a floated pendulous gyrocompass device for the rapid determination of geographic north as required for surveying purposes. Fast approximate alignment with north from an initially misaligned condition is effected, while the gyroscope rotor is being run up to speed, using flux valve control. The control is then shifted to a gyrocompassing mode including settling, integration, and driving steps which complete precise alignment.

Abstract: A gyroscopic azimuth aiming concept adapted to aim a drone or missile at the launch site but also to aim other military and non-military equipment. This concept is characterized by its use of a conventional rate integrating gyroscope to both measure the aiming error, which results from an approximate initial aiming done with a magnetic compass, and to effect the correction of the aiming error without the use of surveying or optical sighting instrument. This invention defines the method of measuring the aiming error including toppling the gyroscope to displace the input axis thereof from horizontal to vertical in order to provide a measure of the required angular correction. This invention also defines a device wherein a conventional rate integrating gyroscope is pivotally mounted to allow rotation of 180.degree. in azimuth between a first and a second measurements of the rotation of the input axis direction and to allow toppling of the input axis as above mentioned.

Abstract: A miniature automatically self-aligning azimuth reference employs a floated pendulous gyrocompass device for the rapid determination of geographic north as required for surveying purposes. Fast alignment with north from an initially misaligned condition is effected in an iterative manner through the action of a unitary vertical-axis magnetic centering-torquer-pick off system employing eddy current forces.

Abstract: Gyroscope instrumentation for providing stabilization of the direction of a ine-of-sight of more than 45.degree. about one or more axes is described utilizing a two axes optical system. An inner gimbal supports a gyro rotor and a first mirror diagonal with a clearance window to admit light. The gyro rotor keeps the first mirror aligned in a fixed direction relative to an inner gimbal axis. The inner gimbal is supported by an outer gimbal. The outer gimbal has a second mirror mounted on it. The gyro rotor keeps the second mirror aligned with the outer gimbal axis. The net effect is that the optical axis at the input has a fixed orientation in space and the optical axis at the output axis has a fixed orientation relative to a platform on which the system is mounted.

Abstract: A gyroscope unit having a horizontal spin axis hangs from a suspension band within a container. The container is rotatably supported about a vertical axis. A transducer generates a control signal representative of the angular displacement between the gyroscope unit and the container about the vertical axis from a reference position. The container is rotated about the vertical axis responsive to the control signal to reduce the angular displacement from the reference position. A torque about the vertical axis that opposes the angular displacement is directly applied to the gyroscope unit responsive to the control signal. The directly applied torque is a nonlinear function of the angular displacement, being zero below a threshold value of angular displacement and having a predetermined gradient above the threshold value.

Abstract: A method and apparatus for establishing the azimuth position of a remote object is provided utilizing a north seeking gyro and a rotating transfer arm. Alignment devices such as an autocollimating telescope is provided at one end of the transfer arm for determining the relative position and alignment of the remote object to the transfer arm. A balance weight is provided at the other end of the arm to provide appropriate compensation for free rotation. The output of the north seeking gyro is connected to the transfer arm through an encoder while the telescope is rotatably connected to the transfer arm also through an encoder. The sum of the two angles measured by the encoders will provide the azimuth position angle for the remote object.