Abstract: Rotation mechanisms for rotating a payload in two, first and second degrees of freedom (DOF), comprising a static base, a first rotation arm coupled mechanically to the static base through a first rotation joint and used for rotating the payload relative to the static base around a first rotation axis that passes through the first rotation joint, a second rotation arm coupled mechanically to the static base through a second rotation joint and used for rotating the payload relative to the static base around a second rotation axis that passes through the second rotation joint, and a follower member rigidly coupled to the payload and arranged to keep a constant distance from the second rotation arm, wherein the rotation of the first arm rotates the payload around the first DOF and the rotation of the second arm rotate the payload around the second DOF.

Abstract: A device comprising a level line detector selectively oriented in reference to a surface; a moveable arm; and a processor in communication with the detector and arm to selectively move the arm, to maintain the arm in surface reference. In another embodiment, a system comprising a level line detector selectively oriented in reference to a surface; a moveable arm; a processor in communication with the detector and arm to selectively move the arm, to maintain the arm in surface reference; and a level line to communicate with the detector. In another embodiment, a method comprising: selectively orienting a level line detector in reference to a surface; detecting a level line; communicating detection data to a moveable arm; and moving the arm based on the data, to maintain surface reference.

Abstract: Using an inertial master box mounted on a carrier for measuring its movements with respect to a geographic frame of reference of fixed directions along three axes Xg, Yg, Zg, a measuring method provides for continuously measuring an orientation of a frame of reference Xm, Ym, Zm tied to the inertial master box. Positioning is provided by applying a sequence of cycles of eight inversions of the inertial master box while keeping the axis Ym in a direction parallel to the axis Yg. A first motor causes a gimbal to pivot on a first axle secured to the carrier, while a second motor causes the inertial master box to pivot about a second perpendicular axle secured to the gimbal. A processor calculates three attitude angles by running a first inertial navigation program of the strapdown type and controls the first and second motors by running a second program.

Abstract: A navigation unit having a gyro sensor mounted thereon. The unit includes a mounting mechanism for changing the mounting direction of the gyro sensor so that the rotation detecting axis of the gyro sensor may be vertical, i.e. normal to a vehicle. In one embodiment, the navigation unit includes a support device for supporting the gyro sensor rotatably with respect to a casing. The gyro sensor may be supported in a rocking manner in the casing, and mounted to be changed between a first mounting direction and a second mounting direction perpendicular to the first mounting direction. In the preferred construction, the gyro sensor has a first pin and a second pin, and the casing has a first guide groove for receiving and guiding the first pin, and a second guide groove extending perpendicular to the first guide groove for receiving and guiding the second pin. The second guide groove provides a rocking center for the gyro sensor.

Abstract: A gyroscopically stabilized artificial horizon instrument used in light aircraft mounts an earth magnetic field sensitive flux sensor on its gyroscope housing to produce a signal indicative of the direction of flight. The signal is processed and produced as a digital display of direction on the face of the instrument such that the planes relation to the artificial horizon and its direction can be observed by the pilot at the same instrument location. Provision is also made for generating signals indicative of airspeed and altitude and displaying in digital form both airspeed and altitude at the same location on the artificial horizon instrument at which direction is displayed.

Abstract: A gyroscopic referenced electronically operated grade and slope attitude indicator enabling a heavy equipment operator to build a slope and/or grade by visual readout. It is a system using a gyro output to compute the grade and slope for display thereof on a dual steering bar indicator. An angle calibration along with cancelling switches allows an equipment operator a selection of slope and grade ratios to work to in a work approach making staking and restaking of a slope and/or grade unnecessary other than for a surveyed starting point with a toe-stake or its equivalent.

Abstract: An aircraft attitude indicator employing a gyro driven tape display. The tape takes the form of a closed loop stretched about a carrier mechanism, and includes a viewable horizon indication. The tape further includes a set of perforations which, preferably, are engaged and driven by sprocket teeth borne on a sprocket wheel member attached to the pitch gimbal of the gyro. The tape travels in response to tilt of the gyro spin axis relative to the aircraft, and in a direction so that reversed pitch sensing is accomplished.

Abstract: Artificial horizon indicators are precise, gyroscopic flight instruments designed to furnish an aircraft pilot with an artificial indication of an aircraft pitch and roll attitude with respect to earth. Basically, such indicators include a gyro gimbaled within a frame which is fixed to the aircraft. Roll indicia is responsive to the gyro for rotation within a display window as a part of the frame about an axis parallel to the roll axis of the aircraft. A spherically shaped horizon indicating member is also responsive to the gyro for movement within the display window to remain parallel to the actual horizon during flight of the aircraft. The spherical horizon indicating member is pivotally mounted to the frame between the gimbal axis of the gyro and the roll indicia. The coupling of a horizon indicating member to the gyro includes a two stage three pin drive to present the aircraft pilot a uniform movement of the horizon indicating member for movement of the aircraft about the pitch axis.