Abstract: Some implementations include a method for operating a centrifuge-based-flight simulator in at least one of several different modes: a heightened G-force mode, a normal G-force mode; and transition modes (i.e., ramp-up or ramp-down modes) between the heightened G-force and normal G-force modes. During the normal-G-force mode the simulator ceases planetary motion altogether or substantially decreases rotations to replicate a plurality of flight conditions that physically imparts, on the trainee during operation of the simulator, a G-force that is not greater than approximately one (1) G. The reduction of planetary motion while maintaining realistic motion and force sensations that are appropriate for the virtual-flight conditions being experienced allows realistic flight simulation experience for the trainee and reduces the negative effects of constant planetary motion.

Abstract: A device for indicating a direction or axis in three dimensions to a user, comprises an indicator member (10, 11) configured to indicate a direction in any three dimensional direction,—a static member (12) for mounting the indicator member; and an actuator arrangement (12, 14, 15) configured to urge the indicator member to rotate relative to the static member in any angle about a single point of rotational symmetry. A direction indicating arrangement calculates an angle in three dimensions for indicating a direction and comprises a drive arrangement (13, 14, 15) that drives a pointing device (10, 11) to point in the calculated direction.

Abstract: An angle measuring guide includes a housing having a plurality of monolithically formed walls and an annular opening formed within selected ones of the walls. The rear wall has a planar surface for being directly mated with the motorcycle. A transparent lens is monolithically formed with the housing and directly connected thereto. A buoyant member is situated within the opening and the cavity. A predetermined quantity of high viscous fluid is contained within the opening and the cavity such that the fluid freely flows therebetween and supports the buoyant member at a free and suspended position during operating conditions. The buoyant member includes a stationary weight member connected to a bottom portion thereof and thereby anchors the buoyant member while allowing the buoyant member to freely rotate about one or both of the x-axis and y-axis.

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: The present invention is a multi-function earthquake alerting apparatus. It is designed and built as an average household item with simple and durable mechanical parts. It can serve as a decorative item. However, when an earthquake happens, it will serve as an information center in a quick glance. The essential functions of the present invention earthquake alerting apparatus include indicating the direction of the epicenter of a major earthquake, providing an auditory alert for small warning shocks and after shocks, and providing information on the exact time of the earthquake.

Abstract: The invention relates to a process for the visual display of the attitude of an aircraft to assist piloting or flying in space. On the basis of the values of cardan or gimbal angles (.psi., .theta., .phi.) of the aircraft marked in a reference mark linked with the celestial cavity or firmament and on the basis of a calculation of quaternions, the process consists of displaying on a screen (1) on board the aircraft, in particular the following informations: a cruciform reticule (7,8,9), a piloting or flying circle B, the value of the roll angle (.phi.) in a scale (10), a net formed by portions of meridians (M) and parallels (P) of the celestial cavity, a symbol (V1) representing the direction pointed by the velocity vector of the aircraft, a short term prediction vector (12) for the aircraft attitude, as well as numerical values (19,21,23) for the roll, pitch and yaw velocities. Application is to the piloting of an aircraft in space.

Abstract: A turn-and-bank indicator can integrate with regard to time the displacement of a pointer of the turn-and-bank indicator, the pointer indicating the turning rate of the airplane. It includes a non-contact converter which outputs an electrical signal in proportion to the deflection of the pointer; an amplifier which amplifies the output of the non-contact converter; an integrator which integrates the output of the amplifier with respect to time; and a digital display unit which displays the output from the integrator at a close position with the pointer.

Abstract: The invention relates to an aircraft attitude indicator having a gyro controlled spherical display with delineations of regularly spaced meridians that maintain a vertical orientation and spaced parallels transverse to the meridians, one of which is an equator that divides the sphere into upper and lower hemispheres and corresponds to a horizon. The lower hemisphere has triangular pointer indicia, each symmetrical to a delineated meridian and with a base on a parallel and an apex proximal to the equator. The pointer indicia cooperate with a reference delineation that is relatively fixed with respect to the aircraft and substantially centered on the display. The pointer indicium nearest the reference designates the "up" direction; those adjacent to it provide information about changes in aircraft attitude relative to "up" that will result from possible maneuvers from the existing attitude.

Abstract: In a gyro horizon type of equipment, roll corrections are fed to the aircraft symbol which is a normally fixed display element and pitch correction is introduced on a movable display element or drum with modification of the position of the display elements of the instrument gyro as a function of an interconnection of the instrument gyro with a gyromaster reference through comparators connected to each of the roll and pitch systems.