Abstract: Airspeed direct sensing transducer apparatus in a system where fast response gust sensors are aircraft wing mounted, each gust sensor mounted on opposite wing halves feeding the absolute value of low-pass filtered direct sensed airstream gust cross-component signals to a difference amplifier providing an electrical indication when one side of the aircraft “sees” disturbed or turbulent air as may be encountered when an aircraft trailing wake-vortex or similar hazardous atmospheric disturbance is approached. This enables the pilot to take evasive action to mitigate or avoid the turbulence disturbance, enhancing free flight aircraft operation.

Abstract: An attitude indicator device for allowing a pilot to determine an aircraft's attitude in case of instrument or power failure. The attitude indicator device includes an L-shaped housing member with a plurality of spirit levels, each lighted utilizing a solar power source and backed up by batteries, that allows a pilot to determine an aircraft's attitude without instrumentation or power from the plane.

Abstract: A water bike equipped with a speed meter wherein a speed meter sensor 1 including a coil for generating a magnetic flux and electrodes disposed at positions vertical to both flowing direction of a fluid and direction of the magnetic flux, and for measuring the speed of the water bike on water by the value of electromotive force generated by an electromagnetic induction operation, is fitted to a submerged portion of the water bike 2.

Abstract: The invention pertains to a multifunction probe for aircraft intended for determining in particular the static pressure (Ps) and the total pressure (Pt) of an airflow located in the vicinity of the aircraft and the angle of incidence (&agr;) of the aircraft with respect to the flow. The probe comprises a movable blade (1) intended to orient itself along the axis of the airflow, the movable blade (1) comprising at least one static pressure tap orifice (13, 14) located on one side of the blade (1) and a pressure tap intended for measuring the angle of incidence (&agr;) of the blade (1) with respect to the flow. The probe furthermore comprises pressure measurement means associated with each pressure tap and means for calculating the total pressure (Pt) of the flow as a function of the measurements carried out by the various measurement means of the probe.

Abstract: A fixed multifunction probe, e.g., for aircraft and configured to measure air flow parameters near an airplane. The probe includes a body closed by a rounded cap, at least three pressure taps situated at specified positions of the body, a pressure measurement mechanism for measuring at least as many pressures as pressure taps, and a calculation device for calculating the air flow parameters.

Abstract: A multi-function probe system that provides redundancy for measurements and compensates for effects of sideslip of an aircraft includes at least two probes that are symmetrically located on the opposite sides of the aircraft, and a third probe mounted on the centerline of the aircraft positioned to directly measure local sideslip with ports that are positioned on opposite sides of the center plane of the aircraft. Each of the probes includes self contained instrumentation for providing signals indicating various pressures. The local angle of sideslip sensed by the third probe is used as a compensation for pressure readings at either of the other probes for determining actual angle of attack, and static pressure.

Abstract: Disclosed are flow separation detectors and, more particularly feedback sensor arrangements adapted to provide for the measurement of surface aerodynamic flow phenomena, and especially with regard to aerodynamic flow separation which is encountered over a surface. In order to obviate or ameliorate the electrical energy requirements in the provision of feedback sensor arrangements, particularly such which are employed for a closed-loop control of aerodynamic flow separation; for instance, that on the wing of an aircraft wherein there can be encountered a breakdown of a boundary-layer flow which may adversely affect the performance of the aircraft, provided is a novel system of flow separation sensors which are based on fiber optics and which may be employed for separation feedback control.

Abstract: A support device for a motorized flying instrument in a wind tunnel.

Abstract: The angle of attack of an airfoil moving through the air can be detected and a display provided electronically through use of an all-solid-state system powered by a D.C. source. A wind vane mounted on one end of a shaft is exposed to the airflow while a windowed mask is provided at the other end of the shaft. By providing an appropriate array of openings in the mask, and a series of associated optical transmitters and receivers on opposed sides of the mask, extremely fine sensitivity can be provided in detection of angle of rotation of the mask and thus in the angle of rotation of the vane. The angle of the vane is directly established by the angle of attack. The detected angle of attack is then displayed on a vertically oriented light bar on the instrument panel, for instance in a light aircraft.

Abstract: A measuring system for determining an air data for an aircraft includes a measuring device for determining measured variables which are a function of the resulting flow vector and the inertia forces acting on a front fuselage section in relation to a rear fuselage section, an acceleration transducer, and an evaluation unit for determining the air data from the measured variables.