Abstract: The invention relates to a fuselage Pitot-static tube comprising three groups of orifices for determining the total pressure (2), static pressure (3) and angle of attack (6, 7), and an axisymmetric body (1) and strut (5) for mounting an anti-icing system having, arranged between them, airways (10) and electric heating elements (8). The orifices for determining the angle of attack are arranged on the strut, whose cross section is constructed in the form of a subsonic aerodynamic profile with a rounded-off nose or a tapered nose, and are arranged between the nose of the profile and the position of its maximum thickness.

Abstract: An aircraft pitot and static pressure sensing device and an aircraft having the sensing device, more particularly a fighter aircraft, include a plurality of pressure sensors disposed in a radome of the aircraft. In addition, a plurality of air intake ports is provided in the radome. The air intake ports are connected through connecting passages to the pressure sensors.

Abstract: A cabin pressure control system for aircraft includes a controller for receiving and comparing set point and actual values for an aircraft cabin pressure. A speed-controlled drive for an air outlet valve is connected to the controller for triggering the valve as a function of the comparison. A remote indication is issued to the controller solely regarding a newly established actual cabin pressure, without a remote position indication from the valve.

Abstract: A sensor for measuring the relative velocity of an oncoming medium includes a tubular and preferably radially symmetrical sensor body having a leading front end, and a wall with an inner surface defining an axial hollow space being open to the outside at the leading front end. The sensor body includes a preferably streamlined sensor head portion associated with the front end, and a remainder of the sensor body forming a sensor shaft. The wall has at least one conduit being radial or having a radial component. The at least one conduit is separated from the axial hollow space and spaced apart from the front end. The at least one conduit is open to the outside from one of the portions. A method of measuring the relative velocity of the medium includes detecting a first measured value representing the sum of the static pressure and the velocity-dependent dynamic pressure of the medium with an axial pitostatic tube discharging at the front end of a sensor body.

Abstract: The frequency of a pulse signal is measured with the aid of a reference signal generated in an oscillator (11). Both the pulses of the frequency to be measured and the pulses of the reference frequency are counted by separate counters (12, 13) and the counts or counted results are stored in separate memories (14, 15). A flip-flop (21) is set and reset to determine each measuring duration. The difference between two successive counts of the measured frequency counter (14) corresponds to the pulses or rather periods counted during the measuring time duration. The difference between two successive counts of the reference frequency counter (15) corresponds to the length of the measuring time duration whereby the resolution is determined by the reference frequency. A microprocessor (16) divides the number of periods counted by the measuring time duration to ascertain the frequency to be measured which may then be displayed.