Abstract: There are provided systems and methods for providing a barometric altitude monitor that assist pilots by providing alerts when a barometric altitude of the ownship aircraft is may be incorrect. Various embodiments of the present invention determine whether significant errors in barometric altitude occur though comparisons to alternate altitude information sources. Through aspects of the present invention, errors arising from manual entry of barometric pressure information by a pilot may be identified before safety issues arise, thus helping to prevent events such as controlled flight into terrain (CFIT).

Abstract: A differential pressure indicator includes a multi-polar driving magnets train clamped on a piston pin that moves in response to the changes in pressure conditions, thereby driving a multi-polar follower magnet carrying an indicating member, to move across a scale for a total angular range of 90° to 270°. The exact angular displacement of the follower magnet per unit linear displacement of the driving magnets train is decided by varying the relative magnetic strengths of the driving and follower magnets or by varying the spacing between adjacent magnets of the driving magnetic train. Further, magnetic flux of an auxiliary magnet fitted on the piston pin at a 90° orientation relative to the driving magnet train is utilized for actuating a magnetic switch in the switch assembly.

Abstract: An airspeed indicator display for an aircraft having a main rotor system and a translational thrust system includes a first indicator operable to display an actual airspeed of the aircraft and a second indicator positioned adjacent the first indicator. The second indicator is operable to display an actual pitch angle of the translational thrust system.

Abstract: The present invention proposes a portable barometric altimeter (10) including a pressure sensor (14), a calculation unit (16) which determines an altitude value (H) as a function of the pressure (P) measured by the sensor (14) and as a function of a reference temperature (T0) corresponding to an estimate of the temperature of the air mass at sea level, and a time measuring unit (18) that supplies calendar data (D), characterized in that it includes a correction circuit (32), which selects the reference temperature value (T0) from among a series of values (TS) contained in a database stored in the altimeter (10), as a function of the date (D) and as a function of a predefined climate value (C). The invention also proposes a method of determining altitude (H).

Abstract: A telemetering system allows a receiver to provide an indication related linearly with the data from a sensor in a transmitter that comprises an amplifier composed of relatively inexpensive and low-quality parts. The transmitter includes an ID ROM (10) that stores an ID code specifying itself, and it transmits the ID code when transmitting the output from a sensor (1). The receiver includes a correction circuit (13), which finds the correction table corresponding to the transmitter in accordance with the received ID code and corrects the received sensor output on the basis of the correction table.

Abstract: A device used to alert an individual of the presense of low atmospheric pressure. This is accomplished through the use of an aeronoid barometer, and an audio/visual alarm. The counterclockwise rotation of the metallic barometer needle contacts the the sensor probe, or metallic contact, at a given low atmospheric pressure. This contact completes an electrical circuit which activates an alarm.

Abstract: An apparatus and a method for manufacturing a thick-walled bent pipe with a simple structure at low production cost, which has durability and can manufacture an elbow material for piping with higher size accuracy, are provided. For this purpose, the manufacturing apparatus is a manufacturing apparatus comprising a presser die (12) and a lower die (20), in which the lower die (20) includes a pair of bottom dies (21, 22) having meshing means (30), and a pair of the bottom dies (21, 22) are allowed to rotate opposite to each other by the meshing means (30), in connection with a descent of the presser die.

Abstract: An altimeter (24) of the aneroid type having a correctable digitizer 26 is shown. When the pilot sets the altimeter to the local barometric pressure, the correctable digitizer is also set to the local barometric pressure. An input device (58) connected between the barometric pressure correction control (66) and the digitizer (62) generates a barometric pressure correction signal (67) which is routed to digitizer (62). Barometric pressure correction signal (67) modifies the aircraft altitude output value of digitizer (62) to a corrected aircraft altitude output value (68) which is routed to one or more external navigation systems (70).

Abstract: A method, an apparatus and a computer program product are provided for accurately determining the vertical speed of an aircraft in a manner independent of signals provided by an air data computer, an inertial reference system and an inertial navigation system. Initially, a first vertical velocity of the aircraft is determined based upon a pressure altitude value associated with the aircraft. A second vertical velocity of the aircraft is also obtained from a GPS receiver carried by the aircraft. The first and second vertical velocities are then combined to determine the vertical speed of the aircraft. In this regard, the first and second vertical velocities are combined by complimentarily filtering the first and second vertical velocities. More particularly, the first vertical velocity is typically low pass filtered to remove high frequency noise that is attributable to the relatively low resolution of the first vertical velocity value.

Abstract: In a pressure instrument with depth/altitude and time display, a measurement time period from a starting instant up to a stopping instant of the time measurement is measured by measurement-time counting means, and also another measurement data is acquired by detecting pressures from the starting instant up to the stopping instant of the pressure measurement. After the measurements are taken and when a measurement stop signal is outputted, a determination is made whether or not the measured time periods are longer than a predetermined time period. If the measured time period is longer than a predetermined time period, this dive is regarded as one for which it is required to store a record, and then the measurement data acquired between the starting instant and the stopping instant of the measurement are stored in a memory.

Abstract: The small altimeter according to the invention comprises a frame (7-11;14,15), a display comprising drums (45,79) and a dial (23) cooperating with a hand (46) and a multiplying gear train (53 to 57) driving the display in response to the displacements obtained by the aneroid elements (1 to 4). It comprises several aneroid elements (1 to 4) which are cylindrical and coaxial and connected together and with the frame (7-11) of the altimeter. This stacking is divided in two opposed groups (1,2; 3,4). The free faces of the two groups (1,2;3,4) of aneroid elements of the stacking are cynematically connected to a same movable member (31), which meshes in diametrically opposed points with two toothed members (29,30) belonging each to one of said cynematic linkages. The movable member (31) drives the display (45, 79, 23, 46) through the multiplying gear train (53, 57). The axis of the stacking of aneroid elements (1-4) is parallel to the shaft of the hand (46) of the display.

Abstract: Mechanism for an aneroid barometer comprising, in a support 2, a primary lever 4 whose center is in contact with the cell 3, the axis of rotation 40 of this primary lever being located at the periphery of the support, an endless screw 5 equipped with a helicoidal ramp 51 made integral with the lever 4 via a bridge 7, a secondary lever 6 whose axis of rotation 60 rests on the free end 41 of the lever 4, the free end 61 of this lever 6 ending in a point 62 which acts permanently on the helicoidal ramp 51. A single spring 8 bears on the support 2 and keeps both the lever 4 in contact with the cell and the secondary lever on the primary lever.

Abstract: An apparatus to continuously monitor a preset altitude for a pilot of an aircraft. It senses a change in altitude and an audible as well as a visible alarm tells the pilot that he has deviated from his preset altitude by a given height. Increase in altitude is signaled by a high pitch tone and by a yellow light while a decrease in altitude is signaled by a low pitch tone and a red light. The invention can also be used to warn a small boat operator of a pressure drop.

Abstract: A servo instrument, particularly a servo altimeter, with a minimum of display error. The instrument comprises a capsule assembly, a sector adapted for rotation corresponding to the displacement of the capsule assembly, a photosensor for producing an output showing its angular position relative to the sector, a support for rotating the photosensor while supporting it adjustably in a direction of tracing the sector, a cam adapted to make the amount of the adjustment of the photosensor variable by the position of the support, a motor, means for generating a signal showing the rotating positional angle of the motor, and an amplifier for amplifying the output of the photosensor and driving the motor so as to maintain the output of the photosensor constant.

Abstract: A pressure transducer such as for use in a radiosonde includes a substrate and a plurality of conductive contacts formed thereon. An arm is movable over the contacts in accordance with the sensed ambient pressure. A group of resistors of different values of resistance are operatively connected to the contacts whereby each contact is characterized by a unique value of resistance. The resistance may be connected as the frequency-determining element of an oscillator, such that each unique value of resistance may be converted to a unique corresponding frequency and upon decoding determine which unique contact is operatively connected.

Abstract: An instrument for providing an altitude representation in accordance with ambient atmospheric pressure has a mechanism that is manually-operable to effect adjustment to the setting of a datum against which the representation is provided. A mechanical feedback is applied to the mechanism in accordance with the datum setting such that the setting of the datum depends both upon the manual operation of the mechanism and the feedback applied to the mechanism as a result of that manual operation. The mechanism may include a worm gear that is rotatable in accordance with manual operation of the mechanism in which case the feedback is introduced into the mechanism by longitudinally displacing the worm gear.

Abstract: A reference index is provided for dial type instruments and includes an indicator selectively positioned on the face of the instrument for operation in either of two functional modes. The reference index includes a mounting pivot which is adapted to be secured to the face of the instrument and carries a mounting block that is relatively rotatable about a pivot axis projecting from the face of the instrument dial. Carried by the mounting block is an indicator having an elongated arm which has one end pivoted in the mounting block for relative rotational movement in a plane parallel to the face of the instrument, or perpendicular to the pivot axis. Formed with the outer end of the arm are first and second reference tabs which are adapted to overlie the circular indicia ring of the instrument. The two tabs are perpendicularly disposed to each other and project transversely to the longitudinal axis of the arm.

Abstract: A solid-state barometric altimeter-encoder. The atmospheric pressure is cared to a reference vacuum on a hybrid IC pressure transducer which generates a proportional signal. This analog signal is then converted into digital data, corrected for atmospheric to altitude non-linearity by use of a ROM look-up table, displayed as a digital readout and also converted to Grey code format for transponder MC (altitude) transmission.

Abstract: A piezoelectrical transducer for providing an altimeter with vibratory motion to attenuate the effect of static friction on the movement of a gear train responding to an altitude responsive aneroid.

Abstract: An altimeter has a pointer which rotates clockwise once round a dial for each thousand unit (feet or meters) increase in altitude, the zero of the dial being in the nine o'clock position.Two digital displays are situated one above and one below the horizontal through the dial zero. When the pointer lies in the upper segment of the dial a reading is shown on the upper display and when the pointer lies in the lower segment of the dial a reading is shown on the lower display. When the pointer is in the region of the zero position (for example within 100 feet of the zero position) a reading is shown on both displays. The upper display then reads thousands corresponding to a pointer position above zero and the lower display reads thousands corresponding to a pointer position below zero (whether the pointer is above or below zero).

Abstract: A correction mechanism for supplying an altimeter indicator with a rotational torque to compensate for the non-linear relationship between pressure altitude and barometric pressure. The correction mechanism has a first gear for receiving an input force and a second gear connected to the first gear. The second gear is eccentrically located on a shaft which connects a third gear with the altitude indicator. Because of the eccentricity of the second gear the line of action between the second gear and the first gear causes the shaft to rotate the third gear through a varying arcuate length for each tooth engagement.

Abstract: Aircraft altitude is visually displayed at a front panel of a flight instrument in analog form by a rotating pointer and in digital form by means of a rotary drum digital indicator. Barometric pressure is converted into rectilinear motion to drive a mechanical-to-electrical transducer providing a signal to a servo amplifier having an output coupled to a servomotor. The servomotor drives both the rotating pointer and the rotary drum digital indicator. Also coupled to the mechanical-to-electrical transducer is a manually adjustable set input signal to correct for atmospheric pressure along a given flight path with respect to sea level. Temperature and altitude error corrections are also coupled to the transducer to correct the servomotor drive signal to give a true indicated altitude display. Also driven by the servomotor is a pressure altitude encoder for providing absolute altitude digital signals for transmission to a ground station.

Abstract: An aircraft altimeter-encoder is provided with an altitude sensitive barometric or aneroid bellows which simultaneously drives a visual altitude indicator and an altitude digital encoder. The indicator includes one or more pointers that register with a dial. The encoder includes a wheel or disc having a series of transparent and opaque regions scanned by photo-optical means. This generates digital signals corresponding to the altitude indicated on the face of the altimeter. The digital signals are adapted to be fed to a transponder for telemetering to a ground station. The altimeter-encoder includes means for simultaneously adjusting both the indicator and the encoder disc to compensate for variations in the local or ambient barometric pressure. Means are also provided for adjusting the relationship between the indicator and the encoder disc whereby the digital altitude signals coupled to the transponder correspond exactly to the altitude indicated on the face of the altimeter, referenced to 29.

Abstract: An altimeter has a rotatably-mounted index that is driven to rotate through one complete revolution around a scale for each change of 1,000 feet in altitude sensed by two evacuated manometric capsules the number of revolutions of the index is indicated by numerical markings visible through an arcuate window which breaks into the scale against a `zero` arrowhead at the top-center of the scale. The markings are distributed around the opaque circumferential-margin of a transparent disc that is mounted coaxially with the index and is driven in the counter direction to the index through step-down gearing. Successive ones of the numerical markings are rotated to the zero arrowhead to indicate the number of units of 1,000 feet appropriate to the altitude measurement, upon successive revolutions of the index.

Abstract: Apparatus and a method for use in determining the optimum direction of progress of a sailing vessel from one point to a second point are described. The angle of leeway between the direction of heading of the vessel and the course of the vessel is measured and the course of the vessel is set to a required apparent wind direction so as to obtain the sum of the angle , leeway and the angle of the apparent wind direction with respect to the direction of heading. The distance covered by the vessel relative to the apparent wind in a given space of time is measured. Simultaneously the distance covered by the vessel relative to the water in said space of time is measured. The quotient of the measured water distance divided by the measured air distance is obtained, and a chart relating the said sum and the said quotient is used to give a figure of merit for the course. Three separate charts for use respectively in "reaching," "beating" and "running" are provided.

Abstract: Aircraft altitude is visually displayed at a front panel of a flight instrument in analog form by a rotating pointer and in digital form by means of a rotary drum digital indicator. Barometric pressure is converted into rectilinear motion to drive a mechanical-to-electrical transducer providing a signal to a servo amplifier having an output coupled to a servomotor. The servomotor drives both the rotating pointer and the rotary drum digital indicator. Also coupled to the mechanical-to-electrical transducer is a manually adjustable set input signal to correct for atmospheric pressure along a given flight path with respect to sea level. Temperature and altitude error corrections are also coupled to the transducer to correct the servomotor drive signal to give a true indicated altitude display. Also driven by the servomotor is a pressure altitude encoder for providing absolute altitude digital signals for transmission to a ground station.

Abstract: An inexpensive, compact and yet highly accurate instrument for transmitting coded signals representing altitudes at which an aircraft is flying, the instrument comprising an altitude sensing unit and a separate encoding unit operatively connected to the sensing unit with means for finely and precisely adjusting the encoding unit relative to the altitude sensing unit.