RU1793282C - Airplane velocity pointer - Google Patents

Abstract

.V acquisition relates to aeronautical engineering and can be used on single-aircraft for various purposes. The goal is to increase the flight safety of the aircraft by providing, along with visual additional speech information about the instrument speed of the aircraft during takeoff and landing. Along with a pressure gauge box 1 with a movable center-2 kinematically connected through a crank mechanism 3, 4 and an axis 5 with a sector 6 with a tube 7, on the conical part of which is attached arrow 9, and a digitized scale 11, a pointer contains a limit switch of the released position of the chassis 15, a voice informant 16, reed switches 10 mounted on a digitized scale 11 according to the corresponding scale marks, and a permanent magnet 12 kinematically connected to the conical part of the sleeve 7 and oriented in the direction of the arrow 9. Each reed switch 10 with its input is electrically connected to the output of the limit switch of the released position of the chassis 15, and with its output - with the corresponding input of the voice informant 16. 1 ill. and /

Description

The invention relates to aircraft and can be used on single-seat aircraft for various purposes.

A known instrument speed indicator is known, comprising a gauge box, a membrane with a moving center, which has kinematic communication with a contact group, designed to provide an electrical signal to external devices. This device is designed to automatically turn on and off the emergency recording system of flight modes when the instrument speed reaches 120 km / h.

A known device is a CCA speed indicator comprising a gauge box, a membrane with a movable center having kinematic connection with a contact group, a set screw, which controls the contact distance. This device provides circuit closure when reaching the instrument speed set on the scale.

The disadvantages of these devices are as follows:

lack of visual readout devices;

an electrical signal is provided to external circuits at only one predetermined point.

The closest in technical essence to the proposed one is a speed indicator containing a manometric box with a movable center kinematically connected to a crank mechanism, which drives the axis with a sector rotating the tribe, on the conical part of which is mounted an arrow moving from the dial with a scale, all elements of the pointer are placed in the housing.

Unlike the analogs described above, this device provides measurement and visual indication of indications of the indicated flight speed, however, it does not provide discrete electrical signals about the indications of the pointer to a voice informant, in order to provide the possibility of verbal information about the indicators of the speed indicator, which has a large human exposure than other means of communication.

The aim of the invention is to increase the flight safety of the aircraft by providing, along with visual additional speech information about the aircraft airspeed on takeoff and landing.

This goal is achieved by the fact that in a known device containing a manometric box with a movable center, kinematically connected through

a crank mechanism and an axis with a sector, with a tube, on the conical part of which the arrow is mounted, and a digitized scale, an end switch of the released position is additionally introduced

0 chassis, voice informant, reed switches mounted on a digitized scale, according to the appropriate scale marks, and a permanent magnet kinematically connected to the conical part of the tribock and oriented in the direction of the arrow, each reed switch being electrically connected to the output of the limit switch of the released the position of the chassis, and with its output, with the corresponding input, speech0 from the informant.

The drawing shows a schematic diagram of an airplane speed indicator.

The aircraft speed indicator contains a pressure gauge box 1 with a movable

5 center 2, crank mechanism 3, 4, axis 5, sector 6, tribe 7, curtain 8, arrow 9, reed switches 10, scale 11, permanent magnet 12, display 13, case 14, limit switch of the released position

0 chassis 15, voice informant 16.

The speed indicator works as follows.

The total pressure Pp from the air pressure receiver is supplied to pressure gauge box 1, and the static pressure P0 to c. case 14 of the device. Under the influence of the difference in total pressure and the static pressure gauge box 1 is deformed. The amount of deformation is proportional

0 dynamic pressure. The deformation (deflection) of the gauge box 1 is converted by a crank mechanism 3, 4 into a rotational movement of the axis 5, on which sector 6 is rigidly fixed

5 shutter 8, opening the scoreboard 13 with the number 1 at one full turn of the arrow. Sector 6 is engaged with a tube 7, on the conical part of which an arrow 9 oriented in one direction is fixed

0 and a permanent magnet 12, designed to control the reed switches 10. The deviation of the arrow 9 and magnet 12 is proportional to the deflection of the gauge box 1 and, therefore, proportional to the indicator speed 5 of the aircraft at a constant air density. Reed switches 10 are oriented relative to the graduated scale marks in the range of landing flight speeds. The number of reed switches and their installation frequency depends on the aerodynamics of a particular aircraft and can be determined by expert judgment of the pilot. When the contacts of the limit switch of the released position of the chassis 15 are closed, the electric signal enters the inputs of the reed switches 10. At the moment of passage of the permanent magnet 12 above one of the reed contacts, its contacts are closed and the electric signal enters the corresponding input of speech information

Matera. which provides for reproducing audio signals of speed indicator readings in the pilot phones. When the contacts of the limit switch 15, i.e. when the chassis is not released, there is no electrical signal at the inputs of the reed switches 10, the speed indicator works in the mode of visual reading of information.

Claims (1)

The claims Airspeed indicator containing a gauge box with a moving center kinematically connected cher ez crank mechanism and an axis with a sector with a tribe, on the conical part of which an arrow is mounted, and a digitized scale, characterized in that | in order to increase the safety of the aircraft’s flight by providing along with visual additional speech information about the aircraft’s instrument speed take-off and landing, a limit switch of the released position of the chassis, a voice informant, reed switches installed on the digitized scale according to the corresponding scale marks, and a permanent magnet kinematically connected to the conical part of the tube and oriented in the direction of the arrow, each reed switch the input is electrically connected to the output of the limit switch of the released chassis position, and the output is connected to the corresponding input of the voice informant.