CN107883980A - Pressure altimeter base level dynamic testing method - Google Patents

Abstract

The invention discloses a basic-level dynamic detection system for a barometric altimeter, comprising: a measured object, a pressure source and a computer; tube; the pressure source produces altitude pressure control output and speed pressure control output to the pitot tube, the barometric altimeter senses the pressure received by the pitot tube, and feeds back the altitude and speed information of the aircraft to the computer, and the computer generates the altitude according to the pressure source Check whether the pressure control output, speed pressure control output, and the altitude and speed information of the aircraft are consistent, and judge whether there is any contamination, blockage of the pitot tube, or air leakage in the connecting pipeline between the barometric altimeter and the pitot tube. The invention can realize accurate detection of pollution and blockage of the pitot tube, and whether the connecting pipeline between the air pressure altimeter and the pitot tube is leaking, etc., so as to ensure the flight safety of the aircraft.

Description

A dynamic detection method at the base level of barometric altimeter

technical field

The invention belongs to the technical field of testing and fault diagnosis of an air pressure altimeter, and relates to a basic-level dynamic detection method for an air pressure altimeter.

Background technique

Barometric altimeters are widely used in the control systems of subsonic aircraft such as aviation aircraft and missiles. A barometric altimeter generally consists of a sensor, a pitot tube, and a connecting air pressure line. In the past, the test of the barometric altimeter mainly adopts the method of static test: a relatively standard air pressure is provided by an external pressure source, and then the measurement accuracy of the sensor is checked. The inspection of the mechanical connection parts such as the pitot tube and the connecting pneumatic pipeline is relatively neglected.

The pitot tube and the connecting pipeline are the input channels of the sensor. When the test time is not strict, even if there is a small amount of blockage in the pipeline, the predetermined pressure balance can still be achieved, and the purpose of checking the measurement accuracy of the sensor can be achieved. But in this case, accurate rate information cannot be provided to the sensor.

After the aircraft is equipped, the pitot and other leaking equipment are generally protected by wrapping and other protection measures. However, due to its frequent maintenance and guarantee, it is inevitable that the pressure input hole will be polluted. Once a mistake occurs during the operation, it will affect the measurement and collection of parameters such as the pressure change rate by the sensor under real flight conditions, and will have a great impact on the flight safety of the aircraft. The traditional static testing method is unable to find this kind of failure. Therefore, it is necessary to improve the test method of the barometric altimeter.

Contents of the invention

(1) Purpose of the invention

The purpose of the invention is: for the traditional static test method can not find and identify the test method defect of barometric altimeter pitot tube pollution, blockage, propose to improve the design by external pressure source, make it not only have the height/ The function of Mach number static fixed-point test, and it has the function of refreshing the output pressure value in real time with a short cycle, realizing the dynamic test function of simulating the flight pressure environment of the aircraft, so as to make up for the shortcomings of the traditional test method and expand the detection coverage of the barometric altimeter rate to ensure the safety of the aircraft.

(2) Technical solutions

In order to solve the above-mentioned technical problems, the present invention provides a kind of barometric altimeter basic level dynamic detection system, and it comprises: measured object, pressure source and computer; The connecting pipeline is connected to the pitot tube; the pressure source generates altitude pressure control output and speed pressure control output to the pitot tube, and the barometric altimeter senses the pressure received by the pitot tube, and feeds back the altitude and speed information of the aircraft to the computer, and the computer According to the altitude pressure control output, speed pressure control output generated by the pressure source, and whether the altitude and speed information of the aircraft are consistent, determine whether there is pitot tube pollution, blockage, air leakage in the connecting pipeline between the barometric altimeter and the pitot tube situation.

Wherein, the pressure source includes: a first air storage tank, an oil-free vacuum pump connected to the first air storage tank and a first quick opening valve; a second air storage tank, and an oil-free compression pump connected to the second air storage tank and the second quick-opening valve; a static pressure sensor is set on the first quick-opening valve, and a full-pressure sensor is set on the second quick-opening valve; the first quick-opening valve is connected to the altitude pressure control output, and the second quick-opening valve is connected to the speed pressure control output ; The control unit is connected to the static pressure sensor and the total pressure sensor. The control unit receives the external program control command or the control command of the panel, converts the command parameters into the pressure control voltage and then adds them to the total pressure sensor and the static pressure sensor respectively. After the sensor and the static pressure sensor respectively form the control voltage, they act on the corresponding quick-opening valve, respectively connect the external output of the second gas storage tank and the first gas storage tank, and when the output pressure reaches the command voltage, the quick-opening valve closes , when the pressure deviates, the quick-opening valve opens for air supplementation.

Wherein, in the pressure source, under the excitation of an external power supply, the oil-free vacuum pump and the oil-free compression pump work to respectively perform negative pressure and positive pressure operations on the first air storage tank and the second air storage tank.

Wherein, the altitude pressure control output and the speed pressure control output are both in the form of sine wave curves, or in the form of climbing, level flight and glide curves with constant slope.

The present invention also provides a dynamic detection method at the base level of the air pressure altimeter. The control method is carried out based on the above detection system. The pressure source provides the altitude pressure control output and the speed pressure control output to the aircraft pitot tube according to the preset control curve. The data information sensed by the altimeter is fed back to the computer, and the computer judges whether the pitot tube of the aircraft is polluted, blocked, or there is air leakage in the connecting pipeline between the barometric altimeter and the pitot tube according to the control curve and the received data information.

Wherein, the control curve is a sine wave curve, or a climb, level flight, and glide curve with a constant slope.

Wherein, when the control curve is a climb, level flight, and glide curve with a constant slope, the data curve of the aircraft in the climb segment and the glide segment is equal to the data curve of the control curve in the climb segment and the glide segment, and the phases are consistent, and the curves of the level flight segment coincide, then It means that the sensor, pitot and pipeline of the barometric altimeter are in correct condition; otherwise, it means that the sensor, pitot or pipeline of the barometric altimeter are in abnormal condition.

Wherein, when the control curve is a climb, level flight, and glide curve with a constant slope, the phase of the data curve of the aircraft in the climb section and the glide section is inconsistent with the phase of the control curve. If the phase of the data curve of the climb section lags behind the control curve, the data curve of the glide section If the phase of the curve is ahead of the control curve, it means that the pipeline is leaking air; if the rising slope of the data curve in the climbing section is lower than the rising slope of the control curve, and the rising slope of the data curve in the downhill section is lower than the rising slope of the control curve, it means that the airspeed There is a blockage in the air pressure hole of the tube.

(3) Beneficial effects

The above-mentioned technical scheme provides a dynamic detection method for the barometric altimeter at the grass-roots level, which can accurately detect the pollution and blockage of the pitot tube, and whether there is air leakage in the connecting pipeline between the barometric altimeter and the pitot tube, so as to ensure the safety of the aircraft. Flight safety.

Description of drawings

Accompanying drawing 1 is the schematic diagram of the principle of the pressure source.

Accompanying drawing 2 is the data comparison diagram when testing to normal state.

Accompanying drawing 3 is the data comparison schematic diagram when testing to the fault state.

Detailed ways

In order to make the purpose, content and advantages of the present invention clearer, the specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

In order to realize the object of the present invention, the present embodiment firstly provides a kind of barometric altimeter basic-level dynamic detection system, and this system comprises: measured object, pressure source and computer; The altimeter is connected to the pitot tube through the connecting pipeline; the pressure source generates altitude pressure control output and speed pressure control output to the pitot tube, and the barometric altimeter senses the pressure received by the pitot tube, and feeds back the altitude and speed information of the aircraft to the pitot tube. Computer, the computer judges whether there is pitot tube pollution, blockage, and the connecting tube between the barometric altimeter and the pitot tube based on the altitude pressure control output, speed pressure control output, and aircraft altitude and speed information generated by the pressure source. Road leaks.

Wherein, as shown in Figure 1, the pressure source includes: a first gas storage tank, an oil-free vacuum pump connected to the first gas storage tank and a first quick-opening valve; a second gas storage tank, and an oil-free vacuum pump connected to the second gas storage tank; Oil-free compression pump and the second quick-opening valve; a static pressure sensor is set on the first quick-opening valve, and a total pressure sensor is set on the second quick-opening valve; the first quick-opening valve is connected to the altitude pressure control output, and the second quick-opening valve is connected to Speed and pressure control output; the control unit is connected to the static pressure sensor and the total pressure sensor. The control unit receives the external program control command or the control command of the panel, converts the command parameters into the pressure control voltage, and then adds them to the total pressure sensor and the static pressure sensor respectively. , the total pressure sensor and the static pressure sensor act on the corresponding quick-opening valve after forming the control voltage respectively, and connect the external output of the second gas storage tank and the first gas storage tank respectively. When the output pressure reaches the command voltage, The quick-opening valve is closed, and when the pressure deviates, the quick-opening valve is opened for air supply operation.

In the pressure source structure, under the excitation of the external power supply, the oil-free vacuum pump and the oil-free compression pump work to respectively perform negative pressure and positive pressure operations on the first air storage tank and the second air storage tank.

As long as the pressure source is within the performance range of the two vacuum pumps, it can meet the requirement of dynamically controlling the stable output pressure within a specified time.

In this embodiment, both the altitude pressure control output and the speed pressure control output are in the form of sine wave curves, or in the form of climbing, level flight and glide curves with constant slopes.

In combination with the above-mentioned system, the barometric altimeter basic-level dynamic detection method of the present invention, the process is that the pressure source provides the altitude pressure control output and the speed pressure control output to the aircraft pitot tube according to the preset control curve, and the data information sensed by the barometric altimeter Feedback to the computer, the computer judges whether the pitot tube of the aircraft is polluted, blocked, or there is air leakage in the connecting pipeline between the barometric altimeter and the pitot tube according to the control curve and the received data information.

Specifically, graph a in Figure 2 is the mission control curve. In theory, the pressure source provides altitude pressure control output to the barometric altimeter according to the planning of the curve, that is, the process of climb, level flight, and descent. The curve in Figure b is a schematic diagram of the combination of the control curve and the return value of the measured object. In the figure, the solid line curve is the same as that in Figure a, and the dotted line curve is the height data returned by the measured object. It can be seen from the comparison that the dotted line curve is parallel to the solid line curve in the climb and glide sections, and there is a certain phase difference, and they are almost coincident in the level flight section.

The pressure output by the pressure source is balanced by a long pipeline to produce a phase delay, and the sensor can correctly sense the external pressure change. Such a combination figure shows that the sensor, pitot tube and pipeline of the barometric altimeter are all in the correct state.

If there is an air leak in the pipeline, as shown in Figure 3 a, the phase of the data curve and the control curve of the aircraft during the climb and glide sections is inconsistent. Passive change, so the phase of the dotted line curve lags behind the solid line curve; and in the downhill section, if there is an air leak in the pipeline, the pressure in the confined space will return to normal pressure faster, showing that the phase of the dotted line curve is ahead of the solid line curve . If the air pressure hole of the pitot tube is blocked, as shown in Figure 3 b, the climb rate felt by the aircraft during the climb section is lower than the control rate, which means that the rising slope of the dotted curve is lower than the rising slope of the realized curve.

The above is the climb, level flight, and glide curves with constant slope as an example. The judgment process of changing the control curve to a sinusoidal curve is similar, so I won’t repeat it here.

It can be seen from the above technical solution that the present invention not only has the function of performing altitude/Mach number static fixed-point test on the barometric altimeter by improving the design of the external pressure source, but also has the ability to refresh the output pressure value in a short period in real time , to realize the dynamic test function of simulating the flight pressure environment of the aircraft, to make up for the shortcomings of traditional test methods, and to expand the detection coverage of the barometric altimeter to ensure the safety of the aircraft.

The above is only a preferred embodiment of the present invention, it should be pointed out that for those of ordinary skill in the art, without departing from the technical principle of the present invention, some improvements and modifications can also be made. It should also be regarded as the protection scope of the present invention.

Claims (8)

1. A kind of 1. pressure altimeter base level dynamic detection system, it is characterised in that including：Measurand, pressure source and calculating Machine；Measurand includes aircraft, and aircraft is provided with pressure altimeter, and pressure altimeter connects air speed by connecting line Pipe；Pressure source produces high stress control output and pressure and speed control is exported to pitot, pressure altimeter sensing pitot The pressure received, and the height of aircraft and velocity information are fed back into computer, computer is high according to caused by pressure source It is consistent whether the height of the output of degree Stress control, pressure and speed control output and aircraft corresponds to velocity information, and judgement is It is no exist pitot pollution, obstruction, between pressure altimeter and pitot connecting line gas leakage situation.
2. 2. pressure altimeter base level dynamic detection system as claimed in claim 1, it is characterised in that the pressure source bag Include：First air accumulator, and the oilless vacuum pump and the first quck-opening valve of the first air accumulator of connection；Second air accumulator, and connection The oil free compression pump and the second quck-opening valve of second air accumulator；Static pressure transducer is set on the first quck-opening valve, set on the second quck-opening valve Put total head sensor；The connection high stress control output of first quck-opening valve, the output of the second quck-opening valve connection speed Stress control；Control Unit processed, static pressure transducer and total head sensor are connected, control unit receives this control instruction of outside program control command or panel, will Order parameter conversion is to be added separately on total head sensor and static pressure transducer after Stress control voltage, by total head sensor and quiet Pressure sensor is applied to after control voltage is formed respectively on corresponding quck-opening valve, is respectively turned on the second air accumulator and the first gas storage The external output of tank, when output pressure reaches command voltage, quck-opening valve is closed, and when pressure shifts, quck-opening valve is opened Carry out tonifying Qi operation.
3. 3. pressure altimeter base level dynamic detection system as claimed in claim 2, it is characterised in that in the pressure source, Under the excitation of external power source, oilless vacuum pump and oil free compression pump work, enter respectively to the first air accumulator and the second air accumulator Row takes out negative pressure and beats positive pressure operation.
4. 4. pressure altimeter base level dynamic detection system as claimed in claim 2, it is characterised in that the high stress control System output and pressure and speed control output are sine wave curve form, or for the climbing of constant-slope, it is flat fly, glide Form.
5. 5. a kind of pressure altimeter base level dynamic testing method, its spy is just that the control method is based on claim 2 institute The detecting system stated is carried out, pressure source according to default controlling curve to aircraft airspeed pipe provide high stress control output and Pressure and speed control exports, and the data message of pressure altimeter sensing feeds back to computer, and computer is according to controlling curve and connects The data message received, judge that the pitot of aircraft connects with the presence or absence of between pollution, obstruction, pressure altimeter and pitot The situation of pipeline gas leakage.
6. 6. pressure altimeter base level dynamic detection system as claimed in claim 5, it is characterised in that the controlling curve is The climbing of sine wave curve or constant-slope, it is flat fly, glide.
7. 7. pressure altimeter base level dynamic detection system as claimed in claim 6, it is characterised in that the controlling curve is The climbing of constant-slope, it is flat fly, glide when, aircraft is climbing in section of climbing with downslide segment data curve and controlling curve Equal and phase is consistent with downslide segment data, and flat winged section curve co-insides, then illustrate sensor, the pitot of pressure altimeter with And the equal state of pipeline is correct；Otherwise, then illustrate that the sensor, pitot or pipeline state of pressure altimeter are abnormal.
8. 8. pressure altimeter base level dynamic detection system as claimed in claim 7, it is characterised in that the controlling curve is The climbing of constant-slope, it is flat fly, glide when, aircraft climb section and downslide segment data curve with controlling curve phase not Unanimously, if the phase for the segment data curve that climbs lags behind controlling curve, and downslide segment data curve phase shifts to an earlier date in controlling curve, Then illustrate pipeline gas leakage；If the rate of rise of segment data of climbing curve is less than the rate of rise of controlling curve, and downslide segment data The rate of rise of curve is less than the rate of rise of controlling curve, then illustrates that the pressure hole of pitot has congestion situations.