A drag cone system delay test device and method

Abstract

The application provides a drag cone system delay test device and method, which comprises pressure sensor A and pressure sensor B for detecting the pressure at the end of the static pressure measuring tube and the static pressure hole respectively, the pressure sensor A and the pressure sensor B are connected with a data acquisition and recorder respectively, and a pressure control device is arranged at the static pressure hole; a target air pressure height and a change rate are set through the pressure control device, the pressure control device adjusts the air pressure in the drag cone system at the set change rate after the pressure control device is started, at this time, the pressure sensor A and the pressure sensor B measure the current pressure in the pipeline in real time and send to the data acquisition and recorder, and the delay time of the drag cone system can be obtained by analyzing the data collected and recorded by the two sensors. The application is convenient to operate, the method is reasonable, the result is intuitive and accurate, and the delay of the drag cone system when the airplane climbs or descends at different rates at different air pressure heights can be simulated and measured in one test.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of flight test, in particular to a drag cone system delay test device and method. BACKGROUND

[0002] Static pressure is a key parameter for calculating the flight height and speed of an aircraft. In the flight test of airspeed calibration, stall speed, flight thrust determination, RVSM and other subjects, a drag cone system is often used to introduce a static pressure source away from the fuselage and not affected by the airflow disturbance of the aircraft to the cabin for measurement.

[0003] The drag cone static pressure method has the characteristics of high measurement accuracy, no airspace restriction, high take-off and landing success rate of flight test, and good data regularity. However, the length of the drag cone system pipeline is generally more than several dozen meters. Due to the viscosity of gas, there is a delay when the air pressure is conducted from one end of the static pressure hole to the sensor at the other end. Especially when the aircraft climbs or descends at different rates at different air pressure altitudes, the delay is different, causing reference static pressure delay error. In order to correct the delay error, the drag cone system needs to carry out delay test before use to determine the delay time.

[0004] Traditionally, the method of vacuum extraction is often used to determine the delay time of the drag cone system, that is, the pressure in the drag cone pipeline is extracted to a certain vacuum degree from the static pressure hole by a vacuum pump, and a certain pressure difference Δp is formed with the outside atmosphere. After the pressure is stable, the pressure at the static pressure hole is released instantaneously, and the time difference used by the pressure values of the sensors at both ends to return to atmospheric pressure is recorded and compared, which is the delay time corresponding to the pressure difference Δp. Repeat the test multiple times to measure the delay time corresponding to different pressure differences. Through multiple point fitting, the delay time when the pressure difference is zero can be obtained, which is considered as the delay time of the drag cone system.

[0005] This method needs to repeat the test multiple times to measure the delay time corresponding to different pressure differences, and through multiple point fitting, the delay time when the pressure difference is zero is obtained. The test process of this method is complicated, and the error of reading the delay time is large each time, which cannot simulate the delay time when the aircraft climbs or descends at different rates at different air pressure altitudes in a single test. SUMMARY

[0006] The purpose of the present application is to solve the above problems and provide a drag cone system delay test device and method for measuring the delay of the drag cone system in the flight test process.

[0007] The present application provides a drag cone system delay test device, which comprises a pressure sensor A for detecting the pressure at the end of the static pressure measurement pipe and a pressure sensor B for detecting the pressure at the static pressure hole on the static pressure measurement pipe. The pressure sensor A and the pressure sensor B are respectively connected with a data acquisition and recorder, and a pressure control device is arranged at the static pressure hole.

[0008] Further, the static pressure measuring tube is provided with an airtight clamp covering the static pressure hole at a position close to the static pressure hole.

[0009] Further, the airtight clamp, the pressure sensor B and the pressure control device are connected through a tee pipe.

[0010] Further, the end of the static pressure measuring tube is connected with the pressure sensor A through a straight pipe.

[0011] Further, the pressure sensor A and the pressure sensor B are respectively connected with the data acquisition and recorder through sensor cables.

[0012] The present application also provides a drag cone system delay test method. During the test, the target air pressure height and the change rate are set by the pressure control device, and the different climbing rates or descending rates of the airplane are simulated by the change rate. After the pressure control device is started, the pressure control device adjusts the air pressure in the drag cone system to the target air pressure height at the set change rate. At this time, the pressure sensor A and the pressure sensor B measure the current pressure in the pipe in real time and send it to the data acquisition and recorder. By analyzing the data collected and recorded by the two sensors, the delay time of the drag cone system can be obtained.

[0013] Further, the air pressure is adjusted by the pressure control device multiple times in a single test to simulate the climbing or descending of the airplane at different rates at different air pressure heights.

[0014] The present application is easy to operate, the measurement method is scientific and reasonable, the measurement result is intuitive and accurate, and the delay of the drag cone system when the airplane climbs or descends at different rates at different air pressure heights can be simulated and measured in one test. The traditional method of vacuum extraction to a set value, release from the static pressure hole and then vacuum extraction again is effectively replaced, and the result can be obtained without complex data analysis. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed in the specific embodiments or the prior art description will be briefly introduced. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0016] Figure 1 The present application is a structural schematic diagram;

[0017] Explanation of reference signs:

[0018] In the figure: 1-pressure sensor A, 2-data acquisition and recorder, 3-sensor cable, 4-pressure sensor B, 5-pressure control device, 6-three-way pipeline, 7-static pressure measuring tube, 8-airtight clamp, 9-straight pipeline; DETAILED DESCRIPTION

[0019] The technical solutions of the present application will be clearly and completely described below in combination with the embodiments. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0020] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0021] In addition, the terms "first", "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise specifically limited. In addition, the terms "mounting", "connecting", "connecting" should be broadly understood, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0022] Embodiment 1

[0023] As Figure 1 shown:

[0024] A drag cone system delay test device, comprising a pressure sensor A1 for detecting the pressure at the end of the static pressure measuring tube 7 and a pressure sensor B4 for detecting the pressure at the static pressure hole of the static pressure measuring tube 7, the pressure sensor A1 and the pressure sensor B4 are connected with the data acquisition and recorder 2 respectively, and the static pressure hole is also provided with a pressure control device 5.

[0025] The pressure control device 5 in the embodiment is composed of common pressure controller and air pump and the like, and realizes the adjustment of the pressure at the static pressure hole, which is not described in detail here.

[0026] The static pressure measuring pipe 7 is provided with an airtight clamp 8 covering the static pressure hole at a position close to the static pressure hole.

[0027] The airtight clamp 8, the pressure sensor B4 and the pressure control device 5 are connected through the three-way pipe 6.

[0028] The end of the static pressure measuring pipe 7 is connected with the pressure sensor A1 through the straight-through pipe 9.

[0029] The pressure sensor A1 and the pressure sensor B4 are respectively electrically connected with the data acquisition and recorder 2 through the sensor cable 3.

[0030] The tow cone system in the embodiment includes the static pressure measuring pipe 7 and a tail cone body at the rear end of the static pressure measuring pipe 7.

[0031] The present application also provides a tow cone system delay test method, in which the target air pressure height and the change rate are set through the pressure control device 5, the pressure control device 5 adjusts the air pressure in the static pressure measuring pipe 7 of the tow cone system at the set change rate after being started, the pressure sensor A1 and the pressure sensor B4 measure the current pressure in the static pressure measuring pipe 7 in real time and send to the data acquisition and recorder 2 at this time, since the pressure sensor A1 and the pressure sensor B4 are respectively installed at two positions far away from each other on the static pressure measuring pipe 7, there is a delay in the conduction of the pressure from one end to the other end, and the delay time of the tow cone system can be obtained by analyzing the data collected and recorded by the two sensors.

[0032] All target air pressures are adjusted in turn in a single test, and finally released from the static pressure hole.

[0033] The present application is convenient to operate, different target air pressure heights and change rates can be set through the pressure control device, the working conditions of the aircraft when climbing or descending at different rates at different air pressure heights can be truly simulated, the pressure in the tow cone system is measured in real time through the two pressure sensors, the delay of the tow cone system in the whole flight profile can be simulated and measured in one test, effectively replacing the traditional method of vacuum extraction to a set value, release from the static pressure hole and then vacuum extraction again; the measurement method is scientific and reasonable, the measurement result is intuitive and accurate, and the result can be obtained without complex data analysis.

[0034] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, and are not intended to limit the present application; although the present application has been described in detail with reference to the above embodiments, those skilled in the art should understand that the technical solutions recorded in the above embodiments can be modified, or some or all of the technical features can be replaced by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. A time delay test device for a drag cone system, characterized in that: It includes a pressure sensor A for detecting the pressure at the end of the static pressure measuring tube and a pressure sensor B for detecting the pressure at the static pressure hole on the static pressure measuring tube. The pressure sensor A and the pressure sensor B are respectively connected to a data acquisition and recorder. A pressure control device is also provided at the static pressure hole, which is used to adjust the pressure at the static pressure hole. In a single test, the pressure control equipment repeatedly adjusted the air pressure to simulate the aircraft climbing or descending at different rates at different air pressure altitudes.

2. The delay test device for a towing cone system according to claim 1, characterized in that: An airtight clamp covering the static pressure hole is installed on the static pressure measuring tube near the static pressure hole.

3. The delay test device for a towing cone system according to claim 2, characterized in that: The airtight clamp, the pressure sensor B, and the pressure control device are connected via a three-way pipe.

4. The delay test device for a towing cone system according to claim 1, characterized in that: The end of the static pressure measuring tube is connected to the pressure sensor A via a straight pipe.

5. The delay test device for a towing cone system according to claim 1, characterized in that: The pressure sensor A and the pressure sensor B are respectively connected to the data acquisition and recorder via sensor cables.

6. A time delay test method for a drag cone system, characterized in that: During the test, the target air pressure altitude and rate of change were set through the pressure control device. The rate of change was used to simulate different climb or descent rates of the aircraft. The pressure control device was used to adjust the pressure at the static pressure orifice. After the pressure control device was activated, it adjusted the air pressure in the tow cone system to the target air pressure altitude according to the set rate of change. At this time, pressure sensor A and pressure sensor B measured the current pressure in the pipeline in real time and sent it to the data acquisition and recorder. By analyzing the data collected and recorded by the two sensors, the delay time of the tow cone system could be obtained. In a single test, the pressure control equipment repeatedly adjusted the air pressure to simulate the aircraft climbing or descending at different rates at different air pressure altitudes.

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