Airborne atmospheric parameter measuring device

Abstract

The utility model discloses an airborne atmospheric parameter measuring device which comprises an airspeed tube, a differential pressure sensor chamber, a main control chamber, an attitude chamber and a wake flow chamber, the end face of the airspeed tube is provided with a plurality of front pressure holes, and the side edge of the airspeed tube is provided with a plurality of first side static pressure holes. A plurality of second lateral static pressure holes are formed in the surface of the differential pressure sensor cavity, a differential pressure sensor is installed in the differential pressure sensor cavity, and a temperature and humidity sensor is installed in the wake flow cavity. According to the utility model, the three-dimensional wind speed measured by the five-hole wind measurement probe adopting the differential pressure wind measurement principle in the air can be corrected, and the true value measurement of the three-dimensional wind direction and wind speed in a high-altitude atmospheric wind field is realized.

Description

TECHNICAL FIELD

[0001] The utility model belongs to atmospheric parameter measurement technical field, concretely relates to a kind of airborne atmospheric parameter measuring device. BACKGROUND

[0002] In the field of high-altitude meteorological detection, aircraft carries meteorological equipment to measure high-altitude atmospheric parameters, which is an important observation method. Although traditional radar and radiosonde observation plays an important role in meteorological detection, aircraft detection can provide more real-time and accurate high-altitude atmospheric data, which is of great significance for flight safety, meteorological research and weather modification operations. However, at present, China mainly relies on imports in airborne atmospheric parameter measurement equipment, and multi-parameter observation equipment is scattered, which meets the increasing demand for meteorological detection. Therefore, a comprehensive airborne atmospheric parameter measurement system is designed, which is fully autonomous and localized, and integrates multiple observation elements.

[0003] Therefore, the utility model is proposed. CONTENT OF UTILITY MODEL

[0004] To solve the above technical problems, the basic idea of the technical solution of the utility model is as follows:

[0005] The high-speed response temperature and humidity sensor is built-in in the designed micro wake effect cavity to realize accurate measurement of high-altitude temperature and humidity. At the same time, the three-dimensional wind speed measured by the five-hole wind probe using differential pressure measurement principle in high-altitude atmosphere is corrected by using built-in GNSS and attitude fusion technology, to realize true value measurement of three-dimensional wind direction and speed in high-altitude atmospheric wind field.

[0006] An airborne atmospheric parameter measuring device includes an airspeed tube 1, a differential pressure sensor chamber 2, a main control chamber 3, an attitude chamber 4 and a wake cavity 5. The end surface of the airspeed tube 1 is provided with a plurality of front pressure holes 11, and the side edge of the airspeed tube 1 is provided with a plurality of first side static pressure holes 12. The surface of the differential pressure sensor chamber 2 is provided with a plurality of second side static pressure holes 21. The differential pressure sensor is installed inside the differential pressure sensor chamber 2. The wake cavity 5 is closed and installed to form an internal space by installing a base 51 and a fairing 52. The internal space is installed with a temperature and humidity sensor 53. The temperature and humidity sensor 53 is provided with a breathable protective sleeve 54 outside.

[0007] The wake cavity 5 is closed and installed to form an internal space by installing a base 51 and a fairing 52. The internal space is installed with a temperature and humidity sensor 53. The temperature and humidity sensor 53 is provided with a breathable protective sleeve 54 outside.

[0008] The main control chamber 3 and the attitude chamber 4 are used to place and install integrated circuit boards.

[0009] Compared with the prior art, the utility model has the following beneficial effects:

[0010] The utility model discloses a three-dimensional wind speed correction device for high-altitude wind field measurement.

[0011] The utility model discloses a three-dimensional wind speed correction device for high-altitude wind field measurement. BRIEF DESCRIPTION OF DRAWINGS

[0012] In the drawings:

[0013] Fig. 1 For the utility model structure schematic drawing;

[0014] Fig. 2 For the utility model another direction schematic drawing;

[0015] Fig. 3 For the utility model local area exploded view.

[0016] In the drawings: 1, air speed pipe;2, differential pressure sensor chamber;3, main control chamber;4, attitude chamber;5, wake chamber;11, front pressure hole;12, first side static pressure hole;21, second side static pressure hole;51, mounting base;52, fairing;53, temperature and humidity sensor;54, breathable protective sleeve;521, inclined air hole. DETAILED DESCRIPTION

[0017] In order to make the utility model embodiment's purpose, technical scheme and advantage more clear, below will combine the drawings in the utility model embodiment, to the technical scheme in the embodiment, clear, complete description, following embodiment is used to explain the utility model.

[0018] As Figs. 1 to 3 Indicated, the temperature and humidity measurement system of the patent application design is based on the wake effect, and the inclined air hole 521 hydrophobic structure on the surface of the fairing 52 is combined with the low hysteresis and condensation-proof temperature and humidity sensor 53, which is an air temperature and humidity measurement device, which can stably and accurately measure the air temperature and humidity. P 1 When the sensor is in flight, high-speed airflow will flow over the surface of the fairing 52, and the surface pressure P 2> P 1The reverse flow effect is generated. Based on this principle, the flow interaction between the atmosphere and the sensitive element can be realized, so as to accurately measure the current atmospheric temperature and humidity. However, due to the high water vapor content in high altitude flight, especially the aircraft often in and out of the clouds, a large amount of liquid water will enter the inside of the temperature and humidity sensor 53, which will cause the sensor to be corroded and damaged for a long time, so the hydrophobic structure design is needed. By using the reverse flow and the gravity of liquid water, by increasing the inclined air hole on the fairing 52, the reverse backflow caused by turbulence can be prevented, and the drainage and ventilation function can also be realized.

[0019] The pressure difference between the front pressure hole 11 and the first side static pressure hole 12 and the second side static pressure hole 21 is measured, and the airspeed tube 1 (i.e. probe) is calibrated by the wind tunnel, and then the relative three-dimensional wind direction and wind speed are calculated by using the pressure difference and the probe calibration data. Through the real-time attitude revision of the relative three-dimensional wind measurement by the attitude inertial navigation data, the error caused by the flight attitude is eliminated, and the final relative earth coordinate system three-dimensional true wind is obtained.

[0020] When measuring high altitude wind, real-time high frequency attitude data and GNSS data acquisition are needed, and the pitch angle, roll angle and heading angle are used to calculate the relative three-dimensional wind of the five front pressure holes 11 V x ，V y ，V z The space correction is performed to obtain V x ’，V y ’，V z ’ The wind data in the unified three-dimensional space is ensured to be accurately obtained. The northward, eastward and upward velocities measured by the GNSS are relative to the three-dimensional space V x ’，V y ’，V z ’ Difference is made.

Claims

1. An airborne atmospheric parameter measuring device, characterized by, The utility model relates to an air speed tube (1), a differential pressure sensor chamber (2), a main control chamber (3), a posture chamber (4) and a wake chamber (5), the end face of air speed tube (1) is equipped with a plurality of front pressure holes (11), and the side of air speed tube (1) is equipped with a plurality of first side static pressure holes (12), the surface of differential pressure sensor chamber (2) is equipped with a plurality of second side static pressure holes (21), differential pressure sensor is installed inside differential pressure sensor chamber (2), and the inside of wake chamber (5) is installed with temperature and humidity sensor (53).

2. An airborne atmospheric parameter measuring apparatus according to claim 1, characterized by The wake chamber (5) is closed and installed to form an internal space through the mounting base (51) and the flow guide cover (52), and the temperature and humidity sensor (53) is installed inside, and the temperature and humidity sensor (53) is provided with the breathable protective sleeve (54) outside.

3. An airborne atmospheric parameter measuring apparatus according to claim 2, characterized in that, The surface of the flow guide cover (52) is provided with a plurality of wake chambers (5).

4. An airborne atmospheric parameter measuring apparatus according to claim 3, characterized by The number of front pressure holes (11) is 5.

5. An airborne atmospheric parameter measuring apparatus according to claim 4, characterized by The main control chamber (3) and the posture chamber (4) are used to place and install the integrated circuit board.

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