Helicopter distributed three-axis atmosphere data measuring device

Abstract

The invention belongs to the technical field of atmosphere data detection, and particularly discloses a helicopter distributed three-axis atmosphere data measuring device which comprises a left three-axis atmosphere measuring assembly and a right three-axis atmosphere measuring assembly which are installed on the two sides of a nose and are the same in structure. Each airspeed tube consists of a rotary airspeed tube and an electronic component; the rotary airspeed tube and the electronic component are electrically connected through the fuselage skin opening; the rotating airspeed tubes are mounted outside skins on two sides of the machine head and used for sensing total pressure, static pressure, local attack angle and local sideslip angle of the synthetic gas flow in real time; the electronic component is arranged in the machine head skin and used for collecting the total pressure, the static pressure, the local attack angle, the local sideslip angle and the atmospheric temperature of the synthetic gas flow, conducting parameter calculation and outputting atmospheric parameters. According to the invention, the problem that a centralized atmosphere data system, a distributed atmosphere data system and a three-axis atmosphere data system have different restrictions on the use of a helicopter at present is solved.

Description

Technical Field

[0001] The invention belongs to the technical field of atmospheric data detection, and in particular relates to a distributed three-axis atmospheric data measuring device for a helicopter. Background Art

[0002] Helicopters have many flight states, generally including hovering, level flight, climb / descent, sideslip, side flight, and backward flight. In different flight states, the coupling state of the rotor airflow and the flight airflow is also different. Combined with the influence of the fuselage, the flow field near the fuselage becomes complex and changeable, which brings great difficulties to atmospheric data detection.

[0003] The atmospheric data detection methods currently used by helicopters include: centralized atmospheric data system, distributed atmospheric data system and three-axis atmospheric data system, but all of them have different limitations and problems for helicopter use.

[0004] The centralized atmospheric data system, consisting of a pitot tube, static pressure holes, an atmospheric data computer, and a temperature sensor, cannot measure the helicopter's angle of attack and sideslip angle. When the helicopter is operating at low speed, affected by the rotor airflow, the local airflow angle of the pitot tube is very large, resulting in serious dynamic pressure loss. Therefore, airspeed measurement cannot be achieved at low speeds (below 50km / h).

[0005] The distributed air data system, consisting of a left distributed air compressor, a right distributed air compressor, and a temperature sensor, integrates the pitot tube, static pressure port, and air data computer. By integrating the left and right components, the system addresses the dynamic pressure loss caused by fuselage obstruction during sideslip flight. Similar to the limitations of the integrated air data system, the distributed air data system cannot measure angle of attack and sideslip angle, and cannot measure airspeed at low speeds (below 50 km / h).

[0006] The three-axis air data system (ADS) is an air data detection method specifically designed for helicopters. It consists of a velocity vector sensor, a vector sensor mounting bracket, and a three-axis ADS computer. The ADS uses a rotating pitot tube to address the problem of large local airflow angles caused by rotor airflow, enabling airspeed measurement at low speeds. The velocity vector sensor measures both air pressure intensity and airflow angle, enabling angle of attack and sideslip measurements. To ensure the velocity vector sensor's sensing, the ADS uses a vector sensor mounting bracket that extends a certain distance from the fuselage. To ensure strength, the mounting bracket is heavy and bulky, resulting in high aerodynamic drag, making it unsuitable for high-speed helicopters. When the velocity vector sensor is mounted on one side, the local airflow is blocked by the fuselage during sideslip flight, resulting in poor measurement quality. Summary of the Invention

[0007] The purpose of the present invention is to solve the problem that the centralized air data system, distributed air data system and three-axis air data system currently used in helicopters have different limitations, and proposes a helicopter distributed three-axis air data measurement device.

[0008] The technical solution of the present invention is: a distributed three-axis atmospheric data measurement device for a helicopter, comprising: a left three-axis atmospheric measurement assembly and a right three-axis atmospheric measurement assembly installed on both sides of the nose of the helicopter, the left three-axis atmospheric measurement assembly and the right three-axis atmospheric measurement assembly having the same structure, both consisting of a rotating pitot tube and electronic components; the rotating pitot tube and the electronic components are electrically connected through openings in the fuselage skin; The rotating pitot tube is installed on the outside of the nose skin and is used to sense the total pressure, static pressure, local angle of attack and local sideslip angle of the synthetic airflow in real time; The electronic components are built into the nose skin and are used to collect the total pressure, static pressure, local angle of attack, local sideslip angle and atmospheric temperature of the synthetic airflow, perform parameter calculations, and output atmospheric parameters.

[0009] Preferably, the rotating pitot tube includes a straight tube, a tail fin, a first rotating shaft and a second rotating shaft; The first rotating axis and the second rotating axis adopt an orthogonal nested design, one end of the first rotating axis is connected to the second rotating axis, and the other end of the first rotating axis is connected to the base, and the base is fixed to the nose skin; the second rotating axis is set in the middle of the straight tube; the tail wing is set at one end of the straight tube.

[0010] Preferably, the straight pipe is used to sense the total pressure and static pressure and transmit them to the electronic components; The tail wing is used to provide aerodynamic force for the rotating pitot tube, so that the rotating pitot tube can rotate freely with the synthetic airflow; The first rotation axis is used to sense the local angle of attack and transmit it to the electronic component. The first rotation axis allows the rotating pitot tube to rotate in the pitch direction; The second rotating shaft is used to sense the local sideslip angle and transmit it to the electronic component. The second rotating shaft allows the rotating pitot tube to rotate in the yaw direction; The second rotating shaft is used to sense the local sideslip angle and transmit it to the electronic component. The second rotating shaft allows the rotating pitot tube to rotate in the yaw direction.

[0011] Preferably, a temperature sensor is provided on the base for measuring the atmospheric temperature; the temperature sensor is communicatively connected with the electronic component.

[0012] Preferably, the electronic components include an air pressure sensor, an angle sensor and an electronic circuit unit; The air pressure sensor is used to measure total pressure and static pressure; The angle sensor measures the rotation angle of the first rotation axis to obtain the local angle of attack in real time, and measures the rotation angle of the second rotation axis to obtain the local sideslip angle in real time; The electronic circuit unit is used to receive total pressure, static pressure, local angle of attack, local angle of sideslip and atmospheric temperature, and process the total pressure, static pressure, local angle of attack, local angle of sideslip and atmospheric temperature to output atmospheric parameters.

[0013] Preferably, the left three-axis atmospheric measurement component and the right three-axis atmospheric measurement component are communicatively connected to perform data exchange, complete left and right data fusion, and eliminate the asymmetric effect of the layout on both sides of the fuselage.

[0014] Preferably, the synthetic airflow includes flight airflow and rotor airflow.

[0015] Preferably, the atmospheric parameters include pressure altitude, indicated airspeed, longitudinal true airspeed, lateral true airspeed, vertical true airspeed, angle of attack and sideslip angle.

[0016] The beneficial effects of the present invention are: 1. Compared with traditional three-axis atmospheric velocity vector sensors, the rotating pitot tube proposed in this invention has a volume reduced by more than 50%, achieving a compact design. The distributed three-axis atmospheric measurement assembly, consisting of a small rotating pitot tube and electronic components, integrates the sensing and measurement of static pressure, total pressure, local angle of attack, local sideslip angle, and atmospheric temperature, enabling low-speed airspeed measurement, angle of attack, and sideslip angle measurement.

[0017] 2. The present invention uses a small-volume rotating pitot tube design and is installed close to the skin, avoiding the weight and aerodynamic drag problems caused by a large-volume mounting frame, and improving the adaptability of the distributed three-axis atmospheric measurement method.

[0018] 3. The three-axis atmospheric measurement assembly with a left-right distributed layout proposed in the present invention eliminates the left-right asymmetry caused by the fuselage through left-right data fusion, solves the problem of fuselage obstruction during sideslip flight, and improves the atmospheric data measurement capability. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 Shown is a schematic structural diagram of the left three-axis atmospheric measurement component and the right three-axis atmospheric measurement component.

[0020] Figure 2 Shown is a schematic diagram of the composition of a rotating pitot tube.

[0021] Figure 3 Shown is a schematic diagram of the onboard layout of the helicopter's distributed three-axis atmospheric data measurement device.

[0022] Explanation of reference numerals: 1—left three-axis atmospheric measurement assembly, 2—right three-axis atmospheric measurement assembly, 3—rotating pitot tube, 4—electronic component, 31—straight tube, 32—tail, 33—first rotating axis, 34—second rotating axis, 5—base, 6—temperature sensor. DETAILED DESCRIPTION

[0023] The exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be understood that the embodiments shown and described in the accompanying drawings are merely exemplary and are intended to illustrate the principles and spirit of the present invention, rather than to limit the scope of the present invention.

[0024] Example 1: like Figure 1 、 Figure 2 and Figure 3 As shown, a distributed three-axis atmospheric data measurement device for a helicopter includes: a left three-axis atmospheric measurement component 1 and a right three-axis atmospheric measurement component 2 installed on both sides of the nose, Figure 3 The black part in the middle is the nose. The left three-axis atmospheric measurement assembly 1 and the right three-axis atmospheric measurement assembly 2 have the same structure, both consisting of a rotating pitot tube 3 and an electronic component 4. The rotating pitot tube 3 and the electronic component 4 are electrically connected through an opening in the fuselage skin. Figure 1 The yellow part in the middle is the rotating pitot tube 3, and the blue part is the electronic component 4; The rotating pitot tube 3 is installed on the outside of the nose skin and is used to sense the total pressure, static pressure, local angle of attack and local sideslip angle of the synthetic airflow in real time; The electronic component 4 is built into the nose skin and is used to collect the total pressure, static pressure, local angle of attack, local sideslip angle and atmospheric temperature of the synthetic airflow, perform parameter calculations, and output atmospheric parameters; the synthetic airflow includes flight airflow and rotor airflow.

[0025] In this embodiment, the rotating pitot tube 3 includes a straight tube 31, a tail wing 32, a first rotating shaft 33 and a second rotating shaft 34; The first rotating shaft 33 and the second rotating shaft 34 adopt an orthogonal nested design, one end of the first rotating shaft 33 is connected to the second rotating shaft 34, and the other end of the first rotating shaft 33 is connected to the base 5, and the base 5 is fixed to the nose skin; the second rotating shaft 34 is arranged in the middle of the straight tube 31; the tail wing 32 is arranged at one end of the straight tube 31.

[0026] The rotating pitot tube 3 features a compact design, reducing its volume by over 50% compared to conventional three-axis atmospheric velocity vector sensors. While existing three-axis mounting brackets are over 1 meter long, the present invention's is no longer than 0.3 meters. The exposed portions of the rotating pitot tube 3, including the straight tube 31, tail fin 32, first rotating shaft 33, and second rotating shaft 34, are mounted close to the nose skin to minimize aerodynamic drag.

[0027] In this embodiment, the straight pipe 31 is used to sense the total pressure and static pressure and transmit them to the electronic component 4; The tail wing 32 is used to provide aerodynamic force for the rotating pitot tube 3, so that the rotating pitot tube 3 can rotate freely with the synthetic airflow; The first rotating shaft 33 is used to sense the local angle of attack and transmit it to the electronic component 4; The second rotating shaft 34 is used to sense the local sideslip angle and transmit it to the electronic component 4; As the rotating pitot tube 3 rotates freely with the airflow, powered by the aerodynamic force provided by the tail fin 32, the first rotation axis 33 and the second rotation axis 34 decompose the airflow direction into two orthogonal angular components. The first rotation axis 33 allows the rotating pitot tube 3 to rotate in the pitch direction, while the second rotation axis 34 allows the rotating pitot tube 3 to rotate in the yaw direction.

[0028] In this embodiment, a temperature sensor 6 is provided on the base 5 for measuring the atmospheric temperature; the temperature sensor 6 is in communication connection with the electronic component 4; and the temperature sensor is a platinum resistance temperature sensor.

[0029] In this embodiment, the electronic component 4 includes an air pressure sensor, an angle sensor and an electronic circuit unit; The air pressure sensor adopts a silicon resonant pressure sensor or a vibrating cylinder pressure sensor to measure total pressure and static pressure; The angle sensor uses a high-precision sine-cosine transformer or a Hall-type angular displacement sensor to measure the local angle of attack and the local sideslip angle. The local angle of attack is obtained in real time through the rotation angle of the first rotating shaft 33; the local sideslip angle is obtained in real time through the rotation angle of the second rotating shaft 34. The electronic circuit unit includes a voltage, a CPU, and a memory chip, and is used to receive total pressure, static pressure, local angle of attack, local angle of sideslip, and atmospheric temperature, and to calculate and output atmospheric parameters such as pressure altitude, indicated airspeed, longitudinal true airspeed, lateral true airspeed, vertical true airspeed, angle of attack, and sideslip angle based on the total pressure, static pressure, local angle of attack, local angle of sideslip, and atmospheric temperature.

[0030] In this embodiment, the left three-axis atmospheric measurement component 1 and the right three-axis atmospheric measurement component 2 are communicatively connected to exchange data, and the static pressure data on both sides are corrected or averaged to complete the left and right data fusion, eliminate the asymmetric effect caused by the layout on both sides of the fuselage, solve the problem of fuselage obstruction during sideslip flight, and improve the measurement capability of atmospheric data.

[0031] The distributed three-axis helicopter air data measurement device proposed in this invention uses rotating pitot tubes installed on either side of the nose to sense the combined airflow of flight and rotor airflow, enabling low-speed airspeed measurement. The rotating pitot tubes simultaneously sense and measure the combined airflow intensity and angle, enabling measurement of angle of attack and sideslip angle. A distributed layout mitigates the effects of left and right fuselage asymmetry and resolves the issue of fuselage obstruction during sideslip flight. Installation close to the fuselage reduces the volume of exposed components and air resistance. This effectively addresses the challenges of existing helicopter air data measurement methods and demonstrates excellent application results.

[0032] The helicopter distributed three-axis atmospheric data measurement device proposed in the present invention has the advantages of low-speed airspeed measurement, angle of attack and sideslip angle measurement of the three-axis atmospheric data system, as well as the advantages of low weight, small size and low aerodynamic resistance of the distributed atmospheric data system. At the same time, through the left and right distributed layout, the atmospheric data measurement capability is improved, it can be adapted to most helicopters, and can achieve good measurement results.

[0033] Those skilled in the art will appreciate that the embodiments described herein are intended to help readers understand the principles of the present invention, and it should be understood that the scope of protection of the present invention is not limited to such specific descriptions and embodiments. Those skilled in the art can make various other specific variations and combinations based on the technical teachings disclosed in the present invention without departing from the essence of the present invention, and such variations and combinations are still within the scope of protection of the present invention.

Claims

1. A helicopter distributed three-axis atmospheric data measurement device, characterized in that: include: A left three-axis atmospheric measurement assembly (1) and a right three-axis atmospheric measurement assembly (2) are installed on both sides of the nose. The left three-axis atmospheric measurement assembly (1) and the right three-axis atmospheric measurement assembly (2) have the same structure and are both composed of a rotating pitot tube (3) and an electronic component (4). The rotating pitot tube (3) and the electronic component (4) are electrically connected through an opening in the fuselage skin. The rotating pitot tube (3) is installed on the outside of the nose skin and is used to sense the total pressure, static pressure, local angle of attack and local sideslip angle of the synthetic airflow in real time; The electronic component (4) is built into the nose skin and is used to collect the total pressure, static pressure, local angle of attack, local sideslip angle and atmospheric temperature of the synthetic airflow, perform parameter calculations, and output atmospheric parameters.

2. The helicopter distributed three-axis air data measurement device according to claim 1, characterized in that: The rotating pitot tube (3) comprises a straight tube (31), a tail wing (32), a first rotating shaft (33) and a second rotating shaft (34); The first rotating shaft (33) and the second rotating shaft (34) are designed to be orthogonally nested. One end of the first rotating shaft (33) is connected to the second rotating shaft (34), and the other end of the first rotating shaft (33) is connected to the base (5). The base (5) is fixed to the nose skin. The second rotating shaft (34) is arranged in the middle of the straight tube (31). The tail wing (32) is arranged at one end of the straight tube (31).

3. The helicopter distributed three-axis air data measurement device according to claim 2, characterized in that: The straight pipe (31) is used to sense the total pressure and static pressure and transmit them to the electronic component (4); The tail wing (32) is used to provide aerodynamic force for the rotating pitot tube (3), so that the rotating pitot tube (3) can rotate freely with the synthetic airflow; The first rotating shaft (33) is used to sense the local angle of attack and transmit it to the electronic component (4), and the first rotating shaft (33) allows the rotating pitot tube (3) to rotate in the pitch direction; The second rotating shaft (34) is used to sense the local sideslip angle and transmit it to the electronic component (4). The second rotating shaft (34) allows the rotating pitot tube (3) to rotate in the yaw direction.

4. The helicopter distributed three-axis air data measurement device according to claim 2, characterized in that: A temperature sensor (6) is provided on the base (5) for measuring the atmospheric temperature; the temperature sensor (6) is communicatively connected with the electronic component (4).

5. The helicopter distributed three-axis air data measurement device according to claim 4, characterized in that: The electronic component (4) includes an air pressure sensor, an angle sensor and an electronic circuit unit; The air pressure sensor is used to measure total pressure and static pressure; The angle sensor obtains the local angle of attack in real time by measuring the rotation angle of the first rotation axis (33), and obtains the local sideslip angle in real time by measuring the rotation angle of the second rotation axis (34); The electronic circuit unit is used to receive total pressure, static pressure, local angle of attack, local angle of sideslip and atmospheric temperature, and process the total pressure, static pressure, local angle of attack, local angle of sideslip and atmospheric temperature to output atmospheric parameters.

6. The helicopter distributed three-axis air data measurement device according to claim 1, characterized in that: The left three-axis atmospheric measurement component (1) and the right three-axis atmospheric measurement component (2) are connected in communication to perform data exchange, thereby completing left and right data fusion and eliminating the asymmetric influence of the layout on both sides of the fuselage.

7. The helicopter distributed three-axis air data measurement device according to claim 1, characterized in that: The combined airflow includes a flight airflow and a rotor airflow.

8. The helicopter distributed three-axis air data measurement device according to claim 1, characterized in that: The atmospheric parameters include pressure altitude, indicated airspeed, longitudinal true airspeed, lateral true airspeed, vertical true airspeed, angle of attack and sideslip angle.

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