Helicopter atmosphere data system and atmosphere parameter measuring method thereof

Abstract

The invention discloses a helicopter atmosphere data system and an atmosphere parameter measurement method thereof, and belongs to the technical field of atmosphere data measurement, the helicopter atmosphere data system comprises a fixed total static pressure probe, a follow-up multifunctional static pressure probe and an atmosphere data processing module which are electrically connected with one another; the fixed total static pressure probe is arranged on the surface of the head end of the helicopter body through a fixing bracket; the follow-up multifunctional static pressure probe is arranged on the surface of the head end of the helicopter body through the follow-up bracket; the atmospheric data processing module is integrated in a helicopter control system, the fixed total static pressure probe and the follow-up multifunctional static pressure probe are fixedly arranged on a helicopter body and used for measuring different flight states of the helicopter respectively, and real-time calculation is carried out through the atmospheric data processing module. The airspeed of the helicopter is accurately measured, and the solved airspeed is sent to equipment such as an airspeed indicator in the helicopter, so that an operator can conveniently check the airspeed in time.

Description

Technical Field

[0001] The present invention relates to the technical field of atmospheric data measurement, and in particular to a helicopter atmospheric data system and an atmospheric parameter measurement method thereof. Background Art

[0002] Helicopters are rotary-wing aircraft. The rotating shaft of the rotor is approximately vertical. It generates upward lift through rotation, and can generate horizontal components of force in the front, back, left and right directions through special devices, so that the helicopter can fly forward, backward, left and right. Therefore, helicopters can take off and land vertically, hover and fly in any direction, which is very different from fixed-wing aircraft. The rotor is a key component of the helicopter. Its movement characteristics have a significant impact on the entire helicopter flow field, resulting in a huge difference from the flow field of fixed-wing aircraft. First, due to the rotational motion of the rotor, different positions of the blades have different linear velocities. Usually, there are transonic speeds at the tip of the blade and incompressible flow areas near the hub at the same time; secondly, the wake of each blade of the rotor quickly rolls up a strongly concentrated contraction and spiral development of the blade tip vortex and vortex surface, until it needs to go far downstream to dissipate. These vortices dominate the entire rotor flow field. These make the entire flow field very complicated. At the same time, helicopter rotors also have special movements such as flapping, shimmying, periodic torque change and total pitch change, making the entire flow field very complicated.

[0003] Therefore, helicopters widely use fixed total pressure tubes + fuselage static pressure holes, or total static pressure sensors, which are almost unusable when disturbed by the rotor, and are almost powerless to measure airspeed under low-speed conditions. To solve this problem, a helicopter three-axis atmospheric data system has emerged, which uses a three-axis velocity vector sensor installed on a mounting bracket that extends a certain distance from the fuselage. It can sense the total pressure, static pressure and airflow deflection angle of the synthetic airflow of the flight airflow, rotor downwash and wind speed through the rotating pitot tube, and adjust the parameters through the algorithm model and the real flight model to finally obtain information such as atmospheric parameters. However, the three-axis atmospheric data system must be extended through the mounting rod, and the structure is complex. At the same time, it must be corrected by adjusting the parameters through a large amount of flight data. Its application is greatly limited and is only used on high-end military helicopters. At the same time, it is still impossible to measure under extremely low-speed conditions. Summary of the invention

[0004] In view of the problems existing in the above-mentioned prior art, the present invention provides a helicopter atmospheric data system and an atmospheric parameter measurement method thereof, which solves the problem that the existing helicopter atmospheric data system cannot measure atmospheric parameters under low-speed conditions of the helicopter.

[0005] In order to achieve the above-mentioned object of the invention, the technical solution adopted by the present invention is:

[0006] Provided is a helicopter atmospheric data system, which includes a fixed full static pressure probe, a follow-up multifunctional static pressure probe and an atmospheric data processing module electrically connected to each other;

[0007] The fixed total static pressure probe is arranged on the surface of the helicopter fuselage head end through a fixed bracket, and is used to measure the total atmospheric pressure and static pressure;

[0008] The follow-up multifunctional static pressure probe is arranged on the surface of the helicopter fuselage head end through a follow-up bracket, and is used to measure the atmospheric total pressure and static pressure at multiple angles;

[0009] The atmospheric data processing module is integrated into the helicopter control system.

[0010] Furthermore, the follower bracket includes a base fixedly connected to the surface at the head end of the helicopter fuselage, a rotating shaft is vertically arranged on the base, a follower rod is arranged on the top of the rotating shaft, the top of the rotating shaft is fixedly connected to the middle part of the follower rod, one end of the follower rod is provided with the follower multifunctional static pressure probe, and the other end is fixedly provided with an angle of attack wind vane, and the plane where the angle of attack wind vane is located is parallel to the plane formed by the axis of the rotating shaft and the axis of the follower rod.

[0011] Furthermore, the base is in a truncated cone structure, and is provided with a plurality of mounting holes for fixed connection with the surface of the helicopter fuselage, and the plurality of mounting holes are evenly spaced in a circumferential direction around the axis of the base.

[0012] The present invention also provides an atmospheric parameter measurement method of a helicopter atmospheric data system, which comprises:

[0013] The airspeed solution calculation formula for a fixed total static pressure probe is:

[0014] Pt 固 =0.5ρV 固 2 +Ps;

[0015] Among them, Pt 固 is the total pressure measured by the fixed full static pressure probe, Ps is the static pressure measured by the fixed full static pressure probe, and ρ is the air density;

[0016] The airspeed calculation formula for the full pressure of the follow-up multi-function static pressure probe is:

[0017] Pt 动 =0.5ρV 动 2 +Ps;

[0018] Among them, Pt 动 is the total pressure of the follow-up multifunctional static pressure probe, Ps is the static pressure measured by the fixed total static pressure probe, and ρ is the air density;

[0019] When flying at high speed, it can be considered that the helicopter body is not affected by the rotor downwash, or the velocity component of the downwash is too small to be ignored; at this time, the follow-up multifunctional static pressure probe outputs the local angle of attack value α and the total pressure value, and the fixed total static pressure probe outputs the total pressure value, and the two total pressure values ​​are the same; at this time:

[0020] V 固 =V 动 ;

[0021] Atmospheric data processing module output V 指示 =V 固 , where V 指示 V is the indicated airspeed output to the airspeed indicator and its supporting full static pressure probe system in the helicopter. 固 V is the airspeed calculated by the fixed total static pressure probe; 动 The airspeed calculated by the follow-up multi-function static pressure probe;

[0022] When the helicopter is hovering, the follow-up multifunctional static pressure probe outputs the total pressure value and the angle of attack value, and the fixed total static pressure probe outputs the total pressure value. At this time, the total pressure value output by the fixed total static pressure probe is even lower than the static pressure value of the fixed total static pressure probe, so it is invalid; and the angle of attack value α of the follow-up multifunctional static pressure probe is 90°, that is, the angle of attack wind vane is vertically upward, and the atmospheric data processing module outputs V 指示 =V 动 cos90°=0;

[0023] When the helicopter flies forward at an extremely low speed, the follow-up multifunctional static pressure probe outputs the total pressure value and the angle of attack value, and the fixed total static pressure probe outputs the total pressure value. At this time, the total pressure value output by the fixed total static pressure probe is even lower than the static pressure value of the fixed total static pressure probe, so it is invalid; and when the angle of attack value α of the follow-up multifunctional static pressure probe is corrected to 20-90°, the atmospheric data processing module outputs V 指示 =V 动 cosα;

[0024] When the helicopter flies forward normally, the follow-up multifunctional static pressure probe outputs the total pressure value and the angle of attack value, the fixed total static pressure probe outputs the total pressure value, and the angle of attack value α of the follow-up multifunctional static pressure probe is less than 20° after correction, the atmospheric data processing module outputs V 指示 =V 固 .

[0025] The beneficial effects of the present invention are as follows: 1. A helicopter atmospheric data system and an atmospheric parameter measurement method thereof of the present invention respectively provide a fixed full static pressure probe and a follow-up multifunctional static pressure probe on the helicopter fuselage, wherein the fixed full static pressure probe and the follow-up multifunctional static pressure probe are respectively used to measure different flight states of the helicopter, and are solved in real time by an atmospheric data processing module to achieve accurate measurement of the helicopter airspeed, and the solved airspeed is sent to the airspeed meter and other equipment in the helicopter, so that the operator can check it in time.

[0026] 2. A helicopter atmospheric data system and an atmospheric parameter measurement method thereof of the present invention, wherein the follow-up multifunctional static pressure probe rotates with the helicopter to provide an angle of attack measurement function.

[0027] 3. Compared with the traditional pitot tube airspeed measurement and three-axis atmospheric data system, the helicopter atmospheric data system and atmospheric parameter measurement method of the present invention solve the problem of insufficient accuracy of the traditional pitot tube airspeed measurement when the helicopter is flying forward at a low speed. At the same time, the probe does not need to extend far outside the fuselage, and the structure is simple and the applicability is strong. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 The schematic diagram of the structure of a helicopter atmospheric data system is shown in FIG.

[0029] Figure 2 It is a schematic diagram of the structure of the follower bracket.

[0030] Among them, 1. Fixed full static pressure probe; 2. Follow-up multifunctional static pressure probe; 3. Fixed bracket; 4. Follow-up bracket; 401. Base; 402. Rotating shaft; 403. Follow-up rod; 404. Angle of attack wind vane; 405. Mounting hole; 5. Helicopter fuselage. DETAILED DESCRIPTION

[0031] The specific implementation modes of the present invention are described below so that those skilled in the art can understand the present invention. However, it should be clear that the present invention is not limited to the scope of the specific implementation modes. For those of ordinary skill in the art, as long as various changes are within the spirit and scope of the present invention as defined and determined by the attached claims, these changes are obvious, and all inventions and creations utilizing the concept of the present invention are protected.

[0032] like Figures 1-2 As shown, the present invention provides a helicopter atmospheric data system, which includes a fixed full static pressure probe 1, a follow-up multifunctional static pressure probe 2 and an atmospheric data processing module electrically connected to each other;

[0033] The fixed full static pressure probe 1 is arranged on the surface at the head end of the helicopter fuselage 5 through a fixed bracket 3, and is used to measure the total atmospheric pressure and static pressure; the follow-up multifunctional static pressure probe 2 is arranged on the surface at the head end of the helicopter fuselage 5 through a follow-up bracket 4, and is used to measure the total atmospheric pressure and static pressure at multiple angles; the atmospheric data processing module is integrated into the helicopter control system.

[0034] By respectively arranging a fixed full static pressure probe 1 and a follow-up multifunctional static pressure probe 2 on the helicopter fuselage 5, the fixed full static pressure probe 1 and the follow-up multifunctional static pressure probe 2 are respectively used to measure different flight states of the helicopter, and the atmospheric data processing module performs real-time calculation to achieve accurate measurement of the helicopter airspeed, and the calculated airspeed is sent to the airspeed indicator and other equipment in the helicopter, so that the operator can check it in time.

[0035] Specifically, as a specific setting method of the follow-up bracket 4, the follow-up bracket 4 includes a base 401 fixedly connected to the surface at the head end of the helicopter fuselage 5, a rotating shaft 402 is vertically arranged on the base 401, a follow-up rod 403 is arranged on the top of the rotating shaft 402, and the top of the rotating shaft 402 is fixedly connected to the middle part of the follow-up rod 403, one end of the follow-up rod 403 is provided with the follow-up multifunctional static pressure probe 2, and the other end is fixedly provided with an angle of attack wind vane 404, and the plane where the angle of attack wind vane 404 is located is parallel to the plane formed by the axis of the rotating shaft 402 and the axis of the follow-up rod 403.

[0036] When the helicopter is in different flight states, the angle of attack wind vane 404 is affected by wind flows at different angles, driving the follow-up multifunctional static pressure probe 2 on the rotating shaft 402 to rotate, thereby enabling the follow-up multifunctional static pressure probe 2 to rotate with the helicopter to provide an angle of attack measurement function.

[0037] Furthermore, the base 401 is a truncated cone structure, and is provided with a plurality of mounting holes 405 for fixedly connecting with the surface of the helicopter fuselage 5 . The plurality of mounting holes 405 are evenly spaced in the circumferential direction around the axis of the base 401 .

[0038] The present invention also provides an atmospheric parameter measurement method of a helicopter atmospheric data system, which comprises:

[0039] The airspeed calculation formula for the fixed total static pressure probe 1 is:

[0040] Pt 固 =0.5ρV 固 2 +Ps;

[0041] Among them, Pt 固 is the total pressure measured by the fixed total static pressure probe 1, Ps is the static pressure measured by the fixed total static pressure probe 1, and ρ is the air density;

[0042] The airspeed calculation formula for the full pressure of the follow-up multi-function static pressure probe 2 is:

[0043] Pt 动 =0.5ρV 动 2 +Ps;

[0044] Among them, Pt 动 is the total pressure of the follow-up multifunctional static pressure probe 2, Ps is the static pressure measured by the fixed total static pressure probe 1, and ρ is the air density;

[0045] When flying at high speed, it can be considered that the helicopter body is not affected by the rotor downwash, or the velocity component of the downwash is too small to be ignored; at this time, the follow-up multifunctional static pressure probe 2 outputs the local angle of attack value α and the total pressure value, and the fixed total static pressure probe 1 outputs the total pressure value, and the two total pressure values ​​are the same; at this time:

[0046] V 固 =V 动 ;

[0047] Atmospheric data processing module output V 指示 =V 固 , where V 指示 V is the indicated airspeed output to the airspeed indicator and its supporting full static pressure probe system in the helicopter. 固 V is the airspeed calculated by the fixed total static pressure probe 1; 动 The airspeed calculated by the follow-up multifunctional static pressure probe 2;

[0048] When the helicopter is hovering, the follow-up multifunctional static pressure probe 2 outputs the total pressure value and the angle of attack value, and the fixed total static pressure probe 1 outputs the total pressure value. At this time, the total pressure value output by the fixed total static pressure probe 1 is even lower than the static pressure value of the fixed total static pressure probe 1, so it is invalid; and the angle of attack value α of the follow-up multifunctional static pressure probe 2 is 90°, that is, the angle of attack wind vane 404 is vertically upward, and the atmospheric data processing module outputs V 指示 =V 动 cos90°=0;

[0049] When the helicopter flies forward at an extremely low speed, the follow-up multifunctional static pressure probe 2 outputs the total pressure value and the angle of attack value, and the fixed total static pressure probe 1 outputs the total pressure value. At this time, the total pressure value output by the fixed total static pressure probe 1 is even lower than the static pressure value of the fixed total static pressure probe 1, so it is invalid; and when the angle of attack value α of the follow-up multifunctional static pressure probe 2 is corrected to 20-90°, the atmospheric data processing module outputs V 指示 =V 动 cosα;

[0050] When the helicopter flies forward normally, the follow-up multifunctional static pressure probe 2 outputs the total pressure value and the angle of attack value, the fixed total static pressure probe 1 outputs the total pressure value, and the angle of attack value α of the follow-up multifunctional static pressure probe 2 is less than 20° after correction, the atmospheric data processing module outputs V 指示 =V 固 .

[0051] In summary, compared with the traditional pitot tube airspeed measurement and three-axis atmospheric data system, the helicopter atmospheric data system and atmospheric parameter measurement method of the present invention solve the problem of insufficient accuracy of the traditional pitot tube airspeed measurement when the helicopter is flying forward at a low speed. At the same time, the probe does not need to extend far outside the fuselage, the structure is simple, and the applicability is strong.

Claims

1. A helicopter air data system, characterized in that: It includes a fixed full static pressure probe, a follow-up multifunctional static pressure probe and an atmospheric data processing module which are electrically connected to each other; The fixed total static pressure probe is arranged on the surface of the helicopter fuselage head end through a fixed bracket, and is used to measure the total atmospheric pressure and static pressure; The follow-up multifunctional static pressure probe is arranged on the surface of the helicopter fuselage head end through a follow-up bracket, and is used to measure the atmospheric total pressure and static pressure at multiple angles; The atmospheric data processing module is integrated into the helicopter control system.

2. The helicopter air data system according to claim 1, characterized in that: The follower bracket includes a base fixedly connected to the surface at the head end of the helicopter fuselage, a rotating shaft is vertically arranged on the base, a follower rod is arranged on the top of the rotating shaft, the top of the rotating shaft is fixedly connected to the middle part of the follower rod, one end of the follower rod is provided with the follower multifunctional static pressure probe, and the other end is fixedly provided with an angle of attack wind vane, and the plane where the angle of attack wind vane is located is parallel to the plane formed by the axis of the rotating shaft and the axis of the follower rod.

3. The helicopter air data system according to claim 2, characterized in that: The base is in a truncated cone structure, and is provided with a plurality of mounting holes for fixed connection with the surface of the helicopter fuselage, and the plurality of mounting holes are evenly spaced in the circumferential direction around the axis of the base.

4. A method for measuring atmospheric parameters of a helicopter atmospheric data system according to any one of claims 1 to 3, characterized in that: include: The airspeed solution calculation formula for a fixed total static pressure probe is: Pt 固 =0.5ρV 固 2 +Ps; Among them, Pt 固 Ps is the fixed total static pressure probe measuring total pressure, Ps is the fixed total static pressure probe measuring static pressure, ρ is the air density; The airspeed calculation formula for the full pressure of the follow-up multi-function static pressure probe is: Pt 动 =0.5ρV 动 2 +Ps; Among them, Pt 动 is the total pressure of the follow-up multifunctional static pressure probe, Ps is the static pressure measured by the full static pressure probe, and ρ is the air density; When flying at high speed, it can be considered that the helicopter body is not affected by the rotor downwash, or the velocity component of the downwash is too small to be ignored; at this time, the follow-up multifunctional static pressure probe outputs the local angle of attack value α and the total pressure value, and the fixed total static pressure probe outputs the total pressure value, and the two total pressure values ​​are the same; at this time: V 固 =V 动 ; Atmospheric data processing module output V 指示 =V 固 , where V 指示 V is the indicated airspeed output to the airspeed indicator and its supporting full static pressure probe system in the helicopter. 固 V is the airspeed calculated by the fixed total static pressure probe; 动 The airspeed calculated by the follow-up multi-function static pressure probe; When the helicopter is hovering, the follow-up multifunctional static pressure probe outputs the total pressure value and the angle of attack value, and the fixed total static pressure probe outputs the total pressure value. At this time, the total pressure value output by the fixed total static pressure probe is even lower than the static pressure value of the fixed total static pressure probe, so it is invalid; and the angle of attack value α of the follow-up multifunctional static pressure probe is 90°, that is, the angle of attack wind vane is vertically upward, and the atmospheric data processing module outputs V 指示 =V 动 cos90°=0; When the helicopter flies forward at an extremely low speed, the follow-up multifunctional static pressure probe outputs the total pressure value and the angle of attack value, and the fixed total static pressure probe outputs the total pressure value. At this time, the total pressure value output by the fixed total static pressure probe is even lower than the static pressure value of the fixed total static pressure probe, so it is invalid; and when the angle of attack value α of the follow-up multifunctional static pressure probe is corrected to 20-90°, the atmospheric data processing module outputs V 指示 =V 动 cosα; When the helicopter flies forward normally, the follow-up multifunctional static pressure probe outputs the total pressure value and the angle of attack value, the fixed total static pressure probe outputs the total pressure value, and the angle of attack value α of the follow-up multifunctional static pressure probe is less than 20° after correction, the atmospheric data processing module outputs V 指示 =V 固 .

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