CN214622710U - Airspeed detection device - Google Patents

Abstract

The utility model relates to an airspeed detection device, including airspeed head, horizontal stabilizer, horizontal rotating shaft and attack angle sensor, horizontal stabilizer is symmetrical wing section stabilizer, and the airspeed head sets up the first terminal surface at horizontal stabilizer, and horizontal rotating shaft sets up in the second terminal surface of horizontal stabilizer, and horizontal stabilizer can rotate around horizontal rotating shaft's axial, but attack angle sensor and horizontal rotating shaft rotation setting, and the directional extension direction with the string of a thread of horizontal stabilizer of airspeed head is parallel. Above-mentioned airspeed detection device, horizontal stabilizer is symmetrical wing section stabilizer, when the declination appears with horizontal stabilizer in the air current, horizontal stabilizer can produce a corresponding moment and makes horizontal stabilizer take place the rotation for the angle of attack sensor, the airspeed tube is on a parallel with the incoming flow vector always, it is accurate to survey the wind speed value, horizontal stabilizer can be around the axial of horizontal rotating shaft and rotate, can detect the angle of incoming flow, improve the accuracy that detects the airspeed, have the significance to improving flight safety.

Description

Airspeed detection device

Technical Field

The utility model relates to an airspeed detects technical field, especially relates to an airspeed detection device.

Background

Airspeed, which is the velocity of an aircraft (e.g., an airplane) relative to the movement of air, is often determined by detecting the dynamic pressure generated when the airplane moves relative to the air, and is an important indicator for detecting flight conditions. The traditional method for detecting airspeed is to arrange an airspeed tube at a certain position of an airplane, wherein the airspeed tube generally consists of two concentric circular tubes, the inner circular tube is a total pressure tube, and the outer sleeve is a static pressure tube. The measuring principle of the airspeed head is that the relative speed of air and an airplane is measured by using the Bernoulli principle of incompressible flow, and when the airplane flies forwards, the total pressure pipe head is perpendicular to incoming flow, so that the flow rate of the air at the total pressure pipe head is 0, and the pressure is transmitted to the total pressure end of the differential pressure sensor; the opening of the static pressure pipe is parallel to the incoming flow, the air flow speed at the static pressure pipe is the same as the speed of the airplane, and the pressure is transmitted to the static pressure end of the differential pressure sensor. The differential pressure sensor obtains the differential pressure of total pressure and static pressure, and according to the Bernoulli principle, the differential pressure at this moment is the aircraft dynamic pressure, can obtain the airspeed value of aircraft through the conversion.

However, the traditional airspeed head is fixed in installation position, and when the actual incoming flow has a certain drift angle with the airspeed head installation direction, the total pressure of measurement begins to drop, so that the airspeed head detected under certain conditions has a large measurement error with the actual airspeed, the detection result is inaccurate, and the flight safety of the aircraft is affected.

SUMMERY OF THE UTILITY MODEL

Based on this, it is necessary to provide an airspeed detection device to the inaccurate airspeed of traditional airspeed head, influences the problem of the flight safety of aircraft.

The utility model provides an airspeed detection device, includes airspeed tube, horizontal stabilizer, horizontal rotating shaft and attack angle sensor, horizontal stabilizer is symmetry wing section stabilizer, the airspeed tube sets up the first terminal surface of horizontal stabilizer, horizontal rotating shaft set up in the second terminal surface of horizontal stabilizer, horizontal stabilizer can center on horizontal rotating shaft's axial rotates, attack angle sensor with horizontal rotating shaft can the rotation setting each other, the sensing of airspeed tube with the extension direction of the string of a muscle of horizontal stabilizer is parallel.

Above-mentioned airspeed detection device, including airspeed head, horizontal stabilizer, horizontal rotating shaft and attack angle sensor, horizontal stabilizer is symmetrical wing section stabilizer, and the airspeed head sets up the first terminal surface at horizontal stabilizer, and horizontal rotating shaft sets up in the second terminal surface of horizontal stabilizer, and horizontal stabilizer can center on horizontal rotating shaft's axial rotation, but attack angle sensor and horizontal rotating shaft rotation each other set up, and the directional of airspeed head is parallel with the extending direction of the chord line of horizontal stabilizer. Because the horizontal stabilizer is the symmetrical wing section stabilizer, when the incoming flow velocity is parallel to the wing section chord line, the pitching moment is not generated, the horizontal stabilizer can rotate around the axial direction of the horizontal rotating shaft, when the deflection angle occurs between the airflow and the horizontal stabilizer, the horizontal stabilizer can generate a corresponding moment to enable the horizontal stabilizer to rotate relative to the attack angle sensor, the position where the airspeed head faces at the moment is the vector direction of the actual incoming flow, the angle of the incoming flow can be detected, and simultaneously, because the airspeed head is always parallel to the incoming flow vector, the measured wind speed value is also accurate, the accuracy of airspeed detection can be improved, and the method has important significance for improving the flight safety.

In one embodiment, the airspeed detection device further comprises a vertical stabilizer, and the vertical stabilizer is arranged perpendicular to the horizontal stabilizer.

In one embodiment, the airspeed detection device further comprises a vertical rotating shaft and a sideslip angle sensor, the vertical rotating shaft is vertically arranged on one end face, away from the attack angle sensor, of the vertical stabilizing face, and the sideslip angle sensor and the vertical rotating shaft can be arranged in a mutually rotating mode.

In one embodiment, the airspeed detection device further comprises a mounting plate, and the sideslip angle sensor is arranged on the mounting plate.

In one embodiment, the vertical rotating shaft is a hollow rotating shaft, and a signal wire of the attack angle sensor is connected with the sideslip angle sensor through the vertical rotating shaft.

In one embodiment, airspeed detection device still includes pipe clamp and installation curb plate, the airspeed pipe passes through the pipe clamp is installed on the installation curb plate, the installation curb plate set up in the first terminal surface of horizontal stabilizer.

In one embodiment, the horizontal rotating shaft is arranged at the pneumatic center point of the horizontal stabilizing surface.

In one embodiment, the airspeed detection device further comprises a counterweight, and the counterweight is arranged on the horizontal stabilizer.

In one embodiment, the airspeed detection device further comprises a differential pressure detector arranged in the horizontal stable surface, and the differential pressure detector is connected with the airspeed head.

In one embodiment, the horizontal rotating shaft is a hollow rotating shaft, and a signal wire of the differential pressure detector is connected with the attack angle sensor through the horizontal rotating shaft.

Drawings

FIG. 1 is a block diagram of an airspeed detection device in one embodiment;

FIG. 2 is a block diagram of an airspeed detection device in another embodiment;

fig. 3 is a block diagram of an airspeed detection device in yet another embodiment.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is described more fully below by way of examples in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention.

In an embodiment, please refer to fig. 1-3, which provides an airspeed detection device, including a pitot tube 110, a horizontal stabilizer 100, a horizontal rotation shaft 140 and an attack angle sensor 150, where the horizontal stabilizer 100 is a symmetric airfoil stabilizer, the pitot tube 110 is disposed at a first end surface of the horizontal stabilizer 100, the horizontal rotation shaft 140 is disposed at a second end surface of the horizontal stabilizer 100, the horizontal stabilizer 100 is rotatable around an axial direction of the horizontal rotation shaft 140, the attack angle sensor 150 and the horizontal rotation shaft 140 are rotatably disposed with each other, and a pointing direction of the pitot tube 110 is parallel to an extending direction of a chord line of the horizontal stabilizer 100. Because the horizontal stabilizer 100 is a symmetrical airfoil stabilizer, when the incoming flow velocity is parallel to the airfoil chord line, no pitching moment is generated, the horizontal stabilizer 100 can rotate around the axial direction of the horizontal rotating shaft 140, when the deviation angle occurs between the airflow and the horizontal stabilizer 100, the horizontal stabilizer 100 can generate a corresponding moment to enable the horizontal stabilizer 100 to rotate relative to the attack angle sensor 150, and at the moment, the position where the pitot tube 110 faces is the vector direction of the actual incoming flow, the angle of the incoming flow can be detected, and meanwhile, because the pitot tube 110 is always parallel to the incoming flow vector, the measured wind speed value is also accurate, the accuracy of detecting the airspeed can be improved, and the method has important significance for improving the flight safety.

In particular, the airspeed detection device may be located at various locations on the aircraft or other aircraft as desired, such as on the nose or wing. The number of airspeed detection devices is also not unique, and when the number of airspeed detection devices was more than two, each airspeed detection device can set up the different positions at the aircraft to detect the airspeed at the different positions of aircraft, improve the accuracy of the airspeed that the detection obtained. When airspeed detection device sets up on the aircraft, horizontal stabilizer 100 is parallel with the aircraft position that has set up airspeed detection device, and when the aircraft level flies, horizontal stabilizer 100 is parallel with the horizon. The horizontal stabilizer 100 is a symmetrical airfoil stabilizer, and the horizontal stabilizer 100 includes a leading edge and a trailing edge, which can be determined according to the flow direction of the fluid, and in this embodiment, when the aircraft flies, the air flows from the leading edge to the trailing edge of the horizontal stabilizer 100. Further, the pitot tube 110 is disposed at the first end face of the horizontal stabilizer 100, and particularly may be disposed at the leading edge of the first end face, to detect the flow rate of the gas with which the aircraft comes into contact, making the detected airspeed more accurate.

The chord line of the horizontal stabilizer 100 is a straight line connecting the leading edge and the trailing edge of the horizontal stabilizer 100, the horizontal stabilizer 100 is a symmetrical airfoil, and the horizontal stabilizer 100 is vertically symmetrical about the chord line thereof. When the incoming flow direction is parallel to the airfoil chord line of the horizontal stabilizer 100, the horizontal stabilizer 100 does not generate a pitching moment. The chord line is taken as a dividing line, the horizontal stabilizing surface 100 comprises a first arc surface and a second arc surface, and the first end surface and the second end surface of the horizontal stabilizing surface 100 are surfaces which are perpendicular to the first arc surface and the second arc surface and are positioned at two ends of the horizontal stabilizing surface 100. Airspeed tube 110 sets up the first terminal surface at horizontal stabilizer 100, can be that the one end setting of airspeed tube 110 is at the first terminal surface of horizontal stabilizer 100, and the other end and the air contact of airspeed tube 110 are convenient for detect the airspeed. The pitot tube 110 is oriented parallel to the direction of extension of the chord line of the horizontal stabilizer 100, i.e., the pitot tube 110 is oriented parallel to the plane of the chord line, and when the horizontal stabilizer 100 is in a horizontal position, the pitot tube 110 is oriented horizontally.

The horizontal rotating shaft 140 is arranged on the second end face of the horizontal stabilizing face 100, namely, the end face far away from the pitot tube 110, so that the mutual influence of the work of the horizontal rotating shaft 140 and the operation of the pitot tube 110 can be avoided, and the space is reasonably utilized. When the second end surface of the horizontal stabilizer 100 is a plane, the axial direction of the horizontal rotating shaft 140 may be perpendicular to the second end surface of the horizontal stabilizer 100, so that the horizontal rotating shaft 140 may rotate around the axis thereof, thereby driving the horizontal stabilizer 100 to rotate, and when the horizontal stabilizer 100 rotates, the plane where the first end surface is located does not change, and the plane where the second end surface is located does not change. The angle of attack sensor 150 and the horizontal rotating shaft 140 can be rotatably disposed, generally, the horizontal rotating shaft 140 can rotate, the angle of attack sensor 150 can be fixed, and the angle of attack sensor 150 and the horizontal rotating shaft 140 can also be rotatably disposed. The attack angle sensor 150 can detect the rotation angle of the horizontal rotating shaft 140, and since the rotation angle of the horizontal stabilizer 100 is substantially consistent with the rotation angle of the horizontal rotating shaft 140, the attack angle sensor 150 can also measure the rotation angle of the horizontal stabilizer 100. The angle of attack sensor 150 may detect the angle of attack, which is the angle of the incoming flow in the up-down direction with respect to the installation reference plane. The horizontal stabilizer 100 can rotate around the axial direction of the horizontal rotating shaft 140, when the air flow deviates from the horizontal stabilizer 100, the horizontal stabilizer 100 can generate a corresponding moment to enable the horizontal stabilizer 100 to rotate relative to the attack angle sensor 150, at the moment, the position where the airspeed tube 110 faces is the vector direction of the actual incoming flow, and the angle of the incoming flow can be detected, meanwhile, because the airspeed tube 110 is always parallel to the incoming flow vector, the detection error caused by the deviation angle between the actual incoming flow and the installation direction of the airspeed tube 110 is reduced, therefore, the measured air speed value is also accurate, the accuracy of airspeed detection can be improved, and the flight safety is improved.

In one embodiment, referring to fig. 1, the airspeed detection device further includes a vertical stabilizer 200, and the vertical stabilizer 200 is disposed perpendicular to the horizontal stabilizer 100. The vertical stabilizer 200 is perpendicular to the horizontal stabilizer 100, so that an airspeed detection axis system can be formed, and the incoming flow angle can be conveniently detected.

Specifically, the vertical stabilizer 200 and the horizontal stabilizer 100 have the same shape, so as to improve the structural consistency of the airspeed detection device, which is beneficial to reducing detection errors. The vertical stabilizing surface 200 is perpendicular to the horizontal stabilizing surface 100, which means that the plane of the chord line of the vertical stabilizing surface 200 is perpendicular to the plane of the chord line of the horizontal stabilizing surface 100, and the vertical stabilizing surface 200 is perpendicular to the horizontal stabilizing surface 100, so that an airspeed detection axis system can be formed, and the incoming flow angle can be conveniently detected. When the airspeed detection device further includes the vertical stabilizer 200, an end surface of the vertical stabilizer 200 away from the horizontal stabilizer 100 may be disposed on the aircraft, and the vertical stabilizer 200 is perpendicular to the aircraft portion on which it is disposed, so that the horizontal stabilizer 100 is parallel to the aircraft portion on which the airspeed detection device is disposed. The vertical stabilizer 200 includes two end surfaces, the attack angle sensor 150 is disposed on one end surface of the vertical stabilizer 200 adjacent to the horizontal stabilizer 100, and the horizontal stabilizer 100 is connected to the attack angle sensor 150 disposed on the vertical stabilizer 200 through the horizontal rotation shaft 140, so that the horizontal stabilizer 100 is connected to the vertical stabilizer 200. Further, the attack angle sensor 150 may be specifically disposed in an end surface of the vertical stabilizer 200 close to the horizontal stabilizer 100, so that the vertical stabilizer 200 may play a role in protecting the attack angle sensor 150, and the angle detected by the attack angle sensor 150 only includes an angle value at which the horizontal stabilizer 100 rotates to drive the horizontal rotating shaft 140 to rotate, which may improve error reduction and improve accuracy of the detection result.

In one embodiment, referring to fig. 1-3, the airspeed detection device further includes a vertical shaft 220 and a sideslip angle sensor 210, the vertical shaft 220 is vertically disposed on an end surface of the vertical stabilizer 200 away from the attack angle sensor 150, and the sideslip angle sensor 210 and the vertical shaft 220 are rotatably disposed with respect to each other.

Specifically, the vertical rotating shaft 220 is disposed on an end surface of the vertical stabilizer 200 away from the attack angle sensor 150, so that the vertical rotating shaft 220 can be prevented from being influenced by the horizontal rotating shaft 140, the attack angle sensor 150 and the horizontal stabilizer 100, and the space can be reasonably utilized. The vertical shaft 220 is vertically disposed on an end surface of the vertical stabilizer 200 away from the attack angle sensor 150, an axial direction of the vertical shaft 220 is perpendicular to the end surface of the vertical stabilizer 200, and the vertical shaft 220 can rotate around an axis thereof, so that the vertical stabilizer 200 rotates, and planes of the two end surfaces do not change when the vertical stabilizer 200 rotates. The sideslip angle sensor 210 and the vertical rotating shaft 220 can be rotatably disposed, generally, the vertical rotating shaft 220 can rotate, the sideslip angle sensor 210 can be fixed in position, and the sideslip angle sensor 210 and the vertical rotating shaft 220 can also be rotatably disposed. The sideslip angle sensor 210 may detect a rotation angle of the vertical rotation shaft 220, and since the rotation angle of the vertical stabilizer 200 is substantially identical to the rotation angle of the vertical rotation shaft 220, the sideslip angle sensor 210 may also achieve measurement of the rotation angle of the vertical stabilizer 200. The vertical stabilizer 200 can rotate around the axial direction of the vertical rotating shaft 220, and when the air flow deviates from the vertical stabilizer 200, the vertical stabilizer 200 can generate a corresponding moment to enable the vertical stabilizer 200 to rotate relative to the sideslip angle sensor 210, so that the sideslip angle sensor 210 can detect the angle of the incoming flow relative to the vertical stabilizer 200. Because the horizontal stabilizer 100 and the vertical stabilizer 200 are symmetrical airfoil stabilizers, the air flow stability is achieved. When the airflow is off-angled from the horizontal stabilizer 100, the horizontal stabilizer 100 can generate a corresponding moment to rotate the horizontal stabilizer 100 relative to the angle of attack sensor 150, and when the airflow is off-angled from the vertical stabilizer 200, the vertical stabilizer 200 can generate a corresponding moment to rotate the vertical stabilizer 200 relative to the sideslip angle sensor 210. The attack angle and the sideslip angle of the airflow shafting relative to the machine body shafting can be obtained through the attack angle detected by the attack angle sensor 150 and the sideslip angle detected by the sideslip angle sensor 210, and meanwhile, the measured wind speed value is also accurate because the airspeed head 110 is always parallel to the incoming flow vector and the position where the airspeed head 110 faces is the vector direction of the actual incoming flow.

In one embodiment, referring to fig. 1, the airspeed detection device further includes a mounting plate 230, and the sideslip angle sensor 210 is disposed on the mounting plate 230. The side slip angle sensor 210 is disposed on the mounting plate 230, and the mounting plate 230 may serve as a carrier of the side slip angle sensor 210, so that the position of the side slip angle sensor 210 is maintained stably, thereby improving the operating performance of the side slip angle sensor 210. It is understood that since the vertical rotating shaft 220 is rotatable around its axial direction, the fixed position of the slip angle sensor 210 also enables the vertical rotating shaft 220 and the slip angle sensor 210 to be rotatable with respect to each other.

Specifically, the shape and the position of the mounting plate 230 are not exclusive, and for example, the mounting plate 230 may be a mounting plate 230 having a through hole formed in the middle thereof, and the side slip angle sensor 210 may be disposed in the through hole, and the side slip angle sensor 210 may be connected to the edge of the through hole to maintain the position thereof fixed. When the mounting plate 230 is a mounting plate 230 with a through hole in the middle, the position of the sideslip angle sensor 210 is kept fixed, and the sideslip angle sensor 210 can be conveniently connected with the vertical rotating shaft 220. Alternatively, the mounting plate 230 may be a solid plate disposed on a side of the sideslip angle sensor 210 away from the vertical rotating shaft 220, so as to avoid affecting the operation of the vertical rotating shaft 220. It can be understood that the outer contour of the mounting plate 230 may be circular to avoid the change of the airflow direction caused by the irregular shape of the mounting plate 230, reduce the error of the mounting plate 230 to the detected sideslip angle, and improve the accuracy of the detection result. The vertical stabilizer 200 is connected to a sideslip angle sensor 210 mounted on a mounting plate 230 through a vertical rotating shaft 220. The vertical shaft 220 is fixedly connected to the vertical stabilizer 200, so that the vertical shaft 220 can rotate relative to the sideslip angle sensor 210, thereby facilitating the detection of the sideslip angle of the incoming flow.

In one embodiment, the vertical shaft 220 is a hollow shaft, and the signal line of the attack angle sensor 150 is connected to the sideslip angle sensor 210 through the vertical shaft 220. When the vertical shaft 220 is a hollow shaft, the through hole in the vertical shaft 220 can be used for placing a signal line, and the penetrating direction of the through hole is consistent with the axial direction of the vertical shaft 220. The signal line of the attack angle sensor 150 is connected with the sideslip angle sensor 210 through the vertical rotating shaft 220, so that data transmission can be realized for the attack angle sensor 150 and the sideslip angle sensor 210, and the space can be saved, in addition, the signal line is distributed through the through hole in the vertical rotating shaft 220, the storage is convenient, the influence of the arrangement disorder of the signal line on the trimming of the vertical stabilizing surface 200 can be reduced, and the improvement of the working performance of the vertical stabilizing surface 200 is facilitated.

In one embodiment, referring to fig. 1-3, the airspeed detection device further includes a tube clamp 120 and a mounting side plate 130, wherein the airspeed tube 110 is mounted on the mounting side plate 130 through the tube clamp 120, and the mounting side plate 130 is disposed on the first end surface of the horizontal stabilizer 100. The pitot tube 110 is mounted on a mounting side plate 130 through the tube clamp 120, and the mounting side plate 130 is disposed on the first end surface of the horizontal stabilizer 100, so that the tube clamp 120 can be better kept fixed in position.

Specifically, since pitot tube 110 is a tubular object, the position of pitot tube 110 can be more stable by mounting one end of pitot tube 110 on mounting side plate 130 using tube clamp 120, and tube clamp 120 can be fixedly connected with mounting side plate 130 to maintain the stability of the overall structure. The shape of the tube clamp 120 is not exclusive and may be a hollow cylinder into which the pitot tube 110 is inserted to maintain a fixed position, and other structures may be disposed within the hollow cylinder to improve the stability of the pitot tube 110. Pitot tube 110 can be dismantled with pipe clamp 120 and be connected, is convenient for change different pitot tubes 110, and it is convenient to use. The mounting side plate 130 is disposed on the first end surface of the horizontal stabilizer 100, and can serve as a carrier for the pitot tube 110 and the tube clamp 120, and the position of the mounting side plate is kept fixed. The shape of the mounting side plate 130 is not exclusive, for example, the mounting side plate 130 may be a plate having the same shape and area as the first end of the horizontal stabilizer 100, and the effect on the aerodynamic performance of the airspeed detection device may be reduced while maintaining the position of the tube clamp 120 and the airspeed head 110 fixed. It is understood that in other embodiments, the clamp 120 and the mounting plate 130 can have other configurations as will be appreciated by those skilled in the art.

In one embodiment, the horizontal axis of rotation 140 is disposed at the aerodynamic center point of the horizontal stabilizer 100. When the horizontal rotating shaft 140 is disposed at the pneumatic center point of the horizontal stabilizing surface 100, the horizontal stabilizing surface 100 can be kept horizontal by adjusting the counterweight in a windless state, the pitot tube 110 points to keep horizontal, if the incoming flow velocity is parallel to the airfoil chord line, the airfoil chord line is always parallel to the incoming flow, and the horizontal stabilizing surface 100 does not generate a pitching moment, so as to measure the angle of the incoming flow.

Specifically, the location of the aerodynamic center point of the horizontal stabilizer 100 is not unique, for example, when the horizontal stabilizer 100 is a symmetric airfoil, the aerodynamic center point of the horizontal stabilizer 100 is directed from the leading edge to the trailing edge at the symmetric airfoil chord 1/4. Generally speaking, 20% -30% of symmetrical airfoil chord length from the leading edge to the trailing edge can all satisfy the demand, and the specific value can be adjusted according to actual conditions. When the horizontal rotating shaft 140 is disposed at the aerodynamic center point of the horizontal stabilizer 100, the horizontal stabilizer 100 is kept horizontal in a windless state, the pitot tube 110 points to keep horizontal, if the incoming flow velocity is parallel to the airfoil chord line, the airfoil chord line is always parallel to the incoming flow, and the horizontal stabilizer 100 does not generate a pitching moment, so as to measure the angle of the incoming flow.

In one embodiment, referring to fig. 3, the airspeed detection device further includes a weight 170, and the weight 170 is disposed on the horizontal stabilizer 100. Specifically, the counterweight block 170 may be disposed in a counterweight cabin in the horizontal stabilizer 100, and counterweight is performed by the counterweight block 170, so that the center of gravity of the horizontal stabilizer 100 may fall at the aerodynamic center point of the horizontal stabilizer 100, and when the horizontal stabilizer 100 is disposed at the aerodynamic center point of the horizontal stabilizer 100, and the aerodynamic center point is the symmetric airfoil chord length 1/4 from the leading edge to the trailing edge, the counterweight block 170 may cause the center of gravity of the horizontal stabilizer 100 to fall at the center of the horizontal rotation shaft 140. The counterweight 170 enables the horizontal stabilizer 100 to be parallel to the ground, the horizontal stabilizer 100 to remain horizontal, and the pitot tube 110 to be pointed to remain horizontal under windless conditions, such that the center of gravity of all components of the horizontal stabilizer 100 falls at 1/4 of the airfoil chord length to more accurately detect airspeed.

In one embodiment, airspeed detection device further comprises a differential pressure detector disposed within horizontal stabilizer 100, the differential pressure detector being coupled to airspeed tube 110. The pressure differential detector can acquire the dynamic pressure value of the pitot tube 110, thereby realizing the detection of the airspeed.

Specifically, the differential pressure detector is arranged in the horizontal stabilizing surface 100, and specifically can be arranged in a sensor mounting bin in the horizontal stabilizing surface 100, the horizontal stabilizing surface 100 can protect the differential pressure detector, and few air flows flow in the horizontal stabilizing surface 100, so that the measurement error of the differential pressure detector can be reduced. The structure of the differential pressure detector is not unique, please refer to fig. 3, in this embodiment, the differential pressure detector includes a differential pressure sensor 161 and two pressure measuring hoses 162, one end of each of the two pressure measuring hoses 162 is connected to the differential pressure sensor 161, the other end of each of the two pressure measuring hoses 162 is connected to the pitot tube 110, and the two pressure measuring hoses 162 can respectively measure the total pressure and the static pressure of the pitot tube 110 and send the total pressure and the static pressure to the differential pressure sensor 161, so that the differential pressure sensor 161 can calculate a corresponding dynamic pressure value to complete the detection of the pitot. It is understood that in other embodiments, the pressure difference detector may have other structures, as long as the implementation is considered by those skilled in the art.

In one embodiment, the horizontal rotating shaft 140 is a hollow rotating shaft, and the signal line of the differential pressure detector is connected to the attack angle sensor 150 through the horizontal rotating shaft 140. When the horizontal rotation shaft 140 is a hollow rotation shaft, the through hole in the horizontal rotation shaft 140 can be used for placing a signal line, and the penetrating direction of the through hole is consistent with the axial direction of the horizontal rotation shaft 140. The signal line of pressure differential detector passes through horizontal rotating shaft 140 and connects angle of attack sensor 150, can make angle of attack sensor 150 and pressure differential detector all can realize data transmission, also can practice thrift the space, and in addition, the signal line passes through the through-hole wiring in the horizontal rotating shaft 140, is convenient for accomodate, also can reduce the signal line and arrange the influence of mixed and disorderly to horizontal stabilizer 100 trim, is favorable to improving the working property of horizontal stabilizer 100. The type of the signal line is not unique, in this embodiment, the signal line of the differential pressure detector is a CAN bus, and in an extensible manner, the differential pressure sensor, the attack angle sensor, and the sideslip angle sensor may all use the CAN bus to transmit signals, and other types of signal lines may also be used to transmit signals, as long as those skilled in the art think that the signals CAN be transmitted.

For a better understanding of the above embodiments, the following detailed description is given in conjunction with a specific embodiment. In one embodiment, referring to fig. 1-3, the airspeed detection device includes a horizontal stabilizer 100, a vertical stabilizer 200, a corresponding rotating shaft, a mounting plate 230, and the like, wherein the pitot tube 110 is mounted on the mounting side plate 130 through a tube clamp 120 and is connected to the horizontal stabilizer 100 through a fastener, the horizontal rotating shaft 140 is mounted at the other end of the horizontal stabilizer 100, and the horizontal rotating shaft 140 is fixedly connected to the horizontal stabilizer 100. The horizontal stabilizer 100 is a symmetrical airfoil and has a horizontal axis of rotation 140 mounted at 1/4 of the airfoil chord length. The horizontal stabilizer 100 is connected to the vertical stabilizer 200, and is connected to an attack angle sensor 150 built in the vertical stabilizer 200 through a horizontal rotating shaft 140, and the rotating shaft and the attack angle sensor 150 can rotate with each other. The vertical stabilizer 200 is connected to the sideslip angle sensor 210 installed on the mounting base through a vertical rotating shaft 220, the vertical rotating shaft 220 is fixedly connected to the vertical stabilizer 200, and the vertical rotating shaft 220 can rotate relative to the sideslip angle sensor 210. The horizontal stabilizer 100 is provided with a weight block 170 so that the center of gravity of all the components of the horizontal stabilizer 100 falls at 1/4 of the airfoil chord length, and by balancing the weight block 170, the center of gravity falls at the center of the horizontal rotating shaft 140. In the calm state, the horizontal stabilizer 100 is kept horizontal and the pitot tube 110 is pointed to keep horizontal. The horizontal stabilizer 100 is internally provided with a differential pressure sensor 161, and the total pressure and the static pressure of the pitot tube 110 are measured through 2 pressure measuring hoses 162, so that the differential pressure sensor 161 obtains a corresponding dynamic pressure value. The signal line of the differential pressure sensor 161 is connected to the attack angle sensor 150 through a hollow rotating shaft, and all signals are finally transmitted to the sideslip angle sensor 210 in the same way. The attack angle and the sideslip angle of the airflow shafting relative to the engine body shafting can be obtained through the measuring angle of the corresponding angle sensor, and meanwhile, the measured wind speed value is also accurate because the airspeed head 110 is always parallel to the incoming flow vector.

Because the symmetrical wing profile has airflow stability, when the airflow deviates from the stabilizing plane, the stabilizing plane can generate a corresponding moment to enable the stabilizing plane to rotate relative to the angle sensor. The position toward which pitot tube 110 is oriented is now in the vector direction of the actual incoming flow. By adopting the airspeed detection device, the airspeed measurement direction is consistent with the incoming flow direction in real time, the measurement error caused by the deflection angle of the air flow can be reduced, and the scalar value of the air speed can be accurately measured. The wind speed vector direction with two degrees of freedom can be measured by the attack angle sensor 150 and the sideslip angle sensor 210, the attack angle and the sideslip angle of the incoming flow direction relative to the reference system can be obtained in real time, and therefore the vector value of the incoming flow direction can be obtained.

The airspeed detection device comprises an airspeed head 110, a horizontal stabilizer 100, a horizontal rotating shaft 140 and an attack angle sensor 150, wherein the horizontal stabilizer 100 is a symmetrical airfoil stabilizer, the airspeed head 110 is arranged on a first end face of the horizontal stabilizer 100, the horizontal rotating shaft 140 is arranged on a second end face of the horizontal stabilizer 100, the axial direction of the horizontal rotating shaft 140 is perpendicular to the second end face of the horizontal stabilizer 100, the attack angle sensor 150 and the horizontal rotating shaft 140 can be arranged in a mutually rotating mode, and the pointing direction of the airspeed head 110 is parallel to the extending direction of a chord line of the horizontal stabilizer 100. Because the horizontal stabilizer 100 is a symmetrical airfoil stabilizer, when the incoming flow velocity is parallel to the airfoil chord line, no pitching moment is generated, the horizontal stabilizer 100 can rotate around the axial direction of the horizontal rotating shaft 140, when the deviation angle occurs between the airflow and the horizontal stabilizer 100, the horizontal stabilizer 100 can generate a corresponding moment to enable the horizontal stabilizer 100 to rotate relative to the attack angle sensor 150, and at the moment, the position where the pitot tube 110 faces is the vector direction of the actual incoming flow, the angle of the incoming flow can be detected, and meanwhile, because the pitot tube 110 is always parallel to the incoming flow vector, the measured wind speed value is also accurate, the accuracy of detecting the airspeed can be improved, and the method has important significance for improving the flight safety.

The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.

The above-mentioned embodiments only represent some embodiments of the present invention, and the description thereof is specific and detailed, but not to be construed as limiting the scope of the present invention. It should be noted that, for those skilled in the art, without departing from the spirit of the present invention, several variations and modifications can be made, which are within the scope of the present invention. Therefore, the protection scope of the present invention should be subject to the appended claims.

Claims (10)

1. The utility model provides an airspeed detection device, its characterized in that includes airspeed head, horizontal stabilizer, horizontal rotating shaft and attack angle sensor, horizontal stabilizer is symmetry wing section stabilizer, the airspeed head sets up the first terminal surface of horizontal stabilizer, horizontal rotating shaft set up in the second terminal surface of horizontal stabilizer, horizontal stabilizer can center on horizontal rotating shaft's axial is rotated, attack angle sensor with horizontal rotating shaft can rotate each other and set up, the sensing of airspeed head with the extension direction of the string of a thread of horizontal stabilizer is parallel.

2. The airspeed detection device of claim 1, further comprising a vertical stabilizer disposed perpendicular to the horizontal stabilizer.

3. The airspeed detection device of claim 2, further comprising a vertical shaft and a sideslip angle sensor, wherein the vertical shaft is vertically disposed on an end surface of the vertical stabilizer facing away from the attack angle sensor, and the sideslip angle sensor and the vertical shaft are rotatably disposed with respect to each other.

4. An airspeed detection device as recited in claim 3, further comprising a mounting plate, the sideslip angle sensor being disposed on the mounting plate.

5. The airspeed detection device of claim 3, wherein the vertical rotating shaft is a hollow rotating shaft, and the signal line of the attack angle sensor is connected to the sideslip angle sensor through the vertical rotating shaft.

6. The airspeed detection device of claim 1, further comprising a pipe clamp and a mounting side plate, wherein the airspeed pipe is mounted on the mounting side plate through the pipe clamp, and the mounting side plate is disposed on the first end face of the horizontal stabilizer.

7. The airspeed detection device of claim 1, wherein the horizontal rotating shaft is disposed at a pneumatic center point of the horizontal stabilizer.

8. The airspeed detection device of claim 1, further comprising a counterweight disposed on the horizontal stabilizer.

9. The airspeed detection device of claim 1, further comprising a differential pressure detector disposed within the horizontal stabilizer plane, the differential pressure detector being connected to the airspeed tube.

10. The airspeed detection device of claim 9, wherein the horizontal rotating shaft is a hollow rotating shaft, and the signal line of the differential pressure detector is connected to the attack angle sensor through the horizontal rotating shaft.

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