Flight sideslip angle resolving method based on static pressure sensor

Abstract

The invention belongs to the technical field of aircraft flight sideslip angle measurement, and discloses a static pressure sensor-based flight sideslip angle calculation method, which comprises the following steps of: symmetrically mounting static pressure sensors on the left and right sides of an aircraft, measuring static pressure acquired by the static pressure sensors on the left and right sides, and calculating to obtain a static pressure difference between the static pressure sensors on the left and right sides; and calculating the flight sideslip angle of the aircraft through the static pressure difference. According to the method, the sideslip angle is calculated through the differential pressure of the static pressure sensors symmetrically installed on the aircraft body left and right, and an original weather vane sensor is avoided, so that the problem that the measured value of the original weather vane sensor is affected by the flight speed of the aircraft is solved; therefore, the number of sensors on two sides of the fuselage is reduced, on one hand, cost is reduced, and on the other hand, appearance characteristics of the aircraft are improved.

Description

Technical Field

[0001] This invention belongs to the field of aircraft sideslip angle measurement technology, and relates to a method for measuring the sideslip angle of an aircraft using static pressure difference, specifically a method for calculating the sideslip angle based on a static pressure sensor. Background Technology

[0002] The sideslip angle is the angle between the direction of flight velocity and the plane of symmetry of the fuselage. The sideslip angle of an aircraft has a significant impact on flight safety. It is typically obtained using a weathervane-type sideslip angle sensor. However, this method is greatly affected by flight speed, exhibiting significant errors at low speeds. Furthermore, it requires specialized equipment, especially when redundant sideslip angle signals are needed, necessitating the installation of multiple weathervane-type sideslip angle sensors. Additionally, weathervane-type sensors also have a significant impact on stealth characteristics. Summary of the Invention

[0003] To address the aforementioned issues, this invention provides a flight sideslip angle calculation method based on a hydrostatic sensor, eliminating the need for a weather vane-type sensor and thus avoiding the adverse effects of weather vane-type sensors on the aircraft. Furthermore, it is unaffected by flight speed.

[0004] The technical solution of the present invention is as follows: A method for calculating the sideslip angle based on static pressure sensors involves symmetrically installing static pressure sensors on the left and right sides of the aircraft. During flight, the static pressure at the static pressure sensors on the left and right sides of the aircraft is measured in real time, and the static pressure difference between the left and right sides of the static pressure sensors is calculated in real time. The real-time sideslip angle of the aircraft is then calculated from the static pressure difference.

[0005] Furthermore, the method for calculating the aircraft's sideslip angle using static pressure difference is as follows: based on CFD simulation or wind tunnel test results, the variation law of static pressure at the static pressure sensor installation location within the flight sideslip angle and angle of attack envelope with the angle of attack and sideslip angle is obtained, and the variation law is used as the formula for calculating the flight sideslip angle using static pressure difference.

[0006] Further, the specific steps include: selecting a moderate sideslip angle, calculating the variation of the difference between the static pressure on the right side of the fuselage and the static pressure on the left side of the fuselage with the angle of attack, and fitting a functional relationship between the static pressure difference and the aircraft's angle of attack; transmitting the pressure measurements from the static pressure sensors on both sides of the aircraft to the flight control computer or air data computer; calculating the static pressure difference between the right side and the corresponding left side of the fuselage in real time during flight, and introducing the aircraft's angle of attack signal in real time, thereby calculating the aircraft's sideslip angle.

[0007] Furthermore, the medium sideslip angle is defined as a 10-degree sideslip angle.

[0008] Furthermore, the fitted functional relationship between the static pressure difference and the aircraft angle of attack is as follows: ΔCP =C pR -C PL =f(α) Among them, C pR For right static pressure, C PL The static pressure is on the left, α is the angle of attack, and ΔC is the static pressure. P This is the static pressure difference.

[0009] Furthermore, the aircraft sideslip angle calculated in real time during flight is: β=10 / ΔC P =10 / f(α) Where β is the aircraft sideslip angle.

[0010] Furthermore, the installation position setting method for the static pressure sensor is as follows: under a fixed angle of attack, confirm whether the pressure difference between the left and right static pressure sensors changes linearly within a 20-degree side slip angle and whether it changes monotonically within a 35-degree side slip angle. If so, it can be used as the installation position for the static pressure sensor.

[0011] Furthermore, it was confirmed that the fixed angles of attack were -4 degrees, 0 degrees, 4 degrees, 8 degrees, and 12 degrees, respectively.

[0012] Technical effects: 1. This invention uses static pressure sensors symmetrically installed on the left and right sides of the aircraft fuselage to calculate the sideslip angle, avoiding the use of the original wind vane sensor, thus solving the problem that the measurement value of the original wind vane sensor is affected by the aircraft's flight speed.

[0013] 2. In order to measure the atmospheric static pressure in the aircraft's flight environment, static pressure sensors are usually arranged symmetrically on both sides of the fuselage. Each static pressure sensor is connected to a pressure measurement module, which can accurately measure the local static pressure value of the fuselage. This invention uses these existing static pressure sensors to reduce the number of sensors on both sides of the fuselage, thereby reducing costs and improving the aircraft's appearance characteristics. Detailed Implementation

[0014] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific design details are set forth in the following detailed description to provide a more complete understanding of the invention. However, it will be apparent to those skilled in the art that the invention can be practiced without some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setup and method set forth below, but covers any improvements, substitutions, and modifications to the structures, methods, and devices without departing from the spirit of the invention.

[0015] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in turn. The present invention will now be described in detail with reference to the embodiments.

[0016] Example 1: A method for calculating the sideslip angle of a flight based on static pressure sensors involves symmetrically installing static pressure sensors on the left and right sides of the aircraft, measuring the static pressure collected by the static pressure sensors on both sides, calculating the static pressure difference between the two sides, and then calculating the sideslip angle of the aircraft based on the static pressure difference.

[0017] The method for calculating the aircraft's sideslip angle using static pressure difference is as follows: Based on CFD simulation or wind tunnel test results, the variation law of static pressure at the static pressure sensor installation location within the flight sideslip angle and angle of attack envelope with the angle of attack and sideslip angle is obtained, and the variation law is used as the formula for calculating the flight sideslip angle using static pressure difference.

[0018] Specifically, the steps include: selecting a moderate sideslip angle, calculating the variation of the difference between the static pressure on the right side of the fuselage and the static pressure on the left side of the fuselage with the angle of attack, and fitting a functional relationship between the static pressure difference and the aircraft's angle of attack; transmitting the pressure measurements from the static pressure sensors on both sides of the aircraft to the flight control computer or air data computer; calculating the static pressure difference between the right side and the corresponding left side of the fuselage in real time during flight, and introducing the aircraft's angle of attack signal in real time, thereby calculating the aircraft's sideslip angle.

[0019] The medium sideslip angle is 10 degrees.

[0020] The fitted functional relationship between static pressure difference and aircraft angle of attack is as follows: ΔC P =C pR -C PL =f(α) Among them, C pR For right static pressure, C PL The static pressure is on the left, α is the angle of attack, and ΔC is the static pressure. P This is the static pressure difference.

[0021] The aircraft's sideslip angle, calculated in real time, is: β=10 / ΔC P =10 / f(α) Where β is the aircraft sideslip angle.

[0022] The installation position of the static pressure sensor is set as follows: Under a fixed angle of attack, confirm whether the pressure difference between the left and right static pressure sensors changes linearly within a 20-degree side slip angle and whether it changes monotonically within a 35-degree side slip angle. If so, it can be used as the installation position of the static pressure sensor.

[0023] Confirm that the fixed angles of attack are -4 degrees, 0 degrees, 4 degrees, 8 degrees and 12 degrees respectively.

[0024] Example 2: Static pressure sensors are symmetrically installed on both sides of the fuselage. This set of static pressure sensors is usually part of the airspeed measurement system.

[0025] Each static pressure sensor is connected to a pressure measurement module, which can directly measure the atmospheric pressure at the location where the static pressure sensor is installed.

[0026] Based on CFD simulation or wind tunnel test results, the static pressure at the installation location of the static pressure sensor within the flight sideslip angle and angle of attack envelope is obtained as a function of the angle of attack and sideslip angle.

[0027] To confirm whether the pressure difference between the left and right static pressure sensors changes linearly within a 20-degree sideslip angle and monotonically within a 35-degree sideslip angle at a fixed angle of attack (typically -4°, 0°, 4°, 8°, and 12°), and under these conditions, the installation position of the static pressure sensor usually meets these conditions. If the linearity is poor or not monotonically variable, a more complex calculation method is required.

[0028] A moderate sideslip angle is selected, typically 10 degrees, but can also be 8 degrees, 12 degrees, etc. The variation of the static pressure difference between the right and left sides of the fuselage with the angle of attack is calculated, and the static pressure difference ΔC is fitted. P Functional relationship with angle of attack α: ΔC P =C pR -C PL =f(α).

[0029] The pressure measurements from the static pressure sensors on both sides of the fuselage are transmitted to the flight control computer or air data computer, which then calculates the real-time static pressure difference ΔC between the right and corresponding left sides of the fuselage. P， And the aircraft's angle of attack signal is introduced in real time.

[0030] C pR For right static pressure, C PL For left static pressure, The sideslip angle β is: β = 10 / ΔC P =10 / f(α).

[0031] Here, 10 corresponds to a 10-degree medium sideslip angle. If 8 degrees or 12 degrees are chosen, then 8 or 12 is divided by ΔC. P .

[0032] The above description is only a preferred embodiment of the present invention. It should be noted that those skilled in the art can make several improvements without departing from the principle of the present invention, and these improvements should also be considered within the scope of protection of the present invention.

Claims

1. A method for calculating the flight sideslip angle based on a static pressure sensor, characterized in that, The static pressure sensors are symmetrically installed on the left and right sides of the airplane, and the static pressures of the left and right sides of the airplane at the static pressure sensors are measured in real time during the flight of the airplane, and the static pressure difference of the left and right sides of the static pressure sensors is calculated in real time, and the real-time flight sideslip angle of the airplane is calculated through the static pressure difference.

2. The method according to claim 1, wherein, The method for calculating the flight sideslip angle of the airplane through the static pressure difference is as follows: according to the CFD simulation or wind tunnel test results, the variation law of the static pressure of the static pressure sensor installation position in the flight sideslip angle and angle of attack envelope range with the angle of attack and the sideslip angle is obtained, and the variation law is used as the formula for calculating the flight sideslip angle through the static pressure difference.

3. The method according to claim 2, wherein, Specifically, the following steps are included: The variation law of the difference between the static pressure of the right side of the airplane and the static pressure of the left side of the airplane with the angle of attack is calculated in a medium sideslip angle state, and a function relationship between the static pressure difference and the angle of attack of the airplane is fitted; the pressure measurement values of the static pressure sensors on the left and right sides of the airplane are transmitted to the flight control computer or the atmospheric data computer, the static pressure difference between the right side of the airplane and the corresponding left side is calculated in real time during the flight of the airplane, and the angle of attack signal of the airplane is introduced in real time, so that the sideslip angle of the airplane is calculated.

4. The method according to claim 3, wherein, The medium sideslip angle state is 10 degrees of sideslip angle.

5. The method according to claim 4, wherein, The fitted function relationship between the static pressure difference and the angle of attack of the airplane is as follows: ΔC P = C pR - C PL = f(a) where C pR is the right static pressure, C PL is the left static pressure, a is the angle of attack, and AC P is the static pressure difference.

6. The method according to claim 5, wherein, The real-time calculated sideslip angle of the airplane during the flight of the airplane is as follows: β = 10 / ΔC P = 10 / f(a) Wherein, β is the sideslip angle of the airplane.

7. The method according to claim 1, wherein the method is characterized by: The installation position of the static pressure sensor is set as follows: under the condition of a fixed angle of attack, it is confirmed whether the pressure difference of the left and right sides of the static pressure sensor changes linearly within 20 degrees of sideslip angle and changes monotonously within 35 degrees of sideslip angle, and if so, the installation position of the static pressure sensor can be confirmed.

8. The method according to claim 7, wherein the method is characterized by, The fixed angle of attack is-4 degrees, 0 degrees, 4 degrees, 8 degrees and 12 degrees, respectively.