Embedded atmosphere data sensor system full-flight envelope atmosphere data construction method

Abstract

The invention discloses a full-flight envelope atmosphere data construction method of an embedded atmosphere data sensor system, and belongs to the field of space flight and aviation. The five pressure sensors are conformally designed and installed on the surface of the aircraft, and air pressure data are collected in real time; based on a general aerodynamic law of total pressure, static pressure and Mach number, Mach number solving is carried out by utilizing a linear relation between a specific value of a sensor pressure maximum value and an ideal pressure in design layout and the Mach number; and further synchronously resolving the attack angle, the sideslip angle, the total pressure and the static pressure according to the established linear mapping relationship between the pressure combination operation and the attack angle and the sideslip angle. According to the method, the limitation of a traditional three-point method and a neural network is broken through, high-precision atmospheric parameter calculation in the full flight envelope is achieved, and the atmospheric data construction method can provide high-reliability atmospheric data parameters for flying wing aerodynamic layout aircrafts and is not limited by the aerodynamic configuration of the aircrafts.

Description

Technical Field

[0001] The present invention relates to the field of aerospace, and particularly to a method for constructing atmospheric data of an embedded atmospheric data sensor system over the entire flight envelope. Background Art

[0002] Due to the advantages of good aerodynamic characteristics, small impact on the overall performance of the aircraft, low radar cross-section (RCS), good stealth performance, and effective reduction of aerodynamic heat of the flying wing aerodynamic layout technology, it has been widely used in the aerodynamic design of aircraft and hypersonic weapons. The embedded atmospheric data sensor system designed to be conformal with and installed on the aircraft surface not only does not affect the overall aerodynamic and stealth performance of the aircraft, but also can provide redundant atmospheric data such as barometric altitude, Mach number, airspeed, angle of attack, and sideslip angle through a multi-sensor array. The embedded atmospheric data sensor system is the optimal solution for the atmospheric data measurement device of the flying wing aerodynamic layout aircraft.

[0003] In the prior art, there are documents on the design of embedded atmospheric data sensors. The atmospheric data such as barometric altitude, Mach number, angle of attack, and sideslip angle that can meet the usage accuracy of the aircraft are obtained through the three-point method and the least square method based on the pressure sensed by the pressure measurement holes arranged in a cross shape at the front end of the blunt body, but it is not applicable to the flying wing aerodynamic layout aircraft. The total pressure, static pressure, angle of attack pressure coefficient, and sideslip angle pressure coefficient disclosed in the patent "GB2424285A - Method and apparatus for extending the useful range of air data parameter calculation in a flush air data system" for the embedded atmospheric data system of the flying wing aerodynamic layout aircraft are only applicable to constant flight speeds and constant flight altitudes, and cannot meet the usage requirements of atmospheric data over the entire flight envelope.

[0004] The atmospheric data such as total pressure, static pressure, Mach number, angle of attack, and sideslip angle disclosed in the patent "GB2432914A - Aviation data system based on artificial intelligence" for the embedded atmospheric data system of the flying wing aerodynamic layout aircraft are obtained through neural network algorithms. Although the neural network algorithm has strong non-linear fitting ability, there are defects such as the error performance function falling into a local minimum, and inappropriate numbers of hidden layer neurons may also lead to under-fitting or over-fitting of the network. In addition, the selection of the learning rate lacks theoretical guidance, and the atmospheric data obtained solely by relying on the neural network algorithm cannot guarantee the accuracy of the atmospheric data within the entire flight envelope of the aircraft. Summary of the Invention

[0005] In view of the above deficiencies in the prior art, the present invention provides a method for constructing atmospheric data of an embedded atmospheric data sensor system over the entire flight envelope.

[0006] In order to achieve the above invention objective, the technical solution adopted by the present invention is as follows: An embedded atmospheric data sensor system full flight envelope atmospheric data construction method, comprising the following steps: S1. Layout a plurality of embedded atmospheric data sensors on the surface of a flying wing layout aircraft; S2. During flight, detect the flight air pressure at the installation position in real time and verify its effectiveness, and verify the linear relationship between the ratio of the maximum pressure sensed by the embedded atmospheric data sensors designed by the layout, the ideal total pressure and static pressure, and the Mach number; S3. Calculate the Mach number during flight in real time according to the general distribution law of total pressure, static pressure and Mach number; S4. Calculate the angle of attack, sideslip angle, total pressure and static pressure according to the linear relationship between the pressure sensed by the embedded atmospheric data sensors at different Mach numbers and the angle of attack and the linear relationship with the sideslip angle.

[0007] Further, in S1, five embedded atmospheric data sensors are included, three of which are arranged on the upper fuselage and two are arranged on the lower fuselage.

[0008] Further, S3 specifically includes the following steps: S31. Set an initial value of Mach number M, and calculate the first coefficient K M-1 at the initial value of the set Mach number M according to the pressure sensed by the embedded atmospheric data sensor; S32. Calculate the difference between the total pressure and the static pressure and determine whether the difference between the total pressure and the static pressure is valid. If it is not valid, re-collect the pressure sensed by the embedded atmospheric data sensor. If it is valid, calculate the second coefficient K M-2 at different Mach numbers M according to the pressure sensed by the embedded atmospheric data sensor; S33. Judge the relationship between the first coefficient K M-1 and the second coefficient K M-2 . If |K M-1 - K M-2 | < 0.002, output the Mach number M; if |K M-1 - K M-2 | ≥ 0.002, then increase K M-1 by 0.0001 and return to step S31.

[0009] Further, the calculation method of the first coefficient K M-1 is:

[0010]

[0011] In the formula, P1, P2, P3, P4, and P5 are the pressures sensed by the embedded atmospheric data sensors respectively, is the maximum pressure, and P tis the total pressure, P s is the static pressure.

[0012] Furthermore, the calculation method of the second coefficient K M-2 is as follows:

[0013]

[0014] In the formula, P1, P2, P3, P4, and P5 are the pressures sensed by the embedded air data sensor respectively, P t is the total pressure, P s is the static pressure, and K is an intermediate quantity.

[0015] Furthermore, the specific steps of S4 are as follows: S41. Calculate the values of the coefficient K when the Mach number M is 0.1, 0.3, 0.5, and 0.7 according to the pressure values sensed by the embedded air data sensor, and form a coefficient table of the first coefficient K M-1 ; M-1 Coefficient table; S42. Calculate the values of the coefficient K when the Mach number M is 0.1, 0.3, 0.5, and 0.7 according to the pressure values sensed by the embedded air data sensor, and form a coefficient table of the second coefficient K M-2 ; M-2 Coefficient table; S43. Calculate the angle of attack, sideslip angle, total pressure, and static pressure according to the linear relationship between the pressure operation sensed by the embedded air data sensor at different Mach numbers and the angle of attack and the linear relationship with the sideslip angle.

[0016] Furthermore, the specific calculation methods of the angle of attack, sideslip angle, total pressure, and static pressure in S43 are as follows:

[0017]

[0018]

[0019] In the formula, P1, P2, P3, P4, and P5 are the pressures sensed by the embedded air data sensor respectively, P t is the total pressure, P s is the static pressure, α is the angle of attack, β is the sideslip angle, and M is the Mach number.

[0020] The present invention has the following beneficial effects: This method for constructing air data can provide highly reliable air data parameters for various types of flying-wing aerodynamic layout aircraft, and is not limited by the aerodynamic shape of the aircraft. Description of the Drawings

[0021] Figure 1 It is a schematic layout diagram of an embedded air data sensor in an embodiment of the present invention.

[0022] Figure 2 It is a flow chart for Mach number calculation in an embodiment of the present invention.

[0023] Figure 3 It is a schematic diagram of the distribution law of the ratio of the maximum value of the pressures sensed by 5 embedded air data sensors in an embodiment of the present invention to the ideal total pressure and static pressure and the Mach number.

[0024] Figure 4 It is a schematic diagram of the distribution law of the ratio of the pressures sensed by 5 embedded air data sensors in an embodiment of the present invention after performing mathematical operations in a specific manner to the ideal total pressure and static pressure and the Mach number.

[0025] Figure 5 It is a schematic diagram of the distribution law of the angles of attack after performing mathematical operations in a specific manner on the pressures sensed by 5 embedded air data sensors at different Mach numbers in an embodiment of the present invention.

[0026] Figure 6 It is a schematic diagram of the distribution law of the sideslip angles after performing mathematical operations in a specific manner on the pressures sensed by 5 embedded air data sensors at different Mach numbers in an embodiment of the present invention.

[0027] Figure 7 It is a curve graph of Mach number error in an embodiment of the present invention.

[0028] Figure 8 It is a curve graph of angle of attack error in an embodiment of the present invention.

[0029] Figure 9 It is a curve graph of sideslip angle error in an embodiment of the present invention.

[0030] Figure 10 It is a curve graph of static pressure error in an embodiment of the present invention.

[0031] Figure 11 It is a curve graph of total pressure error in an embodiment of the present invention. Detailed implementation manners

[0032] The following describes the detailed implementation manners of the present invention to facilitate those skilled in the art of the present technology to understand the present invention. However, it should be clear that the present invention is not limited to the scope of the detailed implementation manners. For those of ordinary skill in the art of the present technology, as long as various changes are within the spirit and scope of the present invention defined and determined by the appended claims, these changes are obvious, and all inventions created using the concept of the present invention are within the scope of protection.

[0033] A method for constructing air data over the entire flight envelope of an embedded air data sensor system includes the following steps: S1. Layout and design multiple embedded air data sensors on the surface of a flying wing layout aircraft; As Figure 1 shown, a method for constructing air data over the entire flight envelope of an embedded air data sensor system. In this method, first, 5 embedded air data sensors are conformally installed on the surface of a flying wing layout aircraft. During flight, the flight air pressures at 5 positions are sensed in real time. 3 of the 5 embedded air data sensors are installed on the upper fuselage, and the remaining 2 embedded air data sensors are installed on the lower fuselage.

[0034] S2. During flight, detect the flight air pressure at the installation position in real time and verify its effectiveness, and verify the linear relationship between the ratio of the maximum pressure received by the embedded air data sensors designed by the layout and the ideal total pressure and static pressure and the Mach number; During flight, sense the flight air pressures at 5 positions in real time, and determine whether the pressure values sensed by the 5 embedded air data sensors are valid. If valid, find the maximum pressure sensed by the 5 embedded air data sensors. If invalid, perform detection again.

[0035] The relationship between the total pressure, static pressure and Mach number of a flying wing aerodynamic layout aircraft conforms to the general aerodynamic distribution law. As Figure 3 and Figure 4 shown, the ratio of the maximum value of the pressure sensed by the 5 embedded air data sensors conformally installed on the surface of the flying wing layout aircraft designed by the layout to the ideal total pressure and static pressure is linearly related to the Mach number. According to the general distribution law of total pressure, static pressure and Mach number, the Mach number during flight is calculated in real time, and then the angle of attack, sideslip angle, total pressure and static pressure are calculated by solving the linear relationship between the pressure sensed by the 5 embedded air data sensors and the angle of attack and the linear relationship with the sideslip angle at different Mach numbers.

[0036] S3. Calculate the Mach number during flight in real time according to the general distribution law of total pressure, static pressure and Mach number; In this embodiment, the Mach number M is calculated according to the following process: S31: Calculate the coefficient K M-1 value at different Mach numbers M according to the pressures sensed by the 5 embedded air data sensors. The calculation method is:

[0037]

[0038] In the formula, P1, P2, P3, P4, and P5 are the pressures sensed by the 5 embedded air data sensors respectively, P t is the total pressure, and P s is the static pressure.

[0039] S32. Calculate the difference between the total pressure and the static pressure and determine whether the difference is valid. If it is not valid, re-collect the pressure sensed by the embedded air data sensor. If it is valid, calculate the second coefficient K at different Mach numbers M based on the pressure sensed by the embedded air data sensor. M-2 The calculation method is as follows:

[0040]

[0041] S33. Determine the relationship between the first coefficient K M-1 and the second coefficient K M-2 If |K M-1 - K M-2 | < 0.002, output the Mach number M. If |K M-1 - K M-2 | ≥ 0.002, then increase K M-1 by 0.0001 and return to step S31.

[0042] S4. Calculate the angle of attack, sideslip angle, total pressure, and static pressure based on the linear relationship between the pressure sensed by the embedded air data sensor at different Mach numbers and the angle of attack and the linear relationship with the sideslip angle.

[0043] In this embodiment, the following steps are specifically included: S41. Calculate the coefficient K M-1 values when the Mach number M is 0.1, 0.3, 0.5, and 0.7 based on the pressure values sensed by the embedded air data sensor and form a coefficient table of the first coefficient K M-1 as shown in Table 1: Table 1 K m-1 Coefficient table

[0044] S42. Calculate the coefficient K M-2 values when the Mach number M is 0.1, 0.3, 0.5, and 0.7 based on the pressure values sensed by 5 embedded air data sensors and form a coefficient table of the second coefficient K M-2 as shown in Table 2: Table 2 K m-2 Coefficient table

[0045] S43. Calculate the angle of attack, sideslip angle, total pressure, and static pressure based on the linear relationship between the pressure sensed by the embedded air data sensor at different Mach numbers and the angle of attack and the linear relationship with the sideslip angle The following will explain the specific embodiments of the present invention in detail with reference to the accompanying drawings.

[0046] P1 to P5 are the flight pressures at five positions sensed in real time by five embedded atmospheric data sensors conformally installed with the flying wing aerodynamic layout aircraft 1. Table 1 shows the coefficient K at different Mach numbers M obtained according to Equations (1) and (2). M-1 The values, and Table 2 shows the coefficient K at different Mach numbers M obtained according to Equations (3) and (4). M-2 The values. According to P1 to P5 and Figure 2 the Mach number M calculation flowchart shown, the value of the Mach number M is obtained, and according to Figure 5 the pressure sensed by the five embedded atmospheric data sensors at different Mach numbers M shown, a mathematical operation is performed in a specific manner and the relationship diagram between the angle of attack distribution and Figure 6 the relationship diagram between the pressure sensed by the five embedded atmospheric data sensors at different Mach numbers M shown, a mathematical operation is performed in a specific manner and the sideslip angle distribution, and Equations (5) to (7) are used to calculate the angle of attack α, the sideslip angle β, the total pressure P t and the static pressure P s .

[0047] (1) (2) (3) (4) (5) (6) (7) In the embodiment of the present invention, the calculation accuracy of the Mach number M is a key factor for the angle of attack α, the sideslip angle β, the total pressure P t , and the static pressure P s . In this embodiment, the error curve of the Mach number M calculated according to Figure 2 is as shown in Figure 7 , the error of the Mach number M is not greater than 0.002; the error curve of the angle of attack α is as shown in Figure 8 , the error of the angle of attack α is not greater than 0.5°; the error curve of the sideslip angle β is as shown in Figure 9 , the error of the sideslip angle β is not greater than 0.5°; the error curve of the total pressure P t is as shown in Figure 11 , the error of the total pressure Pt is not greater than 100 Pa; the error curves of the static pressure P s are respectively as shown in Figure 10 , the error of the static pressure P s is not greater than 150 Pa. If higher-precision atmospheric data is required, according to the total pressure P t , the static pressure P sCompensate for the correction amount.

[0048] In the present invention, specific embodiments are used to elaborate on the principles and implementation manners of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manners and application scopes. In summary, the content of this specification should not be construed as a limitation on the present invention.

[0049] Those of ordinary skill in the art will realize that the embodiments described herein are for helping the reader understand the principles of the present invention, and it should be understood that the protection scope of the present invention is not limited to such specific statements and embodiments. Those of ordinary skill in the art can make various other specific deformations and combinations that do not depart from the essence of the present invention based on these technical revelations disclosed by the present invention, and these deformations and combinations are still within the protection scope of the present invention.

Claims

1. An atmospheric data construction method for an embedded atmospheric data sensor system throughout the flight envelope, characterized in that, It includes the following steps: S1. Layout multiple embedded air data sensors on the surface of the flying wing layout aircraft; S2. During flight, detect the flight air pressure at the installation position in real time and verify its effectiveness, through the linear relationship between the ratio of the maximum pressure sensed by the embedded air data sensors designed by the layout and the ideal total pressure and static pressure, and the Mach number; S3. Calculate the Mach number during flight in real time according to the general distribution law of total pressure, static pressure and Mach number; S4. Calculate the angle of attack, sideslip angle, total pressure and static pressure according to the linear relationship between the pressure sensed by the embedded air data sensors at different Mach numbers and the angle of attack and the linear relationship with the sideslip angle.

2. The method for constructing atmospheric data for the full flight envelope of the embedded air data sensor system according to claim 1, wherein In S1, it includes 5 embedded air data sensors, of which three are arranged on the upper fuselage and two are arranged on the lower fuselage.

3. The method for constructing atmospheric data over the entire flight envelope of an embedded atmospheric data sensor system according to claim 1, characterized in that, S3 specifically includes the following steps: S31. Set an initial value of Mach number M, and calculate the value of the first coefficient K at the initial value of Mach number M set according to the pressure sensed by the embedded air data sensor. M-1 value; S32. Calculate the difference between the total pressure and the static pressure, and determine whether the difference between the total pressure and the static pressure is valid. If it is not valid, re-collect the pressure sensed by the embedded air data sensor. If it is valid, calculate the second coefficient K at different Mach numbers M based on the pressure sensed by the embedded air data sensor M-2 value; S33. Determine the first coefficient K M-1 and the second coefficient K M-2 to determine their relationship. If |K M-1 - K M-2 | < 0.002, then output the Mach number M; if |K M-1 - K M-2 | ≥ 0.002, then increase K M-1 by 0.0001 and return to step S31.

4. The method for constructing atmospheric data for the entire flight envelope of an embedded air data sensor system according to claim 3, wherein The first coefficient K M-1 is calculated as follows: Wherein, P1, P2, P3, P4, and P5 are the pressures sensed by the embedded air data sensor respectively. is the maximum pressure, and P t is the total pressure, and P s is the static pressure.

5. The method for constructing atmospheric data for the full flight envelope of the embedded atmospheric data sensor system according to claim 3, characterized in that, The second coefficient K M-2 is calculated as follows: Wherein, P1, P2, P3, P4, and P5 are the pressures sensed by the embedded air data sensor, P t is the total pressure, P s is the static pressure, and K is an intermediate quantity.

6. The method for constructing atmospheric data over the full flight envelope of an embedded air data sensor system according to claim 3, wherein S4 specifically includes the following steps: S41. Calculate the values of coefficient K when the Mach number M is 0.1, 0.3, 0.5, and 0.7 based on the pressure value sensed by the embedded air data sensor and form a coefficient table of the first coefficient K M-1 ; M-1 ​ S42. Calculate the coefficient K values when the Mach number M is 0.1, 0.3, 0.5, and 0.7 based on the pressure value sensed by the embedded air data sensor and form a second coefficient K M-2 coefficient table; M-2 ​ S43. Calculate the angle of attack, sideslip angle, total pressure and static pressure according to the linear relationship between the pressure sensed by the embedded air data sensors at different Mach numbers and the angle of attack and the linear relationship with the sideslip angle.

7. The method for constructing atmospheric data for the entire flight envelope of the embedded atmospheric data sensor system according to claim 6, wherein The specific calculation methods of the angle of attack, sideslip angle, total pressure and static pressure in S43 are: Wherein, P1, P2, P3, P4, and P5 are the pressures sensed by the embedded air data sensor, P t is the total pressure, P s is the static pressure, α is the angle of attack, β is the sideslip angle, and M is the Mach number.

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