CN110046473B - Aircraft atmospheric parameter resolving method and device and computer equipment - Google Patents
Aircraft atmospheric parameter resolving method and device and computer equipment Download PDFInfo
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- CN110046473B CN110046473B CN201910448547.0A CN201910448547A CN110046473B CN 110046473 B CN110046473 B CN 110046473B CN 201910448547 A CN201910448547 A CN 201910448547A CN 110046473 B CN110046473 B CN 110046473B
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Abstract
The embodiment of the application provides an aircraft atmospheric parameter calculating method, an aircraft atmospheric parameter calculating device and a computer device.
Description
Technical Field
The application relates to the field of flight state measurement, in particular to an aircraft atmospheric parameter calculating method and device and computer equipment.
Background
The atmospheric data system is an important onboard electronic system on the airplane, and atmospheric parameters such as an attack angle, a sideslip angle, a Mach number, static pressure, total temperature and the like provided by the atmospheric data system are important for flight efficiency and safe operation of the airplane. At present, a resolving method for atmospheric parameters on an aircraft is a nonlinear optimization method, and an optimal atmospheric parameter estimation value in the least square sense is obtained by utilizing a least square principle and a nonlinear iterative algorithm such as gradient descent after a pressure distribution mathematical model is linearized. However, in practice, it is found that a relatively accurate initial value is required for calculating the atmospheric parameter by using the nonlinear optimization method, and when part of data of the initial value is damaged or lost, the nonlinear iterative algorithm diverges, thereby affecting the calculation accuracy or generating an incorrect calculation result. Therefore, the existing calculation method for the atmospheric parameters is low in stability and easy to generate errors.
Disclosure of Invention
The embodiment of the application aims to provide an aircraft atmospheric parameter calculating method, an aircraft atmospheric parameter calculating device and computer equipment, which are high in stability, high in calculation accuracy and small in error.
The embodiment of the application provides an aircraft atmospheric parameter calculating method, which comprises the following steps:
determining a pressure measuring point scheme for resolving atmospheric parameters on the aircraft from a plurality of pressure measuring point schemes to be selected, and determining a plurality of pressure measuring points for resolving the atmospheric parameters on the aircraft according to the pressure measuring point scheme;
acquiring the pressure of a measuring point of each pressure measuring point when the aircraft flies, and calculating a target characteristic coefficient according to the pressure of the measuring point of each pressure measuring point;
and calculating a target inflow parameter according to the target characteristic coefficient and a pre-constructed mathematical model of the relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight, wherein the target inflow parameter is the atmospheric parameter of the aircraft.
In the implementation process, a pressure measurement point scheme is determined, and a mathematical model of the relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight is constructed according to the pressure measurement point scheme. And for the flight working condition needing to be solved, acquiring the pressure of the pressure measuring point scheme selected when the aircraft flies, calculating a target characteristic coefficient, and finally substituting the target characteristic coefficient into a pre-constructed mathematical model to inversely solve the target inflow parameter to obtain the atmospheric parameter to be solved, thereby realizing the technical effects of high stability, high calculation precision and small error.
Further, the determining a pressure point scheme for calculating atmospheric parameters on the aircraft from a plurality of pressure point schemes to be selected comprises:
determining a plurality of pressure point schemes to be selected according to preset pressure section data and preset pressure point distribution mode data, wherein each pressure point scheme to be selected comprises a plurality of pressure points to be selected and the measuring point pressure of each pressure point to be selected;
calculating a characteristic coefficient corresponding to each pressure point scheme to be selected according to the pressure of the measuring point of each pressure point to be selected in each pressure point scheme to be selected and a preset characteristic coefficient calculation rule;
generating a curve function corresponding to each pressure point scheme to be selected through a cubic spline interpolation algorithm according to the characteristic coefficient corresponding to each pressure point scheme to be selected;
calculating the value of the Jacobian determinant of the curve function corresponding to each pressure point scheme to be selected;
and determining a pressure point scheme to be selected from the multiple pressure point schemes to be selected according to a preset screening rule and the value of the Jacobian of the curve function corresponding to each pressure point scheme to be selected, wherein the pressure point scheme to be selected is used as the pressure point scheme for calculating the atmospheric parameters on the aircraft.
In the implementation process, the pressure measuring point position is selected accurately, so that a pressure measuring point scheme is obtained, the uniqueness of the finally obtained atmospheric parameter solution can be ensured, the stability is further improved, and meanwhile, the calculation precision is also improved.
Further, after determining a pressure point solution for resolving an atmospheric parameter on the aircraft from a plurality of candidate pressure point solutions, the method further comprises:
acquiring a plurality of groups of pressure distribution data of the surface of the aircraft in different flight states from a pre-stored database;
and constructing a mathematical model of the relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight according to the pressure measuring point scheme and the pressure distribution data of the surfaces of the plurality of groups of aircraft.
In the implementation process, before the atmospheric parameters are solved, a mathematical model for solving the atmospheric parameters needs to be constructed in advance, and the mathematical model is obtained by directly calculating a pressure measurement point scheme and pressure distribution data of a plurality of groups of aircraft surfaces. The mathematical model comprises the relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight, and in actual use, the inflow parameter can be reversely solved according to the characteristic coefficient and the mathematical model during flight of the aircraft, so that the atmospheric parameter is obtained.
Further, the multiple sets of pressure distribution data on the aircraft surface include one or more of the multiple sets of pressure distribution data on the aircraft surface detected by the aircraft in the flight experimental state, the multiple sets of pressure distribution data on the aircraft surface detected by the aircraft in the wind tunnel experimental state, and the multiple sets of pressure distribution data on the aircraft surface obtained by the aircraft through CFD calculation.
Further, according to the pressure measurement point scheme and the multiple groups of aircraft surface pressure distribution data in the flight state, a mathematical model of the relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight is constructed, and the mathematical model comprises the following steps:
determining a calculation rule for calculating the characteristic coefficient of the aircraft during flight according to the pressure measuring point scheme and a preset coefficient calculation rule base;
and calculating the characteristic coefficient corresponding to each flight state of the aircraft according to the calculation rule and the aircraft surface pressure distribution data under the multiple groups of flight states.
And constructing a mathematical model of the relationship between the characteristic coefficients and the inflow parameters of the aircraft during flight according to the characteristic coefficients corresponding to the flight states of the aircraft and the surface pressure distribution data of the aircraft in the multiple groups of flight states.
In the implementation process, the obtained mathematical model is a mathematical model of the relation between the characteristic coefficient and the inflow parameter of the aircraft during flight, and in actual use, the inflow parameter can be reversely solved according to the characteristic coefficient and the mathematical model during flight of the aircraft, so that the atmospheric parameter is obtained.
Further, the mathematical model comprises an incoming flow parameter and a characteristic coefficient, wherein the incoming flow parameter comprises an attack angle, a sideslip angle, a Mach number and a static pressure, and the characteristic coefficient comprises an attack angle coefficient, a sideslip angle coefficient, a Mach number coefficient and a static pressure coefficient.
In the implementation process, after the target characteristic coefficient is calculated, the inflow parameters can be inversely solved according to the mathematical model, the solved inflow parameters are the solved aircraft atmospheric parameters, the calculation process is simple, and the calculation precision is high.
Further, the calculating a target characteristic coefficient according to the measured point pressure of each pressure measuring point comprises:
determining a target calculation rule for calculating a target characteristic coefficient according to the pressure measuring point scheme and a preset coefficient calculation rule base;
and calculating a target characteristic coefficient according to the target calculation rule and the measuring point pressure of each pressure measuring point.
In the implementation process, the target characteristic coefficient is obtained through calculation according to the target calculation rule and the measuring point pressure of each pressure measuring point, the physical representation is visual, and the target characteristic coefficient is not only high in association degree with the corresponding atmospheric parameter, but also low in association degree with other parameters, so that the system is ensured to have high precision.
Further, the target incoming flow parameters comprise an attack angle, a sideslip angle, a Mach number and static pressure;
the target characteristic coefficients comprise a target attack angle coefficient, a target sideslip angle coefficient, a target Mach number coefficient and a target static pressure coefficient;
calculating a target inflow parameter according to the target characteristic coefficient and the mathematical model, wherein the target inflow parameter comprises the following steps:
calculating an attack angle, a sideslip angle and a Mach number in the target incoming flow parameters through a nonlinear equation set numerical method and the mathematical model according to a target attack angle coefficient, a target sideslip angle coefficient and a target Mach number coefficient in the target characteristic coefficient;
and calculating the static pressure in the target incoming flow parameters according to a preset static pressure calculation rule and the target static pressure coefficient in the target characteristic coefficients, and further obtaining the target incoming flow parameters.
In the implementation process, through the target characteristic coefficient and the mathematical model, the attack angle, the sideslip angle, the Mach number and the static pressure in the target incoming flow parameters can be respectively calculated, so that the atmospheric parameters are obtained, and the calculation speed and the calculation precision are high.
The second aspect of the invention discloses an aircraft atmospheric parameter resolving device, which comprises:
the scheme determining module is used for determining a pressure measuring point scheme for resolving atmospheric parameters on the aircraft from a plurality of pressure measuring point schemes to be selected;
the pressure measuring point determining module is used for determining a plurality of pressure measuring points for resolving atmospheric parameters on the aircraft according to the pressure measuring point scheme;
the acquisition module is used for acquiring the measuring point pressure of each pressure measuring point when the aircraft flies;
the coefficient calculation module is used for calculating a target characteristic coefficient according to the measuring point pressure of each pressure measuring point;
and the atmospheric parameter calculation module is used for calculating a target inflow parameter according to the target characteristic coefficient and a pre-constructed mathematical model of the relationship between the characteristic coefficient and the inflow parameter when the aircraft flies, wherein the target inflow parameter is the atmospheric parameter of the aircraft.
In the implementation process, the pressure measurement point scheme determining module firstly determines the pressure measurement point scheme, the coefficient calculating module calculates the target characteristic coefficient according to the pressure measurement point scheme, and finally the atmospheric parameter calculating module substitutes the target characteristic coefficient into a pre-constructed mathematical model to reversely solve the target inflow parameter, so that the atmospheric parameter to be solved is obtained, and the technical effects of high stability, high calculation precision and small error are achieved.
In a third aspect, the invention discloses a computer device, comprising a memory for storing a computer program and a processor for executing the computer program to make the computer device execute part or all of the aircraft atmospheric parameter calculation method disclosed in the first aspect.
A fourth aspect of the present invention discloses a computer-readable storage medium storing the computer program for use in the computer apparatus of the third aspect.
Drawings
To more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments of the present application will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and that those skilled in the art can also obtain other related drawings based on the drawings without inventive efforts.
FIG. 1 is a schematic block diagram of a flow chart of an aircraft atmospheric parameter calculation method according to an embodiment of the present disclosure;
FIG. 2 is a schematic view of a cross-sectional pressure measurement point and a mid-sectional pressure measurement point of an aircraft head provided in an embodiment of the present application;
fig. 3 is a schematic numbering diagram of pressure measurement points of a head section and pressure measurement points of a middle section of an aircraft according to an embodiment of the present disclosure;
FIG. 4 is a schematic block diagram of a flow chart of an aircraft atmospheric parameter calculation method provided in the second embodiment of the present application;
FIG. 5 is a block diagram schematically illustrating an aircraft atmospheric parameter resolver according to a third embodiment of the present disclosure;
FIG. 6 is a block diagram schematically illustrating another aircraft atmospheric parameter resolver according to a third embodiment of the present disclosure.
Detailed Description
The technical solutions in the embodiments of the present application will be described below with reference to the drawings in the embodiments of the present application.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures. Meanwhile, in the description of the present application, the terms "first", "second", and the like are used only for distinguishing the description, and are not to be construed as indicating or implying relative importance.
Example 1
The aircraft atmospheric parameter solution method described in the present application is based on an embedded atmospheric data system (FADS). The embedded type atmosphere data system (FADS) measures the pressure distribution of the surface of the aircraft in a mode of embedding the pressure sensor arrays at different positions of the surface of the aircraft, and solves parameters of the atmosphere data by utilizing a model of the relation between the pressure distribution and the atmosphere parameters. The pressure sensor array adopted by the embedded atmospheric data system has the following advantages: no mechanical device is needed, and integration and miniaturization are easier; the pressure sensor is flush with the surface of the aircraft, so that the stealth design is facilitated; the parallel design of a plurality of pressure sensors ensures better redundancy fault-tolerant capability and can provide higher measurement accuracy and reliability.
The atmospheric parameters obtained by the aircraft atmospheric parameter calculation method described in the application can be applied to other avionics systems such as a flight control system, a navigation system, an engine control system and a flight data recording system of the aircraft, and are of great importance to the flight efficiency and safe operation of the aircraft.
The execution subject of the aircraft atmospheric parameter calculation method described in the present application may be an aircraft atmospheric parameter calculation device, a computer device, and the like, where the aircraft atmospheric parameter calculation device or the computer device may be disposed on an aircraft, and this embodiment is not limited at all.
Referring to fig. 1, fig. 1 is a schematic block diagram of a flow of an aircraft atmospheric parameter calculation method according to an embodiment of the present application. As shown in fig. 1, the aircraft atmospheric parameter calculation method includes:
s101, determining a pressure measuring point scheme for calculating atmospheric parameters on the aircraft from the multiple pressure measuring point schemes to be selected, and determining multiple pressure measuring points for calculating the atmospheric parameters on the aircraft according to the pressure measuring point scheme.
In the embodiment of the present application, the aircraft is an apparatus flying in the atmosphere or in the space (space) outside the atmosphere, and includes types of aircrafts, spacecraft, rockets, missiles, and the like, which is not limited in any way.
As an optional implementation manner, a scheme of pressure measurement points to be selected may be constructed in a manner of combining the head section pressure measurement points and the middle section pressure measurement points, and after a plurality of pressure measurement points for resolving atmospheric parameters on the aircraft are determined according to the scheme of pressure measurement points, the obtained plurality of pressure measurement points include the head section pressure measurement points and the middle section pressure measurement points.
In the above embodiment, when selecting the pressure measurement point, it is necessary to select within the FADS application envelope, where the FADS application envelope includes a mach number range, an attack angle range, a sideslip angle range, and the like, and this embodiment is not limited at all. For example, the FADS application envelope comprises Mach number of 0.3-1.2, attack angle of-6-12 degrees and sideslip angle of-6 degrees.
In the above embodiment, please refer to fig. 2, fig. 2 is a schematic diagram of a pressure measurement point of a head section and a pressure measurement point of a middle section of an aircraft according to the present embodiment. As shown in fig. 2, the aircraft surface pressure points include a head section pressure point and a middle section pressure point. Selecting 3-6 sections at the head of the aircraft along the axial direction, and uniformly distributing pressure measuring points at intervals of a circumferential angle of 45 degrees on each section; 3-6 sections are selected in the middle of the aircraft, for rocket type aircraft, middle pressure measuring points are uniformly distributed on each section at intervals of a circumferential angle of 90 degrees, and for aircraft, the upper surface and the lower surface of the aircraft body are respectively taken one.
In the above embodiments, fig. 2 only shows a schematic illustration of aircraft head section pressure measurement points and middle section pressure measurement points, wherein the number of sections selected in the aircraft head and middle section and the distribution manner of pressure measurement points on the aircraft head section and middle section are not limited in any way in the embodiments of the present application.
Referring to fig. 3, fig. 3 is a schematic view illustrating numbering of pressure measurement points of a head section and a middle section of an aircraft according to the present embodiment. As shown in fig. 3, when the scheme of pressure points to be selected is constructed by combining the head section pressure points and the middle section pressure points, when 4 pressure points are selected from the head section pressure points, points numbered 1, 2, 3, and 4 in fig. 3 are selected, and the arrangement mode is a "+" type pressure point distribution mode, and points numbered 5, 6, 7, and 8 in fig. 3 are selected, and the arrangement mode is an "X" type pressure point distribution mode. The middle pressure measuring point can be the pressure measuring point with the same section, and the points with the numbers of 9, 10, 11 and 12 can be selected. Finally, the selected head pressure measurement point and the middle pressure measurement point are combined to obtain a set of pressure measurement point schemes to be selected, for example, when the head pressure measurement point selects the points numbered 1, 2, 3, and 4 in fig. 3, the obtained plurality of pressure measurement points corresponding to the pressure measurement schemes to be selected are the points numbered 1, 2, 3, 4, 9, 10, 11, and 12 in fig. 3, and when the head pressure measurement point selects the points numbered 5, 6, 7, and 8 in fig. 3, the obtained plurality of pressure measurement points corresponding to the pressure measurement schemes to be selected are the points numbered 5, 6, 7, 8, 9, 10, 11, and 12 in fig. 3.
In the above embodiment, a plurality of pressure measurement point schemes to be selected can be obtained by arranging and combining different pressure measurement cross sections and different pressure measurement point distribution modes. For example, if the head and the middle of the aircraft are respectively provided with 5 pressure measuring point sections, and two distribution modes of a plus type and an X type are considered, 5 × 2 sets, namely 50 sets of candidate pressure measuring point schemes to be selected can be obtained in total.
After step S101, the following steps are also included:
s102, measuring point pressure of each pressure measuring point is obtained when the aircraft flies, and a target characteristic coefficient is calculated according to the measuring point pressure of each pressure measuring point.
As an alternative embodiment, the survey point pressure of each survey point during the flight of the aircraft can be measured by an embedded array of pressure sensors at different locations on the aircraft surface by an embedded atmospheric data system (FADS).
In the embodiment of the application, according to the pressure of the measuring point of each pressure measuring point when the aircraft flies, a preset characteristic coefficient calculation rule can be adopted to calculate the target characteristic coefficient according to the pressure of the measuring point of each pressure measuring point.
S103, calculating a target inflow parameter according to the target characteristic coefficient and a pre-constructed mathematical model of the relationship between the characteristic coefficient and the inflow parameter when the aircraft flies, wherein the target inflow parameter is the atmospheric parameter of the aircraft.
In the embodiment of the present application, the step S103 of building the mathematical model may occur before the step S102, or may occur after the step S102, and may be executed simultaneously with the step S102, which is not limited in this embodiment of the present application.
In the embodiment of the present application, the atmospheric parameter includes one or more of an angle of attack, a sideslip angle, a mach number, a static pressure, a total temperature, and the like, which is not limited in any way, and is crucial to the flight efficiency and safe handling of the aircraft.
In the embodiment of the present application, angle of Attack (also called Angle of Attack) is a fluid mechanics term. For the missile, the angle of attack defines the included angle between the projection of the velocity vector V on the longitudinal symmetry plane and the longitudinal axis of the missile, the raising is positive, the lowering is negative, and the common symbol is alpha.
In the embodiment of the present application, the sideslip angle refers to an included angle between the flight velocity vector V of the aircraft and a longitudinal symmetry plane thereof. And if the velocity vector V is on the right side of the symmetry plane, the corresponding sideslip angle is positive, otherwise, the corresponding sideslip angle is negative. The sideslip angle is an important parameter in determining the attitude of an aircraft.
In the embodiment of the present application, the mach number is an important dimensionless parameter for characterizing the compressibility degree of a fluid in fluid mechanics, and is denoted as Ma, and is defined as a ratio of a velocity v of a certain point in a flow field to a local sound velocity c of the point, that is, ma = v/c.
In the embodiment of the application, the static pressure refers to the pressure on the surface when an object is at rest or moves linearly at a constant speed. The unit is as follows: pa. In the design and operation of an aircraft, static pressure is the air pressure in the aircraft's static pressure system. The altimeter of the aircraft is controlled by a static pressure system, and the airspeed indicator of the aircraft is controlled by the static pressure system and a pitot pressure system.
In the embodiment of the application, after the target characteristic coefficient is calculated, the target characteristic coefficient is substituted into a pre-constructed mathematical model of the relationship between the characteristic coefficient and the inflow parameter when the aircraft flies for reverse calculation, and the obtained target inflow parameter is the aircraft atmospheric parameter to be solved.
In the aircraft atmospheric parameter calculation method described in fig. 1, a pressure measurement point scheme is determined, a target characteristic coefficient is calculated according to the pressure measurement point scheme, and the target characteristic coefficient is substituted into a pre-constructed mathematical model to reversely solve a target inflow parameter, so that an atmospheric parameter to be calculated is obtained. Therefore, the technical effects of high stability, high calculation accuracy and small error can be realized by implementing the aircraft atmospheric parameter calculation method described in the figure 1.
Example 2
Referring to fig. 4, fig. 4 is a schematic block diagram of a flow of an aircraft atmospheric parameter calculation method according to an embodiment of the present application. As shown in fig. 4, the aircraft atmospheric parameter calculation method includes:
s201, determining a plurality of pressure point schemes to be selected according to preset pressure section data and preset pressure point distribution mode data.
In the embodiment of the present application, each scheme of pressure points to be measured includes a plurality of pressure points to be measured and a pressure of a measuring point of each pressure point to be measured, which is not limited in any way. The pressure value of the pressure point to be selected is generally obtained by a Computational Fluid Dynamics (CFD) method or a wind tunnel test method.
S202, calculating a characteristic coefficient corresponding to each scheme of the pressure points to be measured according to the measuring point pressure of each scheme of the pressure points to be measured and a preset characteristic coefficient calculation rule.
As an alternative embodiment, the feature coefficient calculation rule includes a feature coefficient calculation formula of a "+" type distribution of the head pressure measurement points and a feature coefficient calculation formula of an "X" type distribution of the head pressure measurement points.
Specifically, taking the pressure measurement point labels shown in fig. 3 as an example, the calculation formula of the "+" shaped distribution characteristic coefficients of the head pressure measurement points is as follows:
the calculation formula of the characteristic coefficients of the X-shaped distribution of the head pressure measuring points is as follows:
where K α represents an angle of attack coefficient, K β represents a sideslip angle coefficient, km represents a Mach number coefficient, kp ∞ Expressing static pressure coefficient, alpha expressing atmospheric parameter incidence angle, beta expressing sideslip angle, M expressing Mach number, p ∞ Denotes static pressure, P 1 、P 2 、P 3 、P 4 、P 5 、P 6 、P 7 、P 8 、P 9 、P 10 、P 11 、P 12 The pressures of the measuring points corresponding to the 12 pressure measuring points at the head part and the middle part shown in the figure 3 are correspondingly represented respectively.
In the above embodiment, each set of pressure point to be measured scheme can obtain K α, K β, and Km according to the characteristic coefficient rule, where K α, K β, and Km are values of (K α, K β, km) on the flight combination lattice point (α, β, M).
After step S202, the following steps are also included:
and S203, generating a curve function corresponding to each pressure point scheme to be detected through a cubic spline interpolation algorithm according to the characteristic coefficient corresponding to each pressure point scheme to be detected.
In the embodiment of the present application, after the characteristic coefficient corresponding to each pressure point to be selected is calculated, the value of (K α, K β, km) at the flight combination lattice point (α, β, M) may be expanded by a cubic spline interpolation algorithm to be a curve function of (K α, K β, km) with respect to (α, β, M) within the application envelope of the FADS, which is denoted as F, that is, (K α, K β, km) = F (α, β, M).
And S204, calculating the value of the Jacobian determinant of the curve function corresponding to each pressure point scheme to be measured.
In the embodiment of the present application, the value of the jacobian is the value of the jacobian corresponding to the jacobian matrix.
S205, determining a pressure point scheme to be selected from the pressure point schemes to be selected according to a preset screening rule and the value of the Jacobian of the curve function corresponding to each pressure point scheme to be selected, wherein the pressure point scheme to be selected is used as the pressure point scheme for resolving the atmospheric parameters on the aircraft.
Theoretically, the Jacobian matrix of the curve function F is set as A, and as long as the determinant value | A | of the Jacobian matrix A of the curve function F in the FADS application envelope is not zero, the uniqueness of the solution in the FADS application envelope can be ensured, and the problems of generating wrong resolving results and the like are effectively avoided.
In the embodiment of the present application, since (K α, K β, km) = F (α, β, M), when the flight lattice point (α, β, M) is dense, the value | a | of the jacobian matrix a of the curve function F keeps fully positive, or fully negative, it can satisfy that the FADS application envelope | a | is not zero. Thus, the predetermined filtering rules include one or more of the value | a | of the jacobian or the value | a | of the jacobian being non-zero, the minimum number of pressure-measuring points determined in accordance with the pressure-measuring point scheme to be selected, the conditional number of the jacobian matrix a, the ratio of prime coefficients to non-prime coefficients of the jacobian matrix a, etc., without any limitation to this embodiment.
In the embodiment of the present application, the pressure measurement point scheme for calculating the atmospheric parameter on the aircraft can be determined from a plurality of pressure measurement point schemes to be selected by executing the steps S201 to S205.
In the embodiment of the application, the pressure values of all pressure measurement points to be selected on the surface of the aircraft under the working condition of a plurality of inflow parameter combinations are required. The pressure value is generally obtained by a Computational Fluid Dynamics (CFD) method or a wind tunnel test method.
After step S205, the following steps are also included:
and S206, determining a plurality of pressure measuring points for resolving atmospheric parameters on the aircraft according to the pressure measuring point scheme.
And S207, acquiring multiple groups of pressure distribution data of the surface of the aircraft in different flight states from a pre-stored database.
In the embodiment of the present application, the different flight states are determined by FADS application envelopes, for example, when the FADS application envelopes include mach numbers of 0.3 to 1.2, angles of attack of-6 to 12 °, and sideslip angles of-6 to 6 °, M =0.3, 0.5, 0.6, 0.7, 0.8, 0.9, 1.0, 1.1, and 1.2, angles of attack of-6 to 12 °, intervals of 2 °, and sideslip angles of-6 to 6 ° may be selected as different flight states to be cross-combined.
In this embodiment of the present application, the multiple sets of pressure distribution data on the surface of the aircraft include one or more of multiple sets of pressure distribution data on the surface of the aircraft detected by the aircraft in a flight experimental state, multiple sets of pressure distribution data on the surface of the aircraft detected by the aircraft in a wind tunnel experimental state, and multiple sets of pressure distribution data on the surface of the aircraft calculated by the aircraft through a Fluid dynamic Dynamics (CFD) method, which is not limited in this embodiment of the present application.
After step S207, the following steps are also included:
and S208, constructing a mathematical model of the relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight according to the pressure measuring point scheme and the pressure distribution data of the surfaces of the plurality of groups of aircraft.
In the embodiment of the application, the mathematical model comprises incoming flow parameters and characteristic coefficients, wherein the incoming flow parameters comprise an attack angle, a sideslip angle, a Mach number and static pressure, and the characteristic coefficients comprise an attack angle coefficient, a sideslip angle coefficient, a Mach number coefficient and a static pressure coefficient.
In the embodiment of the application, the mathematical model of the relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight can be obtained by calculation according to the pressure measuring point scheme and the pressure distribution data of the surface of the aircraft.
As an optional implementation manner, after a mathematical model of the relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight is obtained, the mathematical model can be optimized by adding flight combination working condition data, wind tunnel test data or flight test data, and the calculation accuracy of calculating the atmospheric parameter according to the mathematical model is further improved.
In the above embodiment, the flight combination condition data, that is, data such as pressure at a pressure measurement point and a characteristic coefficient value of the aircraft surface under the flight combination condition (α, β, M), may be encrypted and calculated by a Fluid dynamic Dynamics (CFD) method to construct a mathematical model, and the obtained mathematical model is finer, so as to reduce an interpolation error of the characteristic coefficient.
In the embodiment of the present application, steps S207 to S208 may occur after step S205 and before step S210, and the embodiment of the present application only shows one execution sequence of the steps.
As an optional implementation manner, constructing a mathematical model of a relationship between a characteristic coefficient and an inflow parameter of an aircraft during flight according to a pressure measurement point scheme and multiple sets of aircraft surface pressure distribution data in a flight state may include the following steps:
determining a calculation rule for calculating the characteristic coefficient of the aircraft during flight according to the pressure point measuring scheme and a preset coefficient calculation rule base;
and calculating the characteristic coefficient corresponding to the flight state of each aircraft according to the calculation rule and the aircraft surface pressure distribution data under the multiple groups of flight states.
And constructing a mathematical model of the relationship between the characteristic coefficients and the inflow parameters of the aircraft during flight according to the characteristic coefficients corresponding to the flight states of each aircraft and the surface pressure distribution data of the aircraft in multiple groups of flight states.
In the above embodiment, the obtained mathematical model is a mathematical model of a relationship between the characteristic coefficient and the inflow parameter when the aircraft flies, and in actual use, the inflow parameter can be inversely solved according to the characteristic coefficient and the mathematical model when the aircraft flies, so as to obtain the atmospheric parameter.
In the above embodiments, the experimental pressure values are obtained by the following methods: (1) directly inheriting from the data obtained in the first step; (2) testing and measuring by a wind tunnel test method; (3) The test result is measured by a flight test method, and the embodiment of the application is not limited. The method comprises the following steps of obtaining calculated pressure distribution data of the surface of the aircraft in different incoming flow states through CFD (Computational Fluid Dynamics), wherein the method is low in cost; the method has the advantages that the actually measured pressure distribution data of the surface of the aircraft, detected by the aircraft in different inflow states, are obtained through flight tests, the cost is high, the obtained data are consistent with the actual flight state, and the accuracy of the mathematical model established through the method is good under the condition that the inflow parameters of the aircraft are reliable; the method has the advantages that multiple groups of experimental pressure distribution data of the aircraft surface section, detected by the aircraft in different wind tunnel experimental states, are obtained through wind tunnel experiments, the cost is controllable, and the precision is high.
After step S208, the following steps are also included:
s209, acquiring the pressure of the measuring point of each pressure measuring point when the aircraft flies, and calculating a target characteristic coefficient according to the pressure of the measuring point of each pressure measuring point.
As an alternative embodiment, calculating the target characteristic coefficient according to the measured point pressure of each pressure measuring point may include the following steps:
determining a target calculation rule for calculating a target characteristic coefficient according to the pressure point scheme and a preset coefficient calculation rule base;
and calculating a target characteristic coefficient according to the target calculation rule and the measured point pressure of each pressure measuring point.
In the above embodiment, the preset coefficient calculation rule base is the same as the preset feature coefficient calculation rule, and includes a feature coefficient calculation formula of a "+" type distribution of head pressure measurement points and a feature coefficient calculation formula of an "X" type distribution of head pressure measurement points.
S210, calculating an attack angle, a sideslip angle and a Mach number in target incoming flow parameters through a nonlinear equation set numerical method and a mathematical model according to a target attack angle coefficient, a target sideslip angle coefficient and a target Mach number coefficient in the target characteristic coefficient.
In the embodiment of the application, the target incoming flow parameters comprise an attack angle, a sideslip angle, a Mach number and static pressure; the target characteristic coefficients comprise a target attack angle coefficient, a target sideslip angle coefficient, a target Mach number coefficient and a target static pressure coefficient.
In the embodiment of the application, when a target incoming flow parameter is calculated, a cubic spline interpolation algorithm is first used to generate curve functions between an attack angle coefficient K α, a sideslip angle coefficient K β and a mach number coefficient Km and an attack angle α, a sideslip angle β and a mach number M, which are marked as F, that is, (K α, K β, km) = F (α, β, M), and similarly, a cubic spline interpolation algorithm is used to generate a static pressure coefficient Kp ∞ With angles of attack alpha, sideslip angle beta and Mach number MCurve function, denoted Fp, i.e. Kp ∞ ＝Fp ∞ (α, β, M). And then, calculating a target attack angle coefficient K alpha _ cal, a target sideslip angle coefficient K beta _ cal and a target Mach number coefficient Km _ cal according to the measuring point pressure of each measuring point when the aircraft flies.
In the embodiment of the present application, the nonlinear equation set numerical method may be a newton iteration method, a quasi-newton iteration method, a genetic algorithm, a gradient method, or the like, and the embodiment of the present application is not limited at all.
As an alternative, the non-linear equation set numerical method may be a newton iteration method. For example, newton's iteration is first used to solve (α, β, M) = (K α, K β, km) and inversely (α, β, M), and the obtained results are (α _ cal, β _ cal, M _ cal), which are the attack angle, the sideslip angle and the mach number in the target incoming flow parameter.
In the above embodiment, when (α _ cal, β _ cal, M _ cal) is calculated by newton's iteration, it is possible to determine (K α, K β, km) near (α _ cal, β _ cal, M _ cal) from a mathematical model, and then to use (α, β, M) corresponding to (K α, K β, km) as an initial value of newton's iteration.
After step S210, the method further includes the following steps:
s211, calculating static pressure in the target incoming flow parameters according to the preset static pressure calculation rule and the target static pressure coefficients in the target characteristic coefficients, and further obtaining the target incoming flow parameters.
In the embodiment of the present application, static pressure p is calculated ∞ And (c) calculating a value of the Fp function at a point (alpha _ cal, beta _ cal, M _ cal), namely a target static pressure coefficient, and recording the value as Kp _ cal, and then calculating the static pressure in the target inflow parameter according to a preset static pressure calculation rule and the target static pressure coefficient in the target characteristic coefficient.
Taking fig. 2 and fig. 3 provided in the first embodiment as an example, the calculation formula of the preset static pressure calculation rule may be expressed as:
P ∞ _cal＝(P 9 +P 10 +P 11 +P 12 )/(4*Kp_cal)；
finally, the target incoming flow parameters include the angle of attack α _ cal,Slip angle β _ cal, mach number M _ cal, incoming hydrostatic pressure p ∞ Cal is calculated and these parameters may be used in the flight control system of the aircraft (e.g., as input parameters to a control gain table, etc.).
In the embodiment of the present application, the steps S210 to S211 are executed, so that a target inflow parameter can be calculated according to the target characteristic coefficient and a pre-constructed mathematical model of a relationship between the characteristic coefficient and the inflow parameter when the aircraft flies, and the target inflow parameter is an aircraft atmospheric parameter.
Therefore, the technical effects of high atmospheric calculation accuracy and small error are realized by implementing the aircraft atmospheric parameter calculation method described in the figure 4.
Example 3
Referring to fig. 5, fig. 5 is a schematic block diagram of a structure of an aircraft atmospheric parameter resolver according to an embodiment of the present application. As shown in fig. 5, the aircraft atmospheric parameter solver comprises:
and the scheme determining module 310 is used for determining a pressure point scheme for resolving the atmospheric parameter on the aircraft from a plurality of pressure point schemes to be selected.
And the pressure measuring point determining module 320 is used for determining a plurality of pressure measuring points for resolving atmospheric parameters on the aircraft according to the pressure measuring point scheme.
And the obtaining module 330 is configured to obtain the pressure of the measurement point of each pressure measurement point when the aircraft flies.
And the coefficient calculating module 340 is used for calculating a target characteristic coefficient according to the measured point pressure of each measured point.
And the atmospheric parameter calculation module 350 is configured to calculate a target inflow parameter according to the target characteristic coefficient and a pre-constructed mathematical model of a relationship between the characteristic coefficient and the inflow parameter when the aircraft flies, where the target inflow parameter is an aircraft atmospheric parameter.
Referring to fig. 6 as an alternative implementation, fig. 6 is a schematic block diagram of a structure of another aircraft atmospheric parameter resolver according to an embodiment of the present disclosure. The aircraft atmospheric parameter solver shown in fig. 6 is optimized by the aircraft atmospheric parameter solver shown in fig. 5. As shown in fig. 6, the scheme determining module 310 includes:
and the preselection scheme determining submodule 311 is configured to determine a plurality of pressure point schemes to be selected according to preset pressure section data and preset pressure point distribution mode data, where each pressure point scheme to be selected includes a plurality of pressure points to be selected and a measurement point pressure of each pressure point to be selected.
The characteristic coefficient calculating submodule 312 is configured to calculate a characteristic coefficient corresponding to each scheme of the pressure points to be measured according to the pressure of the pressure point to be measured in each scheme of the pressure points to be measured and a preset characteristic coefficient calculating rule.
And the curve function calculation submodule 313 is used for generating a curve function corresponding to each pressure point scheme to be selected through a cubic spline interpolation algorithm according to the characteristic coefficient corresponding to each pressure point scheme to be selected.
And the determinant value operator module 314 is configured to calculate a value of a jacobian of the curve function corresponding to each pressure point scheme to be measured.
And the scheme selection submodule 315 is configured to determine, according to the preset screening rule and the value of the jacobian of the curve function corresponding to each pressure point scheme to be selected, one pressure point scheme to be selected from the plurality of pressure point schemes to be selected, and use the pressure point scheme as a pressure point scheme for resolving the atmospheric parameter on the aircraft.
As an optional embodiment, the aircraft atmospheric parameter solver further comprises:
and the pressure distribution data acquisition module 360 is used for acquiring multiple groups of pressure distribution data of the aircraft surface in different flight states from a pre-stored database after determining a pressure point scheme for resolving atmospheric parameters on the aircraft from multiple pressure point schemes to be selected.
In this embodiment of the present application, the multiple sets of pressure distribution data of the aircraft surface include one or more of multiple sets of pressure distribution data of the aircraft surface detected by the aircraft in a flight experimental state, multiple sets of pressure distribution data of the aircraft surface detected by the aircraft in a wind tunnel experimental state, and multiple sets of pressure distribution data of the aircraft surface calculated by the aircraft through a Fluid dynamic Dynamics (CFD) method, which is not limited in this embodiment of the present application.
And the model building module 370 is used for building a mathematical model of the relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight according to the pressure measuring point scheme and the pressure distribution data of the surfaces of a plurality of groups of aircraft.
In the above embodiment, the mathematical model includes an incoming flow parameter and a characteristic coefficient, wherein the incoming flow parameter includes an angle of attack, a sideslip angle, a mach number, and a static pressure, and the characteristic coefficient includes an angle of attack coefficient, a sideslip angle coefficient, a mach number coefficient, and a static pressure coefficient.
In the above embodiment, after the scenario determination module 310 determines the pressure measurement point scenario for resolving the atmospheric parameter on the aircraft from the multiple pressure measurement point scenarios to be selected, the pressure distribution data acquisition module 360 may be further triggered to perform the step of acquiring multiple sets of pressure distribution data of the aircraft surface in different flight states from the pre-stored database.
As an alternative embodiment, the model building module 370 includes:
and the calculation rule determining submodule 371 is configured to determine a calculation rule for calculating a characteristic coefficient of the aircraft during flight according to the pressure measurement point scheme and a preset coefficient calculation rule base.
And the calculating submodule 372 is used for calculating the characteristic coefficient corresponding to each aircraft flight state according to the calculation rule and the multiple groups of aircraft surface pressure distribution data in the flight states.
And the building submodule 373 is configured to build a mathematical model of a relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight according to the characteristic coefficient corresponding to each aircraft flight state and multiple sets of aircraft surface pressure distribution data in the flight state.
As an optional implementation manner, the coefficient calculating module 340 includes:
and a rule determining submodule 341, configured to determine a target calculation rule for calculating the target feature coefficient according to the pressure measurement point scheme and a preset coefficient calculation rule base.
And the target coefficient calculating submodule 342 is used for calculating a target characteristic coefficient according to the target calculating rule and the measured point pressure of each measured point.
As an alternative embodiment, the atmospheric parameter calculation module 350 includes:
the first part calculation submodule 351 is used for calculating the attack angle, the sideslip angle and the mach number in the target incoming flow parameters through a nonlinear equation set numerical method and a mathematical model according to the target attack angle coefficient, the target sideslip angle coefficient and the target mach number coefficient in the target characteristic coefficient.
The second part calculation submodule 352 calculates the static pressure in the target incoming flow parameter according to the preset static pressure calculation rule and the target static pressure coefficient in the target characteristic coefficient, so as to obtain the target incoming flow parameter.
In the above embodiment, the target incoming flow parameters include an angle of attack, a sideslip angle, a mach number, and a static pressure; the target characteristic coefficients comprise a target attack angle coefficient, a target sideslip angle coefficient, a target Mach number coefficient and a target static pressure coefficient.
Therefore, the aircraft atmospheric parameter resolving device described in the embodiment is high in stability, high in calculation accuracy and small in error.
In addition, the invention also provides computer equipment. The computer device comprises a memory and a processor, wherein the memory can be used for storing a computer program, and the processor can execute the computer program so as to enable the computer device to execute the functions of the method or the modules in the question-answer interaction device.
The memory may include a storage program area and a storage data area, wherein the storage program area may store an operating system, an application program required for at least one function (such as a sound playing function, an image playing function, etc.), and the like; the storage data area may store data (such as audio data, a phonebook, etc.) created according to the use of the mobile terminal, and the like. Further, the memory may include high speed random access memory, and may also include non-volatile memory, such as at least one magnetic disk storage device, flash memory device, or other volatile solid state storage device.
The embodiment also provides a computer storage medium for storing a computer program used in the computer device.
In the embodiments provided in the present application, it should be understood that the disclosed apparatus and method can be implemented in other ways. The apparatus embodiments described above are merely illustrative, and for example, the flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of apparatus, methods and computer program products according to various embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
In addition, functional modules in the embodiments of the present application may be integrated together to form an independent part, or each module may exist separately, or two or more modules may be integrated to form an independent part.
The functions, if implemented in the form of software functional modules and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present application or portions thereof that substantially contribute to the prior art may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present application. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk, or an optical disk, and various media capable of storing program codes.
The above embodiments are merely examples of the present application and are not intended to limit the scope of the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present application shall be included in the protection scope of the present application. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined or explained in subsequent figures.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present application, and shall be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
It should be noted that, in this document, relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising a … …" does not exclude the presence of another identical element in a process, method, article, or apparatus that comprises the element.
Claims (9)
1. An aircraft atmospheric parameter calculation method is characterized by comprising the following steps:
determining a pressure measuring point scheme for resolving atmospheric parameters on the aircraft from a plurality of pressure measuring point schemes to be selected, and determining a plurality of pressure measuring points for resolving the atmospheric parameters on the aircraft according to the pressure measuring point scheme;
acquiring the pressure of a measuring point of each pressure measuring point when the aircraft flies, and calculating a target characteristic coefficient according to the pressure of the measuring point of each pressure measuring point;
calculating a target inflow parameter according to the target characteristic coefficient and a pre-constructed mathematical model of the relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight, wherein the target inflow parameter is the atmospheric parameter of the aircraft;
wherein, the calculating the characteristic coefficient of the target according to the measuring point pressure of each pressure measuring point comprises the following steps:
determining a target calculation rule for calculating a target characteristic coefficient according to the pressure measuring point scheme and a preset coefficient calculation rule base;
and calculating a target characteristic coefficient according to the target calculation rule and the measuring point pressure of each pressure measuring point.
2. The aircraft atmospheric parameter calculation method according to claim 1, wherein the determining of the pressure point scheme for calculating the atmospheric parameter on the aircraft from among a plurality of pressure point schemes to be selected comprises:
determining a plurality of pressure point schemes to be selected according to preset pressure section data and preset pressure point distribution mode data, wherein each pressure point scheme to be selected comprises a plurality of pressure points to be selected and the measuring point pressure of each pressure point to be selected;
calculating a characteristic coefficient corresponding to each pressure point scheme to be selected according to the pressure of the measuring point of each pressure point to be selected in each pressure point scheme to be selected and a preset characteristic coefficient calculation rule;
generating a curve function corresponding to each pressure point scheme to be selected through a cubic spline interpolation algorithm according to the characteristic coefficient corresponding to each pressure point scheme to be selected;
calculating the value of the Jacobian determinant of a curve function corresponding to each pressure point scheme to be selected;
and determining a pressure point scheme to be selected from the multiple pressure point schemes to be selected according to a preset screening rule and the value of the Jacobian of the curve function corresponding to each pressure point scheme to be selected, wherein the pressure point scheme to be selected is used as the pressure point scheme for calculating the atmospheric parameters on the aircraft.
3. The aircraft atmospheric parameter calculation method according to claim 1, wherein after the determination of the pressure point scheme for calculating the atmospheric parameter on the aircraft from among the plurality of pressure point schemes to be selected, the method further comprises:
acquiring a plurality of groups of pressure distribution data of the surface of the aircraft in different flight states from a pre-stored database;
and constructing a mathematical model of the relationship between the characteristic coefficient and the inflow parameter of the aircraft during flight according to the pressure measuring point scheme and the pressure distribution data of the surfaces of the plurality of groups of aircraft.
4. The aircraft atmospheric parameter calculation method according to claim 3, wherein the multiple sets of pressure distribution data of the aircraft surface include one or more of multiple sets of pressure distribution data of the aircraft surface detected by the aircraft in a flight experiment state, multiple sets of pressure distribution data of the aircraft surface detected by the aircraft in a wind tunnel experiment state, and multiple sets of pressure distribution data of the aircraft surface calculated by the aircraft through CFD.
5. The aircraft atmospheric parameter calculation method according to claim 4, wherein a mathematical model of a relationship between a characteristic coefficient and an inflow parameter of the aircraft during flight is constructed according to the pressure measurement point scheme and a plurality of sets of aircraft surface pressure distribution data in flight states, and the mathematical model comprises:
determining a calculation rule for calculating the characteristic coefficient of the aircraft during flight according to the pressure measuring point scheme and a preset coefficient calculation rule base;
calculating a characteristic coefficient corresponding to each flight state of the aircraft according to the calculation rule and the aircraft surface pressure distribution data under the multiple groups of flight states;
and constructing a mathematical model of the relationship between the characteristic coefficients and the inflow parameters of the aircraft during flight according to the characteristic coefficients corresponding to the flight states of the aircraft and the aircraft surface pressure distribution data under the multiple groups of flight states.
6. The aircraft atmospheric parameter calculation method of claim 3, wherein the mathematical model comprises incoming flow parameters and characteristic coefficients, wherein the incoming flow parameters comprise angle of attack, sideslip angle, mach number, and static pressure, and the characteristic coefficients comprise angle of attack coefficients, sideslip angle coefficients, mach number coefficients, and static pressure coefficients.
7. The aircraft atmospheric parameter calculation method of claim 1, wherein the target incoming flow parameters include angle of attack, sideslip angle, mach number, and static pressure;
the target characteristic coefficients comprise a target attack angle coefficient, a target sideslip angle coefficient, a target Mach number coefficient and a target static pressure coefficient;
calculating a target incoming flow parameter according to the target characteristic coefficient and the mathematical model, wherein the method comprises the following steps:
calculating an attack angle, a sideslip angle and a Mach number in the target incoming flow parameters through a nonlinear equation set numerical method and the mathematical model according to a target attack angle coefficient, a target sideslip angle coefficient and a target Mach number coefficient in the target characteristic coefficient;
and calculating the static pressure in the target incoming flow parameters according to a preset static pressure calculation rule and the target static pressure coefficient in the target characteristic coefficients, and further obtaining the target incoming flow parameters.
8. An aircraft atmospheric parameter solver, comprising:
the scheme determining module is used for determining a pressure measuring point scheme for resolving atmospheric parameters on the aircraft from a plurality of pressure measuring point schemes to be selected;
the pressure measuring point determining module is used for determining a plurality of pressure measuring points for resolving atmospheric parameters on the aircraft according to the pressure measuring point scheme;
the acquisition module is used for acquiring the measuring point pressure of each pressure measuring point when the aircraft flies;
the coefficient calculation module is used for calculating a target characteristic coefficient according to the measuring point pressure of each pressure measuring point;
the atmospheric parameter calculation module is used for calculating a target inflow parameter according to the target characteristic coefficient and a pre-constructed mathematical model of the relationship between the characteristic coefficient and the inflow parameter when the aircraft flies, wherein the target inflow parameter is the atmospheric parameter of the aircraft;
wherein the coefficient calculation module comprises:
the rule determining submodule is used for determining a target calculation rule for calculating a target characteristic coefficient according to the pressure measuring point scheme and a preset coefficient calculation rule base;
and the target coefficient calculation submodule is used for calculating a target characteristic coefficient according to the target calculation rule and the measured point pressure of each measured point.
9. A computer device, characterized by comprising a memory for storing a computer program and a processor for executing the computer program to cause the computer device to carry out the aircraft atmospheric parameter calculation method according to any one of claims 1 to 7.
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