CN112541305B - Aerodynamics analysis method based on global variable derivation - Google Patents
Aerodynamics analysis method based on global variable derivation Download PDFInfo
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- CN112541305B CN112541305B CN202011439734.1A CN202011439734A CN112541305B CN 112541305 B CN112541305 B CN 112541305B CN 202011439734 A CN202011439734 A CN 202011439734A CN 112541305 B CN112541305 B CN 112541305B
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- 238000004458 analytical method Methods 0.000 title claims abstract description 14
- 238000009795 derivation Methods 0.000 title claims abstract description 11
- 238000000034 method Methods 0.000 claims abstract description 12
- 238000007664 blowing Methods 0.000 claims abstract description 6
- 238000013178 mathematical model Methods 0.000 claims abstract description 5
- 230000008878 coupling Effects 0.000 claims description 11
- 238000010168 coupling process Methods 0.000 claims description 11
- 238000005859 coupling reaction Methods 0.000 claims description 11
- 230000003068 static effect Effects 0.000 claims description 4
- 238000004364 calculation method Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000009966 trimming Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The application provides an aerodynamic characteristic analysis method based on all-variable derivation, which comprises the following steps: 1) Performing corresponding shafting addition combination on the basic quantity and various components of the blowing data to form a aerodynamic mathematical model; 2) Aiming at different heights and speeds, the longitudinal aerodynamic force basic characteristics and the longitudinal control surface efficiency are calculated by deriving different angles of attack and horizontal tail deflection in the application range of the angles of attack: 3) Aiming at different heights and speeds, the basic characteristics of the transverse aerodynamic force and the efficiency of the transverse control surface are calculated by deriving the deflection of the control surface from different sideslip angles and sideslip angles within the application range of the deflection of the transverse control surface: 4) Aiming at different heights and speeds, the basic characteristics of the heading aerodynamic force and the efficiency of the heading control surface are calculated by deriving the deflection of the control surface from different sideslip angles and the deflection of the heading control surface in the application ranges of the attack angle, the sideslip angle and the deflection of the heading control surface. The method can comprehensively analyze the pneumatic characteristics and simultaneously can meet the design requirements of the airplane on the control capability and the maneuvering capability.
Description
Technical Field
The application belongs to the technical field of flight control, and particularly relates to an airplane aerodynamic characteristic analysis party based on global variable derivation.
Background
In the design stage of an airplane scheme, in order to quickly evaluate and feed back the overall layout, the airplane operation requirement and the airplane capability requirement of the airplane, the optimization iteration is convenient, and an analysis method capable of comprehensively and efficiently evaluating and calculating aerodynamic characteristics of an airplane body and each control surface is urgently needed.
In the prior art, in the pneumatic characteristic analysis of an aircraft, the analysis in a flat flight or fixed-carrier disk trimming state is generally adopted, and the conclusion of the analysis is insufficient to cover the whole pneumatic characteristic of the aircraft.
Disclosure of Invention
The purpose of the application is to provide an aircraft aerodynamic characteristic analysis method based on global variable derivation, so as to solve or alleviate at least one problem in the background art.
The technical scheme of the application is as follows: an aircraft aerodynamic characteristic analysis method based on global variable derivation, the method comprising:
1) Performing corresponding shafting addition combination on the basic quantity and various components of the blowing data to form a aerodynamic mathematical model;
2) For different heights and speeds, calculating longitudinal aerodynamic force basic characteristics and longitudinal control surface efficiency by deriving different angles of attack and horizontal tail deviation in the application range of angles of attack, wherein the method comprises the following steps:
elevation line slope at different heights, mach numbers, angles of attack:
longitudinal static stability at different heights, mach numbers, angles of attack:
horizontal tail operating efficiency under different heights, mach numbers, angles of attack and control surface deflection:
3) For different heights and speeds, deriving and calculating transverse aerodynamic force basic characteristics and transverse control surface efficiency in the application ranges of attack angles, sideslip angles and transverse control surface skewness, wherein the method comprises the following steps:
lateral stability at different heights, mach numbers, angles of attack, sideslip angles:
aileron roll operating efficiency and differential horizontal tail roll operating efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface deflection:
aileron roll yaw coupling operating efficiency and differential horizontal tail roll yaw coupling operating efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface skewness:
4) Aiming at different heights and speeds, the basic characteristics of the heading aerodynamic force and the efficiency of the heading control surface are calculated by deriving the deflection of the control surface from different sideslip angles and the deflection of the heading control surface in the application ranges of the attack angle, the sideslip angle and the deflection of the heading control surface.
Further, in step 2:
2.1 Line of elevation slope at different altitudes, mach numbers, angles of attack:
2.2 Longitudinal static stability at different heights, mach numbers, angles of attack:
2.3 Horizontal tail control efficiency under different heights, mach numbers, angles of attack and control surface deflection:
further, in step 3:
3.1 Lateral stability at different heights, mach numbers, angles of attack, sideslip angles):
3.2 Aileron roll operating efficiency and differential horizontal tail roll operating efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface deflection:
3.3 Aileron roll yaw coupling operating efficiency and differential horizontal tail roll yaw coupling operating efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface skewness:
further, in step 4:
4.1 Heading stability at different altitudes, mach numbers, angles of attack:
4.2 Rudder yaw roll coupling operating efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface deflection:
4.3 Rudder yaw manipulation efficiency at different heights, mach numbers, angles of attack, sideslip angles, and control surface deflection:
the aerodynamic characteristic analysis method based on the all-variable derivation can comprehensively analyze aerodynamic characteristics, is efficient and simple, is easy to realize, can meet design requirements of airplane maneuvering capability and airplane mobility, and realizes rapid evaluation feedback of overall layout of an airplane.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
FIG. 1 is a schematic diagram of an aircraft aerodynamic characteristic analysis method based on global variable derivation according to the present invention.
Fig. 2 to fig. 7 are schematic diagrams of calculation results according to embodiments of the present application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
In order to overcome the problems pointed out in the prior art, the method for analyzing aerodynamic characteristics efficiently and comprehensively is provided for carrying out derivative calculation aiming at combinations of states of different heights, speeds, attack angles, sideslip angles, control surface skewness and the like of an airplane in different flight phases, combining requirements of airplane maneuvering capability and maneuverability, and realizing auxiliary design of computer circulation calculation and statistical drawing by means of the method.
As shown in fig. 1, the method for analyzing aerodynamic characteristics of an aircraft based on global variable derivation provided by the application comprises the following steps:
s1) carrying out corresponding shafting addition combination on the basic quantity and various components of the blowing data to form a aerodynamic mathematical model;
s2) aiming at different heights and speeds, calculating longitudinal aerodynamic force basic characteristics and longitudinal control surface efficiency by deriving different angles of attack and horizontal tail deflection in the use range of angles of attack, wherein the method comprises the following steps:
a) Elevation line slope at different heights, mach numbers, angles of attack:
b) Longitudinal static stability at different heights, mach numbers, angles of attack:
c) Horizontal tail operating efficiency under different heights, mach numbers, angles of attack and control surface deflection:
s3) aiming at different heights and speeds, deriving and calculating transverse aerodynamic basic characteristics and transverse control surface efficiency of different sideslip angles and control surface skewness in the application ranges of the attack angles, the sideslip angles and the transverse control surface skewness, wherein the method comprises the following steps:
a) Lateral stability at different heights, mach numbers, angles of attack, sideslip angles:
b) Aileron roll operating efficiency and differential horizontal tail roll operating efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface deflection:
c) Aileron roll yaw coupling operating efficiency and differential horizontal tail roll yaw coupling operating efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface skewness:
s4) aiming at different heights and speeds, deriving and calculating aerodynamic basic characteristics of a heading and efficiency of the heading control surface in the application ranges of the angle of attack, the angle of sideslip and the deflection of the heading control surface, wherein the method comprises the following steps:
a) Heading stability at different altitudes, mach numbers, angles of attack:
b) Rudder yaw roll coupling operating efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface deflection:
c) Rudder yaw manipulation efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface deflection:
the present application is further described below in connection with an embodiment of a specific number provided herein.
1) In the scheme stage, after aerodynamic air blowing data of the aircraft are obtained, the basic quantity of the air blowing data and various components are subjected to corresponding shafting addition combination to form an aerodynamic mathematical model;
2) For different heights H, speeds Ma, angles of attack alpha and control surface deflection delta, calculating longitudinal aerodynamic force basic characteristics and longitudinal control surface efficiency, and using computer software to draw curves of aerodynamic characteristics changing with angles of attack and Mach numbers at different heights, such as
3) For different heights H, speeds Ma, attack angles alpha, sideslip angles beta and control surface deflection delta, calculating transverse aerodynamic force basic characteristics, aileron roll operating efficiency and differential horizontal tail roll operating efficiency, and using computer software to draw variation curves of various aerodynamic characteristics along with different variables, such as
4) For different heights H, speeds Ma, attack angles alpha, sideslip angles beta and control surface deflection delta, calculating the aerodynamic basic characteristics of the course and the control surface efficiency, and using computer software to draw the change curves of the aerodynamic characteristics along with different variables, such as
In embodiments of the present application: h-height, 3000m;
Ma-Mach number, 0.9;
α 0 -angle of attack, 8 °,10 °, 12 °;
β 0 -sideslip angle, 0 °;
δ x0 aileron deflection, 10 °
Δδ x Aileron calculation step size, 2 °;
m y a yaw moment coefficient of 8 DEG for aileron deflection at a (10, 8) -angle of attack of 10 DEG, 0.792;
m y (10, 12) -yaw moment coefficient in a state that the aileron deflection is 12 degrees when the attack angle is 10 degrees, 0.792.
From the formula
Is available in the form of
The aerodynamic characteristic analysis method based on the all-variable derivation can comprehensively analyze aerodynamic characteristics, is efficient and simple, is easy to realize, can meet design requirements of airplane maneuvering capability and airplane mobility, and realizes rapid evaluation feedback of overall layout of an airplane.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (1)
1. An aircraft aerodynamic characteristic analysis method based on global variable derivation, which is characterized by comprising the following steps:
1) Performing corresponding shafting addition combination on the basic quantity and various components of the blowing data to form a aerodynamic mathematical model;
2) For different heights and speeds, calculating longitudinal aerodynamic force basic characteristics and longitudinal control surface efficiency by deriving different angles of attack and horizontal tail deviation in the application range of angles of attack, wherein the method comprises the following steps:
elevation line slope at different heights, mach numbers, angles of attack:
longitudinal static stability at different heights, mach numbers, angles of attack:
horizontal tail operating efficiency under different heights, mach numbers, angles of attack and control surface deflection:
3) For different heights and speeds, deriving and calculating transverse aerodynamic force basic characteristics and transverse control surface efficiency in the application ranges of attack angles, sideslip angles and transverse control surface skewness, wherein the method comprises the following steps:
lateral stability at different altitudes, mach numbers, angles of attack, sideslip angles
Aileron roll operating efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface deflection and differential horizontal tail roll operating efficiency are respectively
Aileron roll yaw coupling operating efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface deflection, and differential horizontal tail roll yaw coupling operating efficiency are respectively as follows:
4) Aiming at different heights and speeds, the basic characteristics of the heading aerodynamic force and the efficiency of the heading control surface are calculated by deriving the deviation of the heading control surface from different sideslip angles and different control surface within the application ranges of the attack angle, sideslip angle and the deviation of the heading control surface, and the basic characteristics comprise heading stability under different heights, mach numbers and attack angles:
rudder yaw roll coupling operating efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface deflection:
rudder yaw manipulation efficiency under different heights, mach numbers, attack angles, sideslip angles and control surface deflection:
in the formula, H is the height;
ma is Mach number;
alpha is the angle of attack;
delta is the deflection of the control surface;
beta is the sideslip angle.
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|---|---|---|---|---|
| CN102707723A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Conventional aircraft model-based lateral-directional controller area design method |
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