CN112214834B - Axisymmetric aircraft pneumatic database establishment method - Google Patents

Axisymmetric aircraft pneumatic database establishment method Download PDF

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Publication number
CN112214834B
CN112214834B CN202010955077.XA CN202010955077A CN112214834B CN 112214834 B CN112214834 B CN 112214834B CN 202010955077 A CN202010955077 A CN 202010955077A CN 112214834 B CN112214834 B CN 112214834B
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coefficient
force
moment
directions
axisymmetric
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CN112214834A (en
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郭斌
张敏捷
田政
杨庆
吴文瑞
余抗
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Beijing Institute of Spacecraft System Engineering
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Beijing Institute of Spacecraft System Engineering
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    • 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
    • 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
    • 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
    • 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

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Abstract

The invention relates to a method for establishing an axisymmetric aircraft pneumatic database, S1, based on the axisymmetric body shape of a return cabin, firstly, carrying out simulation analysis and calculation under a sideslip angle of 0 degree to obtain force/moment coefficients in two directions irrelevant to the sideslip angle; s2, by rotating around the body shaft at different angles, the force/moment in two directions is projected to three directions, and a series of force/moment coefficient information related to the three directions related to the rotating body shaft can be obtained. The method is suitable for the axisymmetric aircraft pneumatic database establishment method, and on the premise of meeting the ballistic simulation data requirement, the calculation working conditions under the same height and Mach number can be greatly reduced through the condition of body axis transformation, so that the database establishment time is saved, and meanwhile, the expenditure is greatly reduced.

Description

Axisymmetric aircraft pneumatic database establishment method
Technical Field
The invention belongs to the technical field of spacecrafts, and particularly relates to a method for establishing an axisymmetric aerodynamic database of an aircraft.
Background
The establishment of an aircraft pneumatic database is a precondition for developing the trajectory simulation of an aircraft. According to the requirement of ballistic calculation, the database to be built by the aerodynamic simulation calculation needs to contain aerodynamic data at different speeds, different heights and different postures. The complete ballistic simulation is then calculated by the ballistic design software via the difference values.
Under the condition of the same height and Mach number in the traditional algorithm, the combined working conditions of different attack angles and sideslip angles need to be considered, a huge data matrix is formed, and then follow-up ballistic simulation work is carried out, so that a great amount of time is consumed.
Disclosure of Invention
The invention aims to solve the technical problems and provides a method for establishing an axisymmetric aircraft pneumatic database.
In order to achieve the purpose of the invention, the invention provides an axisymmetric aircraft pneumatic database establishing method, S1, based on the axisymmetric body shape of a return cabin, firstly, carrying out simulation analysis and calculation under the sideslip angle of 0 degree to obtain force/moment coefficients in two directions irrelevant to the sideslip angle; s2, by rotating around the body shaft at different angles, the force/moment in two directions is projected to three directions, and a series of force/moment coefficient information related to the three directions related to the rotating body shaft can be obtained.
In accordance with one aspect of the present invention, in S1, the 0 ° sideslip angle base information calculated using CFD analysis software includes a total angle of attack, an axial force coefficient, a normal force coefficient, a roll moment coefficient, and a pitch moment coefficient.
According to one aspect of the invention, in step S2, force/moment coefficient information for three directions associated with the axis of rotation is obtained in the pneumatic database for different angles of rotation about the body axis, wherein the relationship with the 0 ° data calculated using CFD analysis software is as follows:
name of the name (symbol) Relationship with 0 ° data calculated using CFD analysis software
Rotation angle θ(°)
Total angle of attack αall(°)
Angle of attack α(°) ＝-arcCOS(COS(αall/180*π)/COS(β/180*π))*180/π
Sideslip angle β(°) ＝arcSIN(SIN(θ/180*π)*SIN(αall/180*π))*180/π
Axial force coefficient C A ’ ＝C A
Coefficient of normal force C N ’ ＝C Nall *COS(θ*π/180)
Coefficient of lateral force C Y ’ ＝-C Nall *SIN(θ*π/180)
Coefficient of roll moment C Mx ’ ＝C Mx0
Yaw moment coefficient C My ’ ＝C Mz0ALL *SIN(Θ*π/180)
Coefficient of pitch moment C Mz ’ ＝C Mz0ALL *COS(θ*π/180)
The method is suitable for the axisymmetric aircraft pneumatic database establishment method, and on the premise of meeting the ballistic simulation data requirement, the calculation working conditions under the same height and Mach number can be greatly reduced through the condition of body axis transformation, so that the database establishment time is saved, and meanwhile, the expenditure is greatly reduced.
Drawings
FIG. 1 schematically illustrates an aircraft reentry and return trajectory diagram corresponding to an axisymmetric aircraft pneumatic database creation method in accordance with the present invention;
FIG. 2 schematically illustrates a ballistic calculation sample according to one embodiment of the invention;
figure 3 schematically shows the number of operating conditions according to the same altitude, speed.
Detailed Description
The present invention will be described in detail below with reference to the drawings and the specific embodiments, which are not described in detail herein, but the embodiments of the present invention are not limited to the following embodiments.
The invention provides a method for establishing an axisymmetric aircraft pneumatic database, which is characterized in that S1, based on the shape of an axisymmetric body of a return cabin, simulation analysis and calculation are carried out under the condition of utilizing a sideslip angle of 0 degrees, so that force/moment coefficients in two directions irrelevant to the sideslip angle can be obtained, S2, the forces/moments in the two directions are projected to three directions by rotating around a body axis for different angles, and a series of force/moment coefficient information relevant to the three directions of a rotating body axis can be obtained. The specific method comprises the following steps:
first, the 0 ° sideslip angle base information table calculated by CFD is shown in the following table, which contains only force coefficients and moment coefficients in two directions. As shown in table 1 below:
total angle of attack αall(°)
Coefficient of axial force C A C A
Coefficient of normal force C N C Nall
Coefficient of roll moment C Mx C Mx0
Pitch moment coefficient C Mz C Mz0ALL
TABLE 1CFD simulation result data composition
Then in S2, the force/moment coefficients of three directions related to the rotation axis are obtained in the pneumatic database under the condition of rotating around the body axis by different angles and giving different rotation angles, wherein the relation between the force/moment coefficients and the data of the CFD calculation result is shown in the following table:
rotation angle θ(°)
Total angle of attack αall(°)
Angle of attack α(°) ＝-arcCOS(COS(αall/180*π)/COS(β/180*π))*180/π
Sideslip angle β(°) ＝arcSIN(SIN(θ/180*π)*SIN(αall/180*π))*180/π
Axial force coefficient C A ’ ＝C A
Coefficient of normal force C N ’ ＝C Nall *COS(θ*π/180)
Coefficient of lateral force C Y ’ ＝-C Nall *SIN(θ*π/180)
Coefficient of roll moment C Mx ’ ＝C Mx0
Yaw moment coefficient C My ’ ＝C Mz0ALL *SIN(θ*π/180)
Coefficient of pitch moment C Mz ’ ＝C Mz0ALL *COS(θ*π/180)
TABLE 2 composition of post-rotation axis database results
According to one embodiment of the present invention, 36 calculation samples are selected according to the reentry and return trajectory according to the method of the present invention, as shown in fig. 1 and 2. The calculation conditions at the same height and speed according to the conventional method are shown in fig. 3. The 6 slip angle (β) conditions are assumed with 1 angle of attack (α). The CFD calculation for each calculation sample during the conventional database creation process is 26×6=156. The total CFD calculation for database creation is 5616.
If the method provided by the invention is used, the CFD calculation condition of each calculation sample is 26×1=26. The database establishes the overall CFD calculation as 936. The calculation working condition is greatly saved.
The method is suitable for the axisymmetric aircraft pneumatic database establishment method, and on the premise of meeting the ballistic simulation data requirement, the calculation working conditions under the same height and Mach number can be greatly reduced through the condition of body axis transformation, so that the database establishment time is saved, and meanwhile, the expenditure is greatly reduced.
The above description is only one embodiment of the present invention and is not intended to limit the present invention, and various modifications and variations of the present invention will be apparent to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (1)

1. The method for establishing the axisymmetric aircraft pneumatic database comprises the following steps of S1, based on the axisymmetric body shape of a return cabin, performing simulation analysis and calculation under the condition of 0-degree sideslip angle to obtain force/moment coefficients in two directions irrelevant to the sideslip angle; s2, projecting forces/moments in two directions to three directions by rotating around a body shaft by different angles, so that a series of force/moment coefficients related to the three directions related to the rotating body shaft can be obtained;
in S1, the force/moment coefficients in two directions independent of the sideslip angle beta calculated by CFD analysis software comprise a total attack angle alpha all and an axial force coefficient C A Coefficient of normal force C N Coefficient of roll moment C Mx And pitch moment coefficient C Mz The method comprises the following steps of:
total angle of attack αall(°) Coefficient of axial force C A C A Coefficient of normal force C N C Nall Coefficient of roll moment C Mx C Mx0 Pitch moment coefficient C Mz C Mz0ALL
；
In step S2, force/moment coefficient information of three directions related to the rotating body axis is obtained in the pneumatic database under the condition of rotating around the body axis by different angles, wherein the relation between the force/moment coefficient information and the 0-degree sideslip angle data calculated by using CFD analysis software is as follows:
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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005020660A1 (en) * 2005-05-03 2006-11-09 Deutsches Zentrum für Luft- und Raumfahrt e.V. Stability control system for aircraft computes additional control commands to counteract effects of turbulence and gusts
WO2011055085A2 (en) * 2009-11-06 2011-05-12 Airbus Operations Method and tool for simulating the aerodynamic behaviour of an aerodynamic element of an aircraft having a variable sweep angle
CN104331084A (en) * 2014-09-30 2015-02-04 中国运载火箭技术研究院 Pneumatic rudder deflection range calculation method based on direction rudder roll control strategy
CN106294280A (en) * 2016-08-22 2017-01-04 麻毅威 A kind of trajectory planning method
CN107092765A (en) * 2017-06-22 2017-08-25 洛阳瑞极光电科技有限公司 A kind of Fluid Mechanics Computation aerodynamic data processing method of axial symmetry aircraft

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150203215A1 (en) * 2014-01-17 2015-07-23 Eric T. Falangas Early performance evaluation of conceptual flight and space vehicles
CN108369106A (en) * 2015-09-22 2018-08-03 俄亥俄州立大学 Prevention and recovery flight controller out of control

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005020660A1 (en) * 2005-05-03 2006-11-09 Deutsches Zentrum für Luft- und Raumfahrt e.V. Stability control system for aircraft computes additional control commands to counteract effects of turbulence and gusts
WO2011055085A2 (en) * 2009-11-06 2011-05-12 Airbus Operations Method and tool for simulating the aerodynamic behaviour of an aerodynamic element of an aircraft having a variable sweep angle
CN104331084A (en) * 2014-09-30 2015-02-04 中国运载火箭技术研究院 Pneumatic rudder deflection range calculation method based on direction rudder roll control strategy
CN106294280A (en) * 2016-08-22 2017-01-04 麻毅威 A kind of trajectory planning method
CN107092765A (en) * 2017-06-22 2017-08-25 洛阳瑞极光电科技有限公司 A kind of Fluid Mechanics Computation aerodynamic data processing method of axial symmetry aircraft

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