CN106228014A - A kind of acquisition methods of missile aerodynamic coefficient - Google Patents

Abstract

The present invention relates to the acquisition methods of a kind of missile aerodynamic coefficient, the method solves the problem that polar coordinate system Aerodynamic Coefficient can not use under rectangular coordinate system.The method obtains missile trajectory parameter after first passing through the step that wind tunnel test obtains Aerodynamic Coefficient under the polar coordinate system of guided missile, and obtains missile aerodynamic parameter according to missile trajectory parameter calculation；Wherein, described trajectory parameter is flight speedWith flight attitude angle, described missile aerodynamic parameter is flying drilling angle α and flight sideslip angle beta；The total angle of attack under polar coordinate system is obtained further according to flying drilling angle α, flight sideslip angle beta and conversion formula_∑With roll angle Φ；Afterwards according to described total angle of attack_∑With roll angle Φ, interpolation obtains interpolation polar coordinate Aerodynamic Coefficient；Rectangular coordinate system Aerodynamic Coefficient is obtained further according to described interpolation polar coordinate Aerodynamic Coefficient and conversion formula；And then obtain acceleration and the angular acceleration of guided missile；Finally obtain the trajectory parameter flight speed of guided missile subsequent time

Description

A kind of acquisition methods of missile aerodynamic coefficient

Technical field

The invention belongs to Aero-Space wind tunnel test data processing field, be specifically related to the acquisition of a kind of missile aerodynamic coefficient Method.

Background technology

According to body and airflow space geometric angle relation, the Aerodynamic Coefficient that Missile Design uses is divided into two kinds of systems: straight Angular coordinate system and polar coordinate system.Rectangular coordinate system Aerodynamic Coefficient changes with angle of attack and sideslip angle beta bidimensional, and data point exists Spatially present matrix distribution.Polar coordinate system Aerodynamic Coefficient is with total angle of attack_ΣChanging with roll angle Φ bidimensional, data point is at sky Presenting circular distribution between, closeer near the data of circle centre position, the data away from circle centre position are sparse.Rectangular coordinate system is pneumatic Coefficient and polar coordinate system Aerodynamic Coefficient, in addition to a small amount of data point overlaps, most of data point is misaligned, point Cloth rule differs greatly.

There are differences between rectangular coordinate system Aerodynamic Coefficient and polar coordinate system Aerodynamic Coefficient, cause Ballistic Simulation of Underwater and control Larger difference is there is in loop processed designs etc. in the Aerodynamic Coefficient mode using two kinds of coordinate-systems.Therefore, Ballistic Simulation of Underwater and control Loop processed design can only use the Aerodynamic Coefficient under same coordinate system, and the Aerodynamic Coefficient of two kinds of coordinate-systems can not be general, Change Ballistic Simulation of Underwater and control the coordinate-system of loop design, it is necessary to obtaining identical seat by modes such as wind tunnel test, CFD calculating Aerodynamic Coefficient under mark system.

Summary of the invention

The purpose of the present invention: the main object of the present invention is, finds out the acquisition methods of a kind of missile aerodynamic coefficient in other words It is the test method obtaining missile aerodynamic coefficient, solves what polar coordinate system Aerodynamic Coefficient can not use under rectangular coordinate system Problem.

Technical scheme:

Technical solution of the present invention:

The acquisition methods of a kind of missile aerodynamic coefficient is provided,

The first step, obtains the Aerodynamic Coefficient under the polar coordinate system of guided missile by wind tunnel test；

Second step, it is thus achieved that missile trajectory parameter, and obtain missile aerodynamic parameter according to missile trajectory parameter calculation；Wherein, Described trajectory parameter is flight speedWith flight attitude angle, described missile aerodynamic parameter is flying drilling angle α and flight side Sliding angle beta；

3rd step, obtains the total angle of attack under polar coordinate system according to flying drilling angle α, flight sideslip angle beta by equation below α_∑With roll angle Φ, described formula is:

CosA=cos β .cos α

$tan\mathrm{\Φ}=\frac{tan\mathrm{\β}}{\sin \mathrm{\α}};$

4th step, according to described total angle of attack_∑With roll angle Φ, interpolation obtains interpolation polar coordinate Aerodynamic Coefficient, described Interpolation polar coordinate Aerodynamic Coefficient includes axial force coefficientNormal force coefficient C_ξ(α_Σ, Φ), cross force C_η(α_Σ,Φ)、 Rolling moment coefficientYawing moment coefficient m_ξ(α_Σ, Φ), pitching moment coefficient m_η(α_Σ,Φ)；

5th step, obtains the pneumatic system of rectangular coordinate system according to described interpolation polar coordinate Aerodynamic Coefficient and conversion formula Number, described rectangular coordinate system Aerodynamic Coefficient is axial force coefficientNormal force coefficientCross force CoefficientRolling moment coefficientYawing moment coefficientAnd pitching moment coefficientConversion formula therein is as follows:

With

6th step, the rectangular coordinate system Aerodynamic Coefficient using the 5th step to obtain carries out body kinetics resolving, is led The acceleration of bullet and angular acceleration；

7th step, the acceleration of the guided missile that use the 6th step obtains and angular acceleration, carry out kinesiology resolving, obtain guided missile The trajectory parameter flight speed of subsequent timeWith flight attitude angle；

8th step, resolves the aerodynamic parameter obtaining guided missile subsequent time according to the trajectory parameter of subsequent time.

Advantages of the present invention:

The present invention is converted into the Aerodynamic Coefficient under polar coordinate system under right angle mark system permissible by conversion using method The Aerodynamic Coefficient used, saves development cost and the time cost of the consumings such as CFD calculating, wind tunnel test.

Detailed description of the invention:

Below the present invention is described in further detail.

The acquisition methods of a kind of missile aerodynamic coefficient is provided,

The first step, obtains the Aerodynamic Coefficient under the polar coordinate system of guided missile by wind tunnel test；

Second step, it is thus achieved that missile trajectory parameter, and obtain missile aerodynamic parameter according to missile trajectory parameter calculation；Wherein, Described trajectory parameter is flight speedWith flight attitude angle, described missile aerodynamic parameter is flying drilling angle α and flight side Sliding angle beta；

3rd step, obtains the total angle of attack under polar coordinate system according to flying drilling angle α, flight sideslip angle beta by equation below α_ΣWith roll angle Φ, described formula is:

CosA=cos β .cos α

$tan\mathrm{\Φ}=\frac{tan\mathrm{\β}}{\sin \mathrm{\α}};$

4th step, according to described total angle of attack_ΣWith roll angle Φ, interpolation obtains interpolation polar coordinate Aerodynamic Coefficient, described Interpolation polar coordinate Aerodynamic Coefficient includes axial force coefficientNormal force coefficient C_ξ(α_Σ, Φ), cross force C_η(α_Σ,Φ)、 Rolling moment coefficientYawing moment coefficient m_ξ(α_Σ, Φ), pitching moment coefficient m_η(α_Σ,Φ)；

5th step, obtains the pneumatic system of rectangular coordinate system according to described interpolation polar coordinate Aerodynamic Coefficient and conversion formula Number, described rectangular coordinate system Aerodynamic Coefficient is axial force coefficientNormal force coefficientCross force CoefficientRolling moment coefficientYawing moment coefficientAnd pitching moment coefficientConversion formula therein is as follows:

With

6th step, the rectangular coordinate system Aerodynamic Coefficient using the 5th step to obtain carries out body kinetics resolving, is led The acceleration of bullet and angular acceleration；

7th step, the acceleration of the guided missile that use the 6th step obtains and angular acceleration, carry out kinesiology resolving, obtain guided missile The trajectory parameter flight speed of subsequent timeWith flight attitude angle etc.；

8th step, resolves the aerodynamic parameter obtaining guided missile subsequent time according to the trajectory parameter of subsequent time.

Claims (1)

1. an acquisition methods for missile aerodynamic coefficient, the method comprises the steps:

The first step, obtains the Aerodynamic Coefficient under the polar coordinate system of guided missile by wind tunnel test；

Second step, it is thus achieved that missile trajectory parameter, and obtain missile aerodynamic parameter according to missile trajectory parameter calculation；Wherein, described Trajectory parameter be flight speedWith flight attitude angle, described missile aerodynamic parameter is flying drilling angle α and flight yaw angle β；

3rd step, obtains the total angle of attack under polar coordinate system according to flying drilling angle α, flight sideslip angle beta by equation below_∑With Roll angle Φ, described formula is:

CosA=cos β .cos α

$tan\mathrm{\Φ}\frac{tan\mathrm{\β}}{\sin \mathrm{\α}};$

4th step, according to described total angle of attack_∑With roll angle Φ, interpolation obtains interpolation polar coordinate Aerodynamic Coefficient, described interpolation Polar coordinate Aerodynamic Coefficient includes axial force coefficientNormal force coefficient C_ξ(α_Σ, Φ), cross force C_η(α_Σ, Φ), rolling Moment coefficientYawing moment coefficient m_ξ(α_Σ, Φ), pitching moment coefficient m_η(α_Σ,Φ)；

5th step, obtains rectangular coordinate system Aerodynamic Coefficient, institute according to described interpolation polar coordinate Aerodynamic Coefficient and conversion formula The rectangular coordinate system Aerodynamic Coefficient stated is axial force coefficientNormal force coefficientCornering ratioRolling moment coefficientYawing moment coefficientAnd pitching moment coefficientWherein Conversion formula as follows:

With

6th step, the rectangular coordinate system Aerodynamic Coefficient using the 5th step to obtain carries out body kinetics resolving, obtains guided missile Acceleration and angular acceleration；

7th step, uses the acceleration of guided missile and angular acceleration that the 6th step obtains, carries out kinesiology resolving, obtain guided missile next The trajectory parameter flight speed in momentWith flight attitude angle；8th step, resolves according to the trajectory parameter of subsequent time and is led Play the aerodynamic parameter of subsequent time.