CN105548250A - Heat flow control method, device and system for aerothermodynamic experiment of aircraft - Google Patents

Abstract

The invention provides a heat flow control method, device and system for an aerothermodynamic experiment of an aircraft. The method comprises the steps that preset flying height information and preset flying speed information of the aircraft are acquired; the surface temperature of an aircraft experiment sample is collected in real time; a target heat flow density value is calculated according to the preset flying height information, the preset flying speed information and the surface temperature; a heat flow density value of the aircraft experiment sample is collected in real time; feedback control is performed according to the heat flow density value and the target heat flow density value, and a heat flow heating device is controlled to heat the aircraft experiment sample to reach the target heat flow density value. The simulation accuracy of an aerodynamic heating environment of the aircraft is effectively improved.

Description

The hot-fluid control method of flight vehicle aerodynamic heat test, Apparatus and system

Technical field

The present invention relates to the ground simulation test technical field of flight vehicle aerodynamic heating environment, particularly relate to a kind of hot-fluid control method, Apparatus and system of flight vehicle aerodynamic heat test.

Background technology

Usually temperature control algorithm or hot-fluid control algolithm is adopted in thermal environment ground simulation test.Temperature control algorithm for control object with surface of test piece temperature, according to the temperature-time curve of setting, regulating heating arrangement output by introducing temperature feedback, carrying out whole process simulation to surface of test piece temperature.But accurate acquisition is difficult to for some test specimen thermophysical parameter, is difficult to provide temperature curve, temperature cannot be adopted to control.Hot-fluid control algolithm for control object with surface of test piece hot-fluid, according to the hot-fluid-time curve of setting, exporting by introducing hot-fluid feedback regulation heating arrangement, carrying out whole process simulation to time surface heat flow.If test specimen Calculation of Heat Transfer model is complicated, needs to consider that the coupled problem of aerodynamic force and thermal field and thermal physical property parameter change, be difficult to calculate hot-fluid given curve, hot-fluid cannot be adopted to control.

Summary of the invention

Provide hereinafter about brief overview of the present invention, to provide about the basic comprehension in some of the present invention.Should be appreciated that this general introduction is not summarize about exhaustive of the present invention.It is not that intention determines key of the present invention or pith, and nor is it intended to limit the scope of the present invention.Its object is only provide some concept in simplified form, in this, as the preorder in greater detail discussed after a while.

For solving the problem, the present invention proposes a kind of hot-fluid control method, Apparatus and system of flight vehicle aerodynamic heat test, can under the condition not having temperature given curve and hot-fluid given curve, the temperature that utilization records in real time and heat flow data control, and simulate pneumatic thermal environment.

On the one hand, the invention provides a kind of hot-fluid control method of flight vehicle aerodynamic heat test, comprising:

Obtain pre-set flight elevation information and the pre-set flight velocity information of aircraft;

The surface temperature of Real-time Collection aircraft testpieces;

Target heat flow density value is calculated according to described pre-set flight elevation information, pre-set flight velocity information and surface temperature;

The heat flow density value on aircraft testpieces surface described in Real-time Collection;

Carry out FEEDBACK CONTROL according to described heat flow density value and described target heat flow density value, controlling hot-fluid heating arrangement is that described aircraft testpieces carries out heating to reach target heat flow density value.

Second aspect, the present invention also provides a kind of heat flux control device of flight vehicle aerodynamic heat test, comprising:

Data obtaining module, for obtaining pre-set flight elevation information and the pre-set flight velocity information of aircraft;

Temperature collect module, for controlling the surface temperature of Real-time Collection aircraft testpieces;

Target heat flow density calculates module, for calculating target heat flow density value according to described pre-set flight elevation information, pre-set flight velocity information and surface temperature;

Hot-fluid acquisition module, for controlling the heat flow density value on aircraft testpieces surface described in Real-time Collection;

Heating control module, for carrying out FEEDBACK CONTROL according to described heat flow density value and described target heat flow density value, controlling hot-fluid heating arrangement is that described aircraft testpieces carries out heating to reach target heat flow density value.

The third aspect, the present invention also provides a kind of hot-fluid control system of flight vehicle aerodynamic heat test, and the heat flux control device of above-mentioned flight vehicle aerodynamic heat test, also comprises:

For gathering the temperature sensor of the surface temperature of aircraft testpieces;

For gathering the heat flux sensor of the heat flow density value on described aircraft testpieces surface;

For the hot-fluid heating arrangement heated described aircraft testpieces.

Hot-fluid control method, the Apparatus and system of flight vehicle aerodynamic heat test provided by the invention, control according to the temperature recorded in real time and heat flow data, simulates pneumatic thermal environment, effectively improves the accuracy of flight vehicle aerodynamic heating environment simulation.

Accompanying drawing explanation

In order to be illustrated more clearly in the embodiment of the present invention or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.

Fig. 1 is the process flow diagram of a kind of embodiment of hot-fluid control method of flight vehicle aerodynamic heat test provided by the invention.

Fig. 2 is the control structure schematic diagram of the hot-fluid control method of flight vehicle aerodynamic heat test provided by the invention.

Fig. 3 is the structural representation of a kind of embodiment of heat flux control device of flight vehicle aerodynamic heat test provided by the invention.

Fig. 4 is the structural representation of a kind of embodiment of hot-fluid control system of flight vehicle aerodynamic heat test provided by the invention.

Embodiment

With reference to the accompanying drawings embodiments of the invention are described.The element described in an accompanying drawing of the present invention or a kind of embodiment and feature can combine with the element shown in one or more other accompanying drawings or embodiment and feature.It should be noted that to know object, accompanying drawing and eliminate expression and the description of unrelated to the invention, parts known to persons of ordinary skill in the art and process in illustrating.

Embodiment one

With reference to figure 1, the present embodiment provides a kind of hot-fluid control method of flight vehicle aerodynamic heat test, comprising:

Step S101, obtains pre-set flight elevation information and the pre-set flight velocity information of aircraft;

Step S102, the surface temperature of Real-time Collection aircraft testpieces;

Step S103, calculates target heat flow density value according to described pre-set flight elevation information, pre-set flight velocity information and surface temperature;

Step S104, the heat flow density value on aircraft testpieces surface described in Real-time Collection;

Step S105, carries out FEEDBACK CONTROL according to described heat flow density value and described target heat flow density value, and controlling hot-fluid heating arrangement is that described aircraft testpieces carries out heating to reach target heat flow density value.

Particularly, with reference to figure 2, first pre-set flight elevation information and pre-set flight velocity information is obtained, this pre-set flight elevation information and pre-set flight velocity information given according to the demand of actual tests, afterwards according to pre-set flight high computational air stream on accompany surface temperature, this air stream on accompany surface temperature calculates according to following formula:

$H=\frac{6356766\·h}{6356766+h};---\left(1\right)$

$T_{\mathrm{\&infin;}}=\left\{\begin{array}{cc}288.15-0.0065\&CenterDot;H& H\&le;11000\\ 216.65& 11000<H\&le;20000\\ 216.65+0.001(H-20000)& 20000<H\&le;32000\end{array}\right.;---\left(2\right)$

Wherein, h is pre-set flight height; H is geopotential unit; T _∞for air stream on accompany surface temperature.

Further, according to described air stream on accompany surface temperature computation air flow resistance temperature, this air flow resistance temperature calculates according to following formula:

T _r＝T _∞(1+0.2·r·Ma ² _∞)；(3)

Wherein, T _rfor air flow resistance temperature, T _∞for air stream on accompany surface temperature, r is coefficient of restitution, r<1, and the characteristic according to testpieces is determined by empirical value, M _{a ∞}for boundary-layer outer rim free stream Mach number.

Further, calculate reference temperature according to described air stream on accompany surface temperature, air flow resistance temperature and surface temperature, surface temperature is obtained by temperature sensor collection, and this reference temperature is calculated by following formula:

T ^*＝T _∞+0.5(T _r-T _w)+0.22(T _r-T _∞)；(4)

Wherein, T _rfor air flow resistance temperature, T _∞for air stream on accompany surface temperature, T ^*for reference temperature; T _wfor surface temperature.

Further, calculate convection transfer rate according to described reference temperature, pre-set flight velograph, this convection transfer rate calculates according to following formula:

${\mathrm{Pr}}^{*}=0.722-0.035sin\frac{\mathrm{\&pi;}(T^{*}-273)}{600};---\left(5\right)$

${\mathrm{\&mu;}}^{*}=\frac{14.9\&times;{10}^6{\left(T^{*}\right)}^{\frac{3}{2}}}{T^{*}+110};---\left(6\right)$

${c_{pe}}^{*}=1155.4635-151.8036sin\&lsqb;\frac{\mathrm{\&pi;}}{2}-\frac{\mathrm{\&pi;}}{1200}\left(T^{*}-273\right)\&rsqb;;---\left(7\right)$

${{\mathrm{\&rho;}}_e}^{*}=\frac{{\mathrm{\&rho;}}_e{T}_{\mathrm{\&infin;}}}{T^{*}};---\left(8\right)$

${{\mathrm{St}}_e}^{*}\left\{\begin{array}{cc}=3.26{\left(\mathrm{Re}\right)}^{\frac{1}{2}}{\left(\mathrm{Pr}\right)}^{-\frac{3}{2}};& \mathrm{Re}<1.56\&times;{10}^6\\ =1.81{\left(\begin{array}{cc}\lg & \mathrm{Re}\end{array}\right)}^{-2.584}{\left(\mathrm{Pr}\right)}^{-\frac{3}{2}};& \mathrm{Re}>1.56\&times;{10}^6\end{array}\right.;---\left(9\right)$

$\mathrm{\&alpha;}={\mathrm{St}}_e^{*}\&CenterDot;{\mathrm{\&rho;}}_e^{*}\&CenterDot;{\mathrm{\&upsi;}}_{\mathrm{\&infin;}}^{*}\&CenterDot;c_{pe}^{*};---\left(10\right)$

Wherein, T ^*for reference temperature, for the Prandtl number of air-flow; μ ^*for air flow power viscosity; for air-flow specific heat capacity; for current density; for the Margoulis number of air-flow.

Further, according to described convection transfer rate, air flow resistance temperature, surface temperature, aircraft testpieces surface blackness and blackbody radiation constant calculations target heat flow density value, this target heat flow density value calculates according to following formula:

$q=\mathrm{\&alpha;}(T_r-T_w)-{\mathrm{\&epsiv;\&sigma;}}_0{T}_w^4;---\left(11\right)$

Wherein, T _rfor air flow resistance temperature; T _wfor surface temperature; Q is target heat flow density value, and ε is aircraft testpieces surface blackness; σ ₀for blackbody radiation constant.

The flight vehicle aerodynamic heat test control method that the present embodiment provides, without the need to given curve, controls according to the temperature recorded in real time and heat flow data, simulates pneumatic thermal environment, effectively improves the accuracy of flight vehicle aerodynamic heating environment simulation.

Embodiment two

With reference to figure 3, the present embodiment provides a kind of heat flux control device of flight vehicle aerodynamic heat test, comprising:

Data obtaining module 201, for obtaining pre-set flight elevation information and the pre-set flight velocity information of aircraft;

Temperature collect module 202, for controlling the surface temperature of Real-time Collection aircraft testpieces;

Target heat flow density calculates module 203, for calculating target heat flow density value according to described pre-set flight elevation information, pre-set flight velocity information and surface temperature;

Hot-fluid acquisition module 204, for controlling the heat flow density value on aircraft testpieces surface described in Real-time Collection;

Heating control module 205, for carrying out FEEDBACK CONTROL according to described heat flow density value and described target heat flow density value, controlling hot-fluid heating arrangement is that described aircraft testpieces carries out heating to reach target heat flow density value.

Particularly, target heat flow density calculates module 203 also for according to described pre-set flight high computational air stream on accompany surface temperature; According to described air stream on accompany surface temperature computation air flow resistance temperature; Reference temperature is calculated according to described air stream on accompany surface temperature, air flow resistance temperature and surface temperature; Convection transfer rate is calculated according to described reference temperature, pre-set flight velograph; According to described convection transfer rate, air flow resistance temperature, surface temperature, aircraft testpieces surface blackness and blackbody radiation constant calculations target heat flow density value.

Detailed process please refer to embodiment one, does not repeat them here.

The flight vehicle aerodynamic heat test control device that the present embodiment provides, without the need to given curve, controls according to the temperature recorded in real time and heat flow data, simulates pneumatic thermal environment, effectively improves the accuracy of flight vehicle aerodynamic heating environment simulation.

Embodiment three

With reference to figure 4, the hot-fluid control system of a kind of flight vehicle aerodynamic heat test of the present embodiment, the heat flux control device 301 of flight vehicle aerodynamic heat test, also comprises:

For gathering the temperature sensor 302 of the surface temperature of aircraft testpieces;

For gathering the heat flux sensor 303 of the heat flow density value on described aircraft testpieces surface;

For the hot-fluid heating arrangement 304 heated described aircraft testpieces.

The structure of the heat flux control device 301 of flight vehicle aerodynamic heat test and principle of work please refer to embodiment one and embodiment two, are not repeating at this.

Temperature sensor 302, heat flux sensor 303 and hot-fluid heating arrangement 304 are connected with the heat flux control device 301 of flight vehicle aerodynamic heat test respectively.

The flight vehicle aerodynamic heat test control system that the present embodiment provides, structure is simple, without the need to given curve, controls according to the temperature recorded in real time and heat flow data, simulates pneumatic thermal environment, effectively improves the accuracy of flight vehicle aerodynamic heating environment simulation.

Although described the present invention and advantage thereof in detail, be to be understood that and can have carried out various change when not exceeding the spirit and scope of the present invention limited by appended claim, substituting and conversion.And the scope of the application is not limited only to the specific embodiment of process, equipment, means, method and step described by instructions.One of ordinary skilled in the art will readily appreciate that from disclosure of the present invention, can use perform the function substantially identical with corresponding embodiment described herein or obtain and its substantially identical result, existing and that will be developed in the future process, equipment, means, method or step according to the present invention.Therefore, appended claim is intended to comprise such process, equipment, means, method or step in their scope.

Claims (10)

1. a hot-fluid control method for flight vehicle aerodynamic heat test, is characterized in that, comprising:

Obtain pre-set flight elevation information and the pre-set flight velocity information of aircraft;

The surface temperature of Real-time Collection aircraft testpieces;

Target heat flow density value is calculated according to described pre-set flight elevation information, pre-set flight velocity information and surface temperature;

The heat flow density value on aircraft testpieces surface described in Real-time Collection;

Carry out FEEDBACK CONTROL according to described heat flow density value and described target heat flow density value, controlling hot-fluid heating arrangement is that described aircraft testpieces carries out heating to reach target heat flow density value.

2. the hot-fluid control method of flight vehicle aerodynamic heat test according to claim 1, is characterized in that, calculates target heat flow density value, comprising according to described pre-set flight elevation information, pre-set flight velocity information and surface temperature:

According to described pre-set flight high computational air stream on accompany surface temperature;

According to described air stream on accompany surface temperature computation air flow resistance temperature;

Reference temperature is calculated according to described air stream on accompany surface temperature, air flow resistance temperature and surface temperature;

Convection transfer rate is calculated according to described reference temperature, pre-set flight velograph;

According to described convection transfer rate, air flow resistance temperature, surface temperature, aircraft testpieces surface blackness and blackbody radiation constant calculations target heat flow density value.

3. the hot-fluid control method of flight vehicle aerodynamic heat test according to claim 2, is characterized in that, described air stream on accompany surface temperature is calculated by following formula:

$H=\frac{6356766\&CenterDot;h}{6356766+h};---\left(1\right)$

$T_{\mathrm{\&infin;}}=\left\{\begin{array}{cc}288.15-0.0065\&CenterDot;H& H\&le;11000\\ 216.65& 11000<H\&le;20000\\ 216.65+0.001(H-20000)& 20000<H\&le;32000\end{array}\right.;---\left(2\right)$

Wherein, h is pre-set flight height; H is geopotential unit; T _∞for air stream on accompany surface temperature.

4. the hot-fluid control method of flight vehicle aerodynamic heat test according to claim 3, is characterized in that, described air flow resistance temperature is calculated by following formula:

T _r＝T _∞(1+0.2·r·Ma ² _∞)；(3)

Wherein, T _rfor air flow resistance temperature, T _∞for air stream on accompany surface temperature, r is coefficient of restitution, M _{a ∞}for boundary-layer outer rim free stream Mach number.

5. the hot-fluid control method of flight vehicle aerodynamic heat test according to claim 4, is characterized in that, described reference temperature is calculated by following formula:

T ^*＝T _∞+0.5(T _r-T _w)+0.22(T _r-T _∞)；(4)

Wherein, T _rfor air flow resistance temperature, T _∞for air stream on accompany surface temperature, T ^*for reference temperature; T _wfor surface temperature.

6. the hot-fluid control method of flight vehicle aerodynamic heat test according to claim 5, is characterized in that, described convection transfer rate is calculated by following formula:

${\mathrm{Pr}}^{*}=0.722-0.035sin\frac{\mathrm{\&pi;}(T^{*}-273)}{600};---\left(5\right)$

${\mathrm{\&mu;}}^{*}=\frac{14.9\&times;{10}^6{\left(T^{*}\right)}^{\frac{3}{2}}}{T^{*}+110};---\left(6\right)$

${c_{pe}}^{*}=1155.4635-151.8036sin\&lsqb;\frac{\mathrm{\&pi;}}{2}-\frac{\mathrm{\&pi;}}{1200}(T^{*}-273)\&rsqb;;---\left(7\right)$

${{\mathrm{\&rho;}}_e}^{*}=\frac{{\mathrm{\&rho;}}_e{T}_{\mathrm{\&infin;}}}{T^{*}};---\left(8\right)$

${{\mathrm{St}}_e}^{*}\left\{\begin{array}{cc}=3.26{\left(\mathrm{Re}\right)}^{\frac{1}{2}}{\left(\mathrm{Pr}\right)}^{-\frac{3}{2}};& \mathrm{Re}<1.56\&times;{10}^6\\ =1.81{\left(\begin{array}{cc}\lg & \mathrm{Re}\end{array}\right)}^{-2.584}{\left(\mathrm{Pr}\right)}^{-\frac{3}{2}};& \mathrm{Re}>1.56\&times;{10}^6\end{array}\right.;---\left(9\right)$

$\mathrm{\&alpha;}={\mathrm{St}}_e^{*}\&CenterDot;{\mathrm{\&rho;}}_e^{*}\&CenterDot;{\mathrm{\&upsi;}}_{\mathrm{\&infin;}}^{*}\&CenterDot;c_{pe}^{*};---\left(10\right)$

Wherein, T ^*for reference temperature, for the Prandtl number of air-flow; μ ^*for air flow power viscosity; for air-flow specific heat capacity; for current density; for the Margoulis number of air-flow; α is convection transfer rate.

7. the hot-fluid control method of flight vehicle aerodynamic heat test according to claim 6, is characterized in that, described target heat flow density value is calculated by following formula:

$q=\mathrm{\&alpha;}(T_r-T_w)-{\mathrm{\&epsiv;\&sigma;}}_0{T}_w^4;---\left(11\right)$

Wherein, T _rfor air flow resistance temperature; T _wfor surface temperature; Q is target heat flow density value, and ε is aircraft testpieces surface blackness; σ ₀for blackbody radiation constant.

8. a heat flux control device for flight vehicle aerodynamic heat test, is characterized in that, comprising:

Data obtaining module, for obtaining pre-set flight elevation information and the pre-set flight velocity information of aircraft;

Temperature collect module, for controlling the surface temperature of Real-time Collection aircraft testpieces;

Target heat flow density calculates module, for calculating target heat flow density value according to described pre-set flight elevation information, pre-set flight velocity information and surface temperature;

Hot-fluid acquisition module, for controlling the heat flow density value on aircraft testpieces surface described in Real-time Collection;

Heating control module, for carrying out FEEDBACK CONTROL according to described heat flow density value and described target heat flow density value, controlling hot-fluid heating arrangement is that described aircraft testpieces carries out heating to reach target heat flow density value.

9. the heat flux control device of flight vehicle aerodynamic heat test according to claim 8, is characterized in that, described target heat flow density calculates module also for according to described pre-set flight high computational air stream on accompany surface temperature; According to described air stream on accompany surface temperature computation air flow resistance temperature; Reference temperature is calculated according to described air stream on accompany surface temperature, air flow resistance temperature and surface temperature; Convection transfer rate is calculated according to described reference temperature, pre-set flight velograph; According to described convection transfer rate, air flow resistance temperature, surface temperature, aircraft testpieces surface blackness and blackbody radiation constant calculations target heat flow density value.

10. a hot-fluid control system for flight vehicle aerodynamic heat test, comprises the heat flux control device of flight vehicle aerodynamic heat test as claimed in claim 8 or 9, also comprises:

For gathering the temperature sensor of the surface temperature of aircraft testpieces;

For gathering the heat flux sensor of the heat flow density value on described aircraft testpieces surface;

For the hot-fluid heating arrangement heated described aircraft testpieces.