CN112131667B - Physical simulation method for thermal deformation of wind tunnel scaling model - Google Patents
Physical simulation method for thermal deformation of wind tunnel scaling model Download PDFInfo
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Abstract
The invention provides a physical simulation method for thermal deformation of a wind tunnel scaling model, and belongs to the technical field of design and manufacture of aircraft wind tunnel models. The method comprises a scaling model and piezoelectric fiber composite material actuators, wherein the scaling model is used for wind tunnel tests, the wind tunnel tests are made of fiber reinforced resin matrix composite materials, a plurality of piezoelectric fiber composite material actuators are distributed on the inner surface of a scaling structure according to a certain layout, and the piezoelectric fiber composite material actuators are driven by an external independent power supply to deform so as to simulate the thermal deformation of the structure. The invention has wide temperature range, and can be widely used for wind tunnel test scaling models with different proportions.
Description
Technical Field
The invention belongs to the technical field of similar physical models of aircrafts, and relates to a method for simulating thermal deformation of an aircraft model in a real flight environment.
Background
With the rapid development of technology in the aerospace field, a hypersonic aircraft is very important for the future aerospace force countermeasure, and with the improvement of the flying speed of the aircraft, the temperature of the environment where the aircraft is located can rise sharply, and the influence of the temperature on the structural deformation of the aircraft is more and more serious, and mainly comprises the following steps: first, the mechanical properties such as material modulus, damping and the like change along with the temperature rise; and second, the pneumatic heating causes the structure to generate additional thermal deformation, so that the pneumatic shape of the wing is changed, and the structural function of the aircraft is affected. The novel characteristics bring a series of novel problems of aeroelasticity, so that the practical significance and strategic significance are realized by considering the theoretical basis of the thermoelasticity of the actual flight environment, especially the thermoelasticity under the high-temperature environment and the test system.
Aiming at the aeroelasticity problem caused by aerodynamic heating of the aircraft, researches such as related theoretical analysis, numerical simulation, wind tunnel test and flight test are currently carried out, wherein the wind tunnel test is an essential link in the development process of all the aircraft, and is a main method for obtaining and verifying new aerodynamic phenomena. Therefore, the influence of temperature on the aerodynamic performance of the aircraft is studied, and the most direct method is to manufacture a scaling model with similar structure and perform wind tunnel test. The high-speed blowing test under the actual hypersonic flight thermal environment is realized based on the existing wind tunnel conditions, and the method is specifically shown in the following steps: in order to study the aerodynamic heating effect of an aircraft in a hypersonic flight state, an external heating method is needed to construct a temperature field in the hypersonic flight state, a test device is extremely complex, the test period time is short, the single cost of the hypersonic wind tunnel test is high, and a large amount of energy and funds are consumed in the test due to multiple tests. Thus, it is difficult to perform effective thermokinetic elasticity tests in wind tunnels for a considerable period of time, both in terms of infrastructure, skill level and speed index of hypersonic aircrafts at present.
Disclosure of Invention
The invention provides a wind tunnel scaling model thermal effect physical simulation method based on intelligent materials, which aims to solve the problem that an environmental temperature field under hypersonic flight conditions is difficult to construct under the current wind tunnel test conditions, so that the influence of aerodynamic thermal effect on aerodynamic performance of an aircraft cannot be obtained. The method aims at solving the problems that the thermal dynamic elastic wind tunnel test cost of the existing aircraft is extremely high, the construction progress of test facilities cannot meet the actual test requirement, a piezoelectric fiber composite material actuator is adhered to the inner surface of the aircraft scaling model skin, a driving force is generated by using a reverse piezoelectric effect so as to drive the scaling model to deform, the thermal deformation of the hypersonic aircraft due to pneumatic heat under the actual flight condition is replaced, the thermal deformation generated by different temperature fields can be simulated by regulating and controlling the driving voltage and the layout of the piezoelectric fiber composite material actuator, so that the thermal dynamic elastic test can be performed in the conventional wind tunnel, the limitation of the technical condition of the existing wind tunnel is broken through, and the wind tunnel test cost can be remarkably reduced.
The invention adopts the technical scheme that:
a physical simulation method for thermal deformation of wind tunnel scaling model comprises the following steps:
the piezoelectric fiber composite material is adopted as an actuator to be adhered to the inner surface of the wind tunnel test scaling model 1, and proper voltage is applied to the piezoelectric fiber composite material actuator 2 by utilizing the inverse piezoelectric effect of the piezoelectric fiber composite material, so that the wind tunnel test scaling model 1 generates corresponding deformation, and the thermal deformation generated by the test model caused by aerodynamic heat under the actual flight condition is simulated;
(1) Calculating the thermal load and the corresponding thermal deformation of the wind tunnel test scaling model 1 under the specified flight environment condition;
(2) In the simulation process, dividing a wind tunnel test scaling model 1 into grid areas, adding piezoelectric fiber composite material actuators 2 with fixed sizes on each grid on the inner surface of the wind tunnel test scaling model 1, calculating the deformation state of the wind tunnel test scaling model 1 driven by the piezoelectric fiber composite material actuators 2, extracting a plurality of target design points on the wind tunnel test scaling model 1, taking the sum of absolute error squares of thermal deformation of the target design points under the flying environment condition in the step 1 and the driving deformation of the piezoelectric fiber composite material actuators 2 as optimization targets and taking the driving voltage and the fiber angle of the piezoelectric fiber composite material actuators 2 as optimization design variables, so as to ensure that the deformation of the piezoelectric fiber composite material actuators 2 under the driving has consistency with the thermal deformation under the actual environment; the equivalent calculation method comprises the following steps:
Find:Xi(Ui,θi)i＝1,2,…,n
Min:
Subject to:-500≤Ui≤1500 i＝1,2,…,n
0≤θi≤πi＝1,2,…,n
Wherein U i represents the driving voltage of each piezoelectric fiber composite material actuator 2, theta i represents the fiber angle of each piezoelectric fiber composite material actuator 2, i represents the area number of the attached piezoelectric fiber composite material actuator 2, j represents the target design point number for evaluating the thermal deformation physical simulation effect of the model, v j represents the displacement of the selected evaluation point of the wind tunnel test scaling model 1 in the flying environment, v j * represents the displacement of the selected evaluation point of the wind tunnel test scaling model 1 driven by the piezoelectric fiber composite material actuator 2;
(3) According to the optimization result in the step 2, uniformly pasting the piezoelectric fiber composite material actuators 2 on each grid on the inner side surface of the wind tunnel test scaling model 1, wherein the voltage and the angle of each piezoelectric fiber composite material actuator 2 are determined according to the theoretical analysis result of the wind tunnel test, and the thermal deformation requirement of the model in the test needs to be met.
Manufacturing a wind tunnel test shrinkage model 1 by adopting contact molding, wherein the wind tunnel test shrinkage model 1 is a fiber reinforced resin matrix composite material; the adhesive used for the piezoelectric fiber composite material actuator 2 to be adhered to the wind tunnel test scaling model 1 is epoxy resin adhesive; each piezoelectric fiber composite actuator 2 is driven to generate deformation by an external independent power supply 3 of-500 to +1500V.
The invention has the beneficial effects that: (1) The adopted piezoelectric fiber composite material actuator has good flexibility and machining performance and strong driving capability; (2) The designability is strong, and the fiber angle and the control voltage of each piezoelectric fiber composite material actuator can be designed according to different heating conditions of the structure; (3) Compared with the traditional wind tunnel test, the method can save test cost, and can quickly simulate the thermal deformation of the model under the actual flight condition, so that the thermal dynamic elasticity test research is carried out in the conventional wind tunnel.
Drawings
FIG. 1 is a schematic diagram of a wing model structure using the simulation method of the present invention.
FIG. 2 is a schematic diagram of the thermal deformation of a mold according to the present invention.
In the figure: 1 wind tunnel test scaling model, 2 piezoelectric fiber composite actuator, 3 drive power supply.
Detailed Description
The following detailed description of the invention is based on the technical solutions of the invention and the accompanying drawings:
(1) The invention relates to a method for simulating thermal deformation of an aircraft in actual flight, which comprises an aircraft wind tunnel test scaling model 1 and a piezoelectric fiber composite actuator 2. The piezoelectric fiber composite material actuator 2 is stuck on the inner side surface of the wind tunnel test scaling model 1, and the voltage and the angle of each actuator are determined according to the theoretical analysis result of the wind tunnel test, so that the thermal deformation requirement of the model in the test can be met.
(2) And calculating the thermal load and the corresponding thermal deformation of the wind tunnel test model under the specified flight environment conditions by using computational fluid dynamics and finite element simulation software.
(3) The manufacturability of the wind tunnel test model is considered, the inner surface of the model is divided into a plurality of piezoelectric fiber composite material brakes with fixed sizes, the deformation state of the wind tunnel test model driven by the piezoelectric fiber composite material actuators is calculated through simulation by utilizing finite element analysis software, a plurality of target design points on the model are extracted, the sum of absolute error squares of thermal deformation of the points under the flight environment condition in the step (2) and the driving deformation of the piezoelectric fiber composite material actuators is taken as an optimization target, and the driving voltage and the fiber angle of the piezoelectric fiber composite material actuators are taken as optimization design variables, so that the consistency of the deformation driven by the piezoelectric fiber composite material and the thermal deformation in the actual environment is ensured. The equivalent calculation method comprises the following steps:
Find:Xi(Ui,θi)i＝1,2,…,n
Min:
Subject to:-500≤Ui≤1500 i＝1,2,…,n
0≤θi≤π i＝1,2,…,n
Wherein U i represents the driving voltage of each piezoelectric fiber composite material actuator, theta i represents the fiber angle of each piezoelectric fiber composite material actuator, i represents the area number of the adhered piezoelectric fiber composite material actuator, j represents the target design point number for evaluating the thermal deformation physical simulation effect of the model, v k represents the displacement of the selected evaluation point of the wind tunnel test model in the flying environment, and v k * represents the displacement of the selected evaluation point of the wind tunnel test model under the driving of the piezoelectric fiber composite material actuator.
(4) And manufacturing a wind tunnel test model by adopting contact molding, wherein the model material is a fiber reinforced resin matrix composite material.
(5) Before the final assembly of the model is completed, each piezoelectric fiber composite actuator 2 is adhered to the inner surface of the test model according to the designated position and angle, and the adhesive is epoxy resin glue. And after the adhesive is solidified, the assembly of the wind tunnel test model is completed.
(6) By applying corresponding voltage to the piezoelectric fiber composite material actuator 2, the piezoelectric fiber composite material actuator 2 generates proper extension force or contraction force to drive the wind tunnel test model to deform, so that the deformation effect of the model driven by the piezoelectric fiber composite material actuator is equal to the thermal deformation of the model in a thermal environment.
On the basis of a wind tunnel test system based on an aircraft scaling model, the invention adopts the piezoelectric fiber composite material as an actuator, and the model deforms by applying voltage so as to simulate the thermal deformation of the model in an actual flight environment, thereby solving the cost problem of wind tunnel test thermal environment construction in a hypersonic flight state and providing a solution for researching the thermal dynamic elasticity problem of the hypersonic aircraft.
Claims (2)
1. A physical simulation method for thermal deformation of a wind tunnel scaling model is characterized by comprising the following steps:
According to the physical simulation method, thermal deformation simulation is realized through a wind tunnel test scaling model (1) and a piezoelectric fiber composite material actuator (2);
1) Calculating the thermal load and the corresponding thermal deformation of the wind tunnel test scaling model (1) under the specified flight environment condition;
2) In the simulation process, dividing a wind tunnel test scaling model (1) into grid areas, adding piezoelectric fiber composite material actuators (2) with fixed sizes on each grid on the inner surface of the wind tunnel test scaling model (1), calculating the deformation state of the wind tunnel test scaling model (1) under the driving of the piezoelectric fiber composite material actuators (2), extracting a plurality of target design points on the wind tunnel test scaling model (1), taking the square sum of absolute errors of thermal deformation of the target design points under the flying environment condition in the step 1) and the driving deformation of the piezoelectric fiber composite material actuators (2) as an optimization target, and taking the driving voltage and the fiber angle of the piezoelectric fiber composite material actuators (2) as optimization design variables, so as to ensure that the deformation of the piezoelectric fiber composite material actuators (2) under the driving has consistency with the thermal deformation under the actual environment; the equivalent calculation method comprises the following steps:
Find:Xi(Ui,θi)i＝1,2,…,n
Min:
Subject to:-500≤Ui≤1500 i＝1,2,…,n
0≤θi≤πi＝1,2,…,n
Wherein U i represents the driving voltage of each piezoelectric fiber composite material actuator (2), theta i represents the fiber angle of each piezoelectric fiber composite material actuator (2), i represents the area number of pasting the piezoelectric fiber composite material actuator (2), j represents the target design point number of evaluating the thermal deformation physical simulation effect of the model, v j represents the displacement of the selected evaluation point of the wind tunnel test scaling model (1) in the flying environment, v j * represents the displacement of the selected evaluation point of the wind tunnel test scaling model (1) under the driving of the piezoelectric fiber composite material actuator (2);
3) According to the optimization result in the step 2), uniformly pasting the piezoelectric fiber composite material actuators (2) on each grid on the inner side surface of the wind tunnel test scaling model (1), wherein the voltage and the angle of each piezoelectric fiber composite material actuator (2) are determined according to the theoretical analysis result of the wind tunnel test, and the thermal deformation requirement of the model in the test is required to be met.
2. The method for physical simulation of thermal deformation of a wind tunnel scaling model according to claim 1, wherein,
Manufacturing a wind tunnel test shrinkage model (1) by adopting contact molding, wherein the wind tunnel test shrinkage model (1) is a fiber reinforced resin matrix composite material; the adhesive used for the piezoelectric fiber composite material actuator (2) to be adhered to the wind tunnel test scaling model (1) is epoxy resin adhesive; each piezoelectric fiber composite material actuator (2) is driven to deform by an external independent power supply (3) of-500 to +1500V.
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| CN113820095B (en) * | 2021-08-23 | 2023-05-23 | 北京强度环境研究所 | Binding rocket wind tunnel scaling model assembly |
| CN116720264B (en) * | 2023-08-04 | 2023-10-20 | 中国空气动力研究与发展中心计算空气动力研究所 | Pneumatic layout method considering aerodynamic force/thermal accumulation deformation reverse geometry preset |
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| CN110207946A (en) * | 2019-06-26 | 2019-09-06 | 北京空天技术研究所 | Flow integrated model in wind tunnel scale reduction method inside and outside a kind of high speed |
| CN111006845A (en) * | 2019-12-27 | 2020-04-14 | 中国航天空气动力技术研究院 | High-speed wind tunnel test simulation method for grid rudder with large scaling |
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| CN110207946A (en) * | 2019-06-26 | 2019-09-06 | 北京空天技术研究所 | Flow integrated model in wind tunnel scale reduction method inside and outside a kind of high speed |
| CN111006845A (en) * | 2019-12-27 | 2020-04-14 | 中国航天空气动力技术研究院 | High-speed wind tunnel test simulation method for grid rudder with large scaling |
Non-Patent Citations (2)
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| Effect of Piezoelectric Material in Mitigation of Aerodynamic Forces;Gholamreza Amirinia et al.;Sensors and Instrumentation, Aircraft/Aerospace and Energy Harvesting;20180525;第8卷;33-40 * |
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