CN112131667A - 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 PDF

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CN112131667A
CN112131667A CN202011021522.1A CN202011021522A CN112131667A CN 112131667 A CN112131667 A CN 112131667A CN 202011021522 A CN202011021522 A CN 202011021522A CN 112131667 A CN112131667 A CN 112131667A
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fiber composite
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tunnel test
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CN112131667B (en
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孙士勇
范炜元
潘国港
杨睿
钱卫
牛斌
高飞
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Dalian University of Technology
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Abstract

The invention provides a physical simulation method for thermal deformation of a wind tunnel scale model, and belongs to the technical field of design and manufacture of aircraft wind tunnel models. The method comprises a scaling model for a wind tunnel test and piezoelectric fiber composite actuators, wherein the scaling model for the wind tunnel test is made of fiber reinforced resin matrix composite materials, a plurality of piezoelectric fiber composite actuators are distributed on the inner surface of a scaling structure according to a certain layout, and the piezoelectric fiber composite actuators are driven by an external independent power supply to generate deformation so as to simulate structural thermal deformation. The invention can simulate a wide temperature range and can be widely used for wind tunnel test scale models with different proportions.

Description

Physical simulation method for thermal deformation of wind tunnel scaling model
Technical Field
The invention belongs to the technical field of aircraft physical similarity models, and relates to a method for simulating thermal deformation of an aircraft model in a real flight environment.
Background
Along with the rapid development of the aerospace field technology, the hypersonic aircraft is vital to the strength confrontation of the future aerospace, and along with the improvement of the flight 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 reflected as: firstly, the mechanical properties such as material modulus, damping and the like are changed along with the temperature rise; second, aerodynamic heating causes additional thermal deformations in the structure, thereby changing the aerodynamic profile of the wing, affecting the structural function of the aircraft. These new characteristics bring a series of new problems of aeroelasticity, so that the theoretical basis and the test system of the aeroelasticity under the actual flight environment, particularly the high-temperature environment, have important practical significance and strategic significance.
At present, researches such as relevant theoretical analysis, numerical simulation, wind tunnel test, flight test and the like are developed aiming at the aeroelasticity problem of the aircraft caused by pneumatic heating, wherein the wind tunnel test is a necessary link in the development process of all the aircrafts and is a main method for obtaining and verifying a new pneumatic phenomenon. Therefore, the influence of temperature on the aerodynamic performance of the aircraft is researched, and the most direct method is to manufacture a scaling model with a similar structure and perform a wind tunnel test. And the realization of the high-speed blowing test under the actual hypersonic flight thermal environment based on the existing wind tunnel conditions has considerable difficulty, and the specific expression is as follows: in order to research the aerodynamic heat effect of the aircraft in the hypersonic flight state, an external heating method is needed to construct the temperature field in the hypersonic flight state, the test device is extremely complex, the test period is short, the single cost of the hypersonic wind tunnel test is very high, and multiple tests usually cause the test to consume a large amount of energy and capital. Therefore, it is difficult to perform an effective thermoaeroelastic test in a wind tunnel for a long period of time in terms of infrastructure, technical 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 an intelligent material, aiming at solving the problem that the influence of a pneumatic thermal effect on the pneumatic performance of an aircraft cannot be obtained because an environment temperature field under a hypersonic flight condition is difficult to construct under the current wind tunnel test condition. The thermal aeroelasticity wind tunnel test method aims at solving the problems that the test cost of the thermal aeroelasticity wind tunnel of the existing aircraft is very high, and the construction progress of test facilities cannot meet the actual test requirement, the piezoelectric fiber composite actuator is adhered to the inner surface of a scaling model skin of the aircraft, and the inverse piezoelectric effect is utilized to generate driving force so as to drive the scaling model to deform, so that the thermal deformation of the hypersonic aircraft caused by aerodynamic 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 actuator, the thermal aeroelasticity test can be carried out in the conventional wind tunnel, the limitation of the technical conditions of the existing wind tunnel is broken through, and the wind tunnel test cost can be obviously reduced.
The technical scheme adopted by the invention is as follows:
a physical simulation method for thermal deformation of a wind tunnel scale 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 under the actual flight condition due to the aerodynamic heat is simulated;
(1) calculating the heat load and the corresponding heat deformation of the wind tunnel test scaling model 1 under the specified flight environment condition;
(2) in the simulation process, a wind tunnel test scaling model 1 is divided into grid areas, a piezoelectric fiber composite actuator 2 with fixed size is added on each grid on the inner surface of the wind tunnel test scaling model 1, the deformation state of the wind tunnel test scaling model 1 under the drive of the piezoelectric fiber composite actuator 2 is calculated, a plurality of target design points on the wind tunnel test scaling model 1 are extracted, the sum of squares of absolute errors of thermal deformation of the target design points under the condition of flight environment in the step 1 and the drive deformation of the piezoelectric fiber composite actuator 2 is taken as an optimization target, and the drive voltage and the fiber angle of the piezoelectric fiber composite actuator 2 are taken as optimization design variables, so that the consistency of the deformation under the drive of the piezoelectric fiber composite actuator 2 and the thermal deformation under the actual environment is ensured; the equivalent calculation method comprises the following steps:
Find:Xi(Ui,θi)i＝1,2,…,n
Min:
Figure BDA0002700759660000031
Subject to:-500≤Ui≤1500 i＝1,2,…,n
0≤θi≤πi＝1,2,…,n
wherein, UiRepresents a driving voltage, θ, of each piezoelectric fiber composite actuator 2iDenotes a fiber angle of each piezoelectric fiber composite actuator 2, i denotes a region number to which the piezoelectric fiber composite actuator 2 is attached, j denotes a target design point number to evaluate a physical simulation effect of model thermal deformation, vjRepresenting the displacement, v, of the selected evaluation point of the wind tunnel test scaling model 1 in the flight environmentj *To representThe wind tunnel test scaling model 1 is driven by a piezoelectric fiber composite actuator 2 to select the displacement of an evaluation point;
(3) and (3) uniformly sticking the piezoelectric fiber composite actuators 2 on each grid on the inner side surface of the wind tunnel test scaling model 1 according to the optimization result in the step (2), wherein the voltage and the angle of each piezoelectric fiber composite 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 scaling model 1 by adopting contact molding, wherein the wind tunnel test scaling model 1 is made of a fiber reinforced resin matrix composite material; the adhesive used for adhering the piezoelectric fiber composite actuator 2 on the wind tunnel test scaling model 1 is epoxy resin adhesive; each piezoelectric fiber composite material actuator 2 is driven by an external-500- +1500V independent power supply 3 to generate deformation.
The invention has the beneficial effects that: (1) the adopted piezoelectric fiber composite material actuator has good flexibility, good machining performance and strong driving capability; (2) the designability is strong, and the fiber angle and the control voltage of each piezoelectric fiber composite actuator can be designed according to different heating conditions of the structure; (3) compared with the traditional wind tunnel test, the method can save the test cost, and can quickly realize the simulation of the thermal deformation of the model under the actual flight condition, thereby carrying out the thermoaeroelasticity test research in the conventional wind tunnel.
Drawings
Fig. 1 is a schematic view of a wing model structure of a simulation method adopted in the present invention.
FIG. 2 is a schematic diagram of the present invention for thermally deforming a mold.
In the figure: the method comprises the following steps of 1, wind tunnel test scaling model, 2, piezoelectric fiber composite actuator and 3, driving power supply.
Detailed Description
The following detailed description of the embodiments is made in accordance with the technical solutions of the present invention and the accompanying drawings:
(1) the invention relates to a method for simulating thermal deformation in the actual flight condition of an aircraft, 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 adhered to the inner side surface of the wind tunnel test scaling model 1, the voltage and the angle of each actuator are determined according to the theoretical analysis result of the wind tunnel test, and the requirement of model thermal deformation in the test can be met.
(2) And calculating the heat load and the corresponding heat deformation of the wind tunnel test model under the specified flight environment condition by utilizing computational fluid dynamics and finite element simulation software.
(3) Considering the manufacturability of the wind tunnel test model, dividing a plurality of piezoelectric fiber composite material brakes with fixed sizes on the inner surface of the model, utilizing finite element analysis software to simulate and calculate the deformation state of the wind tunnel test model under the drive of the piezoelectric fiber composite material actuators, extracting a plurality of target design points on the model, taking the sum of the square absolute errors of the thermal deformation of the points under the flight environment condition in the step (2) and the drive deformation of the piezoelectric fiber composite material actuators as an optimization target, and taking the drive voltage and the fiber angle of the piezoelectric fiber composite material actuators as optimization design variables, thereby ensuring that the deformation under the drive of the piezoelectric fiber composite material 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:
Figure BDA0002700759660000051
Subject to:-500≤Ui≤1500 i＝1,2,…,n
0≤θi≤π i＝1,2,…,n
wherein, UiRepresents a driving voltage, theta, of each piezoelectric fiber composite actuatoriDenotes a fiber angle of each piezoelectric fiber composite actuator, i denotes a region number to which the piezoelectric fiber composite actuator is attached, j denotes a target design point number to evaluate a physical simulation effect of model thermal deformation, vkRepresenting the displacement, v, of a selected evaluation point of a wind tunnel test model in a flight environmentk *Representing wind tunnel test model in piezoelectric fiber composite materialThe actuator drives the displacement of the lower selected evaluation point.
(4) A wind tunnel test model is manufactured by adopting contact molding, and 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 material actuator 2 is bonded to the inner surface of the test model according to the specified position and angle, and the bonding agent is epoxy resin glue. And after the adhesive is cured, assembling the wind tunnel test model.
(6) By applying corresponding voltage to the piezoelectric fiber composite actuator 2, the piezoelectric fiber composite actuator 2 generates appropriate 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 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 piezoelectric fiber composite material is used as an actuator, and the model is deformed by applying voltage to simulate the thermal deformation of the model in an actual flight environment, so that the cost problem of the construction of the wind tunnel test thermal environment in a hypersonic flight state is solved, and a solution is provided for researching the thermoaeroelasticity problem of the hypersonic aircraft.

Claims (2)

1. A physical simulation method for thermal deformation of a wind tunnel scale model is characterized by comprising the following steps:
the physical simulation method realizes thermal deformation simulation through a wind tunnel test scaling model (1) and a piezoelectric fiber composite material actuator (2);
1) calculating the heat load and the corresponding heat deformation of the wind tunnel test scaling model (1) under the specified flight environment condition;
2) in the simulation process, the wind tunnel test scaling model (1) is divided into grid areas, a piezoelectric fiber composite actuator (2) with fixed size is added on each grid on the inner surface of the wind tunnel test scaling model (1), the deformation state of the wind tunnel test scaling model (1) driven by the piezoelectric fiber composite actuator (2) is calculated, a plurality of target design points on the wind tunnel test scaling model (1) are extracted, taking the sum of the squares of the absolute errors of the thermal deformation of the target design point under the flying environment condition in the step 1) and the driving deformation of the piezoelectric fiber composite material actuator (2) as an optimization target, the driving voltage and the fiber angle of the piezoelectric fiber composite material actuator (2) are taken as optimization design variables, thereby ensuring that the deformation under the driving of the piezoelectric fiber composite material actuator (2) 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:
Figure FDA0002700759650000011
Subject to:-500≤Ui≤1500 i＝1,2,…,n
0≤θi≤πi＝1,2,…,n
wherein, UiRepresents a driving voltage, theta, of each piezoelectric fiber composite actuator (2)iDenotes a fiber angle of each piezoelectric fiber composite actuator (2), i denotes a number of a region to which the piezoelectric fiber composite actuator (2) is attached, j denotes a number of a target design point for evaluating a physical simulation effect of a model for thermal deformation, vjRepresenting the displacement, v, of a selected evaluation point of a wind tunnel test scaling model (1) in a flight environmentj *Representing the displacement of the selected evaluation point of the wind tunnel test scaling model (1) under the drive of the piezoelectric fiber composite actuator (2);
3) according to the optimization result in the step 2), uniformly sticking the piezoelectric fiber composite 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 actuator (2) are determined according to the theoretical analysis result of the wind tunnel test, and the requirement of model thermal deformation in the test needs to be met.
2. The physical simulation method of thermal deformation of a wind tunnel scaling model according to claim 1,
manufacturing a wind tunnel test scaling model (1) by adopting contact molding, wherein the wind tunnel test scaling model (1) is a fiber reinforced resin matrix composite material; the piezoelectric fiber composite material actuator (2) is stuck on the wind tunnel test scaling model (1) by using epoxy resin glue as a sticking agent; each piezoelectric fiber composite material actuator (2) is driven by an external-500- +1500V independent power supply (3) to generate deformation.
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Publication number Priority date Publication date Assignee Title
CN113820095A (en) * 2021-08-23 2021-12-21 北京强度环境研究所 Wind tunnel scale model assembly of bundled rocket
CN116720264A (en) * 2023-08-04 2023-09-08 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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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

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113820095A (en) * 2021-08-23 2021-12-21 北京强度环境研究所 Wind tunnel scale model assembly of bundled rocket
CN113820095B (en) * 2021-08-23 2023-05-23 北京强度环境研究所 Binding rocket wind tunnel scaling model assembly
CN116720264A (en) * 2023-08-04 2023-09-08 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
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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