CN114235329A - Full-aircraft sudden wind load wind tunnel test device - Google Patents
Full-aircraft sudden wind load wind tunnel test device Download PDFInfo
- Publication number
- CN114235329A CN114235329A CN202111458229.6A CN202111458229A CN114235329A CN 114235329 A CN114235329 A CN 114235329A CN 202111458229 A CN202111458229 A CN 202111458229A CN 114235329 A CN114235329 A CN 114235329A
- Authority
- CN
- China
- Prior art keywords
- full
- steel cable
- model
- wind tunnel
- wind
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 48
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 106
- 239000010959 steel Substances 0.000 claims abstract description 106
- 238000004088 simulation Methods 0.000 claims description 16
- 230000001133 acceleration Effects 0.000 claims description 12
- 239000002184 metal Substances 0.000 claims description 9
- 238000006073 displacement reaction Methods 0.000 claims description 7
- 229920000742 Cotton Polymers 0.000 claims description 5
- 239000011521 glass Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 7
- 230000033001 locomotion Effects 0.000 abstract description 6
- 239000000725 suspension Substances 0.000 description 14
- 238000005259 measurement Methods 0.000 description 6
- 230000005484 gravity Effects 0.000 description 5
- 239000002023 wood Substances 0.000 description 4
- 239000000243 solution Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000011152 fibreglass Substances 0.000 description 2
- 206010034719 Personality change Diseases 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000007853 buffer solution Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
Abstract
The application relates to the technical field of aeroelasticity, in particular to a full-aircraft sudden wind load wind tunnel test device which comprises a full-aircraft elasticity model, a sudden wind generator, a top bracket system and a main steel cable system; the method comprises the steps that a model of the whole machine is arranged to carry out a gust test of the whole machine, a plurality of groups of gust generators are arranged, a swing cylinder in each group of gust generators can drive blades to deflect, and different blades deflect to different angles so as to generate gust in any frequency combination form; through top bracket system and full quick-witted elastic model elastic connection, carry out spacing and direction to the front end and the rear end of model respectively through setting up preceding cable wire mechanism and back cable wire mechanism for the model can be at five degrees of freedom free motions down, makes full quick-witted elastic model can be close real flight state free motion through setting up elastic support, thereby can accurately obtain the full quick-witted gust wind dynamic load wind tunnel test data of aircraft.
Description
Technical Field
The application belongs to the technical field of aeroelasticity, and particularly relates to a full-aircraft wind gushing load wind tunnel test device.
Background
In the prior fighter plane or the small-aspect-ratio plane with relatively rigid wings, the gust dynamic load is not a serious load working condition of the plane design, so that the heavy attention is not needed, and for a large-aspect-ratio transport plane, the gust dynamic load is a key factor influencing the load boundary and the fatigue life of the plane.
At present, some developed gust wind tunnel tests are also only gust dynamic load alleviation tests aiming at components, which have several significant differences from full-machine-level gust dynamic load tests, namely: the suspension mode is different, the parts are generally in a root fixing or floor supporting mode, the whole machine model needs to adopt a suspension supporting mode, and the influence of a supporting system on the sudden wind load is considered. At present, some full-aircraft suspension support systems are developed in flutter tests and comprise five-degree-of-freedom tensioning force suspension support systems and double-cable suspension systems, but the support system mechanism corresponding to the five-degree-of-freedom tensioning force suspension support systems is complex and has a large blocking degree for wind tunnel tests, and the double-cable suspension systems are difficult to support under the condition of large model weight and difficult to adjust and control in stability; secondly, the method comprises the following steps: model attitude control is different, the former component test and the full-aircraft flutter test have no strict requirements on the model attitude, and the full-aircraft gusty wind dynamic load test needs to control the model control surface through a control system so as to maintain the model to carry out test measurement under a certain attitude angle; thirdly, the method comprises the following steps: the load concerns are different, the part gust load alleviation test concerns changes in wing tip and root load increments, while the full-aircraft gust load test concerns changes in distributed loads at the full-aircraft center of gravity, at the wing tip, at the part root and at other important locations.
Therefore, how to more effectively test the full-aircraft sudden wind load is a problem to be solved.
Disclosure of Invention
The application aims to provide a full-aircraft sudden wind load wind tunnel test device to solve the problem that a full-aircraft sudden wind load wind tunnel test is carried out in the prior art.
The technical scheme of the application is as follows: a full-aircraft sudden wind load wind tunnel test device comprises a full-aircraft elastic model, a sudden wind generator arranged in front of the full-aircraft elastic model, a top bracket system connected above the full-aircraft elastic model, and a main steel cable system connected with the full-aircraft elastic model; the gust generator is arranged in at least one group and comprises a swinging cylinder and blades, wherein one end of each blade is connected with the swinging cylinder, and the other end of each blade is rotatably connected to the side wall of the wind tunnel; the top support system is elastically connected with the full-machine elastic model, the main steel cable system comprises a front steel cable mechanism and a rear steel cable mechanism, the front steel cable mechanism is connected with the upper position and the lower position of the front part of the full-machine elastic model, the rear steel cable mechanism is connected with the left side and the right side of the rear part of the full-machine elastic model, the front steel cable mechanism is in running fit with the full-machine elastic model, a free end is arranged at one end, far away from the full-machine elastic model, of the rear steel cable mechanism, and the full-machine elastic model can pull the rear steel cable mechanism to move.
Preferably, the top bracket system comprises a bracket, two groups of upper vertical steel cables, two groups of springs and two groups of lower vertical steel cables, the upper vertical steel cables, the springs and the lower vertical steel cables are arranged in parallel along the length direction of the full-mechanical elastic model, and the upper vertical steel cables are arranged on the bracket; the upper vertical steel cable and the lower vertical steel cable are arranged up and down, the spring is vertically connected between the upper vertical steel cable and the lower vertical steel cable, and the lower end of the lower vertical steel cable is connected with the full-mechanical elastic model.
Preferably, the upper vertical steel cable is provided with a first sliding block, the support is provided with a first sliding rail arranged along the length direction of the full-machine elastic model, and the first sliding block is in sliding fit with the first sliding rail.
Preferably, the support is provided with a cable adjusting device, and the cable adjusting device can adjust the length of the upper vertical cable.
Preferably, the support, the upper vertical steel cable and the spring are located on the outer side of the top of the wind tunnel, an opening is formed in the top of the wind tunnel, the lower vertical steel cable penetrates through the opening and extends into the wind tunnel to be connected with the full-mechanical elastic model, and the diameter of the opening is larger than that of the spring.
Preferably, the front steel cable mechanism comprises a front steel cable and a front pulley, the front steel cable and the front pulley are divided into two groups, two groups of front steel cables are obliquely arranged, one group of front pulleys are rotatably connected to the top of the airplane, the other group of front pulleys are rotatably connected to the bottom of the airplane, one end of one group of front steel cables is connected with the top plate of the wind tunnel, the other end of one group of front steel cables is connected with the front pulley positioned at the top of the model, one end of the other group of front steel cables is connected with the bottom plate of the wind tunnel, and the other end of the other group of front steel cables is connected with the front pulley positioned at the bottom of the model.
Preferably, the rear cable mechanism comprises two groups of rear cables and rear pulleys, one group of rear pulleys is rotatably connected to the left side of the airplane, the other group of rear pulleys is rotatably connected to the right side of the airplane, the two groups of rear cables are obliquely arranged, one group of rear cables is connected with the rear pulley on the left side of the airplane, and the other group of rear cables is connected with the rear pulley on the right side of the airplane; two sets of second slide rails from top to bottom are arranged on the side wall of the wind tunnel, free end pulleys are arranged on the second slide rails, the two sets of free end pulleys are respectively connected with the middle parts of the two sets of rear steel cables, one end, far away from the full-machine elastic model, of each rear steel cable is connected with a weight device, and weights in the weight devices can be increased or decreased.
Preferably, a second sliding block is arranged on the second sliding rail in a sliding fit mode, the second sliding block is connected with the free end pulley, the second sliding rail is arranged along the length direction of the full-mechanical elastic model, and an electric emergency locking mechanism is arranged on a support of the free end pulley.
Preferably, full quick-witted elastic model includes wing, engine, fuselage, horizontal tail and vertical fin, the wing includes metal roof beam and wooden frame, it has the lead to bond on metal roof beam or the wooden frame, the parcel has the cotton paper on wing, horizontal tail and the vertical fin, the parcel has the glass steel on fuselage and the engine, be connected with electric steering engine between wing and the aileron.
Preferably, the system further comprises a measuring system, wherein the measuring system comprises measuring equipment, a data acquisition system and a flight simulation control system, and the data acquisition system and the flight simulation control system are arranged outside the wind tunnel; the measuring equipment comprises a gyroscope, a linear displacement sensor, an acceleration sensor and a strain gauge, wherein the gyroscope and the linear displacement sensor are arranged on the fuselage, the acceleration sensor is arranged on the wingtip of the wing, and the strain gauge is arranged at the root of the wing; the data acquisition system comprises a gust speed acquisition system, a model attitude data acquisition system, an acceleration acquisition system and a strain acquisition system which are connected with the measuring equipment; the flight simulation control system comprises a signal converter, a simulation control system and a steering engine controller, wherein the signal converter, the simulation control system and the steering engine controller are connected with the data acquisition system and the gust generator.
The full-aircraft gushing wind load wind tunnel test device comprises a full-aircraft elastic model, a gushing wind generator, a top bracket system and a main steel cable system; the method comprises the steps that a model of the whole machine is arranged to carry out a gust test of the whole machine, a plurality of groups of gust generators are arranged, a swing cylinder in each group of gust generators can drive blades to deflect, and different blades deflect to different angles so as to generate gust in any frequency combination form; through top bracket system and full quick-witted elastic model elastic connection, carry out spacing and direction to the front end and the rear end of model respectively through setting up preceding cable wire mechanism and back cable wire mechanism for the model can be at five degrees of freedom free motions down, makes full quick-witted elastic model can be close real flight state free motion through setting up elastic support, thereby can accurately obtain the full quick-witted gust wind dynamic load wind tunnel test data of aircraft.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of the overall structure of the present application;
FIG. 2 is a schematic view of a full-mechanical elastic model of the present application;
FIG. 3 is a system block diagram of a data acquisition system and a flight simulation control system according to the present application.
1. A blade; 2. a swing cylinder; 3. a rotating bearing; 4. a support; 5. a first slide rail; 6. a first slider; 7. an upper vertical wire rope; 8. a spring; 9. a lower vertical wire rope; 10. opening a hole; 11. a full-mechanical elastic model; 12. a wire rope adjusting device; 13. a front wire rope; 14. a rear wire rope; 15. a front pulley; 16. a wind tunnel ceiling; 17. a wind tunnel floor; 18. a rear pulley; 19. a wind tunnel sidewall; 20. a second slide rail; 21. an airfoil; 22. an engine; 23. a body; 24. flattening the tail; 25. hanging a tail; 26. a metal beam; 27. a wooden frame; 28. lead blocks; 29. cotton paper; 30. a gust speed acquisition system; 31. a model attitude data acquisition system; 32. an acceleration acquisition system; 33. a strain acquisition system; 34. a signal converter; 35. a simulation control system; 36. a steering engine controller; 37. a free end pulley; 38. a second slider; 39. a weight device.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
Compared with the existing rigid support system, the full-aircraft gushing wind load wind tunnel test device adopts an elastic support mode to carry out the gushing wind load wind tunnel test, particularly supports a model in an elastic suspension mode, and is provided with a main steel cable system to limit and guide the model, so that the full-aircraft model can be subjected to the accurate gushing test.
As shown in fig. 1, the system specifically comprises a full-mechanical elastic model 11, a gust generator, a top bracket system and a main steel cable system. The full-mechanical elastic model 11 is arranged in the wind tunnel, and the gust generator is arranged in front of the full-mechanical elastic model 11; the top support system is arranged at the top of the wind tunnel and connected with the full-mechanical elastic model 11, and is used for supporting the full-mechanical elastic model 11; the main steel cable system is connected with the full-mechanical elastic model 11 and plays a role in auxiliary supporting and guiding.
The wind tunnel side wall 19 is provided with a rotating bearing 3, at least one group of gust generators are arranged, three groups of gust generators are arranged up and down in the figure 1, each gust generator comprises a swinging cylinder 2 and a blade 1, one end of each blade 1 is connected with the swinging cylinder 2, and the other end of each blade 1 is connected with the rotating bearing 3; top mounting system and the 11 elastic connection of full quick-witted elastic model, main cable wire system includes preceding cable wire mechanism and back cable wire mechanism, and preceding cable wire mechanism links to each other with the anterior upper and lower position of full quick-witted elastic model 11, and back cable wire mechanism links to each other with the left and right sides at full quick-witted elastic model 11 rear portion, and preceding cable wire mechanism and full quick-witted elastic model 11 normal running fit, the one end that full quick-witted elastic model 11 was kept away from to back cable wire mechanism sets up the free end, and full quick-witted elastic model 11 can stimulate back cable wire mechanism and remove.
Because full quick-witted elasticity model 11 has the degree of freedom of 5 directions such as deflection, ups and downs, every single move in the gust, the high while of degree of freedom needs to control the flight gesture of aircraft, consequently comes to carry out the stable stay to the aircraft through setting up top mounting system and main cable wire system when, guarantees that 5 degrees of freedom of model can not receive the influence, and main cable wire system can adjust the stability of model simultaneously, avoids interfering.
The gust generator ensures that the full-machine elastic model 11 can be subjected to gusts in all directions, when the gusts in a certain direction are required, the swing cylinder 2 works and drives the blades 1 to deflect, the blades 1 are deflected to a specified angle according to the gust direction, the blades 1 in a plurality of groups of gust generators deflect to different directions, one or more gust fields with mutually combined frequency and amplitude can be generated, and therefore the gusts in any frequency combination form can be generated.
The top bracket system is used for elastically supporting the full-aircraft test model, and is matched with the rotation fit of the front part of the model and the degree of freedom fit of the rear part of the model of the rear steel cable mechanism in cooperation with the front steel cable mechanism, so that the aircraft can rotate or swing in multiple directions, the elastic buffer system of the full-aircraft elastic model 11 is combined, the free flight state of the aircraft can be effectively simulated, the model can be prevented from having large attitude change, the data of the aircraft in the gushing state can be accurately obtained, and the full-aircraft test model is simple in structure and stable and convenient to control.
Preferably, the top bracket system comprises a bracket 4, an upper vertical steel cable 7, a spring 8 and a lower vertical steel cable 9, the bracket 4 is arranged at the outer side of the top of the wind tunnel, the upper vertical steel cable 7, the spring 8 and the lower vertical steel cable 9 are divided into two groups and arranged side by side along the length direction of the full-mechanical elastic model 11, and the upper vertical steel cable 7 is arranged on the bracket 4; the upper vertical steel cable 7 and the lower vertical steel cable 9 are arranged up and down, the spring 8 is vertically connected between the upper vertical steel cable 7 and the lower vertical steel cable 9, the lower end of the lower vertical steel cable 9 is connected with the full-mechanical elastic model 11, and the lower end of the lower vertical steel cable 9 is selected at two nodes of the first-order vertical bending of the machine body 23 at the connecting position of the full-mechanical elastic model 11, so that the influence of a suspension device on the fixed vibration characteristic of the model is reduced.
The steel cable is arranged into two sections of the upper vertical steel cable 7 and the lower vertical steel cable 9, the bracket 4 and the full-mechanical elastic model 11 can be respectively and stably connected, and the spring 8 is connected between the upper vertical steel cable 7 and the lower vertical steel cable 9 to realize elastic support of the full-mechanical elastic model 11.
Preferably, the upper vertical steel cable 7 is provided with a first sliding block 6, the bracket 4 is provided with a first sliding rail 5 arranged along the length direction of the full-machine elastic model 11, and the first sliding block 6 is in sliding fit with the first sliding rail 5. The position between two hoisting points of the full-aircraft elastic model 11 can be adjusted by adjusting the fixed position of the first sliding block 6 on the first sliding rail 5, so that the gravity center position of the aircraft can be accurately controlled.
Preferably, the bracket 4 is provided with a wire rope adjusting device 12, and the wire rope adjusting device 12 can adjust the length of the upper vertical wire rope 7. The initial height of the model in the wind tunnel can be controlled by adjusting the length of the upper vertical wire ropes 7 by the wire rope adjusting device 12.
Preferably, the bracket 4, the upper vertical steel cable 7 and the spring 8 are positioned at the outer side of the top of the wind tunnel, the top of the wind tunnel is provided with an opening 10, the lower vertical steel cable 9 extends into the interior of the wind tunnel through the opening 10 to be connected with a full-mechanical elastic model 11, and the diameter of the opening 10 is larger than that of the spring 8. The support 4, the upper vertical steel and the spring 8 are arranged on the outer side of the top of the wind tunnel, so that the influence of a top support system on the surface flow field of the full-mechanical elastic model 11 in the wind tunnel can be reduced as much as possible, and the diameter of the opening 10 is set to be larger than that of the spring 8 so as to facilitate the vertical hoisting of the model.
Preferably, the front steel cable mechanism comprises a front steel cable 13 and a front pulley 15, the front steel cable 13 and the front pulley 15 are divided into two groups, the two groups of front steel cables 13 are obliquely arranged, one group of front pulley 15 is rotatably connected to the top of the airplane, the other group of front pulley 15 is rotatably connected to the bottom of the airplane, one group of front steel cables 13 is connected with the wind tunnel top plate 16 at one end and is connected with the front pulley 15 at the top of the model at the other end, the other group of front steel cables 13 is connected with the wind tunnel bottom plate 17 at one end and is connected with the front pulley 15 at the bottom of the model at the other end.
By obliquely arranging the two groups of front steel cables 13 at the front upper part and the front lower part of the model respectively, when the airplane is influenced by the gust in the wind tunnel, the upper and lower positions of the nose of the model can be pulled, so that the nose of the model is prevented from generating large displacement.
Preferably, the rear cable mechanism comprises a rear cable 14 and a rear pulley 18, the rear cable 14 and the rear pulley 18 are divided into two groups, one group of rear pulleys 18 are rotatably connected to the left side of the airplane, the other group of rear pulleys 18 are rotatably connected to the right side of the airplane, the two groups of rear cables 14 are obliquely arranged, one group of rear cables 14 are connected with the rear pulley 18 on the left side of the airplane, and the other group of rear cables 14 are connected with the rear pulley 18 on the right side of the airplane; two sets of second slide rails 20 about being equipped with on the wind-tunnel lateral wall 19, be equipped with free end pulley 37 on the second slide rail 20, two sets of free end pulleys 37 link to each other with the middle part of two sets of rear cable wires 14 respectively, and the one end that rear cable wire 14 kept away from full quick-witted elastic model 11 is connected with weight device 39, and weight device 39 is in the horizontality and pulls the model under the effect of gravity, and the weight in the weight device 39 can increase or reduce.
Wherein the left and right sides in the above description are taken from the back of the model as the observation points.
Through locating the back upper place and the back below of model with two sets of the place ahead cable wire 13 slope respectively, the aircraft is when receiving the gust influence in the wind tunnel, can stimulate the tail left and right sides position of model, the pulling force of back cable wire mechanism is applyed through weight device 39, when the wind-force that the model received surpassed weight device 39's pulling force, can stimulate weight device 39 and upwards remove, the model can deflect this moment, multiple motions such as roll-over, through adjusting the weight on the weight device 39, can adjust system's stability, the weight is heavier, stability is better.
The front pulley 15 and the rear pulley 18 are both arranged on the skin of the model fuselage 23 and are not shaped, so that the large pitching and rolling moments can be provided, and the surface flow field of the fuselage 23 is not influenced.
Preferably, a second sliding block 38 is slidably fitted on the second sliding rail 20, the second sliding block 38 is connected with the free end pulley 37, the second sliding rail 20 is arranged along the length direction of the full mechanical elastic model 11, and an electric emergency locking mechanism is arranged on a support of the free end pulley 37. The second sliding block 38 moves along the second sliding rail 20, so that the front-back position of the rear pulley 18 can be changed, the front-back position of the rear steel cable 14 can be adjusted, and the stability of the system can be changed; when the model moves greatly or the overload of the acceleration sensor on the wing exceeds a set limit value, an electric signal is sent to the electric emergency locking mechanism, and the electric emergency locking mechanism fixes the rear steel cable 14 to prevent the model from moving unstably.
As shown in fig. 2, preferably, the full-aircraft elastic model 11 includes an airfoil 21, an engine 22, an aircraft body 23, a horizontal tail 24 and a vertical tail 25, the airfoil 21 includes a metal beam 26 and a wood frame 27, a lead block 28 is bonded on the metal beam 26 or the wood frame 27, the airfoil 21, the horizontal tail 24 and the vertical tail 25 are wrapped with cotton paper 29, the aircraft body 23 and the engine 22 are wrapped with glass fiber reinforced plastics, and an electric steering engine is connected between the airfoil 21 and an aileron. The model of the wing 21 simulates the rigidity characteristic of an airplane through a metal beam 26, dimension and force transmission through a wood frame 27, mass inertia characteristic through a lead block 28 bonded on the metal beam 26 or the wood frame 27, an electric steering engine is used for controlling deflection of a control surface, the shape is simulated through a cotton paper 29 or a glass fiber reinforced plastic as a skin, and the structural form of an engine 22, a fuselage 23, a horizontal tail 24 and a vertical tail 25 is similar to that of the wing 21.
As shown in fig. 2 and 3, preferably, the wind tunnel further includes a measurement system, where the measurement system includes a measurement device, a data acquisition system disposed outside the wind tunnel, and a flight simulation control system; the measuring equipment comprises a gyroscope and a linear displacement sensor which are arranged on the fuselage 23, an acceleration sensor which is arranged on the wingtip of the wing 21 and a strain gauge which is arranged at the root of the wing 21 so as to respectively detect data such as angular motion amount, linear displacement, acceleration, stress, wind speed and the like of the gravity center of the model, the wingtip and the component according to equal positions; the data acquisition system comprises a gust speed acquisition system 30, a model attitude data acquisition system 31, an acceleration acquisition system 32 and a strain acquisition system 33 which are connected with the measuring equipment and are used for receiving various data acquired by the measuring equipment; the flight simulation control system comprises a signal converter 34, a simulation control system 35 and a steering engine controller 36 which are connected with a data acquisition system and a gust generator and used for processing acquired data signals and controlling the gust generator and the full-aircraft elastic model 11, the simulation control system 35 can control the steering engine controller 36 and control the deflection of a control surface, the flight attitude of the full-aircraft model is further changed, the stability of the whole-aircraft system can be changed by changing the control law in the simulation control system 35, and the gust alleviation control can be realized.
Compared with the prior art, the gust generator which is positioned at the front end of the wind tunnel and driven by the single swinging cylinder 2 can generate gust with any frequency combination form; the suspension support system which is positioned in the middle of the wind tunnel and can release five rigid body degrees of freedom and adjust the position and the suspension rigidity can better simulate the free flight state of a real airplane, and has the advantages of simple structure, easy installation, convenient operation, adjustable parameters, safety, reliability and small pneumatic interference, and can meet the requirement of a full-airplane gushing dynamic load test; the test measurement equipment positioned outside the wind tunnel collects incoming flow speed and gust speed signals, gyroscope signals, acceleration sensor signals and strain gauge signals, and processes and displays the signals in real time; the model is an elastic model scaled down according to a certain scale, simulates the appearance, mass and rigidity characteristics of an airplane, is provided with an electric steering engine to control the deflection of a control surface, and is provided with a gyroscope, a displacement sensor, an acceleration sensor, a strain gauge and other measuring equipment.
There are several significant differences from the existing component level gust wind load test, first: the suspension modes are different, the parts are generally root fixing or floor supporting modes, the whole machine model needs to adopt a suspension supporting mode, and the influence of a supporting system on the gust dynamic load is considered; the invention adopts the elastic suspension mode, and can better simulate the free flight state of the airplane; secondly, the method comprises the following steps: model attitude control is different, the former component test and the full-aircraft flutter test have no strict requirements on the model attitude, and the full-aircraft gusty wind dynamic load test needs to control the model control surface through a control system so as to maintain the model to carry out test measurement under a certain attitude angle; thirdly, the method comprises the following steps: the load concerns are different, the part gust load mitigation test concerns the variation of the wing tip and root load increments, and the gust load test concerns the variation of the distributed loads at the center of gravity of the entire aircraft, at the wing tip, at the part root and other important parts.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a wind tunnel test device of full quick-witted sudden wind load which characterized in that: the device comprises a full-mechanical elastic model (11), a gust generator arranged in front of the full-mechanical elastic model (11), a top bracket system connected above the full-mechanical elastic model (11), and a main steel cable system connected with the full-mechanical elastic model (11);
the wind burst generators are arranged in at least one group and comprise swinging cylinders (2) and blades (1), one ends of the blades (1) are connected with the swinging cylinders (2), and the other ends of the blades are rotatably connected to the side walls (19) of the wind tunnel;
the top support system is elastically connected with the full-machine elastic model (11), the main steel cable system comprises a front steel cable mechanism and a rear steel cable mechanism, the front steel cable mechanism is connected with the upper and lower positions of the front part of the full-machine elastic model (11), the rear steel cable mechanism is connected with the left and right sides of the rear part of the full-machine elastic model (11), the front steel cable mechanism is in running fit with the full-machine elastic model (11), one end, far away from the full-machine elastic model (11), of the rear steel cable mechanism is provided with a free end, and the full-machine elastic model (11) can pull the rear steel cable mechanism to move.
2. The full-aircraft wind gust load wind tunnel test device according to claim 1, characterized in that: the top support system comprises a support (4), upper vertical steel cables (7), springs (8) and lower vertical steel cables (9), the support (4) is arranged on the outer side of the top of the wind tunnel, the upper vertical steel cables (7), the springs (8) and the lower vertical steel cables (9) are divided into two groups and arranged side by side along the length direction of the full-mechanical elastic model (11), and the upper vertical steel cables (7) are arranged on the support (4);
the upper vertical steel cable (7) and the lower vertical steel cable (9) are arranged up and down, the spring (8) is vertically connected between the upper vertical steel cable (7) and the lower vertical steel cable (9), and the lower end of the lower vertical steel cable (9) is connected with the full-mechanical elastic model (11).
3. The full-aircraft wind gust load wind tunnel test device according to claim 2, characterized in that: the upper portion vertical steel cable (7) is provided with a first sliding block (6), the support (4) is provided with a first sliding rail (5) arranged along the length direction of the full-machine elastic model (11), and the first sliding block (6) is matched on the first sliding rail (5) in a sliding mode.
4. The full-aircraft wind gust load wind tunnel test device according to claim 2, characterized in that: and the support (4) is provided with a steel cable adjusting device (12), and the steel cable adjusting device (12) can adjust the length of the upper vertical steel cable (7).
5. The full-aircraft wind gust load wind tunnel test device according to claim 2, characterized in that: the support (4), the upper vertical steel cable (7) and the spring (8) are located on the outer side of the top of the wind tunnel, an opening (10) is formed in the top of the wind tunnel, the lower vertical steel cable (9) penetrates through the opening (10) and extends to the interior of the wind tunnel to be connected with a full-mechanical elastic model (11), and the diameter of the opening (10) is larger than that of the spring (8).
6. The full-aircraft wind gust load wind tunnel test device according to claim 1, characterized in that: the front steel cable mechanism comprises a front steel cable (13) and a front pulley (15), the front steel cable (13) and the front pulley (15) are divided into two groups, two groups of front steel cables (13) are all obliquely arranged, one group of front pulley (15) is rotationally connected to the top of the airplane, the other group of front pulley (15) is rotationally connected to the bottom of the airplane, one group of front steel cables (13) is connected with a wind tunnel top plate (16) at one end and is connected with the front pulley (15) located at the top of the model at the other end, the other group of front steel cables (13) is connected with a wind tunnel bottom plate (17) at one end and is connected with the front pulley (15) located at the bottom of the model at the other end.
7. The full-aircraft wind gust load wind tunnel test device according to claim 1, characterized in that: the rear steel cable mechanism comprises two groups of rear steel cables (14) and rear pulleys (18), one group of rear pulleys (18) are rotatably connected to the left side of the airplane, the other group of rear pulleys (18) are rotatably connected to the right side of the airplane, the two groups of rear steel cables (14) are obliquely arranged, one group of rear steel cables (14) are connected with the rear pulleys (18) on the left side of the airplane, and the other group of rear steel cables (14) are connected with the rear pulleys (18) on the right side of the airplane;
two sets of second slide rail (20) about being equipped with on wind-tunnel lateral wall (19), be equipped with free end pulley (37) on second slide rail (20), it is two sets of free end pulley (37) link to each other with the middle part of two sets of rear cable wires (14) respectively, the one end that full quick-witted elastic model (11) was kept away from in rear cable wire (14) is connected with weight device (39), the weight in weight device (39) can increase or reduce.
8. The full-aircraft wind gust load wind tunnel test device according to claim 7, characterized in that: sliding fit has second slider (38) on second slide rail (20), second slider (38) link to each other with free end pulley (37), second slide rail (20) set up along the length direction of full quick-witted elasticity model (11), be equipped with electronic emergent locking mechanism on the support of free end pulley (37).
9. The full-aircraft wind gust load wind tunnel test device according to claim 1, characterized in that: full quick-witted elasticity model (11) are including wing (21), engine (22), fuselage (23), horizontal tail (24) and vertical fin (25), wing (21) are including metal roof beam (26) and wooden frame (27), it has lead (28) to bond on metal roof beam (26) or wooden frame (27), the parcel has cotton paper (29) on wing (21), horizontal tail (24) and vertical fin (25), the parcel has the glass steel on fuselage (23) and engine (22), be connected with electric steering wheel between wing (21) and the aileron.
10. The full-aircraft wind gust load wind tunnel test device according to claim 9, characterized in that: the measuring system comprises measuring equipment, a data acquisition system and a flight simulation control system, wherein the data acquisition system and the flight simulation control system are arranged outside the wind tunnel; the measuring equipment comprises a gyroscope and a linear displacement sensor which are arranged on the fuselage (23), an acceleration sensor which is arranged on the wingtip of the wing (21) and a strain gage which is arranged at the root of the wing (21); the data acquisition system comprises a gust speed acquisition system (30), a model attitude data acquisition system (31), an acceleration acquisition system (32) and a strain acquisition system (33) which are connected with the measuring equipment; the flight simulation control system comprises a signal converter (34), a simulation control system (35) and a steering engine controller (36), wherein the signal converter (34) is connected with the data acquisition system and the gust generator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111458229.6A CN114235329A (en) | 2021-12-02 | 2021-12-02 | Full-aircraft sudden wind load wind tunnel test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111458229.6A CN114235329A (en) | 2021-12-02 | 2021-12-02 | Full-aircraft sudden wind load wind tunnel test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114235329A true CN114235329A (en) | 2022-03-25 |
Family
ID=80752693
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111458229.6A Pending CN114235329A (en) | 2021-12-02 | 2021-12-02 | Full-aircraft sudden wind load wind tunnel test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114235329A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113916489A (en) * | 2021-09-30 | 2022-01-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | Model supporting device for releasing five rigid body degrees of freedom of wind tunnel test model |
| CN115541174A (en) * | 2022-11-29 | 2022-12-30 | 中国航空工业集团公司哈尔滨空气动力研究所 | Large-size dynamic derivative test model structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105486480A (en) * | 2014-10-11 | 2016-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Double-cable suspension system of full-aircraft low-speed flutter model |
| CN110514394A (en) * | 2019-09-18 | 2019-11-29 | 中国空气动力研究与发展中心高速空气动力研究所 | Model in wind tunnel support device and system |
| CN110686857A (en) * | 2019-10-30 | 2020-01-14 | 厦门大学 | Full-aircraft flutter wind tunnel test model suspension system and state adjustment method thereof |
| CN111044250A (en) * | 2020-01-03 | 2020-04-21 | 厦门大学 | Rope tensioning device, full-aircraft flutter wind tunnel test system and test method |
| CN113267315A (en) * | 2021-05-10 | 2021-08-17 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-speed wind tunnel direct-drive gust generating device |
-
2021
- 2021-12-02 CN CN202111458229.6A patent/CN114235329A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105486480A (en) * | 2014-10-11 | 2016-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Double-cable suspension system of full-aircraft low-speed flutter model |
| CN110514394A (en) * | 2019-09-18 | 2019-11-29 | 中国空气动力研究与发展中心高速空气动力研究所 | Model in wind tunnel support device and system |
| CN110686857A (en) * | 2019-10-30 | 2020-01-14 | 厦门大学 | Full-aircraft flutter wind tunnel test model suspension system and state adjustment method thereof |
| CN111044250A (en) * | 2020-01-03 | 2020-04-21 | 厦门大学 | Rope tensioning device, full-aircraft flutter wind tunnel test system and test method |
| CN113267315A (en) * | 2021-05-10 | 2021-08-17 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-speed wind tunnel direct-drive gust generating device |
Non-Patent Citations (2)
| Title |
|---|
| 李周复: "《风洞实验手册》", 31 January 2015, 航空工业出版社, pages: 148 - 149 * |
| 茹科夫斯基中央空气流体动力研究院: "《气动弹性 下》", 30 June 2020, 上海交通大学出版社, pages: 601 - 602 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113916489A (en) * | 2021-09-30 | 2022-01-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | Model supporting device for releasing five rigid body degrees of freedom of wind tunnel test model |
| CN113916489B (en) * | 2021-09-30 | 2023-12-26 | 中国航空工业集团公司哈尔滨空气动力研究所 | Model supporting device for releasing five rigid body degrees of freedom of wind tunnel test model |
| CN115541174A (en) * | 2022-11-29 | 2022-12-30 | 中国航空工业集团公司哈尔滨空气动力研究所 | Large-size dynamic derivative test model structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20210047033A1 (en) | System and method for airborne wind energy production | |
| CN114235329A (en) | Full-aircraft sudden wind load wind tunnel test device | |
| AU2006342737B2 (en) | Aeolian system comprising power wing profiles and process for producing electric energy | |
| CN102917765B (en) | Planform configuration for stability of a powered kite and a system and method for use of same | |
| CN202793734U (en) | Novel system for hanging whole low-speed flutter plane model for wind tunnel test | |
| CN101556205B (en) | Rotary slotted cylinder/movable wing panel type gust generator | |
| JP6655027B2 (en) | Apparatus for extracting power from a fluid stream | |
| CA2837160A1 (en) | Flying electric generators with undisturbed air rotors | |
| CN102717897A (en) | Aerodynamic loading system and loading method for undercarriage self-control spring-damping system | |
| CN109573097B (en) | Vehicle-mounted test method and system for aerodynamic parameters of low-speed aircraft | |
| CN108760220B (en) | External balance tailstock supporting device for measuring six-degree-of-freedom mechanism interference | |
| CN113092053B (en) | Rope hangs full quick-witted experimental strutting arrangement that shimmys | |
| CN212300783U (en) | Large-scale low-speed wind tunnel flutter test full-mode supporting device | |
| CN114563156A (en) | Four-cable supporting system for full-mode flutter wind tunnel test | |
| CN113916489B (en) | Model supporting device for releasing five rigid body degrees of freedom of wind tunnel test model | |
| CN114923657B (en) | Vertical rod rope supporting system for full-aircraft flutter wind tunnel test | |
| CN114923656A (en) | Rope supporting system for full-aircraft flutter wind tunnel test | |
| CN103640687A (en) | Full-motion wingtip gust alleviation device applicable to high-aspect-ratio aircraft | |
| CN115655635B (en) | Two-freedom-degree supporting system for full-body freedom-degree flutter or gust test | |
| Dadd et al. | Comparison of two kite force models with experiment | |
| JPH08313388A (en) | Wind tunnel test device | |
| Cicolani et al. | Flight Test Identification and Simulation of a UH‐60A Helicopter and Slung Load | |
| CN114910244A (en) | Full-aircraft model gust load alleviation wind tunnel test method based on forward-looking feedback | |
| CN115809548A (en) | Helicopter three-point suspension trim calculation method | |
| JP4376376B2 (en) | Towing test equipment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |