CN109870289B - T-shaped horizontal tail flutter model protection device and application thereof - Google Patents
T-shaped horizontal tail flutter model protection device and application thereof Download PDFInfo
- Publication number
- CN109870289B CN109870289B CN201910288178.3A CN201910288178A CN109870289B CN 109870289 B CN109870289 B CN 109870289B CN 201910288178 A CN201910288178 A CN 201910288178A CN 109870289 B CN109870289 B CN 109870289B
- Authority
- CN
- China
- Prior art keywords
- clamping
- model
- horizontal tail
- flutter
- shaped
- 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.)
- Active
Links
- 238000012360 testing method Methods 0.000 claims abstract description 35
- 238000000034 method Methods 0.000 claims description 22
- 230000008569 process Effects 0.000 claims description 17
- 210000000078 claw Anatomy 0.000 claims description 14
- 230000005489 elastic deformation Effects 0.000 claims description 8
- 230000000712 assembly Effects 0.000 claims description 5
- 238000000429 assembly Methods 0.000 claims description 5
- 230000001154 acute effect Effects 0.000 claims description 3
- 230000006378 damage Effects 0.000 claims description 3
- 230000035939 shock Effects 0.000 abstract description 3
- 239000003638 chemical reducing agent Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 5
- 230000008878 coupling Effects 0.000 description 4
- 238000010168 coupling process Methods 0.000 description 4
- 238000005859 coupling reaction Methods 0.000 description 4
- 230000001681 protective effect Effects 0.000 description 4
- 238000007789 sealing Methods 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 2
- 230000003028 elevating effect Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 230000034994 death Effects 0.000 description 1
- 231100000517 death Toxicity 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 230000001012 protector Effects 0.000 description 1
- 238000010992 reflux Methods 0.000 description 1
- 230000011664 signaling Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a T-shaped horizontal tail flutter model protection device and application thereof, belongs to the technical field of aerodynamic wind tunnel test devices, and aims to solve the problems that in the existing T-shaped tail wind tunnel flutter test protection device, the flow field of a T-shaped tail is greatly influenced due to the generation of local supersonic velocity areas and local shock waves near a base and a clamping device, so that the flutter dynamic pressure of the T-shaped tail is reduced, the flutter type is changed, and the accuracy of test results is influenced. The device comprises a lifting unit, a clamping unit, a force sensor and a control system, wherein the clamping unit is connected with the lifting unit; the clamping unit comprises a lifting slide block, a stretching assembly, a connecting rod and a clamping assembly, wherein the lifting unit is connected with the lifting slide block and can drive the lifting slide block to move, and the lifting slide block is connected with the stretching assembly and can drive the stretching assembly to move. The novel energy-saving device is ingenious in conception, reasonable in design, simple in structure, high in application value and good in application prospect.
Description
Technical Field
The application relates to the technical field of wind tunnels, in particular to the technical field of aerodynamic wind tunnel test devices, and specifically relates to a T-shaped horizontal tail flutter model protection device and application thereof. More specifically, the application provides a combined type two-degree-of-freedom high-speed wind tunnel test model protection device, which can realize the structural protection of T-shaped horizontal tail flutter models with different heights in the test process, prevent the models from being damaged due to resonance, effectively improve the test efficiency and has higher application value.
Background
Flutter is a self-excited divergent vibration that occurs after the flight speed of the aircraft exceeds a critical speed, which is the result of the elastic structure aerodynamic forces, inertial forces, and elastic forces coupling to one another. When the flight speed exceeds the flutter critical speed, the amplitude and dynamic stress in the structure may increase dramatically, possibly resulting in rapid destruction or even disintegration of the aircraft within a few seconds, causing a major accident of the aircraft's deaths. Thus, the occurrence of flutter in an aircraft is very dangerous. For this reason, flutter tests are required when designing aircraft.
The purpose of the flutter test is: in the wind tunnel, the flutter phenomenon is reproduced by using a dynamic similar model, the flutter characteristics of the aircraft are known, the flutter critical speed pressure and the flutter frequency in a dangerous flight state are determined, and flight envelope data are provided for the safe flight of the aircraft.
The flutter test is carried out in the temporary flushing wind tunnel, when the flutter is close to or occurs, the model is possibly damaged, and emergency protection needs to be provided for the model. Because the possibility of damaging the model in the flutter test is high, in order to prevent model fragments (such as lead weights and stores) from damaging the wind tunnel, a protective net is usually arranged on a subsonic diffusion section of the transonic reflux wind tunnel.
Protection of the model in transonic testing is typically achieved by two means: firstly, the wind tunnel is stopped emergently, and the wind tunnel is required to reduce the rapid pressure by 10% in half a second; and secondly, changing the position of the supersonic diffusion section, namely reducing Mach number under the condition of unchanged total pressure, so as to achieve the purpose of reducing the velocity pressure and enabling the model to withdraw from flutter.
The above-mentioned safeguards rely on the model observer to operate manually; thus, the model is subject to corruption as long as the decisions and operations are somewhat delayed.
In 2013, 8 months, shi Aiming of northwest university of industry et al in the article "test fluid mechanics" of T-type empennage wind tunnel flutter test protection device bypass characteristic analysis ", a protection device composed of a clamping device and a base is provided. In the document, after the protection device is introduced, the flow field of the T-shaped tail wing is greatly influenced due to the generation of local supersonic velocity areas and local shock waves near the base and the clamping device, so that the flutter pressure of the T-shaped tail wing is reduced and the flutter type is changed, and the accuracy of a test result is influenced.
To this end, a new apparatus and/or method is urgently needed to solve the above-mentioned problems.
Disclosure of Invention
The invention of the present application aims to: aiming at the problems that in the existing T-shaped tail wind tunnel flutter test protection device, the flow field of the T-shaped tail is greatly influenced due to the generation of local supersonic velocity areas and local shock waves near a base and a clamping device, so that the flutter dynamic pressure of the T-shaped tail is reduced, the flutter type is changed, and the accuracy of test results is influenced, the T-shaped horizontal tail flutter model protection device and the application thereof are provided. The novel energy-saving device is ingenious in conception, reasonable in design, simple in structure, high in application value and good in application prospect.
In order to achieve the above purpose, the present application adopts the following technical scheme:
the T-shaped horizontal tail flutter model protection device comprises a lifting unit, a clamping unit for clamping and loosening a horizontal tail, a force sensor and a control system, wherein the clamping unit is connected with the lifting unit, and the lifting unit can drive the clamping unit to move;
the clamping unit comprises a lifting sliding block, a stretching assembly, a connecting rod and a clamping assembly, wherein the lifting unit is connected with the lifting sliding block and can drive the lifting sliding block to move, and the lifting sliding block is connected with the stretching assembly and can drive the stretching assembly to move;
the stretching assembly comprises a cylinder, a plug matched with the cylinder, a pull rod and a reversing control loop, wherein the plug is arranged at one end of the cylinder, the pull rod is arranged in the cylinder, and the reversing control loop is connected with the cylinder;
the clamping assembly comprises a gas claw frame, a clamping arm, a clamping block and a parallel rod, wherein the gas claw frame is connected with the stretching assembly through a connecting rod, and the connecting rod can provide support for the gas claw frame;
the clamping arm is in a V shape and comprises a first connecting section and a second connecting section, the first connecting section and the second connecting section are connected into a whole, an included angle formed by the first connecting section and the second connecting section is an acute angle, the joint of the first connecting section and the second connecting section is marked as a first connecting point, and the clamping arm is movably connected with the gas claw frame through the first connecting point and can rotate around the first connecting point;
the first connecting section is provided with a first connecting hole, the pull rod is hinged with the first connecting section of the clamping arm through the first connecting hole, and the pull rod can drive the clamping arm to rotate around the first connecting point through the first connecting hole; the second connecting section is hinged with the clamping block, and the joint of the second connecting section and the clamping block is marked as a second connecting point; two ends of the parallel rod are respectively hinged with the air jaw frame and the clamping block, the joint of the clamping block and the parallel rod is marked as a third joint point, and the joint of the parallel rod and the air jaw frame is marked as a fourth joint point; the first connecting point, the second connecting point, the third connecting point and the fourth connecting point are arranged in a parallelogram;
the two clamping assemblies are arranged in a way that openings of clamping arms in the two clamping assemblies are opposite to each other, and a clamping space for clamping the model is formed between the two clamping blocks; the force sensor is arranged on the clamping block and is positioned at one side of the clamping block close to the clamping space; the force sensor is connected with the control system and can transmit the measured stress information to the control system;
the lifting unit and the reversing control loop are respectively connected with the control system, and the control system can realize the extension and retraction of the pull rod relative to the cylinder through the reversing control loop.
The gas claw frame is U-shaped, the gas claw frame includes middle section linkage segment, edge linkage segment, the edge linkage segment is a set of and is parallel to each other, the edge linkage segment sets up in middle section linkage segment both sides respectively.
The first connecting hole is a waist-shaped hole.
The first connecting section and the second connecting section are integrally formed.
The connecting rod is connected with the cylinder and the cylinder can provide support for the connecting rod.
The lifting unit comprises a supporting component, a driving component, a ball screw arranged on the supporting component, a screw nut matched with the ball screw and a guiding component, wherein the driving component is connected with the supporting component and can provide support for the driving component, and the ball screw is connected with the driving component and can drive the ball screw to rotate relative to the supporting component;
the screw nut is arranged on the ball screw, the screw nut is connected with the lifting slide block, and the ball screw can drive the lifting slide block to move along the axial direction of the ball screw through the screw nut;
the lifting slide block is connected with the supporting component through the guide component, and the guide component can play a guide role on the lifting slide block so as to ensure the axial movement of the lifting slide block along the ball screw.
The guide assembly comprises a guide groove arranged on the side wall of the lifting sliding block and a guide rail matched with the guide groove, and the guide rail is arranged on the support assembly.
The guide grooves are in a V shape, two guide grooves and two guide rails are respectively arranged, and the guide grooves are uniformly distributed on the lifting sliding blocks.
The lifting slide block is internally provided with a through hole, and the screw nut is arranged on the inner wall of the through hole of the lifting slide block.
The support assembly comprises a base, a lower frame, an upper frame and a vertical plate, wherein the lower frame is arranged on the base, the lower frame, the vertical plate and the upper frame are sequentially connected into a whole, the ball screw is movably connected with the upper frame and the lower frame respectively, the ball screw can rotate relative to the upper frame and the lower frame, and the guide rail is arranged on the vertical plate.
And a fairing connected to the base.
The driving assembly comprises a motor base, a servo motor, a speed reducer and a coupler, wherein the motor base is connected with the supporting assembly, the supporting assembly can provide support for the motor base, the servo motor is arranged on the motor base, and the servo motor is connected with the ball screw through the speed reducer and the coupler and can drive the ball screw to rotate relative to the supporting assembly.
The ball screw is connected with the supporting component through the rotating supporting component.
The rotary support assembly comprises a bearing seat, an angular contact bearing arranged on the bearing seat and a bearing cover matched with the angular contact bearing, and the ball screw is connected with the rotary support assembly in a sliding manner.
The two rotating support assemblies are respectively arranged at the upper end and the lower end of the ball screw, the rotating support assembly at the upper end of the ball screw is connected with the upper frame, and the rotating support assembly at the lower end of the ball screw is connected with the lower frame.
The upper frame and the lower frame are respectively U-shaped or U-shaped.
The T-shaped horizontal tail flutter model protection device is applied to a T-shaped tail wing wind tunnel flutter test.
The method comprises the following steps:
(1) Arranging a T-shaped horizontal tail flutter model protection device on a wallboard of a test section, and clamping the model horizontal tail through a clamping unit of the T-shaped horizontal tail flutter model protection device;
(2) In the flow field building process of the flutter test, the pneumatic elastic deformation of the T-shaped tail wing model is increased, and the lifting unit drives the clamping unit to move upwards along with the horizontal tail of the model;
(3) When the flow field is stable, the clamping unit is loosened, and the T-shaped tail wing model only receives pneumatic load;
(4) When the T-shaped tail wing model flutters, the clamping unit rapidly clamps the model horizontal tail of the T-shaped tail wing model, so that the damage of the T-shaped tail wing model is avoided;
(5) After the flutter test is completed, wind tunnel stopping operation is carried out; in the wind tunnel parking process, the pneumatic elastic deformation of the T-shaped tail wing model is reduced, and the lifting unit drives the clamping unit to move downwards along with the horizontal tail of the model;
in the step (2), two force sensors on the clamping unit respectively measure the forces from the upper end and the lower end of the horizontal tail of the model, and the measured data are transmitted to a control system; the control system compares the data measured by the two force sensors, and if the difference value of the data measured by the two force sensors is larger than a given value, the control system sends out an instruction to enable the lifting unit to drive the clamping unit to move upwards; the above process is repeated until the difference between the data measured by the two force sensors is less than the given value.
In the step 1, a T-shaped horizontal tail flutter model protection device is arranged on a lower wall plate of a test section.
In the step 1, a T-shaped horizontal tail flutter model protection device is connected with a wind tunnel lower wall plate through a base.
The T-shaped horizontal tail flutter model protection device is a group and is used for protecting two wings of the T-shaped horizontal tail flutter model;
or the T-shaped horizontal tail flutter model protection device is single and is used for protecting the half-mould flutter model.
The aforementioned protection device for the T-fin flutter model of northwest industrial university has a large disturbance to the flow field, and in order to reduce the disturbance of the protection device to the test model, the protection device needs to have a small structural size on the one hand, and the base of the protection device needs to be as far away from the test model as possible, and meanwhile, the protection device has the capability of reliably protecting the model. Therefore, the protection device of the present application has the following two functions: one with the ability to follow the static elastic deformation of the airfoil and the ability to rapidly limit the amplitude of the airfoil vibration.
Therefore, the application provides a T-shaped horizontal tail flutter model protection device and application thereof. In this application, fix T type fin flutter model protection device on the wallboard under the test section, utilize its elevating unit and parallel clamping unit to realize the protection to T type fin flutter model.
The working principle of the application is as follows: before the wind tunnel is started, an air cylinder in the clamping unit pushes a pull rod to move backwards, and the pull rod drives a clamping arm, a parallel rod and a clamping block to move so as to clamp the T-shaped horizontal tail of the flutter model; in the starting process of the wind tunnel, the T-shaped tail wing is upwarped by aerodynamic force, force sensors arranged on an upper clamping block and a lower clamping block of the parallel clamping unit sense the force from the horizontal tail of the model, and a control system compares the forces sensed by the two force sensors; if the force is larger than the given value, signaling the servo motor, driving the screw nut to move by the servo motor, and reducing the difference value of the forces on the two force sensors; the above-described movement is repeated until the difference between the two force sensors is less than the given value. After the wind tunnel flow field is stable, the air cylinder pushes the pull rod to move forwards, and the pull rod drives the clamping arm, the parallel rod and the clamping block to move, so that the T-shaped horizontal tail of the flutter model is loosened. In the test process, if the model is vibrated, the control system rapidly clamps the model through the clamping unit, so that the model is prevented from being damaged.
When the protection device works, the working flow is as follows: 1) In the process of establishing a flow field, along with the increase of aerodynamic force, when the aerodynamic elastic deformation of the T-shaped tail wing model is increased, the lifting unit can drive the clamping unit to move upwards along with the tail wing; 2) When the flow field is stable, the parallel clamping units are loosened, and the T-shaped tail wing model is only subjected to pneumatic load; 3) When the T-shaped tail wing model flutters, the clamping units clamp the model rapidly, and the model is prevented from being damaged due to further resonance.
In summary, the present application provides a protection device for a T-shaped horizontal tail flutter model. Before the flow field is established, an air cylinder of the parallel clamping unit pushes a pull rod to move backwards, and the pull rod drives a clamping arm, a parallel rod and a clamping block to move so as to clamp the horizontal tail of the flutter model; in the flow field establishing process, when a force sensor on the lifting unit senses aerodynamic force on the T-shaped horizontal tail, the motor drives the screw rod to move until the force sensor does not sense aerodynamic force; after the flow field is stable, the air cylinder pushes the pull rod to move forwards, and the pull rod drives the clamping arm, the parallel rod and the clamping block to move so as to release the horizontal tail of the model; when flutter occurs, the air cylinder pushes the pull rod to move backwards, so that the clamping of the model horizontal tail is rapidly realized. Compared with the prior device, the horizontal tail flutter model protection device has the following advantages: (1) the structure is compact, and the interference to the model flow field is small; (2) the clamping device can flexibly lift under the drive of the lifting unit, and the stress of the device is small; (3) when only a single-side protection device is used, the mold half flutter model can be protected.
Drawings
The invention will now be described by way of example and with reference to the accompanying drawings in which:
fig. 1 is a schematic side view of the structure of the protector in example 1 connected to a flutter model.
Fig. 2 is a schematic rear view of the structure of fig. 1.
Fig. 3 is a schematic view of the structure of the holding unit in example 1.
Fig. 4 is a partial view of the schematic structure of the clamping unit of fig. 3.
Fig. 5 is a partial view of the schematic diagram of the clamping unit of fig. 3.
Fig. 6 is a schematic view of the structure of the lifting unit in embodiment 1.
Fig. 7 is a partial view one of fig. 6.
Fig. 8 is a partial view two of fig. 6.
Fig. 9 is a schematic rear view of the structure of the elevating unit in embodiment 1.
Fig. 10 is a schematic diagram of the structure of the lifting slider in embodiment 1.
Fig. 11 is a schematic diagram of the commutation control loop of the clamping unit in example 1.
Reference numerals: 1. the vibration model comprises a vibration model, 2, a clamping unit, 3, a lifting unit, 11, a screw nut, 12, a lifting sliding block, 13, a plug, 14, an air cylinder, 15, a pull rod, 16, a connecting rod, 17, a clamping arm, 18, a parallel rod, 19, a clamping block, 20, a force sensor, 21, a pneumatic claw frame, 50, a wind tunnel lower wall plate, 51, a base, 52, a fairing, 53, a bearing seat, 54, a protective cover, 55, an angular contact ball bearing, 56, a bearing cover, 57, a ball screw, 58, a motor seat, 59, a coupling, 60, a speed reducer, 61, a servo motor, 62, a lower frame, 63, a vertical plate, 64, a V-shaped guide rail, 65 and an upper frame.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
Any feature disclosed in this specification may be replaced by alternative features serving the same or equivalent purpose, unless expressly stated otherwise. That is, each feature is one example only of a generic series of equivalent or similar features, unless expressly stated otherwise.
Example 1
Fig. 1 to 11 show a schematic diagram of the structure of the T-shaped horizontal tail flutter model protection device of the present application. As can be seen from the figure, the protection device for the T-shaped horizontal tail flutter model in this embodiment includes a lifting unit, a clamping unit, a force sensor, and a control system, where the clamping unit is connected to the lifting unit. As shown in fig. 1 and 2, the clamping unit is used for clamping and loosening the horizontal tail of the model, and the lifting unit is mainly used for driving the clamping unit to move up and down. In this embodiment, the protection device for the T-shaped horizontal tail flutter model is installed on the lower wall plate of the test section.
As can be seen from fig. 3 to 5, the clamping unit of the embodiment includes a screw nut, a lifting slider, a stretching assembly, a connecting rod, and a clamping assembly. The screw nut is connected with the lifting slide block, and the lifting slide block is connected with the stretching assembly; in the structure, a screw nut drives a stretching assembly to move through a lifting sliding block; when the lifting unit is arranged in the vertical direction, the screw nut drives the stretching assembly to be matched with the horizontal tail of the model to move up and down in the vertical direction through the lifting sliding block.
In this embodiment, the stretching assembly includes a cylinder, a plug, a pull rod, and a reversing control loop. The plug is matched with the air cylinder, the plug is arranged at one end of the air cylinder, the pull rod is arranged in the air cylinder, and the reversing control loop is connected with the air cylinder. Meanwhile, the clamping assembly comprises an air jaw frame, a clamping arm, a clamping block and a parallel rod; the air claw frame is connected with the air cylinder through the connecting rod, and the air cylinder can provide support for the connecting rod; in this structure, the air jaw frame is kept stationary relative to the cylinder at all times. As shown in the figure, the air jaw frame of the embodiment comprises a middle section connecting section and an edge connecting section, wherein the edge connecting section is a group and is used for providing support for the clamping arms and the parallel rods, and the edge connecting sections are respectively arranged on two sides of the middle section connecting section and are integrally U-shaped. In this embodiment, the two edge connection sections are arranged in parallel.
In this embodiment, the arm lock includes first linkage segment, second linkage segment, and first linkage segment links to each other as an organic wholely with the second linkage segment and the contained angle that first linkage segment and second linkage segment become is the acute angle, and the arm lock is whole to be the V type. The joint of the first connecting section and the second connecting section is marked as a first connecting point, the clamping arm is movably connected with the air jaw frame through the first connecting point, and the clamping arm can rotate around the first connecting point; the first connecting section is provided with a first connecting hole, the pull rod is hinged with the first connecting section of the clamping arm through the first connecting hole, and the pull rod can drive the clamping arm to rotate around the first connecting point through the first connecting hole. In this embodiment, the first connection hole is a waist-shaped hole; based on this structure, the pull rod passes through the round pin axle and links to each other with first connecting hole, and when the pull rod was flexible, the round pin axle can follow first connecting hole and slide, and then turns into the rotation of arm lock with the concertina movement of pull rod.
The second connecting section is hinged with the clamping block, and the connecting position of the second connecting section and the clamping block is marked as a second connecting point, so that the clamping block can rotate around the second connecting point; the two ends of the parallel rod are respectively hinged with the air jaw frame and the clamping block, the joint of the clamping block and the parallel rod is marked as a third joint, and the joint of the parallel rod and the air jaw frame is marked as a fourth joint, so that the two ends of the parallel rod can respectively rotate around the air jaw frame and the clamping block. In the structure, the first connecting point, the second connecting point, the third connecting point and the fourth connecting point are arranged in a parallelogram; in other words, the first, second, third, and fourth connection points are located on the four vertices of the parallelogram; based on the structure, the clamping block can always keep the same direction relative to the clamping surface of the model, so that the model airfoil can be effectively clamped. Simultaneously, the clamping assembly is two, and the opening of arm lock sets up in two clamping assembly in opposite directions, constitutes the centre gripping space that is used for the model centre gripping between two clamping blocks. The force sensor is arranged on one side of the clamping block, which is close to the clamping space; the force sensor is connected with the control system. Based on the structure, the clamping arm rotates to drive the clamping block to move up and down, so that clamping and loosening operations are realized. On the other hand, the force sensor can measure the stress condition in real time; and starting the change of elastic deformation based on the airfoil model, so that the stress of the upper force sensor and the lower force sensor is changed and transmitted to a control system, and the control system adjusts the lifting unit based on measured data.
Further, the air cylinder is connected with the lifting slide block through a screw, the connecting rod is connected with the air cylinder through a pin and the screw, and the air claw frame is connected with the connecting rod through the screw and the pin; the pull rod is arranged in the air cylinder and is sealed with the air cylinder through an O-shaped sealing ring and a Y-shaped sealing ring; the plug is in threaded connection with the air cylinder and is sealed through an O-shaped sealing ring; the pull rod is connected with the clamping arm through a pin shaft and an elastic check ring, the clamping arm is connected with the air jaw frame and the clamping block through a pin shaft and an elastic check ring respectively, and the parallel rod is connected with the air jaw frame and the clamping block through a pin shaft and an elastic check ring respectively.
Fig. 11 shows a schematic diagram of a commutation control loop, the tie rod in the clamping unit being controlled in its back and forth movement by the principle as shown. As shown in the figure, in this structure, the spring control valve of the five-way valve is in a normally closed state; the electromagnetic valve is powered on, the five-way valve commutates, the pull rod extends forwards, and the clamping unit loosens the model; the electromagnetic valve is powered off, the five-way valve returns to the initial state, the pull rod retreats backwards, and the clamping unit locks the model. In the embodiment, the lifting unit and the reversing control loop are respectively connected with the control system, and the control system can realize the extension and retraction of the pull rod relative to the cylinder through the reversing control loop.
The lifting unit comprises a supporting component, a driving component, a ball screw arranged on the supporting component and a V-shaped guide rail. The embodiment provides a structure of a supporting component, as shown in the figure, the supporting component comprises a base, a fairing, a lower frame, an upper frame and a vertical plate, wherein the fairing is connected with the base; wherein the upper frame and the lower frame are respectively U-shaped or U-shaped, and the vertical plates are a group; the lower frame is arranged on the base, and the lower frame and the upper frame are connected into a whole through the vertical plate. Meanwhile, the V-shaped guide rail is arranged on the vertical plate, V-shaped guide grooves are respectively formed in the left side and the right side of the lifting slide block, the lifting slide block and the supporting component are matched through the V-shaped guide grooves and the V-shaped guide rail, the lifting slide block can be guided, and then the lifting slide block is restrained from moving in the vertical direction. Meanwhile, a through hole is formed in the center of the lifting sliding block, the screw nut is arranged on the through hole in the lifting sliding block, the ball screw is connected with the screw nut, and the ball screw can provide power for movement of the screw nut.
In this embodiment, drive assembly includes motor cabinet, servo motor, reduction gear, shaft coupling, and the motor cabinet links to each other with the braced component's lower frame, and servo motor sets up on the motor cabinet, and servo motor passes through reduction gear, shaft coupling and links to each other and servo motor can drive the relative braced component rotation of ball. Simultaneously, still include two rotation supporting components, rotate the supporting component and set up respectively at ball upper and lower both ends, be located the rotation supporting component of ball upper end and link to each other with last frame, be located the rotation supporting component of ball lower extreme and link to each other with the lower frame. In this embodiment, the rotation support assembly includes the bearing frame, sets up the angular contact bearing on the bearing frame, with angular contact bearing matched with bearing cap, ball links to each other with the angular contact bearing in the rotation support assembly respectively. Meanwhile, the upper frame is also provided with a protective cover.
In this embodiment, the base of the lifting unit is disposed on the lower wall plate of the wind tunnel. The screw nut is connected with the ball screw, the screw nut is connected with the lifting slide block through screws, and two sides of the lifting slide block are respectively connected with the V-shaped guide rail. Further, the connection relationship between the respective members is as follows: the base is connected with the lower wall plate of the test section through screws, the lower frame is connected with the base through screws, and the fairing is welded with the base; the motor seat is connected with the lower frame through a screw, and a bearing seat in the lower rotary support assembly is connected with the lower frame through a screw; the servo motor is connected with a speed reducer, and the speed reducer is connected with the ball screw through a coupler; the bearing cover in the lower rotary support assembly compresses the outer ring of the angular contact ball bearing through the countersunk head screw, the round nut compresses the inner ring of the angular contact ball bearing, and the angular contact ball bearing is placed in the bearing seat of the lower rotary support assembly; the ball screw is connected with an upper angular contact ball bearing and a lower angular contact ball bearing; the V-shaped guide rail is connected with the vertical plate through a screw, the vertical plate is connected with the lower frame through a screw, and the vertical plate is connected with the upper frame through a screw; the bearing seat of the upper rotating support assembly is connected with the upper frame through a screw, an angular contact ball bearing in the upper rotating support assembly is placed in the bearing seat of the upper rotating support assembly, a bearing cover in the upper rotating support assembly is pressed by the screw to tightly press the outer ring of the lower part of the angular contact ball bearing, the inner ring of the lower part of the angular contact ball bearing is limited by a ball screw shaft shoulder, a round nut is pressed to tightly press the inner ring of the upper part of the angular contact ball bearing, and the outer ring of the upper part of the angular contact ball bearing is clamped in the bearing seat of the upper rotating support assembly; the protective cover is connected with the upper frame through screws.
In the embodiment, the T-shaped tail wing flutter model protection device is fixed on the lower wall plate of the test section, and the protection of the T-shaped tail wing flutter model is realized by utilizing the lifting unit and the parallel clamping unit of the T-shaped tail wing flutter model protection device. The lifting unit realizes the up-and-down movement of the clamping unit, and the parallel clamping unit realizes the clamping and loosening of the model horizontal tail. The clamping unit is driven by the ball screw of the lifting unit to move up and down along the linear guide rail, so that the protection of models with different heights can be realized.
The working process of the device is as follows: before the wind tunnel is started, the clamping unit clamps the T-shaped horizontal tail of the flutter model; in the starting process of the wind tunnel, force sensors arranged on the clamping units sense the force from the horizontal tail of the model and transmit the force to a control system, and the control system compares the forces sensed by the two force sensors; if the force is larger than the given value, a signal is sent to a servo motor, and the servo motor drives a screw nut to move, so that the clamping unit moves upwards, and the difference value of the forces on the two force sensors is reduced; the above-described movement is repeated until the difference between the two force sensors is less than the given value. After the wind tunnel flow field is stable, the clamping unit loosens the model; in the test process, if the model is vibrated, the control system starts the clamping unit to rapidly clamp the model, so that the model is prevented from being damaged.
By adopting the method, in the process of establishing the flow field, along with the increase of aerodynamic force, when the pneumatic elastic deformation of the T-shaped tail wing model is increased, the lifting unit can drive the clamping unit to move upwards along with the tail wing, so that the protection device has the advantages of smaller stress, smaller size and smaller interference on the flow field. When the flow field is stable, the parallel clamping units are loosened, the T-shaped tail wing model only receives pneumatic load, and when the T-shaped tail wing model vibrates, the clamping units rapidly clamp the model, so that the model is prevented from being damaged due to further resonance.
The invention is not limited to the specific embodiments described above. The invention extends to any novel one, or any novel combination, of the features disclosed in this specification, as well as to any novel one, or any novel combination, of the steps of the method or process disclosed.
Claims (10)
1. The T-shaped horizontal tail flutter model protection device is characterized by comprising a lifting unit, a clamping unit for clamping and loosening a horizontal tail, a force sensor and a control system, wherein the clamping unit is connected with the lifting unit, and the lifting unit can drive the clamping unit to move;
the clamping unit comprises a lifting sliding block, a stretching assembly, a connecting rod and a clamping assembly, wherein the lifting unit is connected with the lifting sliding block and can drive the lifting sliding block to move, and the lifting sliding block is connected with the stretching assembly and can drive the stretching assembly to move;
the stretching assembly comprises a cylinder, a plug matched with the cylinder, a pull rod and a reversing control loop, wherein the plug is arranged at one end of the cylinder, the pull rod is arranged in the cylinder, and the reversing control loop is connected with the cylinder;
the clamping assembly comprises a gas claw frame, a clamping arm, a clamping block and a parallel rod, wherein the gas claw frame is connected with the stretching assembly through a connecting rod, and the connecting rod can provide support for the gas claw frame;
the clamping arm is in a V shape and comprises a first connecting section and a second connecting section, the first connecting section and the second connecting section are connected into a whole, an included angle formed by the first connecting section and the second connecting section is an acute angle, the joint of the first connecting section and the second connecting section is marked as a first connecting point, and the clamping arm is movably connected with the gas claw frame through the first connecting point and can rotate around the first connecting point;
the first connecting section is provided with a first connecting hole, the pull rod is hinged with the first connecting section of the clamping arm through the first connecting hole, and the pull rod can drive the clamping arm to rotate around the first connecting point through the first connecting hole; the second connecting section is hinged with the clamping block, and the joint of the second connecting section and the clamping block is marked as a second connecting point; two ends of the parallel rod are respectively hinged with the air jaw frame and the clamping block, the joint of the clamping block and the parallel rod is marked as a third joint point, and the joint of the parallel rod and the air jaw frame is marked as a fourth joint point; the first connecting point, the second connecting point, the third connecting point and the fourth connecting point are arranged in a parallelogram;
the two clamping assemblies are arranged in a way that openings of clamping arms in the two clamping assemblies are opposite to each other, and a clamping space for clamping the model is formed between the two clamping blocks; the force sensor is arranged on the clamping block and is positioned at one side of the clamping block close to the clamping space; the force sensor is connected with the control system and can transmit the measured stress information to the control system;
the lifting unit and the reversing control loop are respectively connected with the control system, and the control system can realize the extension and retraction of the pull rod relative to the cylinder through the reversing control loop;
the first connecting section and the second connecting section are integrally formed.
2. The protection device for the T-shaped horizontal tail flutter model according to claim 1, wherein the gas claw frame is U-shaped and comprises a middle section connecting section and edge connecting sections, the edge connecting sections are in a group and are parallel to each other, and the edge connecting sections are respectively arranged on two sides of the middle section connecting section.
3. The protection device for the T-shaped horizontal tail flutter model according to claim 1, wherein the lifting unit comprises a supporting component, a driving component, a ball screw arranged on the supporting component, a screw nut matched with the ball screw and a guiding component, the driving component is connected with the supporting component and can provide support for the driving component, and the ball screw is connected with the driving component and can drive the ball screw to rotate relative to the supporting component;
the screw nut is arranged on the ball screw, the screw nut is connected with the lifting slide block, and the ball screw can drive the lifting slide block to move along the axial direction of the ball screw through the screw nut;
the lifting slide block is connected with the supporting component through the guide component, and the guide component can play a guide role on the lifting slide block so as to ensure the axial movement of the lifting slide block along the ball screw.
4. The protection device for the T-shaped horizontal tail flutter model according to claim 3, wherein the guide assembly comprises a guide groove arranged on the side wall of the lifting slide block and a guide rail matched with the guide groove;
the support assembly comprises a base, a lower frame, an upper frame and a vertical plate, wherein the lower frame is arranged on the base, the lower frame, the vertical plate and the upper frame are sequentially connected into a whole, the ball screw is movably connected with the upper frame and the lower frame respectively, the ball screw can rotate relative to the upper frame and the lower frame, and the guide rail is arranged on the vertical plate.
5. The T-shaped horizontal tail flutter model protection device of claim 1, further comprising a fairing attached to the base.
6. The use of the T-shaped horizontal tail flutter model protection device according to any one of claims 1 to 5, for use in T-shaped tail wind tunnel flutter tests.
7. The use according to claim 6, characterized in that it comprises the steps of:
(1) Arranging a T-shaped horizontal tail flutter model protection device on a wallboard of a test section, and clamping the model horizontal tail through a clamping unit of the T-shaped horizontal tail flutter model protection device;
(2) In the flow field building process of the flutter test, the pneumatic elastic deformation of the T-shaped tail wing model is increased, and the lifting unit drives the clamping unit to move upwards along with the horizontal tail of the model;
(3) When the flow field is stable, the clamping unit is loosened, and the T-shaped tail wing model only receives pneumatic load;
(4) When the T-shaped tail wing model flutters, the clamping unit rapidly clamps the model horizontal tail of the T-shaped tail wing model, so that the damage of the T-shaped tail wing model is avoided;
(5) After the flutter test is completed, wind tunnel stopping operation is carried out; in the wind tunnel parking process, the pneumatic elastic deformation of the T-shaped tail wing model is reduced, and the lifting unit drives the clamping unit to move downwards along with the horizontal tail of the model;
in the step (2), two force sensors on the clamping unit respectively measure the forces from the upper end and the lower end of the horizontal tail of the model, and the measured data are transmitted to a control system; the control system compares the data measured by the two force sensors, and if the difference value of the data measured by the two force sensors is larger than a given value, the control system sends out an instruction to enable the lifting unit to drive the clamping unit to move upwards; the above process is repeated until the difference between the data measured by the two force sensors is less than the given value.
8. The use according to claim 6 or 7, wherein in step (1), the T-shaped horizontal tail flutter model protection device is arranged on the lower wall plate of the test section.
9. The use according to claim 8, wherein in step (1), the T-shaped horizontal tail flutter model protection device is connected to the wind tunnel lower wall plate through a base.
10. The application according to any one of claims 7 to 9, wherein the protection devices of the T-shaped horizontal tail flutter model are a group for protecting two wings of the T-shaped horizontal tail flutter model;
or the T-shaped horizontal tail flutter model protection device is single and is used for protecting the half-mould flutter model.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910288178.3A CN109870289B (en) | 2019-04-11 | 2019-04-11 | T-shaped horizontal tail flutter model protection device and application thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910288178.3A CN109870289B (en) | 2019-04-11 | 2019-04-11 | T-shaped horizontal tail flutter model protection device and application thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109870289A CN109870289A (en) | 2019-06-11 |
| CN109870289B true CN109870289B (en) | 2024-04-09 |
Family
ID=66922424
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910288178.3A Active CN109870289B (en) | 2019-04-11 | 2019-04-11 | T-shaped horizontal tail flutter model protection device and application thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109870289B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114728328A (en) | 2019-11-21 | 2022-07-08 | 泰州鑫宇精工股份有限公司 | Formwork manufacturing production line and formwork manufacturing method |
| CN111323199A (en) * | 2020-03-31 | 2020-06-23 | 杭州佐格通信设备有限公司 | Debris intercepting mechanism of wind tunnel and wind tunnel |
| CN111797468B (en) * | 2020-06-17 | 2022-12-02 | 江西洪都航空工业集团有限责任公司 | Method for inhibiting flutter of rear edge strip dimensional frame wallboard |
| CN111855132A (en) * | 2020-08-28 | 2020-10-30 | 中国航空工业集团公司沈阳空气动力研究所 | Flutter test safety protection system and method |
| CN114414196B (en) * | 2022-03-28 | 2022-06-03 | 中国空气动力研究与发展中心高速空气动力研究所 | Continuous variable speed pressure control method for sub-transonic flutter test |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09133605A (en) * | 1995-11-10 | 1997-05-20 | Natl Aerospace Lab | Supersonic flutter stopping apparatus |
| JP2004109067A (en) * | 2002-09-20 | 2004-04-08 | National Aerospace Laboratory Of Japan | Transonic flutter stop device |
| CN101629867A (en) * | 2009-06-05 | 2010-01-20 | 中国航空工业集团公司西安飞机设计研究所 | Protector for wing-surface test model |
| CN201724807U (en) * | 2010-02-26 | 2011-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Connector for horizontal stabilizer and vertical stabilizer of flutter model |
| CN203894027U (en) * | 2014-04-17 | 2014-10-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Protective stop mechanism for trailing edge control surface of flutter model |
| CN205209728U (en) * | 2015-12-14 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Flutter wind tunnel model protector based on magnetic force lock |
| CN105841915A (en) * | 2016-05-16 | 2016-08-10 | 中国航空工业集团公司西安飞机设计研究所 | Longitudinal freedom degree simulation full aircraft flutter wind tunnel model support system |
| CN108195543A (en) * | 2017-11-29 | 2018-06-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft wind tunnel model flutter blowing test system |
| CN209459859U (en) * | 2019-04-11 | 2019-10-01 | 中国空气动力研究与发展中心高速空气动力研究所 | T-type horizontal tail flutter model protective device |
-
2019
- 2019-04-11 CN CN201910288178.3A patent/CN109870289B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09133605A (en) * | 1995-11-10 | 1997-05-20 | Natl Aerospace Lab | Supersonic flutter stopping apparatus |
| JP2004109067A (en) * | 2002-09-20 | 2004-04-08 | National Aerospace Laboratory Of Japan | Transonic flutter stop device |
| CN101629867A (en) * | 2009-06-05 | 2010-01-20 | 中国航空工业集团公司西安飞机设计研究所 | Protector for wing-surface test model |
| CN201724807U (en) * | 2010-02-26 | 2011-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Connector for horizontal stabilizer and vertical stabilizer of flutter model |
| CN203894027U (en) * | 2014-04-17 | 2014-10-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Protective stop mechanism for trailing edge control surface of flutter model |
| CN205209728U (en) * | 2015-12-14 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Flutter wind tunnel model protector based on magnetic force lock |
| CN105841915A (en) * | 2016-05-16 | 2016-08-10 | 中国航空工业集团公司西安飞机设计研究所 | Longitudinal freedom degree simulation full aircraft flutter wind tunnel model support system |
| CN108195543A (en) * | 2017-11-29 | 2018-06-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft wind tunnel model flutter blowing test system |
| CN209459859U (en) * | 2019-04-11 | 2019-10-01 | 中国空气动力研究与发展中心高速空气动力研究所 | T-type horizontal tail flutter model protective device |
Non-Patent Citations (4)
| Title |
|---|
| T型尾翼跨声速复合材料颤振模型设计研究;吕彬彬;《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑 (月刊)》(第2期);第C031-18页 * |
| T型尾翼风洞颤振实验保护装置绕流特性分析;史爱明;《实验流体力学》;第27卷(第4期);第57-61、77页 * |
| 超声速颤振风洞试验技术研究;闫昱等;《实验流体力学》;第30卷(第6期);第76-80页 * |
| 高超声速风洞连续变动压舵面颤振试验;季辰等;《实验流体力学》;第31卷(第6期);第37-44页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109870289A (en) | 2019-06-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109870289B (en) | T-shaped horizontal tail flutter model protection device and application thereof | |
| US10018544B2 (en) | Electromagnetic multiaxial fatigue testing machine | |
| CN206012760U (en) | Articulated type pole-climbing detects robot | |
| CN110687274B (en) | Rock shearing-seepage testing machine and testing method thereof | |
| CN208305062U (en) | A kind of Pneumatic flexible rotor gripper structure | |
| CN209459859U (en) | T-type horizontal tail flutter model protective device | |
| CN112284674A (en) | Electromagnet hanging and throwing device for hypersonic wind tunnel model free flight test | |
| CN108535035B (en) | Zero-gravity suspension test device for cylindrical surface unfolding mechanism | |
| CN113776825A (en) | Test device of test bed for simulating power of crankshaft rotor-bearing system | |
| CN110260071B (en) | High-precision mechanical casting | |
| LU502455B1 (en) | Steel wire rope detection apparatus | |
| CN209416737U (en) | A kind of gas source generating means and the pressure decay test system comprising it | |
| CN105445051A (en) | Anti-theft safety door detection device | |
| CN115508442A (en) | Generator bearing bush fault diagnosis structure | |
| CN112763196B (en) | Impact slip test device for shipboard aircraft arresting cable | |
| CN208906929U (en) | Double sided slider bar column examines anti-gravity charging manipulator | |
| CN216424792U (en) | Directional load loading device for rotating mechanism | |
| CN219455694U (en) | Detection device for bridge underwater foundation disease reinforcement | |
| CN212614887U (en) | Railway detection tunnel lining surface state detection vehicle | |
| CN217349629U (en) | Turnover machine | |
| RU2491528C2 (en) | Hydraulic jar test bench | |
| CN212254534U (en) | Aircraft model performance detection device for test | |
| CN110671138A (en) | Pneumatic anchor cable booster suitable for mine roadway full-anchor support and construction method | |
| CN214627172U (en) | Gas well water lock unblocking agent field experiment analogue means | |
| CN109896393A (en) | A kind of falling proof device for elevator and the elevator equipped with the falling proof device |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |