CN107247839A - A kind of low-speed wind tunnel virtual flight flight test vehicle design methods - Google Patents
A kind of low-speed wind tunnel virtual flight flight test vehicle design methods Download PDFInfo
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Abstract
The present invention relates to a kind of low-speed wind tunnel virtual flight flight test vehicle design methods, belong to wind-tunnel virtual flight test model design field.The design method optimizes rudder face type of drive, enable model manipulation face become automatically rudder face so as to implementation model it is pneumatic/function of motion/control coupling.The weight and inertial load of model are alleviated, and makes from structure design model barycenter trim, it is ensured that the actual barycenter of model aircraft reference center, model, virtual flight supporting mechanism pivot are overlapped simultaneously.The design method meets the requirement of processing technology and testing equipment, and mould processing precision meets virtual flight wind tunnel test DATA REASONING required precision, is applied to stable in virtual flight wind tunnel test, installation, convenient disassembly.
Description
Technical field
The present invention relates to a kind of low-speed wind tunnel virtual flight flight test vehicle design methods.
Background technology
Wind tunnel test generally can be Flight Vehicle Design and Control System Design provides aerodynamic characteristics parameter.However as winged
The continuous improvement of row device maneuvering characteristics, higher requirement is proposed to aircraft performance, at present still can preferably describe and
Indicate overload of the aircraft when High Angle of Attack is motor-driven, stability and it is motor-driven when required controling power ground experiment method.For this
One problem, has developed a kind of advanced wind-tunnel dynamic test technique, i.e. wind-tunnel virtual flight experimental technique in recent years.The technology is led to
Cross the true motor-driven motion process of simulated flight device more true to nature, make to realize in wind-tunnel Aircraft flight dynamics characteristic,
Flight control system, navigation system comprehensive verification etc. are possibly realized.
20th century mid-term, various countries begin one's study the virtual flight experiment of model in succession, and state of the art is in a leading position, and
Most representational is USAF Arnold Engineerring Development center (AEDC).It realizes virtual flight first in wind-tunnel and drilled
Show checking test, reproduced rolling locking phenomenon of the guided missile in wind-tunnel, this technology is progressively moved towards engineering from conceptual approach
Practical stage.Germany constructs the wind-tunnel dynamic test of six degree of freedom in DNW low-speed wind tunnel NWB based on parallel principle
Device, can be by manipulating control rudder face implementation model around the flat of the pitching of body axle, rolling and yaw rotation and three directions
It is dynamic.Russia, Britain etc. also have developed for simulating that advanced aircraft maneuvering flight, comprehensive test be pneumatic and flight mechanics characteristic
Integrated experimental rig, carried out substantial amounts of experimental study, be that the flight mechanics performance during aircraft maneuvering flight is comprehensive
Close analysis and provide effective means.It is domestic at present in tool in order to adapt to the active demand that China's advanced aircraft of new generation is developed
On the basis of the high, low speed wind-tunnel single-degree-of-freedom and two-freedom dynamic test technique of a standby capability, existing many units start
Develop wind-tunnel virtual flight experimental technique, but generally also have very over long distances apart from Practical all in the starting stage.
In the experiment of wind-tunnel virtual flight, dummy vehicle need to realize free pitching, driftage, rolling very by support system
It is dynamic to boring, and the control surface motion of the control system Controlling model outside wind-tunnel, under steady or transient Aerodynamic force action, mould
Type changes posture in real time, shows intrinsic flight dynamics characteristic.As can be seen here, the design of test model is to determine to test into
Work(whether basic and key.But different from conventional wind tunnel test, virtual flight test model maximum length is by wind tunnel test
The factor limitation such as section size, therefore modelling difficulty is very big.How to design to process under dimension constraint and meet quality, inertia
The dynamically similar model of requirement of similarity, is still a major challenge that virtual flight test model is developed.The experiment of wind-tunnel virtual flight is same
Sample needs to use scale model, particularly for the aircraft of aircraft class, and the contracting of its geometry is smaller, except non-in process of the test
Outside Unsteady Flow, for the gesture stability of implementation model, in addition it is also necessary to consider flight control computer, attitude measurement system, steering wheel
Control system etc. is installed on the correct position inside scale model, and test model design process is extremely complex, and in model contracting
Than after, overall structure must reach the big requirement of light weight, intensity.At this moment can not be met using metal material manufacture will
Ask.In addition, in virtual flight wind tunnel test, the barycenter of model must be close to simulate the barycenter of actual airplane, determine model
It is initial disturbance and flight stability, handling.To ensure model reference center, the actual barycenter of model, virtual flight supporting mechanism
Pivot is overlapped, and model must carry out trim design.
In summary, how rationally effective design is carried out to virtual flight test model, implementation model control surface is automatic
Become rudder face, it is ensured that the actual barycenter of model aircraft reference center, model, virtual flight supporting mechanism pivot are overlapped simultaneously, and
And the big requirement of light weight, intensity is met, as technical problem urgently to be resolved hurrily.
The content of the invention
Based on above weak point, set it is an object of the invention to provide a kind of low-speed wind tunnel virtual flight flight test vehicle model
Meter method, enable model manipulation face become automatically rudder face so as to implementation model it is pneumatic/function of motion/control coupling.And protect
Card model aircraft reference center, the actual barycenter of model, virtual flight supporting mechanism pivot are overlapped simultaneously.
The technology of the present invention just is as follows：A kind of low-speed wind tunnel virtual flight flight test vehicle design methods, including
Following content：
The selection of moulded dimension：According to test chamber size, virtual flight test model maximum length should be no more than examination
The 70% of section width is tested, it is determined that the ratio of reducing, obtains dynamic "scale" model；
Model general structure is divided into die body, rudder face manipulation component, balance weight assembly, angle keeper, wherein：
1) die body includes model outer mold surface and inner support frame, and model outer mold surface is high using specific strength, specific stiffness
Carbon fibre material by compression molding, arrangement longitudinally, laterally reinforcement composition support frame, model key load inside model
Framework or connector include fuselage framework, pattern board, wing skeleton, all using high intensity superduralumin；
2) control surface of model realizes controlled motion by way of servo driving, linkage carry out motion transmission,
Rudder face manipulation component includes steering wheel, and steering wheel fixture, rocking arm, connecting rod, rotating shaft mounting seat, wherein steering wheel support high speed serialization net
Network, with position feedback function, rotating shaft mounting seat is according to circumstances connected by way of pre-buried, bonding or screw fastening with rudder face
Connect, the limit of sports record position of steering wheel installation site in control system and linkage is coordinated, passes through dynamics software pair
Linkage carries out link motion track in motion simulation, analysis motion process, according to analysis result optimizing structure design, until
Untill mechanism kinematic process does not produce interference with model；
3) counterweight need to be carried out using this body structure of model and subsidiary parts during modelling, model center of gravity is to the rear,
Balance weight assembly need to be arranged in Handpiece Location, balance weight assembly weight is reduced as far as possible, balance weight assembly includes counter weight base, counterweight screw rod
And balancing weight, counter weight base be used for be fixedly connected with pattern board, by adjust balancing weight screw rod vertical direction height and
Configuration thickness realizes that center of gravity is adjusted；
4) design angle keeper carries out each control surface degree of bias demarcation of model, and the angular surveying graduated scale of each control surface is equal
Contact point is closed on as zero degree point perpendicular to control surface shaft axis, and using control surface and graduated scale, is marked successively up and down along circular arc
Radian；
Material properties definition finally is carried out to critical component, according to pneumatic and inertial load, finite element analysis software is utilized
Carry out key component performance evaluation, structure optimization carried out according to analysis result, finally ensure model structure meet intensity, it is rigidity, steady
Qualitative requirement；
After Model Mounting, according to the structure space of internal reservation arrange rudder face manipulation component, gyroscope, flight control computer,
Lithium battery group, is treated after the completion of model intraware installation and debugging, using barycenter and Measuring System of Inertia Moment, adjustment balancing weight exists
Height and weight on screw rod, carry out the overall barycenter trim of model, finally make the actual barycenter in model reference center, model, virtually
Flight supporting mechanism pivot is completely superposed.
The present invention also has following technical characteristic：
1. described in the inside of die body also include pattern board, virtual flight support meanss peace is reserved on pattern board
Attaching mouthful.
2. for some thin parts that thin or size is smaller but type face is complicated directly using the overall machine-shaping of metal, connection
It is connected on die body, is required according to intensity, moulded dimension and processing technology, primarily determine that outer mold surface carbon fiber skin and bone
The thickness of frame.
3. model need to be facilitated to install, dismounting and posture are adjusted according to model support condition, the cover plate of respective design appropriate size
It is whole.
4. described in the corresponding aircraft outer surface of rudder face manipulation component need to design the cover plate of appropriate size, to facilitate steering wheel to pacify
Dress, debugging and dismounting.
5. described in rudder face manipulation component its corresponding control surface use carbon fiber shell in built-in metal skeleton side
Method is molded, and is coupled by base with hinge with die body.
6. described in balance weight assembly material use stainless steel.
7. described in the corresponding aircraft outer surface of balance weight assembly need to design the cover plate of appropriate size, with facilitate steering wheel install,
Debugging and dismounting.
8. correspond to pre-buried at outer mold surface covering or put down in correspondence skeleton appropriate location design metal below described cover plate
Platform, for being connected and fixed with cover plate.
The design method alleviates the weight and inertial load of model, and control can be manipulated by realizing each control surface of aircraft, full
The requirement of sufficient processing technology and testing equipment, is applied to stable in virtual flight wind tunnel test, installation, convenient disassembly.Mould
Type machining accuracy meets virtual flight wind tunnel test DATA REASONING required precision, and dynamic aerodynamics unconventional to post stall maneuver are special
Property technical research plays a significant role.
Brief description of the drawings
Fig. 1 is the design principle schematic；Wherein 1, balance weight assembly, 2, fuselage framework, 3, pattern board, 4, wing bone
Frame, 5, model outer mold surface, 6, steering wheel fixture, 7, steering wheel, 8, rocking arm, 9, connecting rod, 10, rotating shaft mounting seat, 11, slat, 12, bottom
Seat plus and hinge, 13, angle keeper, 14, mounting interface.
Embodiment
Following specific implementation examples are included with reference to Figure of description, technical scheme is described further.
A kind of low-speed wind tunnel virtual flight flight test vehicle design methods, including following content, as shown in figure 1,
The selection of moulded dimension, according to test chamber size, virtual flight test model maximum length should be no more than examination
The 70% of section width is tested, it is determined that the ratio of reducing, obtains dynamic "scale" model；
According to mode shape layout characteristics and model internal unit installation situation, model overall structure is analyzed, assisted
Each space of components structure and mounting means inside mode transfer type.Model general structure is divided into die body, rudder face manipulation component, counterweight
Component 1, angle keeper 13.Wherein：
1) to reduce model weight as far as possible, die body uses metal and composite mix-configuration structure, by outer
Type face and inner support frame composition.It is used as using the high carbon fibre material of specific strength, specific stiffness by compression molding outside model
Type face 5.Longitudinally, laterally reinforcement constitutes load-bearing frame to arrangement inside model.Model key load-bearing frame or connector, such as fuselage
The component materials such as skeleton 2, pattern board 3, wing skeleton 4 use high intensity superduralumin, pass through the mode such as bonding or screw connection
Two kinds of material components are coupled integrally securely.
2) control surface of model realizes controlled motion by way of steering wheel 7 drives, linkage carries out motion transmission.
Rudder face manipulation component mainly includes steering wheel 7, and steering wheel fixture 6, rocking arm 8, connecting rod 9, rotating shaft mounting seat 10, wherein steering wheel 7 are supported
High-speed serial network, with position feedback function, rotating shaft mounting seat 10 can be fastened according to circumstances by pre-buried, bonding, screw etc.
Mode couples with rudder face (such as wing flap, slat 11, aileron, rudder).To the installation site of steering wheel in control system 7 and connecting rod machine
The limit of sports record position of structure is coordinated, and is carried out by dynamics software linkage in motion simulation, analysis motion process
Link motion track, according to analysis result optimizing structure design, untill mechanism kinematic process does not produce interference with model.
3) in order to effectively reduce model weight, this body structure of model need to be utilized as far as possible and subsidiary during modelling
Parts carry out counterweight.Further, since body need to arrange rudder face manipulation component after model, model center of gravity is generally to the rear, need to be by counterweight
Component 1 is arranged in Handpiece Location as far as possible, and the weight of balance weight assembly 1 is reduced as far as possible.Balance weight assembly 1 is by counter weight base, counterweight screw rod
And balancing weight is constituted.Counter weight base is used to be connected with pattern board, high in screw rod vertical direction by adjusting balancing weight
Degree and configuration thickness realize that center of gravity is adjusted.
4) design angle keeper 13 carries out each control surface degree of bias demarcation of model.Each control surface (such as wing flap, slat 11,
Aileron, rudder etc.) angular surveying graduated scale be each perpendicular to control surface shaft axis, and connect with control surface and closing on for graduated scale
Contact is zero degree point, and radian is marked successively up and down along circular arc.
Material properties definition is carried out to critical component, according to pneumatic and inertial load, carried out using finite element analysis software
Key component performance evaluation, carries out structure optimization according to analysis result, finally ensures that model structure meets intensity, rigidity, stability
It is required that.
The inside of described die body also includes pattern board 3, and it is as model skeleton, rudder face manipulation component, top
Spiral shell instrument, flight control computer, the mounting platform of lithium battery group dispatch control system.In addition, reserving virtual flight support on pattern board
Device mounting interface 14, so that the mode of motion such as the free pitching of implementation model, driftage, rolling.According to actual needs at model bottom
Arrange that nail meets each part connection on plate, and appropriate loss of weight design is carried out to subregion.
Can be directly using the overall machine-shaping of metal, connection for some thin parts that thin or size is smaller but type face is complicated
It is connected in main body.It can be required according to intensity, moulded dimension and processing technology, primarily determine that outer mold surface carbon fiber skin and skeleton
Thickness.
According to model support condition, the cover plate of respective design appropriate size facilitates model to install, dismantle and pose adjustment.
Corresponded to below cover plate pre-buried at outer mold surface covering or design metal platform in correspondence skeleton appropriate location, for coupling with cover plate
It is fixed.
The corresponding aircraft outer surface of rudder face component need to design the cover plate of appropriate size, to facilitate steering wheel to install, debug and tear open
Unload.
The corresponding control surface (such as wing flap, aileron, rudder) of rudder face manipulation component is using pre-buried in carbon fiber shell
The method shaping of metallic framework, is realized by way of hinge 12 base and coupled with die body.
To reduce space-consuming, the material of balance weight assembly 1 uses stainless steel.The corresponding aircraft outer surface of balance weight assembly 1 is needed
The cover plate of appropriate size is designed, to facilitate steering wheel to install, debug and dismantle.
After Model Mounting, according to the structure space of internal reservation arrange rudder face manipulation component, gyroscope, flight control computer,
Lithium battery group, is treated after the completion of model intraware installation and debugging, using barycenter and Measuring System of Inertia Moment, adjustment balancing weight exists
Height and weight on screw rod, carry out the overall barycenter trim of model, finally make the actual barycenter in model reference center, model, virtually
Flight supporting mechanism pivot is completely superposed.
The design method alleviates the weight and inertial load of model, and control can be manipulated by realizing each control surface of aircraft, full
The requirement of sufficient processing technology and testing equipment, is applied to stable in virtual flight wind tunnel test, installation, convenient disassembly.
Claims (9)
1. a kind of low-speed wind tunnel virtual flight flight test vehicle design methods, it is characterised in that this method includes following content：
The selection of moulded dimension：According to test chamber size, virtual flight test model maximum length should be no more than test section
The 70% of width, it is determined that the ratio of reducing, obtains dynamic "scale" model；
Model general structure is divided into die body, rudder face manipulation component, balance weight assembly, angle keeper, wherein：
1) die body includes model outer mold surface and inner support frame, and model outer mold surface is using the high carbon of specific strength, specific stiffness
Fibrous material is by compression molding, and longitudinally, laterally reinforcement constitutes support frame, model key load-bearing frame to model inside arrangement
Or connector includes fuselage framework, pattern board, wing skeleton, all using high intensity superduralumin；
2) control surface of model realizes controlled motion, rudder face by way of servo driving, linkage carry out motion transmission
Manipulation component includes steering wheel, and steering wheel fixture, rocking arm, connecting rod, rotating shaft mounting seat, wherein steering wheel support high-speed serial network, tool
There is position feedback function, rotating shaft mounting seat is according to circumstances connected by way of pre-buried, bonding or screw fastening with rudder face, to behaviour
The limit of sports record position of steering wheel installation site and linkage is coordinated in control system, passes through dynamics software linkage
Link motion track in motion simulation, analysis motion process is carried out, according to analysis result optimizing structure design, until mechanism kinematic
Untill process does not produce interference with model；
3) counterweight need to be carried out using this body structure of model and subsidiary parts during modelling, model center of gravity is to the rear, need by
Balance weight assembly is arranged in Handpiece Location, as far as possible reduce balance weight assembly weight, balance weight assembly include counter weight base, counterweight screw rod and
Balancing weight, counter weight base is used to be fixedly connected with pattern board, by adjusting balancing weight in screw rod vertical direction height and configuration
Thickness realizes that center of gravity is adjusted；
4) design angle keeper carries out each control surface degree of bias demarcation of model, and the angular surveying graduated scale of each control surface is vertical
Contact point is closed on as zero degree point in control surface shaft axis, and using control surface and graduated scale, and radian is marked successively up and down along circular arc；
Material properties definition finally is carried out to critical component, according to pneumatic and inertial load, carried out using finite element analysis software
Key component performance evaluation, carries out structure optimization according to analysis result, finally ensures that model structure meets intensity, rigidity, stability
It is required that；
After Model Mounting, rudder face manipulation component, gyroscope, flight control computer, lithium electricity are arranged according to the structure space of internal reservation
Pond group, is treated after the completion of model intraware installation and debugging, using barycenter and Measuring System of Inertia Moment, adjustment balancing weight is in screw rod
On height and weight, carry out the overall barycenter trim of model, finally make the actual barycenter in model reference center, model, virtual flight
Supporting mechanism pivot is completely superposed.
2. a kind of low-speed wind tunnel virtual flight flight test vehicle design methods according to claim 1, its feature exists
In：The inside of described die body also includes reserving virtual flight support meanss mounting interface on pattern board, pattern board.
3. a kind of low-speed wind tunnel virtual flight flight test vehicle design methods according to claim 1, its feature exists
In：For some thin parts that thin or size is smaller but type face is complicated directly using the overall machine-shaping of metal, mould is connected to
In type main body, required according to intensity, moulded dimension and processing technology, primarily determine that the thickness of outer mold surface carbon fiber skin and skeleton
Degree.
4. a kind of low-speed wind tunnel virtual flight flight test vehicle design methods according to claim 1, its feature exists
In：According to model support condition, the cover plate of respective design appropriate size model need to be facilitated to install, dismantle and pose adjustment.
5. a kind of low-speed wind tunnel virtual flight flight test vehicle design methods according to claim 1, its feature exists
In：The corresponding aircraft outer surface of described rudder face manipulation component need to design the cover plate of appropriate size, to facilitate steering wheel to install, debug
And dismounting.
6. a kind of low-speed wind tunnel virtual flight flight test vehicle design methods according to claim 1, its feature exists
In：Described rudder face manipulation component uses the method shaping of built-in metal skeleton in carbon fiber shell in its corresponding control surface,
Coupled by base with hinge with die body.
7. a kind of low-speed wind tunnel virtual flight flight test vehicle design methods according to claim 1, its feature exists
In：Described balance weight assembly material uses stainless steel.
8. a kind of low-speed wind tunnel virtual flight flight test vehicle design methods according to claim 1, its feature exists
In：The corresponding aircraft outer surface of described balance weight assembly need to design the cover plate of appropriate size, to facilitate steering wheel to install, debug and tear open
Unload.
9. a kind of low-speed wind tunnel virtual flight flight test vehicle design methods according to claim 5, its feature exists
In：Corresponded to below described cover plate pre-buried at outer mold surface covering or design metal platform in correspondence skeleton appropriate location, be used for
It is connected and fixed with cover plate.
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| AZAROV, Y. A.ETC.: ""Experience in laser stereolithography and its application in manufacturing wind-tunnel aerodynamic models of various purposes"", 《SEVENTH INTERNATIONAL CONFERENCE ON LASER AND LASER-INFORMATION TECHNOLOGIES》 * |
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