CN106844838A - A kind of aircraft airvane method of evaluating performance - Google Patents
A kind of aircraft airvane method of evaluating performance Download PDFInfo
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Abstract
The present invention relates to a kind of aircraft airvane method of evaluating performance, the method includes air rudder system Static stiffness, dynamic stiffness (torsion frequency) analytical expression is set up, air rudder system FEM model is set up and airvane system-based rigidity, the ess-strain of part, the performance evaluations such as deformation, airvane method for testing performance is formulated, airvane experimental rig is designed, by to airvane Theoretical Analysis of The Performance, simulation analysis and experimental test are combined acquisition aircraft airvane load-carrying properties, Static stiffness and dynamic stiffness, transmission function and and frictional behaviour, it is optimization design aircraft airvane, overall merit airvane performance provides comprehensive evaluating and reliable convenient evaluation method.
Description
Technical field
The present invention relates to a kind of aircraft airvane method of evaluating performance, belong to train of mechanism performance evaluation and test neck
Domain.
Background technology
Aircraft airvane is connected by transmission mechanism with airframe structure, and airvane is by the beat in the range of certain angle
Reach the purpose of adjustment attitude of flight vehicle.The performance of air rudder system is the result of many factors comprehensive function, and transmission mechanism is closed
The configuration mode of key parts, the fit system between the mode of rudder face body and stiffness characteristics, parts, load working condition and ring
Border working condition etc. all influences stationarity, beat precision, transfer function characteristics of airvane performance etc..Rigidity is aircraft air
The first element of rudder system design, estimating rigidity by easily method and carry out optimization in the design phase can improve design effect
Rate.Conventional air rudder method of evaluating performance is relatively simple, and the assumed condition that theory analysis is used is idealized partially, it is difficult to true reflection
Property indices；The method and result of simulation analysis need compatibility test to verify；Performance of the airvane under various operating conditions
Evaluation test scheme can not combine closely with experimental rig design, cause experimental rig unitary function, it is impossible to comprehensively examined
Nuclear test.The aircraft airvane method of evaluating performance of convenient application is to lift air rudder system to set again to set up a kind of reliable results
The effective means of meter technology.
The content of the invention
A kind of drawbacks described above it is an object of the invention to overcome prior art, there is provided aircraft airvane performance evaluation side
Method, the method is combined acquisition aircraft airvane and carries by airvane Theoretical Analysis of The Performance, simulation analysis and experimental test
Performance, Static stiffness and dynamic stiffness, transmission function and and frictional behaviour, be high dynamic and high reliability aircraft airvane and its biography
The design and optimization of dynamic device provide evaluating comprehensively, economic.
What above-mentioned purpose of the invention was mainly achieved by following technical solution：
A kind of aircraft airvane method of evaluating performance, comprises the following steps：
Step (1), the equivalent Line stiffness K onto steering wheel start rod axis of acquisition air rudder systemla, expression formula is as follows：
Wherein：KlIt is the equivalent Line stiffness onto steering wheel start rod axis of transmission mechanism；KsFor steering wheel body is equivalent to steering wheel
Line stiffness on start rod axis；KbaseIt is the Line stiffness on airvane system-based stiffnes s equivalent to steering wheel start rod axis；
KcontFor the contact stiffness of between each parts of transmission mechanism and transmission mechanism and steering wheel junction is equivalent to steering wheel operating bar
Line stiffness on axis；
Step (2), according to Line stiffness KlaObtain the dynamic stiffness f in the range of the full angle of rudder reflection of airvaner, expression formula is as follows：
Wherein：JrIt is air rudder system to the rotary inertia of rudderpost axis, KrFor air rudder system is equivalent to rudderpost axis
Torsional rigidity, expression formula is as follows：
Kr=Kla·ilo 2
Wherein：iloIt is steering wheel operating bar elongation speed VrWith rudder face rotational angular velocity ωdThe ratio between；
Step (3), the stress by requiring position in airvane transmission mechanism bearing capacity test acquisition air rudder system
And strain value；
Step (4), the transmission that transmission mechanism in acquisition air rudder system is tested by airvane transmission mechanism transmission function
Function；
Step (5), the airvane rudderpost tested by airvane transmission mechanism frictional behaviour under acquisition different loads are supported
The frictional force of bearing and the comprehensive frictional force of transmission mechanism.
In above-mentioned aircraft airvane method of evaluating performance, transmission mechanism is equivalent to steering wheel start in the step (1)
Line stiffness K on rod axislObtained by equation below：
In formula, Ly is transmission mechanism rocking arm length；EyIt is transmission mechanism rocking arm elasticity modulus of materials；IeyFor transmission mechanism shakes
Arm equivalenting inertia torque；Lz is steering wheel height of support；γzIt is the steering wheel seat structure plane of symmetry and the angle of steering wheel start rod axis；EZ
It is steering wheel bearing elastic modelling quantity；IezIt is steering wheel bearing equivalenting inertia torque；θ is the folder of transmission mechanism rocking arm and steering wheel start rod axis
Angle；La is rudderpost effective length；GaIt is rudderpost material modulus of shearing, its value is Ga=Ea/2(1+νa), wherein EaIt is rudderpost material
Elastic modelling quantity, νaIt is rudderpost material Poisson's ratio；IaIt is rudderpost second polar moment of area.
In above-mentioned aircraft airvane method of evaluating performance, air rudder system soil rigidity is equivalent in the step (1)
Line stiffness K onto steering wheel start rod axisbaseObtained by equation below：
In formula, Lc be bearing spider highly；γcIt is bearing spider symmetrical configuration face and the angle of steering wheel start rod axis；
Lz is steering wheel height of support；γzIt is the steering wheel seat structure plane of symmetry and the angle of steering wheel start rod axis；Kc_baseIt is bearing branch
The soil rigidity of seat；Kz_baseIt is the soil rigidity of steering wheel bearing.
In above-mentioned aircraft airvane method of evaluating performance, the soil rigidity K of the bearing spiderc_baseWith steering wheel branch
The soil rigidity K of seatz_baseObtain by the following method：
Step (1.1), air rudder system FEM model is set up using finite element software, and set each in air rudder system
The cell attribute of individual parts；
Step (1.2), the way of restraint and drive connection that define each junction of airvane transmission mechanism, airvane is driven
Mechanism's bearing spider and steering wheel bearing rigidifying, will airvane transmission mechanism bearing bearing and steering wheel support material elastic modelling quantity
8~15 times of actual value are assigned, the list of steering wheel thrust direction is applied on airvane transmission mechanism bearing bearing and steering wheel bearing
Position power, obtains deformation of the bearing at trail force load position, equivalent moment of flexure and torsion angle into the bearing root, moment of flexure
With the soil rigidity that the ratio of torsion angle is bearing, the i.e. moment of flexure of airvane transmission mechanism bearing bearing and the ratio of torsion angle
It is Kc_base, the moment of flexure of steering wheel bearing is K with the ratio of torsion anglez_base。
In above-mentioned aircraft airvane method of evaluating performance, in the step (1.1) each zero in air rudder system
The cell attribute of part is：Transmission mechanism parts are simulated with solid element, and rudder face is simulated with shell unit, rudderpost beam element mould
Intend, steering wheel is simulated with spring unit.
In above-mentioned aircraft airvane method of evaluating performance, in the step (1) between each parts of transmission mechanism with
And the equivalent Line stiffness K onto steering wheel start rod axis of contact stiffness of transmission mechanism and steering wheel junctioncontBy following public
Formula is obtained：
Wherein, KlgIt is airvane transmission mechanism combination Line stiffness.
In above-mentioned aircraft airvane method of evaluating performance, the airvane transmission mechanism combination Line stiffness KlgBy such as
Lower method is obtained：
The rudderpost of air rudder system is fixed, steering wheel power closed-loop control, first carry out the gap treatment that disappears, then exported again constant
Thrust, obtains the output displacement of steering wheel operating bar under different power loading situations, and airvane transmission mechanism is obtained by equation below
Combination Line stiffness Klg：
Klg=F/ Δs s
Wherein：F is steering wheel thrust, and Δ s is steering wheel operating bar output displacement.
In above-mentioned aircraft airvane method of evaluating performance, the airvane transmission mechanism combination Line stiffness KlgBy sky
Gas rudder experiment device is obtained, and the airvane experimental rig includes pedestal, adjustable steering wheel bearing, the first transmission mechanism bearing support
Erection support, the second transmission mechanism bearing support erection support, the first support reaction apply component, the second support reaction apply component,
Rudder face inertia simulation disk, angle measure component, moment of torsion charging assembly and torque sensor, wherein adjustable steering wheel bearing is arranged on base
On seat, the steering wheel rear end of air rudder system is arranged on adjustable steering wheel bearing, and steering wheel front end is hinged with the rocking arm of air rudder system,
Rocking arm is fixedly connected with the rudderpost of air rudder system；First transmission mechanism bearing support erection support and the second transmission mechanism are supported
Bearing erection support is arranged on pedestal, bearing spider and bearing for installing fixed air rudder system, air rudder system
Rudderpost passes through the bearing, and applies component and the second support reaction applying component touch with the first support reaction, and described first anti-
Force applying assembly and the second support reaction apply component and are arranged on pedestal, and positioned at the first transmission mechanism bearing support erection support
Between the second transmission mechanism bearing support erection support, radial load is applied for the rudderpost for air rudder system；The rudder
Face inertia simulation disk is arranged on rudderpost one end of air rudder system, for the rotary inertia of simulated air rudder rudder face, the angle
Measurement assembly is fixedly mounted on pedestal；The moment of torsion charging assembly is fixedly mounted on pedestal, the one end with torque sensor
Connection, the other end of the torque sensor is connected with rudderpost.
In above-mentioned aircraft airvane method of evaluating performance, the test in the step (3), step (4) and step (5)
Carried out by airvane experimental rig, the airvane experimental rig includes pedestal, adjustable steering wheel bearing, the first transmission mechanism
Bearing support erection support, the second transmission mechanism bearing support erection support, the first support reaction apply component, the second support reaction to be applied
Plus component, rudder face inertia simulation disk, angle measure component, moment of torsion charging assembly and torque sensor, wherein adjustable steering wheel bearing
On pedestal, the steering wheel rear end of air rudder system is arranged on adjustable steering wheel bearing, steering wheel front end and air rudder system
Rocking arm is hinged, and rocking arm is fixedly connected with air rudder system rudderpost；First transmission mechanism bearing support erection support and the second transmission
Mechanism's bearing support erection support is arranged on pedestal, for installing fixed air rudder system middle (center) bearing bearing and bearing, air
The rudderpost of rudder system passes through the bearing, and applies component and the second support reaction applying component touch with the first support reaction, described
First support reaction applies component and the second support reaction applies component and is arranged on pedestal, and positioned at the first transmission mechanism bearing support
Between erection support and the second transmission mechanism bearing support erection support, apply radially to carry for the rudderpost for air rudder system
Lotus；The rudder face inertia simulation disk is arranged on one end of air rudder system rudderpost, for the rotary inertia of simulated air rudder rudder face,
The angle measure component is fixedly mounted on pedestal；The moment of torsion charging assembly is fixedly mounted on pedestal, with torque sensing
One end connection of device, the other end of the torque sensor is connected with rudderpost.
In above-mentioned aircraft airvane method of evaluating performance, carried by airvane transmission mechanism in the step (3)
Aptitude tests are obtained and require that the specific method of stress and strain value of position is in air rudder system：
(3.1) foil gauge or strain rosette, the steering wheel position of air rudder system, are installed in airvane system parts requirement position
Closed-loop control is put, rudderpost is turned under different angle of rudder reflection, by angle measurement module testing angle of rudder reflection, by the first support reaction
Apply component and the second support reaction applies component for rudderpost applies radial load, read the stress and strain for requiring position
Value, is the stress and strain value of static bearing capacity；
(3.2), the steering wheel position-force control of air rudder system, does frequency sweep and moves with different frequency, anti-by first
It is that rudderpost applies radial load that force applying assembly and the second support reaction apply component, reads the stress and strain for requiring position
Value, is the stress and strain value of dynamic carrying capacity.
In above-mentioned aircraft airvane method of evaluating performance, transmitted by airvane transmission mechanism in the step (4)
The specific method of the transmission function of transmission mechanism is in function test acquisition air rudder system：
Component is applied by moment of torsion charging assembly, the first support reaction respectively and the second support reaction applies component to airvane rudder
Axle applies moment of torsion and support reaction, and steering wheel exports the sinusoidal motion of same amplitude different frequency in transmission mechanism total travel, obtains rudder
The output displacement s of the machine and corner δ of rudderpost, draws the s- δ curves that steering wheel displacement changes with rudderpost corner, and bent according to s- δ
Line carries out the fitting of transmission function, obtains the transmission function of transmission mechanism.
In above-mentioned aircraft airvane method of evaluating performance, the step (5) is by airvane transmission mechanism frictional property
The specific side of the comprehensive frictional force of the airvane rudderpost spring bearing frictional force and transmission mechanism obtained under different loads can be tested
Method is as follows：
(5.1), the steering wheel and rocking arm of air rudder system are disconnected, moment of torsion charging assembly uniform rotation is applied to rudderpost
Plus support reaction, torque T is obtained by torque sensor, rudderpost rotary speed n is obtained by angle measurement component, according to following public affairs
Formula calculates the frictional force F of airvane rudderpost bearing support under different loadsf：
Tn/9.55=Ff·ν
Wherein：V is the linear velocity in bearing friction face.
(5.2), the steering wheel uniform motion of air rudder system, torque sensor is disconnected with moment of torsion charging assembly, and rudderpost is applied
Plus support reaction, torque T is obtained by torque sensor, the airvane transmission mechanism under different loads is calculated according to equation below
Comprehensive frictional force Mf；
Mf=FLy-T
Wherein：F is steering wheel thrust, LyIt is transmission mechanism rocking arm length.
Compared with the prior art, the invention has the advantages that：
(1) to establish the equivalent Line stiffness and the full rudder of airvane to steering wheel start rod axis of aircraft airvane inclined for the present invention
Dynamic stiffness (torsion frequency) analytical expression in angular region.On the premise of without carrying out airvane vibration test, can combine
Simulation analysis, airvane transmission mechanism Static stiffness result of the test easily estimate air rudder system in complete carry-on Static stiffness
And dynamic stiffness, airvane design optimization is effectively instructed, save experimentation cost；
(2) airvane performance test scheme proposed by the present invention covers the steering wheel performance survey of influence airvane combination property
The Multitest methods such as examination, bearing capacity test, rigidity test, transmission function test and frictional behaviour test.
(3) present invention gives experimental rig scheme with reference to airvane transmission mechanism multinomial performance test implementation method, tries
Experiment device can realize that the experiment of the various airvane performances of aircraft is examined by adjusting and changing associated component, and universality is good,
For funds are saved in the experiment of aircraft airvane, for the accumulation of polytype airvane performance data provides basic test facility.
(4) aircraft airvane method of evaluating performance of the present invention includes air rudder system Static stiffness, (torsional oscillation is frequently for dynamic stiffness
Rate) analytical expression foundation, air rudder system FEM model sets up and airvane system-based rigidity, the stress of part are answered
The performance evaluations such as change, deformation, airvane method for testing performance is formulated, airvane experimental rig design, by airvane performance
Theory analysis, simulation analysis and experimental test be combined acquisition aircraft airvane load-carrying properties (i.e. main load parts
Stress and strain value), Static stiffness and dynamic stiffness, transmission function and and frictional behaviour, be optimization design aircraft airvane, synthesis
Evaluate airvane performance and comprehensive evaluating and reliable convenient evaluation method are provided.
Brief description of the drawings
Fig. 1 is airvane method of evaluating performance implementation steps graph of a relation of the present invention；
Fig. 2 is the corresponding mechanism principle figure of airvane rigidity analytic expression of the present invention；
Fig. 3 is the mechanical structure composition schematic diagram of airvane experimental rig of the present invention.
Specific embodiment
Further detailed description is done to the present invention with specific embodiment below in conjunction with the accompanying drawings.
Aircraft airvane method of evaluating performance of the present invention is surveyed by airvane Theoretical Analysis of The Performance, simulation analysis and experiment
Examination be combined acquisition aircraft airvane load-carrying properties, Static stiffness and dynamic stiffness, transmission function and and frictional behaviour, be high dynamic
Design and optimization with high reliability aircraft airvane and its transmission device provide evaluating comprehensively, economic.
It is as shown in Figure 1 airvane method of evaluating performance implementation steps graph of a relation of the present invention, aircraft airvane of the present invention
Method of evaluating performance specifically includes following steps：
Step (1), it is illustrated in figure 2 the corresponding mechanism principle figure of airvane rigidity analytic expression of the present invention, it is considered to steering wheel,
Air rudder system etc. is set up in the full Flight Vehicle Structure basis of transmission mechanism, rudder face and airvane connection in interior air rudder system
The Line stiffness expression formula imitated on steering wheel start rod axis is as follows：
In formula, KlaIt is the equivalent Line stiffness onto steering wheel start rod axis of air rudder system；KlArrived for transmission mechanism is equivalent
Line stiffness on steering wheel start rod axis；KsIt is the equivalent Line stiffness onto steering wheel start rod axis of steering wheel body；KbaseIt is air
The equivalent Line stiffness onto steering wheel start rod axis of rudder system soil rigidity；KcontIt is (such as key between each parts of transmission mechanism
And keyway) and the contact stiffness of transmission mechanism and steering wheel junction (such as hinge pin and steering wheel front journal) equivalent make to steering wheel
Line stiffness on lever axis.
The equivalent Line stiffness K onto steering wheel start rod axis of transmission mechanismlCan be obtained by equation below：
In formula, Ly is transmission mechanism rocking arm length；EyIt is transmission mechanism rocking arm elastic modelling quantity；IeyIt is transmission mechanism rocking arm etc.
Effect the moment of inertia；Lz is steering wheel height of support；γzIt is the steering wheel seat structure plane of symmetry (perpendicular to the transmission triangle shown in Fig. 2
Face) and steering wheel start rod axis angle；EZIt is steering wheel bearing elastic modelling quantity；IezIt is steering wheel bearing equivalenting inertia torque；θ is transmission
The angle of mechanism's rocking arm and steering wheel start rod axis, as shown in Figure 2；La is rudderpost effective length；GaFor rudderpost material shears mould
Amount, its value is Ga=Ea/2(1+νa), wherein EaIt is rudderpost elasticity modulus of materials, νaIt is rudderpost material Poisson's ratio；IaFor rudderpost cuts
Face polar moment of inertia, for circular cross-section, Ia=π d4/ 32, wherein d are diameter of section.
For rectangle non-uniform beam, equivalenting inertia torque IeyAnd IezDetermined by formula (3)：
Wherein, b is the thickness of transmission mechanism rocking arm or steering wheel bearing；ξ is face height ratio, and its value is ξ=h/H, wherein h
For small end highly, H is big end height.
The equivalent Line stiffness K onto steering wheel start rod axis of soil rigidity of air rudder systembaseObtained by equation below
Arrive：
In formula, Lc be bearing spider highly；γcIt is bearing spider symmetrical configuration face (perpendicular to the transmission triangle shown in Fig. 2
Shape face) and steering wheel start rod axis angle；Kc_baseIt is the soil rigidity of bearing spider；Kz_baseFor the basis of steering wheel bearing is firm
Degree.
Wherein Kc_base、Kz_baseValue can be obtained by finite element analysis, comprise the following steps that：
Step (1.1), air rudder system FEM model is set up using finite element software, and set each in air rudder system
The cell attribute of individual parts；Finite element software can have in commercialization including MSC.Patran/Nastran, ANSYS and ABAQUS etc.
Limit meta software.The cell attribute of each parts is in air rudder system in the present invention：Transmission mechanism parts solid element
Simulation, rudder face is simulated with shell unit, and rudderpost is simulated with beam element, and steering wheel is simulated with spring unit.
Step (1.2), the calculating of soil rigidity are carried out on air rudder system FEM model, define airvane driver
The way of restraint and drive connection of each junction of structure, by airvane transmission mechanism bearing bearing and steering wheel bearing rigidifying, Ji Jiangkong
The elastic modelling quantity of gas rudder transmission mechanism bearing bearing and steering wheel support material assigns 8~15 times of actual value, in airvane transmission
Apply the unit force of steering wheel thrust direction on mechanism's bearing spider and steering wheel bearing, obtain the airvane transmission mechanism bearing branch
Seat and deformation of the steering wheel bearing at trail force load position, it is equivalent into the airvane transmission mechanism bearing bearing and steering wheel bearing
The moment of flexure of root and torsional deflection (torsion angle), moment of flexure are the soil rigidity of bearing, i.e. airvane with the ratio of torsion angle and pass
The moment of flexure of motivation structure bearing spider is K with the ratio of torsion anglec_base, the moment of flexure of steering wheel bearing is with the ratio of torsion angle
Kz_base。
The contact stiffness of between each parts of transmission mechanism and transmission mechanism and steering wheel junction is equivalent to steering wheel start
Line stiffness K on rod axiscontObtained by equation below：
Wherein, KlgIt is airvane transmission mechanism combination Line stiffness.
The mechanical structure composition schematic diagram of airvane experimental rig of the present invention is illustrated in figure 3, the present invention passes through airvane
Experimental rig carries out the test of air rudder system various performance parameters, above-mentioned airvane transmission mechanism combination Line stiffness KlgCan pass through
The experimental rig is obtained.
Such as Fig. 3, airvane experimental rig of the present invention includes pedestal 1, adjustable steering wheel bearing 2, the first transmission mechanism support shaft
Hold erection support 301, the second transmission mechanism bearing support erection support 302, the first support reaction and apply component 401, second instead
Force applying assembly 402, rudder face inertia simulation disk 6, angle measure component 7, moment of torsion charging assembly 9 and torque sensor 10, wherein
Adjustable steering wheel bearing 2 is arranged on pedestal 1, and the rear end of steering wheel 8 of air rudder system is arranged on adjustable steering wheel bearing 2, before steering wheel 8
End is hinged with the rocking arm 11 of air rudder system, and rocking arm 11 is fixedly connected with the rudderpost 5 of air rudder system；First transmission mechanism is supported
The transmission mechanism bearing support erection support 302 of bearing erection support 301 and second is arranged on pedestal 1, for installing fixed sky
The bearing spider (bearing of air rudder system is arranged on bearing spider) of gas rudder system, the rudderpost 5 of air rudder system passes through institute
Bearing is stated, and applies the support reaction of component 401 and second applying component 402 with the first support reaction and contacted, first support reaction is applied
Plus the support reaction of component 401 and second applies component 402 and is arranged on pedestal 1, and installed positioned at the first transmission mechanism bearing support
Between the transmission mechanism bearing support erection support 302 of bearing 301 and second, apply radially for the rudderpost 5 for air rudder system
Load；Rudder face inertia simulation disk 6 is arranged on one end of the rudderpost 5 of air rudder system, and the rotation for simulated air rudder rudder face is used to
Amount, the angle measure component 7 is fixedly mounted on pedestal 1；The moment of torsion charging assembly 9 is fixedly mounted on pedestal 1, with torsion
One end connection of square sensor 10, the other end of the torque sensor 10 is connected with rudderpost 5.
Airvane transmission mechanism combination Line stiffness K in above-mentioned formula (5)lgCan obtain by the following method：
As shown in figure 3, being fixed the rudderpost 5 of air rudder system by mechanical frock, the power closed-loop control of steering wheel 8 is first exported
Low thrust carries out the gap treatment that disappears, and constant thrust is then exported again, obtains the output displacement of steering wheel 8 under different power loading situations
(can also export the stress numerical of each pressure detection point), airvane transmission mechanism combination Line stiffness K is obtained by equation belowlg：
Klg=F/ Δs s
Wherein：F is steering wheel thrust, and Δ s is steering wheel operating bar output displacement.
Step (2), according to Line stiffness KlaObtain dynamic stiffness (torsion frequency) f in the range of the full angle of rudder reflection of airvaner, expression
Formula is as follows：
In formula, KrIt is the equivalent torsional rigidity to rudderpost axis of air rudder system, is determined by formula (7)；JrIt is rudder system to rudder
The rotary inertia of axle axis, is determined by formula (8).
Kr=Kla·ilo 2 (7)
In formula, iloIt is steering wheel operating bar elongation speed VrWith rudder face rotational angular velocity ωdThe ratio between, its value can be by formula
ilo=Lysin θ are obtained, and wherein Ly is transmission mechanism rocking arm length；θ is the folder of transmission mechanism rocking arm and steering wheel start rod axis
Angle.
In formula, JdIt is rudder face to the rotary inertia of rudderpost axis；JaIt is the rotary inertia of rudderpost；JyIt is rocking arm to rudderpost axle
The rotary inertia of line；msIt is the quality of steering wheel operating bar feed screw nut (non-rotating part)；JkIt is steering wheel housing and steering wheel bearing pair
The rotary inertia of steering wheel bearing bearing pin axis (shown in Fig. 2, crossing the vertical paper of A points)；LABIt is steering engine actuator along axial length (2
It is individual install pin-and-hole distance), 2 wire lengths of A, B as shown in Figure 2, the length with steering wheel telescopic variation, its value is by formula (9)
It is determined that.
Wherein, β is the angle of rocking arm and rudderpost axis centre point and steering wheel bearing pin shaft hole line；Ld is in rudderpost axis
The length of heart point and steering wheel bearing pin shaft hole line.
Step (3), the stress by requiring position in airvane transmission mechanism bearing capacity test acquisition air rudder system
And strain value, the test in below step (3), step (4) and step (5) is carried out by airvane experimental rig, such as Fig. 3 institutes
Show, specific method is as follows：
(3.1) foil gauge and strain rosette, the steering wheel 8 of air rudder system, are installed in airvane system parts requirement position
Position-force control, makes rudderpost 5 turn under different angle of rudder reflection, angle of rudder reflection is tested by angle measurement component 7, by first
It is that rudderpost 5 applies radial load that anti-force applying assembly 401 and second support reaction applies component 402, reads the position that requires
Stress and strain value, is the stress and strain value of static bearing capacity；
(3.2), the position-force control of steering wheel 8 of air rudder system, does frequency sweep and moves with different frequency, anti-by first
It is that rudderpost 5 applies radial load that the support reaction of force applying assembly 401 and second applies component 402, and reading is described to require answering for position
Power and strain value, are the stress and strain value of dynamic carrying capacity.
Requirement position in the present invention in step (3) can be parts strength weak danger position, weak danger position
Can preset or obtain by the following method：
The way of restraint of each hinged place of airvane transmission mechanism is defined, and rotation relation is set, typically constrained with multinode
Mode (MPC) definition connection, and with discharge the free degree mode simulation mechanism rotation relation；To full aircraft FEM model
Apply constraint and load, general restriction tail end frame applies aerodynamic load in the heart in the pressure of air rudder face, and solution obtains each zero
The stress of part, strain, deformation result, stress, strain, deformation result and each parts material according to each parts pole in itself
Limit stress attribute and malformation requirement, it is determined that weak danger position,
Step (4), the transmission that transmission mechanism in acquisition air rudder system is tested by airvane transmission mechanism transmission function
Function, specific method is as follows：
The support reaction of component 401 and second is applied by moment of torsion charging assembly 9, the first support reaction respectively and applies component 402 pairs
Airvane rudderpost 5 applies moment of torsion and support reaction, and steering wheel 8 exports the sinusoidal fortune of same amplitude different frequency in transmission mechanism total travel
It is dynamic, the output displacement s of the steering wheel 8 and corner δ of rudderpost 5 is obtained, the s- δ curves that steering wheel displacement changes with rudderpost corner are drawn,
And the fitting of transmission function is carried out according to s- δ curves, obtain the transmission function of transmission mechanism.
Step (5), the airvane rudderpost tested by airvane transmission mechanism frictional behaviour under acquisition different loads are supported
The comprehensive frictional force of bearing friction power and transmission mechanism, specific method is as follows：
(5.1), the steering wheel 8 of air rudder system and rocking arm 11 are disconnected, the uniform rotation of moment of torsion charging assembly 9, to rudder
Axle 5 applies support reaction, and torque T is obtained by torque sensor 10, and rudderpost rotary speed n, root are obtained by angle measurement component 7
The frictional force F of different loads lower rudder shaft support bearing is calculated according to equation belowf：
Tn/9.55=Ff·ν
Wherein：V is the linear velocity in bearing friction face.
(5.2), the uniform motion of steering wheel 8 of air rudder system, torque sensor 10 disconnects with moment of torsion charging assembly 9, to rudder
Axle 5 applies support reaction, and torque T is obtained by torque sensor 10, and the airvane calculated according to equation below under different loads is passed
The comprehensive frictional force M of motivation structuref；
Mf=FLy-T
Wherein：F is steering wheel thrust, LyIt is transmission mechanism rocking arm length.
The present invention is combined acquisition aircraft airvane by airvane Theoretical Analysis of The Performance, simulation analysis and experimental test
Load-carrying properties, Static stiffness and dynamic stiffness, transmission function and and frictional behaviour, be high dynamic and high reliability aircraft airvane and
The design and optimization of its transmission device provide evaluating comprehensively, economic.
The above, optimal specific embodiment only of the invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can be readily occurred in,
Should all be included within the scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (12)
1. a kind of aircraft airvane method of evaluating performance, it is characterised in that comprise the following steps：
Step (1), the equivalent Line stiffness K onto steering wheel start rod axis of acquisition air rudder systemla, expression formula is as follows：
Wherein：KlIt is the equivalent Line stiffness onto steering wheel start rod axis of transmission mechanism；KsFor steering wheel body is equivalent to steering wheel start
Line stiffness on rod axis；KbaseIt is the Line stiffness on airvane system-based stiffnes s equivalent to steering wheel start rod axis；KcontFor
The contact stiffness of between each parts of transmission mechanism and transmission mechanism and steering wheel junction is equivalent on steering wheel start rod axis
Line stiffness；
Step (2), according to Line stiffness KlaObtain the dynamic stiffness f in the range of the full angle of rudder reflection of airvaner, expression formula is as follows：
Wherein：JrIt is air rudder system to the rotary inertia of rudderpost axis, KrIt is the equivalent torsion to rudderpost axis of air rudder system
Rigidity, expression formula is as follows：
Kr=Kla·ilo 2
Wherein：iloIt is steering wheel operating bar elongation speed VrWith rudder face rotational angular velocity ωdThe ratio between；
Step (3), by airvane transmission mechanism bearing capacity test obtain air rudder system in require position stress and should
Variate；
Step (4), the transmission function that transmission mechanism in acquisition air rudder system is tested by airvane transmission mechanism transmission function；
Step (5), the airvane rudderpost spring bearing tested by airvane transmission mechanism frictional behaviour under acquisition different loads
Frictional force and transmission mechanism comprehensive frictional force.
2. a kind of aircraft airvane method of evaluating performance according to claim 1, it is characterised in that：The step (1)
The equivalent Line stiffness K onto steering wheel start rod axis of middle transmission mechanismlObtained by equation below：
In formula, Ly is transmission mechanism rocking arm length；EyIt is transmission mechanism rocking arm elasticity modulus of materials；IeyIt is transmission mechanism rocking arm etc.
Effect the moment of inertia；Lz is steering wheel height of support；γzIt is the steering wheel seat structure plane of symmetry and the angle of steering wheel start rod axis；EZIt is rudder
Machine bearing elastic modelling quantity；IezIt is steering wheel bearing equivalenting inertia torque；θ is the angle of transmission mechanism rocking arm and steering wheel start rod axis；
La is rudderpost effective length；GaIt is rudderpost material modulus of shearing, its value is Ga=Ea/2(1+νa), wherein EaIt is rudderpost elastic properties of materials
Modulus, νaIt is rudderpost material Poisson's ratio；IaIt is rudderpost second polar moment of area.
3. a kind of aircraft airvane method of evaluating performance according to claim 1, it is characterised in that：The step (1)
The equivalent Line stiffness K onto steering wheel start rod axis of middle air rudder system soil rigiditybaseObtained by equation below：
In formula, Lc be bearing spider highly；γcIt is bearing spider symmetrical configuration face and the angle of steering wheel start rod axis；Lz is rudder
Machine height of support；γzIt is the steering wheel seat structure plane of symmetry and the angle of steering wheel start rod axis；Kc_baseIt is the base of bearing spider
Plinth rigidity；Kz_baseIt is the soil rigidity of steering wheel bearing.
4. a kind of aircraft airvane method of evaluating performance according to claim 3, it is characterised in that：The bearing spider
Soil rigidity Kc_baseWith the soil rigidity K of steering wheel bearingz_baseObtain by the following method：
Step (1.1), air rudder system FEM model is set up using finite element software, and set in air rudder system each zero
The cell attribute of part；
Step (1.2), the way of restraint and drive connection that define each junction of airvane transmission mechanism, by airvane transmission mechanism
Bearing spider and steering wheel bearing rigidifying, will the elastic modelling quantity of airvane transmission mechanism bearing bearing and steering wheel support material assign
8~15 times of actual value, apply the unit force of steering wheel thrust direction on airvane transmission mechanism bearing bearing and steering wheel bearing,
Obtain deformation of the bearing at trail force load position, equivalent moment of flexure and torsion angle into the bearing root, moment of flexure and torsion
The ratio of corner is the soil rigidity of bearing, the i.e. moment of flexure of airvane transmission mechanism bearing bearing
Kc_base, the moment of flexure of steering wheel bearing is K with the ratio of torsion anglez_base。
5. a kind of aircraft airvane method of evaluating performance according to claim 4, it is characterised in that：The step
(1.1) cell attribute of each parts is in air rudder system in：Transmission mechanism parts are simulated with solid element, and rudder face is used
Shell unit is simulated, and rudderpost is simulated with beam element, and steering wheel is simulated with spring unit.
6. a kind of aircraft airvane method of evaluating performance according to claim 1, it is characterised in that：The step (1)
The contact stiffness of between middle each parts of transmission mechanism and transmission mechanism and steering wheel junction is equivalent to steering wheel start rod axis
On Line stiffness KcontObtained by equation below：
Wherein, KlgIt is airvane transmission mechanism combination Line stiffness.
7. a kind of aircraft airvane method of evaluating performance according to claim 6, it is characterised in that：The airvane is passed
Dynamic Mechanism Combination Line stiffness KlgObtain by the following method：
Fixed, steering wheel (8) power closed-loop control by the rudderpost (5) of air rudder system, first carries out the gap treatment that disappears, and perseverance is then exported again
Determine thrust, obtain the output displacement of steering wheel (8) operating bar under different power loading situations, obtaining airvane by equation below is driven
Mechanism Combination Line stiffness Klg：
Klg=F/ Δs s
Wherein：F is steering wheel thrust, and Δ s is steering wheel operating bar output displacement.
8. a kind of aircraft airvane method of evaluating performance according to claim 7, it is characterised in that：The airvane is passed
Dynamic Mechanism Combination Line stiffness KlgObtained by airvane experimental rig, the airvane experimental rig includes pedestal (1), adjustable rudder
Machine bearing (2), the first transmission mechanism bearing support erection support (301), the second transmission mechanism bearing support erection support
(302), the first support reaction applies component (401), the second support reaction and applies component (402), rudder face inertia simulation disk (6), angle
Measurement assembly (7), moment of torsion charging assembly (9) and torque sensor (10), wherein adjustable steering wheel bearing (2) is installed in pedestal (1)
On, steering wheel (8) rear end of air rudder system is arranged on adjustable steering wheel bearing (2), and steering wheel (8) front end is shaken with air rudder system
Arm (11) is hinged, and rocking arm (11) is fixedly connected with the rudderpost (5) of air rudder system；First transmission mechanism bearing support erection support
(301) with the second transmission mechanism bearing support erection support (302) on pedestal (1), for installing fixed airvane system
The bearing spider and bearing of system, the rudderpost (5) of air rudder system apply component through the bearing with the first support reaction
(401) apply component (402) and contact with the second support reaction, first support reaction applies component (401) and the second support reaction is applied
Plus component (402) is on pedestal (1), and positioned at the first transmission mechanism bearing support erection support (301) and the second transmission
Between mechanism's bearing support erection support (302), radial load is applied for the rudderpost (5) for air rudder system；The rudder face
Inertia simulation disk (6) is described for the rotary inertia of simulated air rudder rudder face installed in rudderpost (5) one end of air rudder system
Angle measure component (7) is fixedly mounted on pedestal (1)；The moment of torsion charging assembly (9) is fixedly mounted on pedestal (1), with
One end connection of torque sensor (10), the other end of the torque sensor (10) is connected with rudderpost (5).
9. a kind of aircraft airvane method of evaluating performance according to claim 1, it is characterised in that：The step (3),
Test in step (4) and step (5) is carried out by airvane experimental rig, and the airvane experimental rig includes pedestal
(1), adjustable steering wheel bearing (2), the first transmission mechanism bearing support erection support (301), the second transmission mechanism bearing support peace
Dress bearing (302), the first support reaction apply component (401), the second support reaction and apply component (402), rudder face inertia simulation disk
(6), angle measure component (7), moment of torsion charging assembly (9) and torque sensor (10), wherein adjustable steering wheel bearing (2) is arranged on
On pedestal (1), steering wheel (8) rear end of air rudder system is arranged on adjustable steering wheel bearing (2), steering wheel (8) front end and airvane
The rocking arm (11) of system is hinged, and rocking arm (11) is fixedly connected with air rudder system rudderpost (5)；First transmission mechanism bearing support is pacified
Dress bearing (301) on pedestal (1), sky is fixed for installing with the second transmission mechanism bearing support erection support (302)
Gas rudder system middle (center) bearing bearing and bearing, the rudderpost (5) of air rudder system through the bearing, and with the first support reaction applying group
Part (401) and the second support reaction apply component (402) contact, and first support reaction applies component (401) and the second support reaction
Apply component (402) on pedestal (1), and passed with second positioned at the first transmission mechanism bearing support erection support (301)
Between motivation structure bearing support erection support (302), radial load is applied for the rudderpost (5) for air rudder system；The rudder
Face inertia simulation disk (6) installed in one end of air rudder system rudderpost, for the rotary inertia of simulated air rudder rudder face, the angle
Degree measurement assembly (7) is fixedly mounted on pedestal (1)；The moment of torsion charging assembly (9) is fixedly mounted on pedestal (1), with torsion
One end connection of square sensor (10), the other end of the torque sensor (10) is connected with rudderpost (5).
10. a kind of aircraft airvane method of evaluating performance according to claim 9, it is characterised in that：The step (3)
In by airvane transmission mechanism bearing capacity test obtain air rudder system in require position stress and strain value it is specific
Method is：
(3.1) foil gauge or strain rosette, steering wheel (8) position of air rudder system, are installed in airvane system parts requirement position
Closed-loop control is put, rudderpost (5) is turned under different angle of rudder reflection, angle of rudder reflection is tested by angle measurement component (7), by first
Support reaction applies component (401) and the second support reaction applies component (402) for rudderpost (5) applies radial load, and reading is described will
The stress and strain value of position is sought, is the stress and strain value of static bearing capacity；
(3.2), steering wheel (8) position-force control of air rudder system, does frequency sweep and moves, by the first support reaction with different frequency
Apply component (401) and the second support reaction applies component (402) for rudderpost (5) applies radial load, reading is described to require position
Stress and strain value, be the stress and strain value of dynamic carrying capacity.
A kind of 11. aircraft airvane method of evaluating performance according to claim 9, it is characterised in that：The step (4)
In by airvane transmission mechanism transmission function test obtain air rudder system in transmission mechanism transmission function specific method
For：
Component (401) is applied by moment of torsion charging assembly (9), the first support reaction respectively and the second support reaction applies component (402)
Moment of torsion and support reaction are applied to airvane rudderpost (5), steering wheel (8) exports same amplitude different frequency in transmission mechanism total travel
Sinusoidal motion, obtains the output displacement s of steering wheel (8) and the corner δ of rudderpost (5), draws what steering wheel displacement changed with rudderpost corner
S- δ curves, and the fitting of transmission function is carried out according to s- δ curves, obtain the transmission function of transmission mechanism.
A kind of 12. aircraft airvane method of evaluating performance according to claim 9, it is characterised in that：The step (5)
Airvane rudderpost spring bearing frictional force and the transmission obtained under different loads are tested by airvane transmission mechanism frictional behaviour
The specific method of the comprehensive frictional force of mechanism is as follows：
(5.1), the steering wheel (8) of air rudder system and rocking arm (11) are disconnected, moment of torsion charging assembly (9) uniform rotation is right
Rudderpost (5) applies support reaction, and torque T is obtained by torque sensor (10), and obtaining rudderpost by angle measurement component (7) rotates
Speed n, the frictional force F of airvane rudderpost bearing support under different loads is calculated according to equation belowf：
Tn/9.55=Ff·ν
Wherein：V is the linear velocity in bearing friction face.
(5.2), steering wheel (8) uniform motion of air rudder system, torque sensor (10) disconnects with moment of torsion charging assembly (9), right
Rudderpost (5) applies support reaction, and torque T is obtained by torque sensor (10), and the sky under different loads is calculated according to equation below
The comprehensive frictional force M of gas rudder transmission mechanismf；
Mf=FLy-T
Wherein：F is steering wheel thrust, LyIt is transmission mechanism rocking arm length.
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