CN106564617B - A kind of FLAP rudder face loading device and function test method - Google Patents
A kind of FLAP rudder face loading device and function test method Download PDFInfo
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Abstract
The invention discloses a kind of FLAP rudder face loading device and function test methods, apparatus of the present invention pass through the mating connection of rudder face and switching tooling, the reseting torque of spring steel plate can be applied to FLAP rudder face in the form that face loads, accurately to simulate the load behavior of the true Aerodynamic binge moment of spacecraft；By the method for the invention, the loading moment of rudder face and the pivot angle of rudderpost, and installation rigidity and moment of friction by calculating, analyzing acquisition loading device can be obtained, provides data supporting for the Structural Strength Design optimization of FLAP rudder face.
Description
Technical field
The present invention relates to a kind of FLAP rudder face loading device and function test methods, belong to world shuttle flight field.
Background technique
World shuttle vehicle brings the decline of haulage time cost, missile armament fighting efficiency with high-speed flight substantially
It improves, thus has obtained countries in the world great attention, it is especially prominent in terms of Military Application, it has also become current aerospace field
Cutting edge technology.The expansion application of world shuttle vehicle technology, it is also possible to space enters, the world is round-trip, long-distance transport
Bring change in equal fields.
For the load behavior of utmostly simulated flight device rudder face the sky operating condition, verifying vehicle rudder transmission mechanism
The reasonability of index parameter design, shortens the lead time of world shuttle vehicle rudder face transmission mechanism, generallys use simulation and adds
It carries to set and realizes ground simulation load test.Existing loading device mostly uses spring steel plate simulation elastic load to be loaded,
FLAP rudderpost and steel plate load main shaft are connected using key connection, mainly have larger difference by the actual condition that rudder face carries in the sky
It is different.
Summary of the invention
Technology of the invention solves the problems, such as: in order to overcome the deficiencies of the prior art, provide a kind of FLAP rudder face loading device and
Function test method, to simulate the load behavior of the true Aerodynamic binge moment of spacecraft, obtain rudder face loading moment and
The pivot angle of rudderpost provides data supporting for the Structural Strength Design optimization of FLAP rudder face.
Technical solution of the invention:
A kind of FLAP rudder face loading device, including actuator, rudder, switching tooling, torque sensor, angular displacement sensor,
Spring steel plate and main shaft, rudder are made of rudderpost and rudder face, and rudderpost is connected on main shaft, and switching tooling and rudder face are solid
Even, switching tooling is not coaxially connected with main shaft, and one end of switching tooling and one end of torque sensor are coaxially connected, torque
The other end of sensor and spring steel plate are coaxially connected；The other end of switching tooling and angular displacement sensor are coaxially connected,
Actuator acts on main shaft, drives rudderpost reciprocating rotation, and then drive rudder face reciprocally swinging, and rudder face is reciprocal
The loading moment of swing passes to switching tooling, and then passes to the torque sensor and angle displacement transducer coaxial with switching tooling
Device, torque sensor while elasticity of torsion steel plate, obtain the elastic reset torque of spring steel plate, the as loading moment of rudder face；
Angular displacement sensor obtains the pivot angle of switching tooling, the as pivot angle of rudderpost.
The loading moment range of spring steel plate is 0~1200Nm.
The gradient scope of torque is 0~48Nm/ °.
The angle of rudder face reciprocally swinging is -25 °~25 °.
A kind of FLAP rudder face function test method, specific steps are as follows:
(1) drive ram acts: Ground Test Unit sends pivot angle command signal and gives SERVO CONTROL driver, SERVO CONTROL
Driver receives pivot angle command signal, and pivot angle command signal is resolved the position command signal for actuator, and position is referred to
Signal is enabled to pass to actuator, meanwhile, electric current I and displacement of the lines L signal are input to SERVO CONTROL driver in real time by actuator, are watched
The clothes control driver electric current I that transmits of acquisition actuator and displacement of the lines L signal, and with the reference input in SERVO CONTROL driver
Signal is compared, and determines displacement of the lines deviation and forms driving signal, driving signal is passed to actuator,
Actuator receives position command signal and driving signal, under servo power power electro ultrafiltration, drives actuation
Device makees straight reciprocating motion；
SERVO CONTROL driver is by electric current I and displacement of the lines L signal real-time delivery to Ground Test Unit；
(2) obtain the loading moment of rudder face and the pivot angle of rudderpost: actuator acts on main shaft, drives rudderpost reciprocating rotary
It is dynamic, and then rudder face reciprocally swinging is driven, the loading moment of rudder face reciprocally swinging is passed into switching tooling, and then pass to and turn
Tooling coaxial torque sensor and angular displacement sensor, torque sensor while elasticity of torsion steel plate are connect, spring steel plate is obtained
Elastic reset torque, obtain the elastic reset torque of spring steel plate, as the loading moment M of rudder face, and by rudder face loading force
Square M signal passes to Ground Test Unit；Angular displacement sensor obtains the pivot angle of switching tooling, as the pivot angle δ of rudderpost, and will put
Angle δ signal passes to Ground Test Unit；
(3) the electric current I and displacement of the lines L, the loading moment M of rudder face, rudderpost of acquisition in step (1) and step (2) are utilized
Pivot angle δ carries out stiffness test data processing and moment of friction experimental data processing.
Stiffness test data processing method in step (3) are as follows:
In stiffness test, the M of torque sensor output and the δ of angular displacement sensor output are 0, are utilized step (1)
Electric current I, the displacement of the lines L of acquisition calculate available loading moment M (I) and rudderpost pivot angle θ (L) by numerical value, by following public
Formula can obtain the rigidity of rudder face loading device:
C=M (I)/θ (L)
In formula: C is the rigidity value of rudder face loading device, unit: Nm/rad；
M (I) is loading moment, M (I)=k1II unit: Nm, wherein k1For the torque coefficient of actuator necessary electromotor, i is
The reduction ratio of actuator；
The rudder face corner that θ (L) is converted by displacement of the lines L, unit: rad, θ (L)=k2L, wherein k2To be transported with actuator geometry
The dynamic relevant coefficient of triangle；
Moment of friction Data Processing Method in step (3) are as follows:
Using the M of step (1) the torque sensor acquisition output and pivot angle δ of angular displacement sensor output, pass through such as lower section
Method can obtain the moment of friction of rudder face loading device:
Using the pivot angle δ of angular displacement sensor output as horizontal axis, using the M of torque sensor acquisition output as the longitudinal axis, draw out
Position torque winding curve in one sinusoidal cycles, position torque winding curve are maximum in y direction projection maximum width
Moment of friction value MmHalf；Position torque winding curve is when pivot angle δ is zero, projection width of the winding curve along y direction
As zero-bit moment of friction MmThe half of '.
Compared with prior art, the present invention has the following advantages:
(1) existing loading device usually loads FLAP rudderpost, cannot achieve the load to FLAP rudder face, can not
Obtain data relevant to rudder face carrying；Apparatus of the present invention pass through the mating connection of rudder face and switching tooling, can be by Elastic Steel
The reseting torque of plate is applied to FLAP rudder face in the form that face loads, accurately to simulate the true Aerodynamic binge moment of spacecraft
Load behavior；
(2) by the method for the invention, the loading moment of rudder face and the pivot angle of rudderpost can be obtained, and by calculating, analyzing
The installation rigidity and moment of friction of loading device are obtained, provides data supporting for the Structural Strength Design optimization of FLAP rudder face.
Detailed description of the invention
Fig. 1 is schematic structural view of the invention；
Fig. 2 is the method for the present invention flow chart.
Specific embodiment
The present invention is described in further detail with reference to the accompanying drawing.
The present invention relates to a kind of FLAP rudder face loading device and function test method, application and world shuttle vehicle rudder
In the transmission mechanism function test of face, by FLAP rudder face tooling and spring steel plate loading device by the elastic reset power of spring steel plate
Square is loaded onto entire FLAP rudder face, the hinge moment of world shuttle vehicle rudder face is simulated, to verify vehicle rudder driver
Whether the design parameters such as structure intensity, rigidity, moment of friction meet performance requirement, and whether processing quality meets design requirement；And it examines
Test kinematics, the correctness of dynamical simulation results, and measure the output of loading device pivot angle, actuator stroke, actuator electric current,
The parameters such as steel plate torque calculate the performance indicators such as rudder face angular speed, actuator linear velocity and mechanism rigidity.
Specific structure is as shown in Figure 1, a kind of FLAP rudder face loading device, including actuator 3, rudder, switching tooling 2, torque
Sensor 8, angular displacement sensor 6, spring steel plate 7 and main shaft 9, rudder are made of rudderpost 4 and rudder face 5, and rudderpost 4 is connected to master
On transmission shaft 9, switching tooling 2 and rudder face 5 are connected, and switching tooling 2 is not coaxially connected with main shaft 9, one end of switching tooling 2
Coaxially connected with one end of torque sensor 8, the other end and spring steel plate 7 of torque sensor 8 are coaxially connected；Switching tooling 2
The other end and angular displacement sensor 6 it is coaxially connected,
Actuator 3 acts on main shaft 9, drives 4 reciprocating rotation of rudderpost, and then drive 5 reciprocally swinging of rudder face, rudder face 5
The angle of reciprocally swinging is -25 °~25 °, the loading moment of 5 reciprocally swinging of rudder face is passed to switching tooling 2, and then pass to
The torque sensor 8 and angular displacement sensor 6 coaxial with switching tooling 2, torque sensor 8 while elasticity of torsion steel plate 7 obtain
The elastic reset torque of spring steel plate 7, the as loading moment of rudder face 5；Angular displacement sensor 6 obtains the pivot angle of switching tooling 2,
The as pivot angle of rudderpost 4.
The loading moment range of spring steel plate 7 is 0~1200Nm, and the gradient scope of torque is 0~48Nm/ °.
By above-mentioned using shaft type mechanism is turned round, actuator 3 converts recommending on FLAP rudderpost for its thrust by rocker arm
Torque, this is recommended torque and passes to FLAP rudder face and switching tooling 2 by keyway, and switching tooling is recommending moment loading lower swing
FLAP rudder face, FLAP rudder face swing process overcome the moment of elasticity of spring steel plate to do work, and loading device main shaft, which is equipped with, to be turned round
Square speed probe and angular displacement sensor, to acquire load torque and pivot angle amplitude on main shaft.Previous aircraft
Rudder face transmission mechanism function test loading device causes spring steel plate load to concentrate on FLAP frequently with direct-push point loading scheme
On rudderpost, it is unable to the true hinge moment situation of simulated flight device rudder face the sky operating condition.
A kind of FLAP rudder face function test method, specific steps are as follows:
(1) drive ram acts: Ground Test Unit 1 sends pivot angle command signal to SERVO CONTROL driver 10, servo
It controls driver 10 and receives pivot angle command signal, and pivot angle command signal is resolved as the position command signal of actuator 3, and general
Position command signal passes to actuator 3, meanwhile, electric current I and displacement of the lines L signal are input to SERVO CONTROL in real time by actuator 3
Driver 10, SERVO CONTROL driver 10 acquires the electric current I and displacement of the lines L signal that actuator 3 transmits, and drives with SERVO CONTROL
Reference-input signal in device 10 is compared, and determines displacement of the lines deviation and forms driving signal, and driving signal is passed to work
Dynamic device 3,
Actuator 3 receives position command signal and driving signal, and under 11 power electro ultrafiltration of servo power power supply, driving is made
Dynamic device 3 makees straight reciprocating motion；
SERVO CONTROL driver 10 is by electric current I and displacement of the lines L signal real-time delivery to Ground Test Unit 1；
(2) obtain the loading moment of rudder face and the pivot angle of rudderpost: actuator 3 acts on main shaft 9, drives rudderpost 4 past
Multiple rotation, and then 5 reciprocally swinging of rudder face is driven, the loading moment of 5 reciprocally swinging of rudder face is passed into switching tooling 2, Jin Erchuan
The torque sensor 8 and angular displacement sensor 6 coaxial with switching tooling 2, torque sensor 8 while elasticity of torsion steel plate 7 are passed,
The elastic reset torque of acquisition spring steel plate 7, the elastic reset torque of acquisition spring steel plate 7, the as loading moment M of rudder face,
And rudder face loading moment M signal is passed into Ground Test Unit 1；Angular displacement sensor 6 obtains the pivot angle of switching tooling 2, as
The pivot angle δ of rudderpost 4, and pivot angle δ signal is passed into Ground Test Unit 1；
(3) the electric current I and displacement of the lines L, the loading moment M of rudder face, rudderpost of acquisition in step (1) and step (2) are utilized
Pivot angle δ carries out stiffness test data processing and moment of friction experimental data processing.
Wherein, the stiffness test data processing method in step (3) are as follows:
In stiffness test, the M of torque sensor (8) output and the δ of angular displacement sensor (6) output are 0, utilize step
Suddenly the electric current I, displacement of the lines L of (1) acquisition, calculates available loading moment M (I) and rudderpost pivot angle θ (L) by numerical value, passes through
Following formula can obtain the rigidity of rudder face loading device:
C=M (I)/θ (L)
In formula: C is the rigidity value of rudder face loading device, unit: Nm/rad；
M (I) is loading moment, M (I)=k1II unit: Nm, wherein k1For the torque coefficient of actuator necessary electromotor, i is
The reduction ratio of actuator；
The rudder face corner that θ (L) is converted by displacement of the lines L, unit: rad, θ (L)=k2L, wherein k2To be transported with actuator geometry
The dynamic relevant coefficient of triangle；
Moment of friction Data Processing Method in step (3) are as follows:
Using the M of step (1) the torque sensor acquisition output and pivot angle δ of angular displacement sensor output, pass through such as lower section
Method can obtain the moment of friction of rudder face loading device:
Using the pivot angle δ of angular displacement sensor output as horizontal axis, using the M of torque sensor acquisition output as the longitudinal axis, draw out
Position torque winding curve in one sinusoidal cycles, position torque winding curve are maximum in y direction projection maximum width
Moment of friction value MmHalf；Position torque winding curve is when pivot angle δ is zero, projection width of the winding curve along y direction
As zero-bit moment of friction MmThe half of '.
As shown in Fig. 2,
This bracket loading test platform uses steel plate loading method, and FLAP rudder face switching tooling and FLAP rudder face install matching for crossbeam
It closes layout to use, moment gradients calibration is carried out to load steel plate using technique actuator, largely simulates FLAP rudder face
The actual effect of true installation rigidity and hinge moment face load in the sky provides for the design improvement of vehicle rudder transmission mechanism
Effectively reference.
The present invention completes vehicle rudder transmission mechanism function test for cooperating, including moment of friction measurement is tested, just
Degree measurement test, rudder face corner and actuator stroke Transmission Function measurement test, load test and movenent performance and accuracy testing.
By the ground load test to vehicle rudder, utmostly the load behavior of simulated flight device rudder face the sky operating condition, is verified
The reasonability of the index parameter design of vehicle rudder transmission mechanism, greatly shortens world shuttle vehicle rudder face transmission mechanism
Lead time.
The content that description in the present invention is not described in detail belongs to the well-known technique of professional and technical personnel in the field.
Claims (7)
1. a kind of FLAP rudder face loading device, which is characterized in that including actuator (3), rudder, switching tooling (2), torque sensor
(8), angular displacement sensor (6), spring steel plate (7) and main shaft (9), rudder are made of rudderpost (4) and rudder face (5), rudderpost (4)
It is connected on main shaft (9), switching tooling (2) and rudder face (5) are connected, and switching tooling (2) does not connect coaxially with main shaft (9)
It connects, one end of switching tooling (2) and one end of torque sensor (8) are coaxially connected, the other end and elasticity of torque sensor (8)
Steel plate (7) is coaxially connected；The other end of switching tooling (2) and angular displacement sensor (6) are coaxially connected,
Actuator (3) acts on main shaft (9), drives rudderpost (4) reciprocating rotation, and then drive rudder face (5) reciprocally swinging, will
The loading moment of rudder face (5) reciprocally swinging passes to switching tooling (2), and then passes to the torque coaxial with switching tooling (2)
Sensor (8) and angular displacement sensor (6), torque sensor (8) while elasticity of torsion steel plate (7) obtain spring steel plate (7)
The loading moment of elastic reset torque, as rudder face (5)；Angular displacement sensor (6) obtains the pivot angle of switching tooling (2), as
The pivot angle of rudderpost (4).
2. a kind of FLAP rudder face loading device as described in claim 1, which is characterized in that the loading moment of spring steel plate (7)
Range is 0~1200Nm.
3. a kind of FLAP rudder face loading device as claimed in claim 2, which is characterized in that the gradient scope of torque is 0~
48Nm/°。
4. a kind of FLAP rudder face loading device as described in claim 1, which is characterized in that the angle of rudder face (5) reciprocally swinging
It is -25 °~25 °.
5. a kind of FLAP rudder face function test method, equipment therefor is claim 1 described device, which is characterized in that specific step
Suddenly are as follows:
(1) drive ram acts: Ground Test Unit (1) sends pivot angle command signal and gives SERVO CONTROL driver (10), servo
It controls driver (10) and receives pivot angle command signal, and pivot angle command signal is resolved as the position command signal of actuator (3),
And pass to position command signal actuator (3), meanwhile, electric current I and displacement of the lines L signal are input to by actuator (3) in real time
SERVO CONTROL driver (10), the electric current I and displacement of the lines L signal that SERVO CONTROL driver (10) acquisition actuator (3) is transmitted, and
It is compared with the reference-input signal in SERVO CONTROL driver (10), determines displacement of the lines deviation and forms driving signal, it will
Driving signal passes to actuator (3),
Actuator (3) receives position command signal and driving signal, and under servo power power supply (11) power electro ultrafiltration, driving is made
Dynamic device (3) make straight reciprocating motion；
SERVO CONTROL driver (10) gives electric current I and displacement of the lines L signal real-time delivery to Ground Test Unit (1)；
(2) obtain the loading moment of rudder face and the pivot angle of rudderpost: actuator (3) acts on main shaft (9), drives rudderpost (4)
Reciprocating rotation, and then rudder face (5) reciprocally swinging is driven, the loading moment of rudder face (5) reciprocally swinging is passed into switching tooling
(2), and then the torque sensor (8) and angular displacement sensor (6) coaxial with switching tooling (2), torque sensor (8) are passed to
Elasticity of torsion steel plate (7) simultaneously obtains the elastic reset torque of spring steel plate (7), obtains the elastic reset power of spring steel plate (7)
Square, as the loading moment M of rudder face, and rudder face loading moment M signal is passed into Ground Test Unit (1)；Angular displacement sensor
(6) pivot angle of switching tooling (2), as the pivot angle δ of rudderpost (4) are obtained, and pivot angle δ signal is passed into Ground Test Unit (1)；
(3) pivot angle of the electric current I and displacement of the lines L, the loading moment M of rudder face, rudderpost of acquisition in step (1) and step (2) are utilized
δ carries out stiffness test data processing and moment of friction experimental data processing.
6. a kind of FLAP rudder face function test method as claimed in claim 5, which is characterized in that the rigidity examination in step (3)
Test data processing method are as follows:
In stiffness test, the M of torque sensor (8) output and the δ of angular displacement sensor (6) output are 0, utilize step
(1) electric current I, the displacement of the lines L acquired, calculates available loading moment M (I) and rudderpost pivot angle θ (L) by numerical value, by such as
Lower formula can obtain the rigidity of rudder face loading device:
C=M (I)/θ (L)
In formula: C is the rigidity value of rudder face loading device, unit: Nm/rad；
M (I) is loading moment, M (I)=k1II unit: Nm, wherein k1For the torque coefficient of actuator necessary electromotor, i is actuation
The reduction ratio of device；
The rudder face corner that θ (L) is converted by displacement of the lines L, unit: rad, θ (L)=k2L, wherein k2For with actuator geometry motion three
Angular relevant coefficient.
7. a kind of FLAP rudder face function test method as claimed in claim 5, which is characterized in that the frictional force in step (3)
Square Data Processing Method are as follows:
Using the M of step (1) the torque sensor acquisition output and pivot angle δ of angular displacement sensor output, by the following method may be used
Obtain the moment of friction of rudder face loading device:
Using the pivot angle δ of angular displacement sensor output as horizontal axis, using the M of torque sensor acquisition output as the longitudinal axis, one is drawn out
Position torque winding curve in sinusoidal cycles, position torque winding curve are maximum friction in y direction projection maximum width
Moment values MmHalf；When pivot angle δ is zero, winding curve is position torque winding curve along the projection width of y direction
Zero-bit moment of friction MmThe half of '.
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| CN107621343B (en) * | 2017-09-07 | 2019-11-15 | 北京航空航天大学 | A kind of device for testing dynamic stiffness |
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| CN108248891A (en) * | 2017-12-27 | 2018-07-06 | 彩虹无人机科技有限公司 | A kind of calibration system and scaling method for unmanned plane semiclosed loop rudder face |
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| CN109341917B (en) * | 2018-09-25 | 2021-04-20 | 中国人民解放军海军工程大学 | Rudder force measuring device of rudder wing combined control surface for water tunnel |
| CN111252265A (en) * | 2018-12-03 | 2020-06-09 | 江西洪都航空工业集团有限责任公司 | Control surface clearance test equipment |
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| CN112525528B (en) * | 2020-10-30 | 2022-10-14 | 中国运载火箭技术研究院 | Test method for measuring rigidity of control surface transmission mechanism |
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| CN114394258A (en) * | 2022-01-18 | 2022-04-26 | 湖南航天环宇通信科技股份有限公司 | Mechanical property experiment device and method for aileron driving mechanism |
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| CN2225705Y (en) * | 1995-01-28 | 1996-04-24 | 刘庆和 | Electric liquid load simulator |
| CN1216328C (en) * | 2002-04-12 | 2005-08-24 | 北京航空航天大学 | Speed synchronously controlled electrohydraulic load simulator |
| CN101441477B (en) * | 2007-11-19 | 2011-01-12 | 北京航空航天大学 | Bending combined two-dimension time-varying load loading unit |
| RU2464543C1 (en) * | 2011-06-20 | 2012-10-20 | Открытое акционерное общество "Государственное машиностроительное конструкторское бюро "Вымпел" имени И.И. Торопова" | Test stand for checking opening of rocket rudder |
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