CN106564617A - FLAP control plane loading device and function testing method - Google Patents
FLAP control plane loading device and function testing method Download PDFInfo
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- CN106564617A CN106564617A CN201610959775.0A CN201610959775A CN106564617A CN 106564617 A CN106564617 A CN 106564617A CN 201610959775 A CN201610959775 A CN 201610959775A CN 106564617 A CN106564617 A CN 106564617A
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Abstract
The invention discloses a FLAP control plane loading device and a function testing method. According to the device, reset torque of an elastic steel plate can be exerted on a FLAP control plane in a face loading manner through matched connection between the control plane and a joint tool, and therefore the load condition of the true pneumatic hinge torque of a spacecraft is accurately simulated; and by means of the method, the loading torque of the control plane and the swing angle of a rudder spindle can be obtained, the installation rigidity and the friction torque of the loading device are obtained through calculation and analysis, and the data support is provided for design optimization of the structural strength of the FLAP control plane.
Description
Technical field
The present invention relates to a kind of FLAP rudder faces charger and function test method, belong to world shuttle flight field.
Background technology
World shuttle vehicle brings the decline of haulage time cost, missile armament fighting efficiency significantly with high-speed flight
Improve, thus 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 enter, the world come and go, long-distance transport
Change is brought in field.
For the load behavior of at utmost simulated flight device rudder face the sky operating mode, vehicle rudder drive mechanism is verified
The reasonability that index parameter is designed, is shortened the lead time of world shuttle vehicle rudder face drive mechanism, is generally added using simulation
Carry to put and realize ground simulation load test.Loaded using spring steel plate simulation elastic load more than existing charger,
FLAP rudderposts are connected using bonded with steel plate loading main shaft, have larger difference with the actual condition for mainly being carried by rudder face in the sky
It is different.
The content of the invention
The technology solve problem of the present invention：To overcome the deficiencies in the prior art, there is provided a kind of FLAP rudder faces charger 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, the Structural Strength Design optimization for FLAP rudder faces provide data supporting.
The technical solution of the present invention：
A kind of FLAP rudder faces charger, including actuator, rudder, switching tooling, torque sensor, angular displacement sensor,
Spring steel plate and final drive shaft, rudder are made up of rudderpost and rudder face, and rudderpost is connected on final drive shaft, and switching tooling is solid with rudder face
Even, switching tooling is not coaxially connected with final drive shaft, and one end of switching tooling is coaxially connected with one end of torque sensor, moment of torsion
The other end of sensor is coaxially connected with spring steel plate；The other end of switching tooling is coaxially connected with angular displacement sensor,
Actuator acts on final drive shaft, drives rudderpost reciprocating rotation, and then drives 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 coaxial with switching tooling and angle displacement transducer
Device, torque sensor is while elasticity of torsion steel plate, obtains 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 scope 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 faces function test method, concretely comprises the following steps：
(1) drive ram action：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 transmission is made to actuator, meanwhile, actuator is input into electric current I and displacement of the lines L signal to SERVO CONTROL driver in real time, watches
The clothes control driver electric current I that transmits of collection actuator and displacement of the lines L signal, and with SERVO CONTROL driver in reference input
Signal is compared, and determines displacement of the lines deviation and forms drive signal, drive signal is passed to actuator,
Actuator receiving position command signal and drive signal, under servo power power electro ultrafiltration, drive start
Device makees straight reciprocating motion；
Electric current I and displacement of the lines L signal are passed to Ground Test Unit by SERVO CONTROL driver in real time；
(2) obtain the pivot angle of the loading moment and rudderpost of rudder face：Actuator acts on final drive 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 to into switching tooling, and then is passed to and is turned
The coaxial torque sensor of frock and angular displacement sensor are connect, torque sensor is while elasticity of torsion steel plate, obtains spring steel plate
Elastic reset torque, obtain the elastic reset torque of spring steel plate, the as loading moment M of rudder face, and by rudder face loading force
Square M signal transmissions are 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 transmissions are to Ground Test Unit；
(3) using the electric current I's and displacement of the lines L, the loading moment M of rudder face, rudderpost obtained in step (1) and step (2)
Pivot angle δ, carries out stiffness test data processing and moment of friction experimental data processing.
6th, a kind of FLAP rudder faces function test method as claimed in claim 5, it is characterised in that firm in step (3)
Spending Data Processing Method is：
In stiffness test, the M of torque sensor output and the δ of angular displacement sensor output are 0, using step (1)
The electric current I of collection, actuator displacement L, can obtain loading moment M (I) and rudderpost pivot angle θ (L) by numerical computations, by such as
Lower formula can obtain the rigidity of rudder face charger：
C=M (I)/θ (L)
In formula：Rigidity values of the C for rudder face charger, unit：Nm/rad；
M (I) is loading moment, M (I)=k1II units：Nm, wherein k1For the moment coefficient of actuator necessary electromotor, i is
The speed reducing ratio of actuator；
The rudder face corner that θ (L) is converted by actuator displacement L, unit：Rad, θ (L)=k2L, wherein k2It is several with actuator
The related coefficient of what motion triangle；
7th, a kind of FLAP rudder faces function test method as claimed in claim 5, it is characterised in that rubbing in step (3)
Wiping torque test data processing method is：
The pivot angle δ of the M and angular displacement sensor output of output is gathered using step (1) torque sensor, by such as lower section
Method can obtain the moment of friction of rudder face charger：
Pivot angle δ with angular displacement sensor output gathers the M of output as the longitudinal axis with torque sensor, draws out as transverse axis
M- δ winding curves in one sinusoidal cycles, position torque winding curve are maximum friction in y direction projection Breadth Maximum
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 ＇.
The present invention is had the advantages that compared with prior art：
(1) existing charger is generally loaded to FLAP rudderposts, it is impossible to realize the loading to FLAP rudder faces, it is impossible to
Obtain the data related to rudder face carrying；Apparatus of the present invention are connected by rudder face and switching tooling, can be by Elastic Steel
The reseting torque of plate puts on FLAP rudder faces in the form of the loading of face, accurately to simulate the true Aerodynamic binge moment of spacecraft
Load behavior；
(2) by the inventive method, it is possible to obtain the pivot angle of the loading moment and rudderpost of rudder face, and by calculating, analyzing
The installation rigidity and moment of friction of charger are obtained, the Structural Strength Design optimization for FLAP rudder faces provides data supporting.
Description of the drawings
Fig. 1 is schematic structural view of the invention；
Fig. 2 is the inventive method flow chart.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
The present invention relates to a kind of FLAP rudder faces charger and function test method, its application and world shuttle vehicle rudder
In the drive mechanism function test of face, by FLAP rudder faces frock and spring steel plate charger by the elastic reset power of spring steel plate
Square is loaded onto whole FLAP rudder faces, simulates the hinge moment of world shuttle vehicle rudder face, 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 examine
Test the correctness of kinesiology, dynamical simulation results, and measure the output of charger pivot angle, actuator stroke, actuator electric current,
The parameters such as steel plate moment of torsion, calculate the performance indications such as rudder face angular velocity, actuator linear velocity and mechanism's rigidity.
Concrete structure is as shown in figure 1, a kind of FLAP rudder faces charger, including actuator 3, rudder, switching tooling 2, moment of torsion
Sensor 8, angular displacement sensor 6, spring steel plate 7 and final drive shaft 9, rudder are made up of rudderpost 4 and rudder face 5, and rudderpost 4 is connected to master
On power transmission shaft 9, switching tooling 2 is connected with rudder face 5, and switching tooling 2 is not coaxially connected with final drive shaft 9, one end of switching tooling 2
Coaxially connected with one end of torque sensor 8, the other end of torque sensor 8 is coaxially connected with spring steel plate 7；Switching tooling 2
The other end it is coaxially connected with angular displacement sensor 6,
Actuator 3 acts on final drive shaft 9, drives 4 reciprocating rotation of rudderpost, and then drives 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 is passed to
The torque sensor 8 coaxial with switching tooling 2 and angular displacement sensor 6, torque sensor 8 is while elasticity of torsion steel plate 7, obtains
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 scope 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, its thrust is converted into recommending on FLAP rudderposts by rocking arm by actuator 3
Torque, this is recommended torque and passes to FLAP rudder faces and switching tooling 2 by keyway, and switching tooling is recommending moment loading lower swing
FLAP rudder faces, FLAP rudder face swing process overcome the moment of elasticity of spring steel plate to do work, and charger final drive shaft is provided with torsion
Square speed probe and angular displacement sensor, to gather the loading moment of torsion on final drive shaft and pivot angle amplitude.Conventional aircraft
Rudder face drive mechanism function test charger causes spring steel plate loading to concentrate on FLAP frequently with direct-push point loading scheme
On rudderpost, it is impossible to the true hinge moment situation of simulated flight device rudder face the sky operating mode.
A kind of FLAP rudder faces function test method, concretely comprises the following steps：
(1) drive ram action：Ground Test Unit 1 sends pivot angle command signal to SERVO CONTROL driver 10, servo
Control driver 10 receives pivot angle command signal, and pivot angle command signal is resolved the position command signal for actuator 3, and will
Position command signal passes to actuator 3, meanwhile, actuator 3 is input into electric current I and displacement of the lines L signal to SERVO CONTROL in real time
Driver 2, the electric current I that transmits of collection actuator 4 of SERVO CONTROL driver 2 and displacement of the lines L signal, and with SERVO CONTROL driver
Reference-input signal in 2 is compared, and determines displacement of the lines deviation and forms drive signal, drive signal is passed to actuator
3,
3 receiving position command signal of actuator and drive signal, under 11 power electro ultrafiltration of servo power power supply, drive and make
Dynamic device 3 makees straight reciprocating motion；
Electric current I and displacement of the lines L signal are passed to Ground Test Unit 1 by SERVO CONTROL driver 2 in real time；
(2) obtain the pivot angle of the loading moment and rudderpost of rudder face：Actuator 3 acts on final drive shaft 9, drives rudderpost 4 past
It is multiple to rotate, and then 5 reciprocally swinging of rudder face is driven, the loading moment of 5 reciprocally swinging of rudder face is passed to into switching tooling 2, Jin Erchuan
Pass the torque sensor 8 coaxial with switching tooling 2 and angular displacement sensor 6, the elasticity of torsion steel plate 7 simultaneously of torque sensor 8,
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 by rudder face loading moment M signal transmissions to 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 by pivot angle δ signal transmissions to Ground Test Unit 1；
(3) using the electric current I's and displacement of the lines L, the loading moment M of rudder face, rudderpost obtained in step (1) and step (2)
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) is：
In stiffness test, the δ that the M and angular displacement sensor (6) that torque sensor (8) is exported is exported is 0, using step
Suddenly (1) gathers electric current I, actuator displacement L, can obtain loading moment M (I) and rudderpost pivot angle θ (L) by numerical computations,
The rigidity of rudder face charger can be obtained by equation below：
C=M (I)/θ (L)
In formula：Rigidity values of the C for rudder face charger, unit：Nm/rad；
M (I) is loading moment, M (I)=k1II units：Nm, wherein k1For the moment coefficient of actuator necessary electromotor, i is
The speed reducing ratio of actuator；
The rudder face corner that θ (L) is converted by actuator displacement L, unit：Rad, θ (L)=k2L, wherein k2It is several with actuator
The related coefficient of what motion triangle；
Moment of friction Data Processing Method in step (3) is：
The pivot angle δ of the M and angular displacement sensor output of output is gathered using step (1) torque sensor, by such as lower section
Method can obtain the moment of friction of rudder face charger：
Pivot angle δ with angular displacement sensor output gathers the M of output as the longitudinal axis with torque sensor, draws out as transverse axis
M- δ winding curves in one sinusoidal cycles, position torque winding curve are maximum friction in y direction projection Breadth Maximum
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 ＇.
As shown in Figure 2,
This bracket loading test platform adopts steel plate load mode, FLAP rudder faces switching tooling and FLAP rudder faces to install matching somebody with somebody for crossbeam
Close layout to use, moment gradients demarcation is carried out to loading steel plate using technique actuator, FLAP rudder faces are largely simulated
The actual effect of rigidity and hinge moment face loading in the sky is truly installed, the design improvement for vehicle rudder drive mechanism is provided
Effectively refer to.
The present invention completes vehicle rudder drive mechanism function test for coordinating, including moment of friction determination test, just
Degree determination test, rudder face corner and actuator stroke Transmission Function determination test, load test and exercise performance and accuracy testing.
By the ground load test to vehicle rudder, at utmost the load behavior of simulated flight device rudder face the sky operating mode, verifies
The reasonability of the index parameter design of vehicle rudder drive mechanism, greatly shortens world shuttle vehicle rudder face drive mechanism
Lead time.
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 (7)
1. a kind of FLAP rudder faces charger, it is characterised in that including actuator (3), rudder, switching tooling (2), torque sensor
(8), angular displacement sensor (6), spring steel plate (7) and final drive shaft (9), rudder are made up of rudderpost (4) and rudder face (5), rudderpost (4)
It is connected on final drive shaft (9), switching tooling (2) is connected with rudder face (5), and switching tooling (2) is not coaxially connected with final drive shaft (9)
Connect, one end of switching tooling (2) is coaxially connected with one end of torque sensor (8), the other end and the elasticity of torque sensor (8)
Steel plate (7) is coaxially connected；The other end of switching tooling (2) is coaxially connected with angular displacement sensor (6),
Actuator (3) acts on final drive shaft (9), drives rudderpost (4) reciprocating rotation, and then drives 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 moment of torsion coaxial with switching tooling (2)
Sensor (8) and angular displacement sensor (6), torque sensor (8) is while elasticity of torsion steel plate (7), obtains 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 faces charger as claimed in claim 1, it is characterised in that the loading moment of spring steel plate (7)
Scope is 0～1200Nm.
3. a kind of FLAP rudder faces charger as claimed in claim 2, it is characterised in that the gradient scope of torque is 0～
48Nm/°。
4. a kind of FLAP rudder faces charger as claimed in claim 1, it is characterised in that the angle of rudder face (5) reciprocally swinging
For -25 °～25 °.
5. a kind of FLAP rudder faces function test method, equipment therefor are claim 1 described device, it is characterised in that concrete to walk
Suddenly it is：
(1) drive ram action：Ground Test Unit (1) sends pivot angle command signal and gives SERVO CONTROL driver (10), servo
Control driver (10) receives pivot angle command signal, and pivot angle command signal is resolved the position command signal for actuator (3),
And position command signal is passed to into actuator (3), meanwhile, actuator (3) in real time by electric current I and displacement of the lines L signal be input into
SERVO CONTROL driver (2), electric current I and displacement of the lines L signal that SERVO CONTROL driver (2) collection actuator (4) is transmitted, and with
Reference-input signal in SERVO CONTROL driver (2) is compared, and determines displacement of the lines deviation and forms drive signal, will drive
Signal transmission gives actuator (3),
Actuator (3) receiving position command signal and drive signal, under servo power power supply (11) power electro ultrafiltration, drive and make
Dynamic device (3) makees straight reciprocating motion；
Electric current I and displacement of the lines L signal are passed to Ground Test Unit (1) by SERVO CONTROL driver (2) in real time；
(2) obtain the pivot angle of the loading moment and rudderpost of rudder face：Actuator (3) acts on final drive 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 to into switching tooling
(2), and then the torque sensor (8) coaxial with switching tooling (2) and angular displacement sensor (6), torque sensor (8) are passed to
Elasticity of torsion steel plate (7), obtains the elastic reset torque of spring steel plate (7) simultaneously, obtains the elastic reset power of spring steel plate (7)
The loading moment M of square, as rudder face, and Ground Test Unit (1) is given by rudder face loading moment M signal transmissions；Angular displacement sensor
(6) pivot angle of switching tooling (2), as the pivot angle δ of rudderpost (4) are obtained, and Ground Test Unit (1) are given by pivot angle δ signal transmissions；
(3) using the pivot angle of the electric current I and displacement of the lines L, the loading moment M of rudder face, rudderpost obtained in step (1) and step (2)
δ, carries out stiffness test data processing and moment of friction experimental data processing.
6. a kind of FLAP rudder faces function test method as claimed in claim 5, it is characterised in that the rigidity examination in step (3)
Testing data processing method is：
In stiffness test, the δ that the M and angular displacement sensor (6) that torque sensor (8) is exported is exported is 0, using step
(1) electric current I, the actuator displacement L for gathering, can obtain loading moment M (I) and rudderpost pivot angle θ (L) by numerical computations, lead to
Cross the rigidity that equation below can obtain rudder face charger：
C=M (I)/θ (L)
In formula：Rigidity values of the C for rudder face charger, unit：Nm/rad；
M (I) is loading moment, M (I)=k1II units：Nm, wherein k1For the moment coefficient of actuator necessary electromotor, i is start
The speed reducing ratio of device；
The rudder face corner that θ (L) is converted by actuator displacement L, unit：Rad, θ (L)=k2L, wherein k2It is to transport with actuator geometry
The related coefficient of dynamic triangle.
7. a kind of FLAP rudder faces function test method as claimed in claim 5, it is characterised in that the frictional force in step (3)
Square Data Processing Method is：
The pivot angle δ of the M and angular displacement sensor output of output is gathered using step (1) torque sensor, by the following method may be used
Obtain the moment of friction of rudder face charger：
Pivot angle δ with angular displacement sensor output gathers the M of output as the longitudinal axis with torque sensor, draws out one as transverse axis
M- δ winding curves in sinusoidal cycles, position torque winding curve are maximum friction torque in y direction projection Breadth Maximum
Value MmHalf；When pivot angle δ is zero, winding curve is zero-bit along the projection width of y direction to position torque winding curve
Moment of friction MmThe half of ＇.
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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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| CN109724815A (en) * | 2017-10-31 | 2019-05-07 | 北京精密机电控制设备研究所 | A kind of quasi- loading system of the crank based on rope drive-anti-operating torque of pressure spring type |
| 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 |
| CN110160732A (en) * | 2018-08-09 | 2019-08-23 | 北京机电工程研究所 | Adjustable frictional force device and adjustable frictional force method for flutter test |
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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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