CN117602098A - Follow-up system for fatigue test of aircraft slat and angle tracking control method - Google Patents
Follow-up system for fatigue test of aircraft slat and angle tracking control method Download PDFInfo
- Publication number
- CN117602098A CN117602098A CN202311626261.XA CN202311626261A CN117602098A CN 117602098 A CN117602098 A CN 117602098A CN 202311626261 A CN202311626261 A CN 202311626261A CN 117602098 A CN117602098 A CN 117602098A
- Authority
- CN
- China
- Prior art keywords
- angle
- follow
- driving
- actuator cylinder
- slat
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000009661 fatigue test Methods 0.000 title claims abstract description 17
- 238000000034 method Methods 0.000 title claims description 21
- 238000006073 displacement reaction Methods 0.000 claims abstract description 39
- 238000012360 testing method Methods 0.000 claims abstract description 33
- 230000007246 mechanism Effects 0.000 claims abstract description 22
- 238000005259 measurement Methods 0.000 claims abstract description 19
- 230000009471 action Effects 0.000 claims abstract description 5
- 238000001228 spectrum Methods 0.000 claims description 21
- 230000008859 change Effects 0.000 claims description 5
- 230000001276 controlling effect Effects 0.000 claims description 2
- 230000001105 regulatory effect Effects 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 230000003993 interaction Effects 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 238000012937 correction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 238000013178 mathematical model Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The application provides a follow-up system for fatigue test of an aircraft slat, which comprises a follow-up loading mechanism and an angle tracking control system; the follow-up loading mechanism comprises a frame support, a follow-up frame hinged with the frame support, a driving actuator cylinder for driving the follow-up frame to rotate and a loading actuator cylinder hinged on the follow-up frame and connected with the airfoil test piece; the angle tracking control system comprises a coordinated loading control system, a force transducer and an inclination angle sensor arranged on the follow-up frame, wherein the coordinated loading control system receives a displacement signal of the driving actuator cylinder, a force signal of the force transducer, an angle measurement signal of the inclination angle sensor, a deflection angle signal of the slat wing surface driving system and an angle difference signal, the deflection angle signal is corrected through the angle measurement signal to obtain the relation between the displacement elongation of the driving actuator cylinder and the wing surface deflection angle, and the coordinated loading control system controls the action of the driving actuator cylinder according to the relation between the corrected displacement elongation of the driving actuator cylinder and the wing surface deflection angle.
Description
Technical Field
The application belongs to the technical field of aircraft slat fatigue tests, and particularly relates to an aircraft slat fatigue test follow-up system and an angle tracking control method.
Background
In the full-size fatigue test of the aircraft slat, the wing surface deflection movement is usually completed by adopting an alternating current servo motor driving system, the wing surface load application is completed by a control system through a swing arm type follow-up frame, the two systems respectively move, a digital IO is used as a synchronous movement interaction judgment signal, and the error between the wing surface deflection angle of the driving system and the inclination angle of the follow-up frame is used as the most important criterion for precision control and safety protection, so that the smallest possible angle error has important value for the follow-up system angle tracking control.
The existing follow-up system adopts a swing arm type follow-up mechanism, adopts a hydraulic actuator cylinder to drive the rotation around an airfoil deflection central axis, calculates the displacement of the hydraulic actuator cylinder according to the approximate linear relation (hereinafter referred to as a displacement-angle model) of the displacement elongation and the inclination angle of the hydraulic actuator cylinder in a geometric model of the follow-up mechanism, takes the displacement of the hydraulic actuator cylinder as a controlled physical quantity, inputs the controlled physical quantity into a load spectrum of a control system, realizes that the inclination angle and the airfoil deflection angle of the follow-up mechanism are always consistent, and adopts an angle error as a safety protection measure. The displacement control-based angle control method only takes time as a synchronous motion basis, does not directly control angles, cannot realize real-time angle tracking control, is used as a monitoring quantity or an intermediate quantity only, is influenced by factors such as position control precision of a follower mechanism, precision of a slat wing surface driving system, time difference and the like, can keep the angle error within a range required by test precision through a large amount of debugging work, and cannot be effectively controlled and reduced fundamentally.
Disclosure of Invention
The invention aims to provide an aircraft slat fatigue test follow-up system and an angle tracking control system, which are used for solving or relieving at least one problem in the background technology.
The technical scheme of the application is as follows: an aircraft slat fatigue test follower system, the follower system comprising a follower loading mechanism and an angle tracking control system;
the follow-up loading mechanism comprises a frame support, a follow-up frame hinged with the frame support, a driving actuator cylinder for driving the follow-up frame to rotate and a loading actuator cylinder hinged on the follow-up frame and connected with the airfoil test piece;
the angle tracking control system comprises a coordinated loading control system, a force transducer arranged between a driving actuator cylinder and a follow-up frame and an inclination angle sensor arranged on the follow-up frame, wherein the coordinated loading control system receives displacement signals of the driving actuator cylinder, force signals of the force transducer, angle measurement signals of the inclination angle sensor, deflection angle signals of a slat wing surface driving system for driving wing surface test pieces to deflect and angle difference signals of the angle measurement signals and the deflection angle signals, the deflection angle signals are corrected through the angle measurement signals so as to obtain the relation between the displacement elongation of the driving actuator cylinder and the deflection angle of the wing surface, and the coordinated loading control system controls the action of the driving actuator cylinder according to the relation between the corrected displacement elongation of the driving actuator cylinder and the deflection angle of the wing surface.
Preferably, the driving actuator cylinder is a displacement actuator cylinder.
Preferably, the load ram comprises a first load ram and a second load ram, the first load ram being connected to the outer surface of the airfoil test piece and the second load ram being connected to the leading edge of the airfoil test piece.
Preferably, the first loading actuator cylinder and the second loading actuator cylinder are force control actuator cylinders.
Preferably, the angle tracking control system performs data interaction with the slat airfoil driving system through the IO interface so as to obtain the deflection angle of the slat airfoil driving system to the airfoil test piece.
Preferably, the coordinated load control system modifies the angle difference signal by modifying the displacement signal of the drive ram, the angle measurement signal of the tilt sensor and the yaw angle signal for the slat airfoil drive system prior to controlling the actuation of the drive ram in accordance with the angle difference signal.
On the other hand, the technical scheme provided by the application is as follows: an angle tracking control method of an aircraft slat fatigue test follower system according to any one of the preceding claims, comprising:
introducing the deflection angle of the wing surface driving mechanism 111 into a coordinated loading control system through a slat wing surface driving system by adopting an analog input channel, and installing an inclination sensor on a follow-up frame;
obtaining geometric parameters according to a structural model of a follow-up frame, establishing a relation model of displacement extension of a driving actuator cylinder and deflection angle of an airfoil test piece, and establishing a load spectrum with displacement as a controlled quantity and deflection angle as a target quantity according to the relation model;
the method comprises the steps of enabling an output signal for driving an actuating cylinder, a displacement input for driving the actuating cylinder, a force input for a force transducer, an angle measurement input for an inclination angle sensor, a deflection angle input for a slat airfoil driving system and an angle error input between an angle force measurement input and a deflection angle to be generated in a loading channel of a coordinated loading control system;
inputting displacement in the driving actuator cylinder as main feedback, enabling the driving actuator cylinder to drive the follow-up frame, calibrating angle feedback values of the inclination sensor at different clamping positions according to each clamping state of the slat airfoil driving system, and accordingly determining the corresponding relation between the displacement of the driving actuator cylinder and the airfoil deflection angle;
the angle measurement input of the inclination angle sensor is used as main feedback, an angle command is given, the PID parameters are controlled by setting the angle, a load spectrum with the angle as the controlled quantity of the driving actuator cylinder is established, the load spectrum is circularly operated, and the following performance and the accuracy of the angle control are regulated.
Preferably, the method further comprises:
setting the angle error input as main feedback, establishing a load spectrum taking the angle error as controlled quantity, setting the load spectrum value as zero, starting the slat airfoil surface driving system, verifying the angle change condition of the follow-up system tracking driving system, and properly adjusting PID control parameters to obtain better control quality of angle real-time tracking.
The servo system and the angle tracking control method have the advantages that the driving actuator cylinder in the servo system and the angle tracking control method adopts the angle quantity as the controlled physical quantity, the control principle is simple, on the basis of keeping the hardware resources unchanged, no additional requirements are imposed on the structural design of the servo loading frame, the test cost is saved, the economy is high, the angle tracking control can be finally realized, the servo angle error in the whole test process can be effectively reduced, the influence of the clamping state of the test piece is ignored, and the function realization is simpler.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
Fig. 1 is a schematic view of a follow-up loading mechanism of the present application.
Fig. 2 is a schematic diagram of a follower system angle tracking control system of the present application.
Fig. 3 is a schematic diagram of an angle tracking control process in the present application.
Reference numerals:
101-follow-up frame
102-frame support
103-drive actuator
104-first load ram
105-second load ram
106-airfoil test piece
107-force cell
108-obliquity sensor
109-coordinated load control system
110-slat airfoil drive system
111-airfoil driving mechanism
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
According to the method, based on displacement control-based angle tracking control, the slat deflection angle is introduced into a control system to serve as one path of angle feedback signal, the inclination angle sensor of the follow-up mechanism serves as the other path of angle feedback signal, the angle error between the two is used as a controlled physical quantity, a new angle control load spectrum is established, and angle real-time tracking control is achieved.
To this end, the present application provides a follower system for aircraft slat fatigue testing that includes a follower loading mechanism and an angle tracking control system.
First, as shown in the schematic view of the follower loading mechanism in fig. 1, the lower right corner of the follower frame 101 is hinged to the frame support 102, and the driving actuator cylinder 103 is hinged to the side of the follower frame 101 at one end and to the frame support 102 at the other end. Wherein the drive ram 103 employs a position controlled ram instead of a conventional hydraulic ram. The upper side and the front edge of the airfoil test piece 106 are respectively connected to the follow-up frame 101 through a first loading actuator cylinder 104 and a second loading actuator cylinder 105, and the application of force to the upper side and the front edge of the airfoil test piece 106 is realized through the first loading actuator cylinder 104 and the second loading actuator cylinder 105 so as to simulate the aerodynamic load of each part of the airfoil. Wherein both the first load ram 104 and the second load ram 105 employ force control rams.
The schematic diagram of the angle tracking control system shown in fig. 2 can be used for realizing real-time high-precision tracking driving of a follower system based on angle errors, and the angle tracking control system comprises: load cell 107, tilt sensor 108, and coordinated load control system 109.
A load cell 107 is provided between the drive ram 107 and the follower frame 101 for measuring the driving force of the drive ram 103 acting on the follower frame 101, the measurement of the load cell 107 being transmitted as a physical input to the coordinated load control system 109.
An inclination sensor 108 is provided on the follower frame 101 for measuring the deflection angle of the follower frame 101, and the measurement value of the inclination sensor 108 is also transmitted as a physical input to the cooperative load control system 109.
The coordinated control loading system 109 interacts with the slat airfoil drive system 110 via the I/O interface, and the slat airfoil drive system 110 controls the angular deflection of the airfoil test piece 106 via the airfoil drive structure 111, during which it obtains the deflection angle of the airfoil via analog acquisition of voltage, which is transmitted as a virtual input to the coordinated loading control system 109.
The driving actuator cylinder 103 in the follow-up loading mechanism is connected with the coordinated loading control system 109, and the coordinated loading control system 109 can control the driving actuator cylinder 103 to generate displacement by outputting a displacement control signal and drive the follow-up frame 101 to synchronously move along with the wing surface driving mechanism 111 to control the wing surface test piece 106 to deflect so as to keep the two relatively static.
Wherein coordinating input signals received by the load control system 109 includes: the displacement value generated by the driving actuator cylinder 103, the force value measured by the force sensor 107, the feedback value of the inclination angle of the follow-up frame 101 measured by the inclination angle sensor 108, the deflection angle of the airfoil test piece 106 sent by the slat airfoil driving system 110 and the angle difference value according to the deflection angle and the inclination angle force measurement value are coordinated, and the loading control system 109 generates a displacement control instruction of the driving actuator cylinder 103 according to the angle difference value so as to enable the driving actuator cylinder 103 to generate corresponding displacement.
When the slat airfoil driving system 110 controls the movement of the airfoil test piece 106 through the airfoil driving mechanism 111, in order to realize the relative static loading of the first loading actuator 104 and the second loading actuator 105 to the airfoil test piece 106, the follower frame 101 needs to drive the two loading actuators to move under the driving of the driving actuator 103 under the driving of the "displacement-angle" loading spectrum. The airfoil driving mechanism 106 controls the deflection angle change of the airfoil to cause an angle error, and drives the actuating cylinder 103 to execute corresponding retraction and extension actions, so that the angle feedback of the inclination angle sensor 108 is changed, the angle error is reduced, and when the error tends to zero, the two systems are in a relatively static state. The angle error is used as the controlled quantity, the clamping state is not considered, the follow-up system carries out tracking control according to the angle change of the driving system, and the angle error can be kept within the error requirement range and is continuously reduced. According to the method, on the premise of keeping the original test hardware resources, the load spectrum and the control rate are changed, the high-precision angle real-time tracking control is realized, and the follow-up control in the true sense is realized.
In the following system angle tracking control system diagram shown in fig. 2, the application also provides an angle tracking control process of the following system, which comprises the following steps:
s1, obtaining a deflection angle of the slat airfoil driving system 110: introducing the deflection angle of the wing surface driving mechanism 111 into the coordinated loading control system 109 by adopting an analog input channel, filtering to obtain a smooth deflection angle, avoiding system oscillation caused by fluctuation, and installing an inclination sensor 108 on the follow-up frame 101, wherein the angle feedback is consistent with the direction of the slat deflection angle, namely, the angle feedback is consistent with the positive sign and the negative sign of the deflection angle of the wing surface driving system 110 (both positive signs are positive);
s2, establishing a mathematical model: according to the mechanical structure diagram of the follow-up frame 101 and the loading point position shown in fig. 1, a geometric model and various parameters are obtained in digital-analog software, a relation model (hereinafter referred to as a displacement-angle model) of the displacement elongation of the driving actuator cylinder 103 and the inclination angle of the airfoil test piece 106 is established, a load spectrum with the displacement as a controlled quantity is established according to the relation model, and the load spectrum is used for early test installation and debugging, and at the moment, the force loading actuator cylinder can be temporarily not installed;
s3, setting an output of a driving actuator cylinder 103, an input 1 of a displacement sensor (the driving actuator cylinder 103 is internally provided with the displacement sensor), an input 2 of a load cell 107, an input 3 of an inclination sensor 108, a deflection angle virtual input 4 (the filtered airfoil deflection angle is adjusted through programming), an angle error virtual input 5 (the deflection angle virtual input 4-the inclination sensor input 3), and 1 physical output, 3 physical inputs and 2 virtual inputs in total in the loading channel of the coordinated loading control system shown in FIG. 2, wherein a certain input can be set as a main feedback for correction;
s4, taking the input 1 of the displacement sensor as main feedback, driving the follow-up frame 101 by adopting the driving actuator cylinder 103, and comparing the slat airfoil driving system 110 to reach an initial clamping state, zeroing the inclination sensor 108, calibrating the initial clamping state, calibrating angle feedback values of the inclination sensor 108 at different clamping positions at the same time, determining the accurate corresponding relation between the displacement of the driving actuator cylinder 103 and the airfoil deflection angle, correcting a load spectrum, and ensuring the feedback of the inclination sensor 108 to be true and accurate;
s5, taking the input 3 of the inclination sensor 108 as main feedback, manually giving an angle command according to a control principle as shown in figure 3, setting an angle control PID parameter, establishing a load spectrum taking the angle as a controlled quantity of the driving actuator cylinder 103, circularly running the load spectrum, and adjusting the following performance and accuracy of angle control;
s6, finally setting the virtual angle error input 5 as main feedback, establishing a load spectrum with the angle error as a controlled quantity, setting the load spectrum value to be zero, starting the slat airfoil driving system 110, verifying the angle change condition of the follow-up system tracking driving system, and properly adjusting PID control parameters to obtain better control quality of angle real-time tracking;
s7, test verification: according to the steps, other installation and debugging work of the multi-section slat follow-up system is completed, the feasibility and accuracy of the method are verified through multi-system joint debugging, the angle error monitoring protection action is set, and the stable and safe test operation is ensured through digital IO information interaction.
The servo system and the control method have the advantages that the driving actuator cylinder in the servo system and the control method adopts the angle quantity as the controlled physical quantity, the control principle is simple, on the basis of keeping the hardware resources unchanged, no additional requirements are imposed on the structural design of the servo loading frame, the test cost is saved, the economy is high, finally, the angle tracking control can be realized, the servo angle error in the whole test process can be effectively reduced, the influence of the clamping state of the test piece is ignored, and the function realization is simpler.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. The follow-up system for the fatigue test of the aircraft slat is characterized by comprising a follow-up loading mechanism and an angle tracking control system;
the follow-up loading mechanism comprises a frame support, a follow-up frame hinged with the frame support, a driving actuator cylinder for driving the follow-up frame to rotate and a loading actuator cylinder hinged on the follow-up frame and connected with the airfoil test piece;
the angle tracking control system comprises a coordinated loading control system, a force transducer arranged between a driving actuator cylinder and a follow-up frame and an inclination angle sensor arranged on the follow-up frame, wherein the coordinated loading control system receives displacement signals of the driving actuator cylinder, force signals of the force transducer, angle measurement signals of the inclination angle sensor, deflection angle signals of a slat wing surface driving system for driving wing surface test pieces to deflect and angle difference signals of the angle measurement signals and the deflection angle signals, the deflection angle signals are corrected through the angle measurement signals so as to obtain the relation between the displacement elongation of the driving actuator cylinder and the deflection angle of the wing surface, and the coordinated loading control system controls the action of the driving actuator cylinder according to the relation between the corrected displacement elongation of the driving actuator cylinder and the deflection angle of the wing surface.
2. An aircraft slat fatigue test follower system according to claim 1, wherein the drive ram is a displacement ram.
3. An aircraft slat fatigue test follower system according to claim 1 or 2, wherein the load ram comprises a first load ram and a second load ram, the first load ram being connected to the outer profile of the airfoil test piece and the second load ram being connected to the leading edge of the airfoil test piece.
4. An aircraft slat fatigue test follower system according to claim 3, wherein the first and second load rams are force controlled rams.
5. An aircraft slat fatigue test follower system according to claim 1, wherein the angle tracking control system is data-interactive with the slat airfoil drive system via the IO interface to obtain a yaw angle of the slat airfoil drive system to the airfoil test piece.
6. An aircraft slat fatigue test follower system according to claim 5, wherein the coordinated load control system modifies the angle difference signal by modifying a displacement signal of the drive ram, an angle measurement signal of the tilt sensor, and a yaw angle signal for the slat airfoil drive system prior to controlling actuation of the drive ram in accordance with the angle difference signal.
7. A method of angle tracking control of an aircraft slat fatigue test follower system according to any one of claims 1 to 6, comprising:
introducing the deflection angle of the wing surface driving mechanism 111 into a coordinated loading control system through a slat wing surface driving system by adopting an analog input channel, and installing an inclination sensor on a follow-up frame;
obtaining geometric parameters according to a structural model of a follow-up frame, establishing a relation model of displacement extension of a driving actuator cylinder and deflection angle of an airfoil test piece, and establishing a load spectrum with displacement as a controlled quantity and deflection angle as a target quantity according to the relation model;
the method comprises the steps of enabling an output signal for driving an actuating cylinder, a displacement input for driving the actuating cylinder, a force input for a force transducer, an angle measurement input for an inclination angle sensor, a deflection angle input for a slat airfoil driving system and an angle error input between an angle force measurement input and a deflection angle to be generated in a loading channel of a coordinated loading control system;
inputting displacement in the driving actuator cylinder as main feedback, enabling the driving actuator cylinder to drive the follow-up frame, calibrating angle feedback values of the inclination sensor at different clamping positions according to each clamping state of the slat airfoil driving system, and accordingly determining the corresponding relation between the displacement of the driving actuator cylinder and the airfoil deflection angle;
the angle measurement input of the inclination angle sensor is used as main feedback, an angle command is given, the PID parameters are controlled by setting the angle, a load spectrum with the angle as the controlled quantity of the driving actuator cylinder is established, the load spectrum is circularly operated, and the following performance and the accuracy of the angle control are regulated.
8. The angle tracking control method according to claim 7, characterized by further comprising:
setting the angle error input as main feedback, establishing a load spectrum taking the angle error as controlled quantity, setting the load spectrum value as zero, starting the slat airfoil surface driving system, verifying the angle change condition of the follow-up system tracking driving system, and properly adjusting PID control parameters to obtain better control quality of angle real-time tracking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311626261.XA CN117602098A (en) | 2023-11-30 | 2023-11-30 | Follow-up system for fatigue test of aircraft slat and angle tracking control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311626261.XA CN117602098A (en) | 2023-11-30 | 2023-11-30 | Follow-up system for fatigue test of aircraft slat and angle tracking control method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117602098A true CN117602098A (en) | 2024-02-27 |
Family
ID=89949573
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311626261.XA Pending CN117602098A (en) | 2023-11-30 | 2023-11-30 | Follow-up system for fatigue test of aircraft slat and angle tracking control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117602098A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117906897A (en) * | 2024-03-18 | 2024-04-19 | 西安羚控电子科技有限公司 | Simulated wind load control method and system of wing folding driving device |
| CN117906897B (en) * | 2024-03-18 | 2024-06-11 | 西安羚控电子科技有限公司 | Simulated wind load control method and system of wing folding driving device |
-
2023
- 2023-11-30 CN CN202311626261.XA patent/CN117602098A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117906897A (en) * | 2024-03-18 | 2024-04-19 | 西安羚控电子科技有限公司 | Simulated wind load control method and system of wing folding driving device |
| CN117906897B (en) * | 2024-03-18 | 2024-06-11 | 西安羚控电子科技有限公司 | Simulated wind load control method and system of wing folding driving device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6140787A (en) | Method and apparatus for controlling a work implement | |
| US7281431B2 (en) | Velocity feedback compensation for force control systems | |
| CN107102537B (en) | Double-screw synchronous control method based on virtual main shaft | |
| JP2002308194A (en) | Method and control device for adjusting position of flap swingably supported on rotor blade of helicopter | |
| CN109278042B (en) | Method for correcting eccentricity error of angle detector and robot system | |
| CN108896271A (en) | A kind of lifting airscrew aerodynamic testing five-component force balance original position load calibrating installation | |
| CN112697389B (en) | Automatic angle changing device for closed-loop control surface and control method thereof | |
| US10323999B2 (en) | Variable load and load vector application system | |
| CN115290289B (en) | Optimization method for improving control precision of large-incidence-angle tail support test system | |
| CN117602098A (en) | Follow-up system for fatigue test of aircraft slat and angle tracking control method | |
| CN110286689A (en) | Switching master-slave control method suitable for Dual-spindle linked Exceed load electrohydraulic servo system | |
| US20050004689A1 (en) | Design and control method of a micro-nanometer precision servo pneumatic X-Y positioning table | |
| JPH11114777A (en) | Method for controlling machine tool | |
| KR100741025B1 (en) | Vertical degree automatic control apparature | |
| CN111238558A (en) | Device and method for calibrating PSD nonlinear error | |
| CN111366368A (en) | Automatic thrust loading and calibrating system for aircraft engine test bed and automatic control method | |
| CN116220921A (en) | Method for generating dynamic characteristic evaluation index of executing mechanism of spout control loop | |
| CN114439805B (en) | Leveling system, leveling method and engineering machinery | |
| CN112378558B (en) | Method for measuring eccentric moment of servo platform | |
| EP4015139A1 (en) | Connecting rod rotary table and decoupling control method thereof | |
| CN109250632B (en) | Linear motion mechanism and control method thereof | |
| CN114486517A (en) | Servo loading device and method based on industrial robot system | |
| CN116339147A (en) | Angle compensation control method and system for follow-up system of aircraft slat fatigue test | |
| RU2731425C1 (en) | Control method of aircraft aerodynamic model steering surfaces | |
| CN110926787B (en) | Servo endurance test device for actuating cylinder universal joint |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |