CN111003206A - Airplane steering column starting force and operating force detection equipment and detection method - Google Patents
Airplane steering column starting force and operating force detection equipment and detection method Download PDFInfo
- Publication number
- CN111003206A CN111003206A CN201911244370.9A CN201911244370A CN111003206A CN 111003206 A CN111003206 A CN 111003206A CN 201911244370 A CN201911244370 A CN 201911244370A CN 111003206 A CN111003206 A CN 111003206A
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- China
- Prior art keywords
- force
- driving device
- steering column
- driving
- test
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Classifications
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- 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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/22—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring the force applied to control members, e.g. control members of vehicles, triggers
- G01L5/223—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring the force applied to control members, e.g. control members of vehicles, triggers to joystick controls
Abstract
The invention relates to a method for detecting starting force and operating force of a steering column before installation of an aircraft seat and after installation of the steering column in an aircraft assembly process. A kind of airplane pilot arm starts the force and operates the detection equipment and detection method of the force, including drive equipment and test equipment; the driving device comprises a straight arm, a rocker arm, a driving device and an external controller, wherein one end of the straight arm clamps the steering column, the other end of the straight arm is connected with the driving device through the rocker arm, the driving device drives the rocker arm to swing leftwards and rightwards, and the external controller is connected with the driving device, provides driving force for the driving device and controls the driving device to be opened and closed; the test equipment comprises an external interface and a test computer, wherein the external interface is connected with the airborne flight control computer, and the airborne flight control computer reads the deflection angle of the steering column, the driving force of the steering column and the movement time and feeds the deflection angle, the driving force and the movement time back to the test computer. The invention has the following advantages: 1. the measurement value is accurate, the operation is simple, and the efficiency is high; 2. no special requirements are required for operators.
Description
Technical Field
The invention relates to a device and a method for testing the control force and the starting force of an airplane steering column, which are suitable for detecting the starting force and the control force of the steering column before the installation of an airplane seat and after the installation of the steering column in the airplane assembly process.
Background
The pilot stick of an aircraft is an important control element of the aircraft, and has strict requirements on the control force and the starting force. The existing detection means is completed manually, firstly, the manual operation is difficult to provide constant operation force, when the force changes in the manual force application process, the measurement of the operation force and the starting force can be influenced, and certain difficulty exists in keeping the operation force and the starting force of the airplane control lever in a specific range.
The test currently requires a professional operator (a high-level operator with more than 10 years of working experience) to operate the steering column many times, and another person observes the change of the driving force of the steering column on the airplane onboard equipment. Due to the influence of human factors, the steering column is difficult to push by a constant force due to the operating force, so that the steering column test is often carried out for many times, even if the steering column test is carried out for many times, the test result is inaccurate due to the change of the operating force, and the deviation value of the test data is uncontrollable.
Disclosure of Invention
An object of the present invention is to solve the problems of the prior art and to provide an aircraft pilot starting force and steering force detecting apparatus in which a constant driving force is used to push a pilot.
In order to achieve the purpose, the invention adopts the following technical scheme: an aircraft steering column actuation force and handling force detection device comprises a drive device and a test device; the driving device comprises a straight arm, a rocker arm, a driving device and an external controller, wherein one end of the straight arm clamps the steering column, the other end of the straight arm is connected with the driving device through the rocker arm, the driving device drives the rocker arm to swing leftwards and rightwards, and the external controller is connected with the driving device, provides driving force for the driving device and controls the driving device to be opened and closed; the test equipment comprises an external interface and a test computer, wherein the external interface is connected with the airborne flight control computer, and the airborne flight control computer reads the deflection angle of the steering column, the driving force of the steering column and the movement time and feeds the deflection angle, the driving force and the movement time back to the test computer.
Preferably, the straight arm is inserted into the swing arm and is vertically height-adjustable.
Preferably, the end of the straight arm clamps the steering column through a clamp, and the clamp is inserted into the straight arm and can adjust the distance in the heading direction.
Preferably, the driving device comprises a motor servo mechanism and a belt, the motor servo mechanism drives the belt to drive the rocker arm to rotate, and constant driving force is provided for the straight arm.
Preferably, the motor servo mechanism is connected with a differential, and the differential is used for controlling the swing arm deflection force.
Preferably, the external controller comprises a transmission port, a control button and a torque force adjusting button; the transmission port is connected with an external control box port on the driving device, the control button is used for controlling the opening and closing of the driving device, and the torque force adjusting button is used for adjusting the driving force of the driving rod.
Preferably, the bottom of the driving device is provided with a base and a fastening bolt, and the fastening bolt is used for installing the driving device on a positioning hole in the cabin of the airplane through the base.
Another object of the present invention is to provide a method for detecting an actuation force and a manipulation force of a pilot stick of an aircraft, comprising the steps of:
(1) the external interface is connected with an airplane airborne flight control computer, a test computer is started, and a steering column test monitoring software is started;
(2) the driving rod is placed at a neutral position, the driving equipment is placed to the rear side of the heading direction of the driving rod, and the driving equipment is clamped through a positioning hole and a tightening bolt in the cabin of the aircraft;
(3) adjusting the clamp to clamp the steering column;
(4) turning on a control button of an external controller, starting a driving device to work, and driving a rocker arm to swing through a differential mechanism; the driving force is ensured to be constant in the deflection process.
(5) After the test is finished, the driving device is closed through the external controller;
(6) opening the fastening bolt, and taking out the detection equipment from the aircraft cabin;
(7) and observing a measurement form formed by the test computer to finish the test of the steering column.
The working principle is as follows: when the steering column is used for force testing, the steering column is in a neutral position; the straight arm is tightly clamped with the steering column and is connected with the driving device and the straight arm through the rocker arm; the driving device drives the belt through the motor servo mechanism to drive the rocker arm to rotate so as to provide constant driving force for the straight arm; the straight arm drives the steering column to deflect leftwards, when the steering column moves to the limit position, the servo mechanism rotates reversely to drive the rocker arm to rotate reversely, so that the steering column deflects rightwards and moves to the limit position, and the operation is repeated. The overload protection device is set through a motor servo mechanism. When the driving force exceeds a set rated value, the motor servo mechanism stops rotating, the driving force is no longer provided for the rocker arm, the straight arm stops moving, and the steering column is static. The test equipment is connected with the airborne flight control computer through an external interface, the deflection angle of the steering column, the driving force of the steering column and the movement time are read by utilizing the displacement sensor and the force sensor of the airplane control system, the test computer forms a data recording table according to the angle, the force and the time, the driving force of each time point in the movement process of the steering column is recorded by taking the second as a unit, and the data in the test process is stored by taking the test date and times as a unit. And the operator judges whether the driving force is in a specified range in the current movement process of the steering column according to the data formed by the form, and further judges the mounting qualification of the steering column.
Compared with the prior art, the invention has the following advantages:
1. the measurement value is accurate, the operation is simple, and the efficiency is high;
2. the test device has no special requirements on operators and inexperienced operators can easily complete the test of the starting force and the operating force of the steering column, the test data is accurate, and the test deviation value is small.
Drawings
FIG. 1 is a diagram of an embodiment of the present invention and a steering column in use;
FIG. 2 is a schematic structural diagram of a driving apparatus according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a testing apparatus according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of an external controller according to an embodiment of the present invention;
in the figure, 1, a drive device; 2. a steering column; 3. tightening the bolt; 4. testing equipment; 5. the controller is externally connected; 11. a clamper; 12. a straight arm; 13. a rocker arm; 14. a differential mechanism; 15. a drive device; 16. a fixed base; 17. the external connection control box port; 51. a transfer port; 52. a control button; 53. a torque force adjusting button.
Detailed Description
The invention is described in further detail below with reference to the accompanying figures 1-4: an aircraft steering column starting force and operating force detection device is shown in figures 1-4 and comprises a driving device 1, a fastening bolt 3, a testing device 4 and an external controller 5.
As shown in fig. 2, the driving apparatus 1 includes a clamper 11, a straight arm 12, a rocker arm 13, a differential 14, a driving device 15, a fixed base 16 and an external control box port 17, the clamper 11 is connected with the rocker arm 13 through the straight arm 12, the straight arm 12 is inserted into the rocker arm 13 and is coaxial with the rocker arm 13, the straight arm 12 can perform vertical height adjustment in the barrel of the rocker arm 13, so as to ensure that the clamper 11 and the handle of the steering column 2 are at the same height, and meanwhile, the clamper 11 can perform course distance adjustment in the barrel of the straight arm 12, so as to ensure that the clamper 11 and the steering column 2 are at the same height, and the clamper 11 can be opened and retracted and adjusted according to the diameter of a clamping part required by the steering column 2. The differential 14 is connected with the driving device 15 as an overload protection device and has the function of adjusting and controlling the deflection force of the rocker arm 13, a moment spring is arranged in the differential 14, when the starting force exceeds a set value, the moment spring is disengaged, the rocker arm 13 is not driven any more, the straight arm stops moving, and the steering column is static. The driving device 15 comprises a motor servo mechanism and a belt, wherein the motor servo mechanism drives the belt to drive the rocker arm 13 to rotate so as to provide constant driving force for the straight arm. The fixed base 16 is fixed at the bottom of the driving device 1, and the fastening bolt 3 penetrates through the fixed base 16 to fix the driving device on a positioning hole in the cabin of the airplane. The external control box port 17 is connected with the external controller 5, and the external controller 5 provides driving force for the driving device 15 and controls the opening and closing of the driving device 15.
As shown in fig. 3, the test device 4 includes an external interface and a test computer, the external interface is connected to the onboard flight control computer, the onboard flight control computer reads the deflection angle of the steering column, the driving force of the steering column, and the movement time, the test computer forms a data recording table according to the angle, the force, and the time, and records the driving force at each time point in the movement process of the steering column in seconds.
As shown in fig. 4, the external controller includes a transmission port 51, a control button 52, and a torque adjustment button 53. The transmission port 51 is connected with the external control box port 17 on the driving device, the control button 52 is used for controlling the opening and closing of the driving device 15, and the torsion adjusting button 53 is used for adjusting the driving force of the steering column 2.
A method for detecting the starting force and the operating force of an airplane steering column, wherein the test work must be carried out before an airplane seat is installed, comprises the following steps:
(1) connecting an aircraft onboard flight control computer by using an external interface, starting a test computer, and turning on a steering column test monitoring software;
(2) the driving rod 2 is placed at a neutral position, the driving device 1 is placed to the rear side of the heading direction of the driving rod 2, and the driving device 1 is clamped through a positioning hole in the cabin of the aircraft and a tightening bolt 3;
(3) adjusting the clamp 11 to clamp the steering column 2;
(4) turning on a control button 52 of the external controller 5, starting the driving device 15 to work, and driving the rocker arm 12 to swing through the differential mechanism; according to the test requirements, firstly deflecting to the left to the limit position of the steering column, then reversely deflecting to the right limit position of the steering column, then reversely deflecting to the left limit position of the steering column, and repeating deflecting for 3 times;
(5) after the test is finished, the driving device 15 is closed through the external controller 5;
(6) opening the fastening bolt 3, and taking out the detection equipment from the aircraft cabin;
(7) the tester observes the measurement form that test equipment 4 formed, judges whether in whole motion process, whether there is the circumstances that starting force and operating force are out of tolerance, accomplishes this steering column test.
The device can change the working distance of the device and the driving force of the rocker arm 13 by adjusting the clamping device 11, the straight arm 12, the rocker arm 13 and the torsion adjusting button 53. Therefore, the method is suitable for detecting the starting force and the operating force of the steering column of different types of airplanes.
The above examples are merely preferred embodiments of the present invention and are not to be construed as limiting the invention. Any extensions, modifications, etc. of ordinary skill in the art without departing from the principles of the present invention are within the scope of the present invention.
Claims (8)
1. An aircraft pilot stick actuation force and handling force detection apparatus, characterized by: the device comprises a driving device and a testing device; the driving device comprises a straight arm, a rocker arm, a driving device and an external controller, wherein one end of the straight arm clamps the steering column, the other end of the straight arm is connected with the driving device through the rocker arm, the driving device drives the rocker arm to swing leftwards and rightwards, and the external controller is connected with the driving device, provides driving force for the driving device and controls the driving device to be opened and closed; the test equipment comprises an external interface and a test computer, wherein the external interface is connected with the airborne flight control computer, and the airborne flight control computer reads the deflection angle of the steering column, the driving force of the steering column and the movement time and feeds the deflection angle, the driving force and the movement time back to the test computer.
2. The aircraft pilot-stick activation and handling force detection apparatus of claim 1, wherein: the straight arm is inserted into the rocker arm and can be adjusted in height in the vertical direction.
3. The aircraft pilot-stick activation and handling force detection apparatus of claim 1, wherein: the end part of the straight arm clamps the steering column through a clamp, and the clamp is inserted into the straight arm and can adjust the distance in the course direction.
4. The aircraft pilot-stick activation and handling force detection apparatus of claim 1, wherein: the driving device comprises a motor servo mechanism and a belt, the motor servo mechanism drives the belt to drive the rocker arm to rotate, and constant driving force is provided for the straight arm.
5. The aircraft pilot actuation force and handling force detection apparatus of claim 4, wherein: the motor servo mechanism is connected with a differential mechanism, and the differential mechanism is used for controlling the swing force of the rocker arm.
6. The aircraft pilot-stick activation and handling force detection apparatus of claim 1, wherein: the external controller comprises a transmission port, a control button and a torque force adjusting button; the transmission port is connected with an external control box port on the driving device, the control button is used for controlling the opening and closing of the driving device, and the torque force adjusting button is used for adjusting the driving force of the driving rod.
7. The aircraft pilot-stick activation and handling force detection apparatus of claim 1, wherein: the bottom of the driving device is provided with a base and a tightening bolt, and the tightening bolt is used for installing the driving device on a positioning hole in the cabin of the airplane through the base.
8. A method for detecting starting force and operating force of an airplane steering column is characterized by comprising the following steps: the method comprises the following steps:
(1) the external interface is connected with an airplane airborne flight control computer, a test computer is started, and a steering column test monitoring software is started;
(2) the driving rod is placed at a neutral position, the driving equipment is placed to the rear side of the heading direction of the driving rod, and the driving equipment is clamped through a positioning hole and a tightening bolt in the cabin of the aircraft;
(3) adjusting the clamp to clamp the steering column;
(4) turning on a control button of an external controller, starting a driving device to work, and driving a rocker arm to swing through a differential mechanism; the driving force is ensured to be constant in the deflection process.
(5) After the test is finished, the driving device is closed through the external controller;
(6) opening the fastening bolt, and taking out the detection equipment from the aircraft cabin;
(7) and observing a measurement form formed by the test computer to finish the test of the steering column.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911244370.9A CN111003206B (en) | 2019-12-06 | 2019-12-06 | Airplane steering column starting force and operating force detection equipment and detection method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911244370.9A CN111003206B (en) | 2019-12-06 | 2019-12-06 | Airplane steering column starting force and operating force detection equipment and detection method |
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| Publication Number | Publication Date |
|---|---|
| CN111003206A true CN111003206A (en) | 2020-04-14 |
| CN111003206B CN111003206B (en) | 2021-11-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911244370.9A Active CN111003206B (en) | 2019-12-06 | 2019-12-06 | Airplane steering column starting force and operating force detection equipment and detection method |
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| CN (1) | CN111003206B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112798272A (en) * | 2020-12-25 | 2021-05-14 | 兰州飞行控制有限责任公司 | Test equipment and test method for rolling control of main flight control cockpit device |
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| CN112798272B (en) * | 2020-12-25 | 2023-07-21 | 兰州飞行控制有限责任公司 | Testing equipment and testing method for rolling operation of main flight control cockpit device |
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|---|---|
| CN111003206B (en) | 2021-11-09 |
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