Aircraft control system pedal integrated measurement device and method

Abstract

The present invention belongs to the field of applied aircraft debugging technology, and proposes an aircraft control system pedal integrated measurement device and method. The aircraft control system pedal integrated measurement device includes a dial, a scale indicator, a stroke measuring rod, a process pedal, a pressure sensor, a digital angle measurement device and a numerical display; the present invention integrates three measurement functions into one, and can simultaneously realize the measurement of pedal force, pedal stroke and pedal deflection angle, saving time for frequent replacement of tooling equipment due to measuring different items; the structure is simple and detachable, and the installation and disassembly operations are simple, which is convenient for storage and replacement; applying force with the foot can ensure stability, and the numerical reading is more accurate and the precision is higher; and the debugging errors caused by the operator's visual errors can be eliminated to the greatest extent through numerical reading, greatly improving work efficiency and debugging accuracy.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft debugging, and in particular to a pedal integrated measuring device and method for an aircraft control system. Background Art

[0002] The pedals are important components for pilots to control the aircraft. The stroke, force and angle of their movement will directly affect the pilot's control experience, thereby changing the aircraft's human sensory system and flight characteristics. Taking a certain aircraft as an example, the relevant debugging technical documents have numerical range requirements for the measurement of pedal force and stroke values, which need to be measured during the aircraft control system debugging stage.

[0003] At present, the method for measuring the pedal-related measurements of the aircraft control system is mainly to manually use tools such as steel rulers, squat and bend down to measure and read the values ​​in the cockpit with limited operating space. In the process of reading the pedal stroke, the operator needs to bend over and read the value on the steel ruler. Due to the limited space for the steel ruler, it is often difficult to read it accurately. Therefore, in order to ensure the accuracy of the measured data, it is sometimes necessary to perform multiple re-measurements, which invisibly increases the measurement work and has low work efficiency. When measuring the pedal force, because the dynamometer is used to push forward when it is pressed against the pedal, it is easy for the dynamometer to detach and injure the pedal, damage the dynamometer, or cause injury to the operator. Secondly, because the operator is in a state of applying high force with his hands, the applied force during measurement tends to fluctuate within a certain range and cannot be stabilized within a smaller range, resulting in low reading accuracy. In addition, during the reading process, the operator needs to read the value from the dial of the push-pull dynamometer. The value display is not direct enough, and due to the influence of the dial graduation value and the operator's visual error, it is often impossible to read it accurately. On the contrary, if the measuring device can be fixed on the pedal and the test results can be displayed through a ruler and a handheld numerical display, the work efficiency and numerical accuracy can be greatly improved. Summary of the invention

[0004] In view of the above reasons, an aircraft control system pedal comprehensive measurement device and method was invented, which can be used in fighter jets. The measuring device mainly drives the device to move synchronously through the pedal, so as to efficiently and accurately realize the comprehensive measurement of pedal travel, pedal force and pedal deflection angle and other data. It integrates multiple detection functions, changes the test method of the aircraft control system pedal distance, force value and angle, and does not need to use the original manual measurement method, making up for the shortcomings of difficult to ensure the accuracy of test indicators, long test time, and high labor intensity of operators, greatly improving the efficiency and accuracy of the test work, and to a large extent solving the difficult problems in the measurement process of the aircraft control system pedal detection project.

[0005] The technical solution of the present invention is: an aircraft control system pedal integrated measuring device, comprising a dial 1, a scale indicator 2, a mooring rope 3, a stroke measuring rod 4, a fixing bolt 5, a process pedal 6, a pressure sensor 7, a digital display angle measuring device 8, a fixing support 9, a signal output cable 10 and a numerical display 11;

[0006] One end of the stroke measuring rod 4 is fixed to the process pedal 6, and a dial 1 is arranged on the other end. The scale indicator 2 is connected to the stroke measuring rod 4 through a tether rope 3 to prevent loss and slide in the area of ​​the dial 1; one side of the process pedal 6 is used to withstand the external force applied by the operator, and the other side is connected to the pressure sensor 7; the fixed support 9 is L-shaped and fixed on the aircraft pedal, one side of which is connected to the pressure sensor 7, and the other side is connected to the digital display angle measuring device 8; the pressure sensor 7 and the digital display angle measuring device 8 are both connected to the numerical display 11 through a signal output cable 10, which is used to display the bearing force value and deflection angle of the aircraft pedal.

[0007] The scale plate 1 is located on the stroke measuring rod 4 and is used in conjunction with the scale indicator 2 to read the pedal stroke. The process pedal 6 is used to withstand the external force applied by the operator's foot, thereby driving the equipment to move; the pressure sensor 7 is used to measure the force value; and the digital display angle measuring device 8 is used to measure the pedal deflection angle.

[0008] A comprehensive measurement method for pedals of an aircraft control system comprises the following steps:

[0009] 1) Install the neutral device in the vertical hole of the pedal mechanism so that the pedal is in the neutral position. In this state, the pedal cannot move;

[0010] 2) The aircraft control system pedal integrated measuring device is installed on the aircraft pedal through the fixed support 9;

[0011] 3) The operator holds the numerical display 11 and the scale indicator 2, manually sets the zero position, and records the corresponding position A1 of the scale indicator 2 on the dial 1 at this time;

[0012] 4) Turn on the switch of the numerical display 11, and the display screen will display the force value and angle value. Select the real-time force value reading mode or the peak force value reading mode as required, and press the zero adjustment button to adjust the initial zero position;

[0013] 5) Remove the neutral device from the pedals;

[0014] 6) The operator places his foot on the process pedal and applies force to displace the pedal;

[0015] 7) The displacement of the stroke measuring rod 4 drives the scale plate 1 to move. The operator reads the position value A2 corresponding to the scale indicator 2 on the scale plate 1 according to the relative displacement between the scale plate 1 and the scale indicator 2. At this time, the pedal stroke A=A1-A2;

[0016] 8) When the pedal displacement value is in accordance with the aircraft debugging technical requirements, the force value displayed on the numerical display 11 is the force value under the pedal displacement, and the angle value displayed is the deflection angle of the pedal under the changed displacement. The operator directly observes the display screen reading to obtain it.

[0017] Beneficial effects of the present invention:

[0018] (1) The present invention integrates three measurement functions into one, and can simultaneously measure pedal force, pedal stroke, and pedal deflection angle, saving time for frequent replacement of tooling equipment for measuring different items, saving labor costs, and greatly improving work efficiency;

[0019] (2) The present invention has a simple structure and is detachable. The installation and disassembly operations are simple. After being disassembled into several parts, it is easy to store. If a part is damaged or fails during subsequent use, the part can be replaced separately without affecting the use of the equipment, thus improving maintainability and reducing the risk of affecting the progress of aircraft scientific research and production due to equipment problems.

[0020] (3) The shape of the fixed support is designed according to the shape of the pedal. During use, the device can be completely fitted on the pedal and firmly fixed. During the measurement process, since there is no need to hold a ruler or a steel ruler for measurement, the possibility of shaking when holding a steel ruler or a ruler and affecting the accuracy of the measurement result is largely avoided. When using the present invention for measurement, since the force is applied by the foot, stability can be guaranteed, and the numerical reading is more accurate and the precision is higher.

[0021] (4) The pressure sensor and digital angle measuring device used in the present invention can both provide digital signals and use the same signal output cable. This design allows the operator to directly read the accurate force value and angle using a numerical display, greatly improving the measurement accuracy. The numerical reading can also eliminate debugging errors caused by the operator's visual errors to the greatest extent, greatly improving work efficiency and debugging accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the aircraft control system pedal integrated measurement device of the present invention.

[0023] In the figure: 1- dial, 2- scale indicator, 3- mooring rope, 4- travel measuring rod, 5- fixing bolt, 6- process pedal, 7- pressure sensor, 8- digital angle measuring device, 9- fixing support, 10- signal output cable, 11- numerical display. DETAILED DESCRIPTION

[0024] The specific implementation methods and steps of the present invention are as follows:

[0025] 1) Connect the stroke measuring rod 4 to the process pedal 6 through the fixing bolt 5 to ensure that it is installed firmly;

[0026] 2) Install the digital angle measuring device 8 and the pressure sensor 7 on the fixed support 9 and ensure that they are firmly installed;

[0027] 3) Connect the two assembled components, and connect the numerical display 11 with the digital angle measuring device 8 and the pressure sensor 7 through the signal output cable 10;

[0028] 4) Install the neutral device in the neutral hole of the pedal mechanism so that the pedal is in the neutral position. In this state, the pedal cannot move;

[0029] 5) The aircraft control system pedal integrated measuring device is installed on the aircraft pedal through the fixed support 9;

[0030] 6) The operator holds the numerical display 11 and the scale indicator 2, and manually sets the zero position using the scale indicator 2 at a position convenient for reading the numerical value, and records the corresponding position A1 of the scale indicator 2 on the dial at this time;

[0031] 7) Turn on the switch of the numerical display 11, and the display screen will show the force value and angle value. Select the real-time force value reading mode or the peak force value reading mode as required, and press the zero adjustment button to adjust the initial zero position;

[0032] 8) Remove the neutral device from the pedals;

[0033] 9) The operator places his foot on the process pedal 6 and applies force to displace the pedal;

[0034] 10) The displacement of the stroke measuring rod 4 drives the scale plate 1 to move. The operator can read the position value A2 of the scale indicator 2 on the scale plate 1 according to the relative displacement between the scale plate 1 and the scale indicator 2. At this time, the pedal stroke A = A1-A2

[0035] 11) When the pedal displacement value is in accordance with the aircraft commissioning technical requirements, the force value displayed on the numerical display 11 at this time is the force value under the pedal displacement, and the angle value displayed on the numerical display 11 at this time is the deflection angle of the pedal under the displacement. The operator can directly observe the display readings.

[0036] 12) placing the device on the other pedal to measure the stroke, force and angle according to steps 4) to 11);

[0037] 13) After the above work is completed, remove the device from the pedal, disconnect the stroke measuring rod 4, the fixing bolt 5, the process pedal 6, the digital angle measuring device 8, the pressure sensor 7, and the signal output cable 10 and save them separately.

Claims

1. An aircraft control system pedal integrated measuring device, characterized in that: The aircraft control system pedal integrated measuring device comprises a dial (1), a scale indicator (2), a mooring rope (3), a stroke measuring rod (4), a fixing bolt (5), a process pedal (6), a pressure sensor (7), a digital display angle measuring device (8), a fixing support (9), a signal output cable (10) and a numerical display (11); One end of a stroke measuring rod (4) is fixed to a process pedal (6), and a scale plate (1) is arranged on the other end. A scale indicator (2) is connected to the stroke measuring rod (4) through a tether rope (3) to prevent loss and slide in the scale plate (1) area. One side of the process pedal (6) is used to withstand the external force applied by an operator, and the other side is connected to a pressure sensor (7). A fixed support (9) is L-shaped and fixed to an aircraft pedal. One side of the fixed support is connected to the pressure sensor (7) and the other side is connected to a digital display angle measuring device (8). The pressure sensor (7) and the digital display angle measuring device (8) are both connected to a numerical display (11) through a signal output cable (10) for displaying the bearing force value and deflection angle of the aircraft pedal.

2. A comprehensive measurement method for pedals of an aircraft control system, characterized in that: The specific steps are as follows: 1) Install the neutral device in the vertical hole of the pedal mechanism so that the pedal is in the neutral position. In this state, the pedal cannot move; 2) After the aircraft control system pedal integrated measuring device is assembled, it is installed on the aircraft pedal via a fixed support (9); 3) The operator holds the numerical display (11) and the scale indicator (2), manually sets the zero position, and records the corresponding position A1 of the scale indicator (2) on the dial (1) at this time; 4) Turn on the switch of the numerical display (11), and the display screen will show the force value and angle value. Select the real-time force value reading mode or the peak force value reading mode as required, and press the zero adjustment button to adjust the initial zero position; 5) Remove the neutral device from the pedals; 6) The operator places his foot on the process pedal and applies force to displace the pedal; 7) The displacement of the stroke measuring rod (4) drives the scale plate (1) to move. The operator reads the position value A2 corresponding to the scale indicator (2) on the scale plate (1) according to the relative displacement between the scale plate (1) and the scale indicator (2). At this time, the pedal stroke A = A1-A2; 8) When the pedal displacement value is in accordance with the aircraft debugging technical requirements, the force value displayed on the numerical display (11) is the force value under the pedal displacement, and the angle value displayed is the deflection angle of the pedal under the displacement. The operator directly observes the display screen reading to obtain it.

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