Zeroing device and zeroing method for aircraft control surface actuator

Abstract

The present invention belongs to the technical field of aircraft rudder surface actuators, and specifically relates to a zeroing device and a zeroing method for aircraft rudder surface actuators. The zeroing device is composed of only a telescopic measuring ruler and a ground measuring workbench, which can effectively solve the zeroing problem of aircraft rudder surface actuators; compared with devices with more parts, the zeroing device of the present invention has a very simple structure, which greatly reduces production management costs and is more in line with actual production needs. Based on the zeroing method of the above-mentioned zeroing device, the piston rod of the aircraft rudder surface actuator is adjusted to an appropriate length in advance, which solves the repeated disassembly and assembly of the aircraft rudder surface actuator on the aircraft, and at the same time reduces the disassembly work of the hydraulic pipe joints of the aircraft rudder surface actuator, avoiding the leakage of hydraulic red oil.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft control surface actuators, and in particular relates to a zeroing device and a zeroing method for aircraft control surface actuators. Background Art

[0002] Aircraft control surface actuators are servo actuators. When in the electrical zero position, the aircraft control surface should be in the neutral position. If the control surface is not in the neutral position, the actuator piston rod length needs to be adjusted to bring the control surface into the neutral position.

[0003] Currently, when checking the neutral position of the control surfaces, the actuator is first installed on the aircraft, the aircraft is powered on, and the flight control system sends an actuator zero position signal to check whether the control surfaces are in the neutral position. If the control surfaces are not in the neutral position, the actuator must be removed from the aircraft and the servo actuator piston rod length adjusted to bring the control surfaces into the neutral position. The adjusted servo actuator is then reinstalled on the aircraft, the aircraft is powered back on, and the control surfaces are checked for neutrality. Due to the heavy weight and high mounting position of the servo actuator on the aircraft, the installation and removal of the actuator is dangerous, time-consuming, and labor-intensive. Furthermore, when disconnecting the actuator hydraulic lines, hydraulic fluid can leak into the aircraft, contaminating the cabin. Summary of the Invention

[0004] In response to the existing situation where zeroing aircraft control surface actuators requires repeated disassembly and installation, the present invention provides a zeroing device and method for aircraft control surface actuators, which allows for adjustment of the control surface's neutral position with a single installation. The zeroing device provided by the present invention has a simple structure and is safe and reliable in use, while the zeroing method provided is easy to operate and saves time and effort.

[0005] First, the present invention provides a zeroing device for an aircraft control surface actuator.

[0006] The zero adjustment device consists only of a telescopic measuring ruler and a ground measuring workbench;

[0007] The telescopic measuring ruler is used for on-board measurement and ground measurement; the on-board measurement refers to measuring the target length L1 of the aircraft rudder surface actuator installation intersection when the rudder surface is in a neutral position; the ground measurement refers to measuring the current length L0 of the aircraft rudder surface actuator installation intersection on the ground in conjunction with the ground measurement workbench;

[0008] The ground measurement workbench is set on the ground and is equipped with two sliding bases capable of adjusting the installation position on the table surface;

[0009] The sliding base is used to adapt to the length of the aircraft rudder surface actuator and then install the aircraft rudder surface actuator on the ground measurement workbench. It can be used in conjunction with the telescopic measuring ruler to perform ground measurement, and can also be used in conjunction with the operation of adjusting the length of the aircraft rudder surface actuator piston rod on the ground to perform ground zeroing.

[0010] Furthermore, in order to better implement the present invention, the telescopic measuring ruler is a telescopic grating ruler.

[0011] Furthermore, in order to better implement the present invention, the telescopic measuring ruler has a digital display module that can directly display the measured value.

[0012] Furthermore, in order to better implement the present invention, the sliding base is provided with a bolt and nut assembly for mounting an aircraft control surface actuator.

[0013] Furthermore, in order to better implement the present invention, a linear guide rail is provided on the table top of the ground measurement workbench, and the bottom of the sliding base is slidably installed in the linear guide rail.

[0014] Furthermore, in order to better implement the present invention, the sliding base is provided with a locking block for positioning and locking; the locking block is used to position and lock the sliding base after it is adjusted into place.

[0015] Secondly, the present invention provides a zeroing method for an aircraft control surface actuator based on the above-mentioned zeroing device.

[0016] The zeroing method comprises, on the one hand, using a telescopic measuring ruler to measure a target length L1 of the aircraft rudder surface actuator installation intersection when the rudder surface is in a neutral position in the aircraft, and on the other hand, installing the aircraft rudder surface actuator on the ground measurement workbench and using the telescopic measuring ruler to measure the current length L0 of the aircraft rudder surface actuator installation intersection on the ground; then, calculating the difference ΔL between the target length L1 and the current length L0; then, adjusting the aircraft rudder surface actuator piston rod length on the ground according to the difference ΔL; and after zeroing, installing the aircraft rudder surface actuator on the aircraft.

[0017] Furthermore, in order to better implement the present invention, after the aircraft control surface actuator is installed on the aircraft, the aircraft is powered up to check whether the aircraft control surface is in a neutral position.

[0018] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0019] (1) The present invention provides a zeroing device for an aircraft control surface actuator, which consists only of a telescopic measuring ruler and a ground measuring workbench, and can effectively solve the zeroing problem of the aircraft control surface actuator. Compared with devices with more parts, the zeroing device of the present invention has a minimalist structure, greatly reduces production management costs, and is more in line with actual production needs.

[0020] (2) The zeroing device provided by the present invention is separated from the aircraft control surface actuator, and does not require any changes to the existing aircraft control surface actuator. It can be applied to various aircraft control surface actuators of the servo actuator type;

[0021] (3) The present invention provides a zeroing method for an aircraft control surface actuator, which is extremely simple to operate and can not only improve work efficiency but also reduce the professional requirements for operators, thereby further reducing labor costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only illustrate certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying any creative work.

[0023] Figure 1 It is a simplified structural diagram of the ground measurement workbench in the present invention.

[0024] Figure 2 It is a structural schematic diagram of a grating ruler in the present invention.

[0025] Figure 3 is used Figure 2 Diagram showing the usage of the grating ruler in flight to measure the target length L1 of the intersection point of the aircraft control surface actuator installation when the control surface is in the neutral position.

[0026] Figure 4 yes Figure 1 The ground measurement workbench is installed Figure 2 Schematic diagram of the status of the middle grating ruler.

[0027] Figure 5 yes Figure 1 The aircraft control surface actuator and the Figure 2 Schematic diagram of the status of the middle grating ruler.

[0028] Among them: 100, servo actuator; 200, aircraft control surface;

[0029] 1. Telescopic measuring ruler; 2. Ground measuring workbench; 21. Sliding base. DETAILED DESCRIPTION

[0030] In order to more clearly illustrate the technical solutions claimed for protection by the present invention, the following specific embodiments of the present invention are described in detail with reference to the accompanying drawings. The technical solutions in this embodiment are clearly and completely described. It should be understood that the described embodiments are only part of the embodiments of the present invention, not all of them, and therefore should not be regarded as limiting the scope of protection. Based on the following embodiments, all other technical solutions obtained by ordinary technical personnel in this field without making creative work are within the scope of protection of the present invention.

[0031] Example 1:

[0032] This embodiment uses a servo actuator 100 as an example to provide a zeroing device for an aircraft control surface actuator. The zeroing device comprises only a telescopic measuring ruler 1 and a ground measuring workbench 2 and is used for zeroing an aircraft control surface actuator such as the servo actuator 100.

[0033] The telescopic measuring ruler 1 is used for on-machine measurement and ground measurement.

[0034] The on-board measurement refers to measuring the target length L1 of the installation intersection of the servo actuator 100 when the control surface is in a neutral position on-board.

[0035] The ground measurement refers to measuring the current length L0 of the intersection point installed on the ground servo actuator 100 in cooperation with the ground measurement workbench 2.

[0036] The ground measurement workbench 2 is set on the ground and is equipped with two sliding bases 21 that can adjust the installation position on the table surface.

[0037] The sliding base 21 is used to adapt to the length of the servo actuator 100 and then install the servo actuator 100 on the ground measurement workbench 2. It can cooperate with the telescopic measuring ruler 1 to perform ground measurement, and can also cooperate with the operation of adjusting the piston rod length of the servo actuator 100 on the ground to perform ground zeroing.

[0038] In this embodiment, the main purpose of the ground measurement workbench 2 is to install the servo actuator 100 on the ground to facilitate ground measurement and ground zeroing.

[0039] like Figure 1 The ground measurement workbench 2 shown in FIG. has two sliding bases 21 arranged on the workbench. Figure 4 As shown, two sliding bases 21 are connected to the two ends of the servo actuator 100, one on the left and one on the right, respectively, to achieve a fixed installation of the servo actuator 100. After the servo actuator 100 is installed on the ground via the sliding bases 21, the telescopic measuring ruler 1 can be used to measure the length of the intersection point of the servo actuator 100 on the ground.

[0040] Since different servo actuators 100 have different lengths, in order to better accommodate servo actuators 100 of various lengths, solutions such as adjustable distance between the two sliding bases 21 and adjustable installation positions of the servo actuator 100 and the sliding base 21 are generally adopted.

[0041] To facilitate adjustment of the distance between the two sliding bases 21, in another embodiment, the surface of the floor measurement workbench 2 is provided with a linear guide rail, within which the bottoms of the sliding bases 21 are slidably mounted. Furthermore, the sliding bases 21 are equipped with locking blocks for positioning and locking. These locking blocks are used to position and lock the sliding bases 21 after they have been adjusted into place.

[0042] In order to facilitate adjustment of the installation position of the servo actuator 100 and the sliding base 21, in another embodiment, a long waist-shaped hole is provided on the sliding base 21. The hole shape of the long waist-shaped hole is adapted to the length of the servo actuator 100.

[0043] Other structures may also be used to adapt to the length of the servo actuator 100, which will not be described in detail.

[0044] Furthermore, when installing the servo actuator 100, it can be installed directly using the structure of mutually matching parts, or it can be installed through a third connecting member. When installing using the structure of mutually matching parts, mounting posts that match the diameter of the mounting holes at the ends of the servo actuator 100 can be provided on the sliding base 21. During installation, it is only necessary to pass the mounting posts at both ends through the mounting holes at the ends of the servo actuator 100 to complete the installation. When installing through a third connecting member, process holes can be provided on the sliding base 21, and the corresponding process holes and mounting holes can be axially aligned and positioned using third connecting members such as bolt and nut assemblies and locating pins to complete the installation. In another specific embodiment, the sliding base 21 is equipped with a bolt and nut assembly for mounting the servo actuator 100.

[0045] The main purpose of the telescopic measuring ruler 1 in this embodiment is to measure the length of a specific structure involved in the zeroing operation of the servo actuator 100. The telescopic structure is also used to facilitate measurement.

[0046] In order to improve the measurement accuracy, in another specific embodiment, the telescopic measuring ruler 1 is a telescopic grating ruler.

[0047] In order to improve the convenience of reading, in another specific embodiment, the telescopic measuring ruler 1 has a digital display module that can directly display the measured value.

[0048] like Figure 2The example shown is a retractable grating ruler with a digital display. This type of grating ruler can be purchased directly from the market. This embodiment only utilizes its retractable function for measurement and its digital display for easier reading. It does not involve the optimized design of the grating ruler structure itself, so it will not be described in detail.

[0049] like Figure 3 As shown, in order to facilitate ground measurement and ensure measurement accuracy, both ends of the telescopic measuring ruler 1 can be connected to the sliding base 21 of the ground measurement workbench 2.

[0050] Example 2:

[0051] This embodiment proposes a preferred solution based on embodiment 1.

[0052] The zeroing device consists of only a telescopic measuring ruler 1 and a ground measuring workbench 2. The table top of the ground measuring workbench 2 is provided with a linear slide rail, and the bottoms of the two sliding bases 21 are installed in the linear slide rail. When unlocked, the sliding base 21 can move along the linear slide rail and adjust its position in a certain linear direction of the horizontal working surface; when locked, the position of the sliding base 21 is fixed and no longer moves at will. At the same time, each sliding base 21 is provided with two process holes, one above and one below, and the central axis is located in the same vertical plane, which is perpendicular to the horizontal working surface. A group of process holes above each of the two sliding bases 21 is located in the same horizontal plane, and a group of process holes below each is located in the same horizontal plane. Usually, the upper group of process holes is used to install the servo actuator 100, and the lower group of process holes is used to install the telescopic measuring ruler 1.

[0053] It should be noted that the relationships herein, such as horizontal planes, vertical planes, perpendicular relationships, and coplanarity, are not limited to ideal absolute relationships but can be interpreted as relative relationships that conform to actual allowable machining errors. For example, when the central axes of two process holes on the same sliding base 21 are not absolutely parallel, but the minimum spatial angle between them is less than 1 degree, which meets the machining error requirements, the two process holes can be simply considered to belong to the same plane.

[0054] like Figure 3 、 Figure 4 As shown, on the same sliding base 21, two process holes for connecting with one end of the servo actuator 100 and one end of the telescopic measuring ruler 1 are located in the same vertical plane. In this case, the distance S1 between the set of process holes for installing the servo actuator 100 and the distance S2 between the set of process holes for installing the telescopic measuring ruler 1 on the two sliding bases 21 are equal, making measurement more convenient.

[0055] Example 3:

[0056] This embodiment provides a zeroing method for an aircraft control surface actuator based on embodiment 1 or embodiment 2.

[0057] First, on the one hand, the telescopic measuring ruler 1 is used to measure the target length L1 of the servo actuator 100 installation intersection when the control surface is in the neutral position in the aircraft. On the other hand, the servo actuator 100 is installed on the ground measurement workbench 2 and the telescopic measuring ruler 1 is used to measure the current length L0 of the servo actuator 100 installation intersection on the ground.

[0058] When measuring on the machine, Figure 5 As shown, first place the aircraft control surface 200 in the neutral position, then install the telescopic measuring ruler 1 to the installation intersection holes of the servo actuator 100, and measure the length between the installation intersections of the servo actuator 100 at this time, that is, measure the target length L1 of the installation intersection of the servo actuator 100 when the control surface is in the neutral position.

[0059] When measuring on the ground, Figure 4 As shown, the servo actuator 100 is installed on the ground measurement workbench 2 and measured using the telescopic measuring ruler 1 to obtain the current length L0 of the installation intersection of the servo actuator 100.

[0060] Then, the difference ΔL between the target length L1 and the current length L0 is calculated, ie, ΔL=L1-L0.

[0061] Next, the piston rod length of the servo actuator 100 is adjusted on the ground according to the difference ΔL so that L0 = L1, thereby achieving ground zeroing.

[0062] After zeroing, the servo actuator 100 is installed on the aircraft.

[0063] Furthermore, after the servo actuator 100 is installed on the aircraft, the aircraft is powered up to check whether the aircraft control surface 200 is in the neutral position.

[0064] The above zeroing method can simplify the zeroing process of aircraft control surfaces, shorten the working cycle and reduce the work intensity.

[0065] Using the zeroing device described in Example 1 or Example 2, the piston rod of the servo actuator 100 is adjusted to the appropriate length in advance, eliminating the need for repeated assembly and disassembly of the aircraft's control surface actuator. This also reduces the need for disassembly of the hydraulic piping connectors of the aircraft's control surface actuator, thus preventing leakage of hydraulic oil. Furthermore, the zeroing device has a simple structure, is easy to operate, saves effort and time, and is relatively inexpensive. Therefore, it is highly practical, easily applicable, and possesses significant practical value.

[0066] The rest of this embodiment is the same as that of Embodiment 1 or 2, and therefore will not be described in detail.

[0067] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent change made to the above embodiment based on the technical essence of the present invention shall fall within the scope of protection of the present invention.

Claims

1. A zeroing device for an aircraft control surface actuator, characterized in that: It only consists of a telescopic measuring ruler (1) and a ground measuring workbench (2); The telescopic measuring ruler (1) is used for on-board measurement and ground measurement; the on-board measurement refers to measuring the target length L1 of the aircraft rudder actuator installation intersection when the rudder is in a neutral position on-board; the ground measurement refers to measuring the current length L0 of the aircraft rudder actuator installation intersection on the ground in conjunction with the ground measurement workbench (2); The ground measurement workbench (2) is arranged on the ground, and is provided with two sliding bases (21) capable of adjusting the installation position on the table surface; both ends of the telescopic measuring ruler (1) can be connected to the sliding bases (21) of the ground measurement workbench (2); The sliding base (21) is used to adapt to the length of the aircraft rudder surface actuator and then install the aircraft rudder surface actuator on the ground measurement workbench (2). It can cooperate with the telescopic measuring ruler (1) to perform ground measurement, and can also cooperate with the operation of adjusting the length of the aircraft rudder surface actuator piston rod on the ground to perform ground zeroing.

2. A zeroing device for an aircraft control surface actuator according to claim 1, characterized in that: The telescopic measuring ruler (1) is a telescopic grating ruler.

3. A zeroing device for an aircraft control surface actuator according to claim 2, characterized in that: The telescopic measuring ruler (1) has a digital display module capable of directly displaying measured values.

4. A zeroing device for an aircraft control surface actuator according to claim 1, characterized in that: The sliding base (21) is provided with a bolt and nut assembly for mounting an aircraft control surface actuator.

5. The zeroing device for an aircraft control surface actuator according to claim 1, wherein: A linear guide rail is provided on the table surface of the ground measurement workbench (2), and the bottom of the sliding base (21) is slidably mounted in the linear guide rail.

6. A zeroing device for an aircraft control surface actuator according to claim 1, characterized in that: The sliding base (21) is provided with a locking block for positioning and locking.

7. A method for zeroing an aircraft control surface actuator, comprising: using the zeroing device according to claim 1 to zero the aircraft control surface actuator; wherein: The zeroing method comprises the following steps: first, using a telescopic measuring ruler (1) to measure a target length L1 of an aircraft rudder surface actuator installation intersection when the rudder surface is in a neutral position in-flight; and secondly, installing the aircraft rudder surface actuator on the ground measurement workbench (2) and using the telescopic measuring ruler (1) to measure a current length L0 of the aircraft rudder surface actuator installation intersection on the ground; Then, the difference ΔL between the target length L1 and the current length L0 is calculated; then, the length of the piston rod of the aircraft control surface actuator is adjusted on the ground according to the difference ΔL; After zeroing, install the aircraft control surface actuator on the aircraft.

8. A zeroing method for an aircraft control surface actuator according to claim 7, characterized in that: After the aircraft control surface actuator is installed on the aircraft, the aircraft is powered up to check whether the aircraft control surface (200) is in a neutral position.

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