Airplane rudder servo controller test board
By designing a test bench for aircraft rudder servo controllers, using hydraulic pump stations and servo cylinders to simulate pneumatic loads, the complex and cost-effective testing problems in the existing technology are solved, and convenient and accurate testing results are achieved.
Patent Information
- Application Number
- CN202422069999.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-26
- Publication Date
- 2025-07-29
- Estimated Expiration
- 2034-08-26
AI Technical Summary
The existing technology is difficult to effectively test the aircraft rudder servo controller, and the purchase of foreign equipment is high and the maintenance is cumbersome. The ordinary test bench is not suitable, resulting in complex repair and testing.
A test bench for aircraft rudder servo controllers is designed to provide hydraulic power and load through hydraulic pump stations. Combined with servo cylinders and sensors, it simulates the aerodynamic load during the aircraft operation and realizes accurate testing of the servo controllers.
It realizes convenient testing of the aircraft rudder servo controller, obtains accurate test data, reduces testing costs and simplifies maintenance processes.
Smart Images
Figure CN223167052U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of rudder servo controller repair, in particular to an aircraft rudder servo controller test bench. Background Technique
[0002] The rudder servo controller is installed on the main control surface (rudder) of the aircraft, used to receive the control instructions of the flight control system, and drive the rudder to deflect, so as to complete the control of the flight attitude of the aircraft; during the operation of the aircraft, the aircraft jitter fault is relatively frequent, and the jitter caused by the rudder servo controller accounts for a relatively high proportion. Since the rudder servo controller has a more complex structure than other servo controllers and adds the structure of the rocker arm, ordinary test benches are not applicable. The existing test bench needs to be modified by external tooling and other methods, and the whole process is complex and troublesome, which has a certain impact on the repair and test of the rudder servo controller. Buying foreign original equipment is very expensive, and there are also problems such as long maintenance period and cumbersome procedures in later maintenance. Therefore, we propose an aircraft rudder servo controller test bench. Content of the Utility Model
[0003] The purpose of the utility model is to provide an aircraft rudder servo controller test bench to solve the problems raised in the above background technique.
[0004] An aircraft rudder servo controller test bench includes a rudder servo controller. The cylinder end of the rudder servo controller is connected to a fixed seat, and the fixed seat is fixedly installed on the bench. One end of a first connecting rod is hinged to the piston rod of the rudder servo controller. The other end of the first connecting rod is hinged to one end of a second connecting rod. The other end of the second connecting rod is connected to a connecting seat. The first connecting rod and the second connecting rod form a rocker arm. The connecting seat is installed on a first sliding connecting seat, and the first sliding connecting seat is slidably installed on a first slide rail. The side of the first sliding connecting seat is connected to a first displacement sensor, and the first displacement sensor is used to measure the displacement of the first sliding connecting seat. The first displacement sensor is installed on the bench parallel to the first slide rail. The first sliding connecting seat is also connected to the first telescopic rod of a first servo oil cylinder;
[0005] The piston rod end of the rudder servo controller is connected to one end of a second sliding connecting seat. The other end of the second sliding connecting seat is connected to one end of a force sensor. The other end of the force sensor is connected to one end of a third sliding connecting seat. The other end of the third sliding connecting seat is connected to the second telescopic rod of a second servo oil cylinder. The second sliding connecting seat and the third sliding connecting seat are slidably installed on a second slide rail. The side of the second sliding connecting seat is connected to a second displacement sensor, and the second displacement sensor is used to measure the displacement of the second sliding connecting seat. The second displacement sensor is installed on the bench parallel to the second slide rail.
[0006] Preferably, both the first servo cylinder and the second servo cylinder are installed on the bench, and both the first servo cylinder and the second servo cylinder are connected to the hydraulic source of the hydraulic pump station. The hydraulic pump station includes a booster pump, an oil tank, a relief valve, a directional control valve, an electric control box, etc., and can output a hydraulic source of 0 - 3000 psi and 10 gal / min. The servo valve is installed on the oil path between the hydraulic pump station and the first servo cylinder.
[0007] Preferably, the first displacement sensor, the second displacement sensor, and the force sensor are all signal - connected to an external industrial control computer, and the sensor signals are processed and displayed by the industrial control computer.
[0008] Compared with the prior art, the beneficial effects of the present utility model are as follows:
[0009] During the test, a hydraulic pressure is provided by an external hydraulic pump station to the first servo cylinder as a power source and to the second servo cylinder as a load source. Then, the pressure change is controlled by an external servo valve, causing the first telescopic rod of the first servo cylinder to make a reciprocating motion, driving the first sliding connection seat and the connection seat to move. Further, the rocker arm composed of the second connecting rod and the second connecting rod swings, driving the piston rod of the rudder servo controller to move. During the movement process, the load applied by the second servo cylinder to the piston rod through the second telescopic rod, the second sliding connection seat, and the third sliding connection seat is overcome, simulating the aerodynamic load during the flight of the aircraft. During the test process, the change of the force on the load is measured by the force sensor, and the speed and rate of the movement are measured by the first displacement sensor and the second displacement sensor. Then, the test results are obtained through calculation.
[0010] This test bench integrates a variety of data - testing functions, making the test of the aircraft rudder servo controller easy to operate and capable of accurately obtaining the test data results, which has a high promotion value in this field. BRIEF DESCRIPTION OF THE DRAWINGS
[0011] Figure 1 is the top view of the present utility model;
[0012] Figure 2 is the front view of the present utility model.
[0013] In the figure: 1. Rudder servo controller, 101. Piston rod, 102. First connecting rod, 103. Second connecting rod, 2. Bench, 21. Fixed seat, 3. First sliding connection seat, 31. Connection seat, 4. First slide rail, 5. First servo cylinder, 51. First telescopic rod, 6. First displacement sensor, 7. Second sliding connection seat, 8. Second displacement sensor, 9. Force sensor, 10. Third sliding connection seat, 11. Second slide rail, 12. Second servo cylinder, 121. Second telescopic rod. DETAILED DESCRIPTION OF THE EMBODIMENTS
[0014] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without making creative efforts belong to the scope of protection of the present invention.
[0015] Refer to Figure 1-2 , an aircraft rudder servo controller test bench, including a rudder servo controller 1. The cylinder end of the rudder servo controller 1 is connected to a fixed seat 21, and the fixed seat 21 is fixedly installed on a bench 2. One end of a first connecting rod 102 is hinged to the piston rod 101 of the rudder servo controller 1. The other end of the first connecting rod 102 is hinged to one end of a second connecting rod 103. The other end of the second connecting rod 103 is connected to a connecting seat 31. The first connecting rod 102 and the second connecting rod 103 form a rocker arm. The connecting seat 31 is installed on a first sliding connecting seat 3. The first sliding connecting seat 3 is slidably installed on a first slide rail 4. The side of the first sliding connecting seat 3 is connected to a first displacement sensor 6. The first displacement sensor 6 is used to measure the displacement of the first sliding connecting seat 3. The first displacement sensor 6 is installed on the bench 2 parallel to the first slide rail 4. The first sliding connecting seat 3 is also connected to a first telescopic rod 51 of a first servo oil cylinder 5. During the test, a hydraulic pressure is provided by an external hydraulic pump station to the first servo oil cylinder 5 as a power source, and the pressure change is controlled by an external servo valve, so that the first telescopic rod 51 of the first servo oil cylinder 5 makes a reciprocating motion, driving the first sliding connecting seat 3 and the connecting seat 31 to move, and further causing the rocker arm formed by the second connecting rod 103 and the second connecting rod 103 to swing, driving the piston rod 101 of the rudder servo controller 1 to move.
[0016] One end of the piston rod 101 of the rudder servo controller 1 is connected to one end of the second sliding connection seat 7. The other end of the second sliding connection seat 7 is connected to one end of the force sensor 9. The other end of the force sensor 9 is connected to one end of the third sliding connection seat 10. The other end of the third sliding connection seat 10 is connected to the second telescopic rod 121 of the second servo oil cylinder 12. The second sliding connection seat 7 and the third sliding connection seat 10 are slidably mounted on the second slide rail 11. The side surface of the second sliding connection seat 7 is connected to the second displacement sensor 8. The second displacement sensor 8 is used to measure the displacement of the second sliding connection seat 7. The second displacement sensor 8 and the second slide rail 11 are parallelly mounted on the bench 2. During the test, hydraulic pressure is provided by an external hydraulic pump station to the second servo oil cylinder 12 as a load source. The piston rod 101 of the servo controller 1 overcomes the load applied by the second servo oil cylinder 12 to the piston rod 101 through the second telescopic rod 121, the second sliding connection seat 7, and the third sliding connection seat 10 during the movement process, simulating the aerodynamic load during the flight of the aircraft.
[0017] Both the first servo oil cylinder 5 and the second servo oil cylinder 12 are mounted on the bench 2, and both the first servo oil cylinder 5 and the second servo oil cylinder 12 are connected to the hydraulic source of the hydraulic pump station. The hydraulic pump station includes a booster pump, an oil tank, a relief valve, a directional control valve, an electric control box, etc., and can output a hydraulic source of 0 - 3000 psi and 10 gal / min. The servo valve is mounted on the oil path between the hydraulic pump station and the first servo oil cylinder 5. The first displacement sensor 6, the second displacement sensor 8, and the force sensor 9 are all signal-connected to an external industrial control computer, and the sensor signals are processed and displayed by the industrial control computer.
[0018] Working principle: During the test, hydraulic pressure is provided by an external hydraulic pump station to the first servo oil cylinder 5 as a power source and to the second servo oil cylinder 12 as a load source. Then, the external servo valve is used to control the pressure change to make the piston rod 101 of the first servo oil cylinder 5 reciprocate, driving the first sliding connection seat 3 and the connection seat 31 to move. Further, the rocker arm formed by the second connecting rod 103 and the second connecting rod 103 swings, driving the piston rod 101 of the rudder servo controller 1 to move. During the movement process, the piston rod 101 overcomes the load applied by the second servo oil cylinder 12 to the piston rod 101 through the second telescopic rod 121, the second sliding connection seat 7, and the third sliding connection seat 10, simulating the aerodynamic load during the flight of the aircraft. During the test process, the change of the force on the load is tested by the force sensor 9, and the speed and rate of the movement are measured by the first displacement sensor 6 and the second displacement sensor 8. Then, the test results are obtained through calculation.
[0019] For those skilled in the art, it is obvious that the present utility model is not limited to the details of the above-mentioned exemplary embodiments, and the present utility model can be implemented in other specific forms without departing from the spirit or basic characteristics of the present utility model. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present utility model is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be embraced within the present utility model. Any reference signs in the claims should not be construed as limiting the claims involved.
[0020] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.
Claims
1. An aircraft rudder servo controller test bench, including a rudder servo controller (1), characterized in that: The cylinder end of the rudder servo controller (1) is connected to the fixed seat (21), the fixed seat (21) is fixedly installed on the bench (2), one end of the first connecting rod (102) is hinged to the piston rod (101) of the rudder servo controller (1), the other end of the first connecting rod (102) is hinged to one end of the second connecting rod (103), the other end of the second connecting rod (103) is connected to the connecting seat (31), the connecting seat (31) is installed on the first sliding connecting seat (3), the first sliding connecting seat (3) is slidably installed on the first slide rail (4), the side surface of the first sliding connecting seat (3) is connected to the first displacement sensor (6), the first displacement sensor (6) is installed on the bench (2) parallel to the first slide rail (4), and the first sliding connecting seat (3) is also connected to the first telescopic rod (51) of the first servo oil cylinder (5); The piston rod (101) end of the rudder servo controller (1) is connected to one end of the second sliding connecting seat (7), the other end of the second sliding connecting seat (7) is connected to one end of the force sensor (9), the other end of the force sensor (9) is connected to one end of the third sliding connecting seat (10), the other end of the third sliding connecting seat (10) is connected to the second telescopic rod (121) of the second servo oil cylinder (12), the second sliding connecting seat (7) and the third sliding connecting seat (10) are slidably installed on the second slide rail (11), the side surface of the second sliding connecting seat (7) is connected to the second displacement sensor (8), and the second displacement sensor (8) is installed on the bench (2) parallel to the second slide rail (11).
2. The aircraft rudder servo controller test bench according to claim 1, characterized in that: Both the first servo oil cylinder (5) and the second servo oil cylinder (12) are installed on the bench (2), and both the first servo oil cylinder (5) and the second servo oil cylinder (12) are connected to the hydraulic source of the hydraulic pump.
3. The aircraft rudder servo controller test bench according to claim 1, characterized in that: Both the first displacement sensor (6), the second displacement sensor (8) and the force sensor (9) are signal-connected to an external industrial control computer.