Amphibious aircraft ground integration test flap control surface loading method and system

Abstract

The invention belongs to the technical field of aviation engineering tests, and discloses a flap control surface loading method and system for an amphibious aircraft ground integration test, and the method comprises the steps: designing a parallel loading system composed of a rocker arm, a pull rod and a loading cylinder, and carrying out the loading of a flap control surface according to a preset flap load spectrum in a flight control ground test, the loading cylinder is used for driving the parallelogram mechanism to simulate the action of the pneumatic hinge moment on the control surface in real flight. The problem that a traditional loading mode is difficult to accurately simulate the distributed load borne by the flap in real flight is solved, and the verification accuracy and reliability are improved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aeronautical engineering test, and particularly relates to a method and system for simulating flap load in flight control ground integration test of a large amphibious aircraft. BACKGROUND

[0002] The flap is an important part of a large aircraft and plays a key role in the process of take-off and landing of the aircraft. The function and performance of the flap can be verified through loading test, which can provide strong guarantee for flight safety. At present, electro-hydraulic servo loading is a common loading method. This technology directly connects the loading cylinder with the control surface to apply concentrated load for loading operation, and is widely used in tests due to its convenient operation.

[0003] However, this traditional loading method has obvious shortcomings: Firstly, the traditional "point-to-surface" force application form is difficult to accurately simulate the distributed load of the flap in real flight. Due to the high diversity of the mechanical structure of the flap and the different motion form of the flap from other conventional control surfaces, the simple "point-to-surface" loading cannot truly restore the actual stress condition of the flap, which makes it difficult to meet the high requirements of test accuracy. Secondly, the concentrated load application method puts forward very high requirements for the strength of the control surface material. This loading method will cause the control surface to bear excessive stress locally, which not only increases the design and manufacturing cost, but also has the risk of damage to the control surface due to excessive stress.

[0004] The existence of these problems seriously affects the accuracy and reliability of the flap function verification. SUMMARY

[0005] The present application provides a method and system for loading flap control surface in ground integration test of an amphibious aircraft, which can apply load in real time and accurately according to the change of the flap deflection angle, thereby effectively simulating the aerodynamic hinge moment of the control surface in real flight.

[0006] The technical solution of the present application is as follows: In a first aspect, the present application provides a method for loading flap control surface in ground integration test of an amphibious aircraft, which includes the following steps: Selecting a loading method according to test requirements; When force control mode is selected, the loading system switches to loading mode. The loading cylinder actuator follows the movement of the rudder surface. The loading computer queries the load spectrum based on the current displacement of the loading cylinder and outputs force control commands. The electro-hydraulic servo valve controls the opening according to the force control commands. The loading cylinder actuator moves and outputs loading force to the rudder surface. It is determined whether the rudder surface stops moving. If it stops, the test ends. If it does not stop, the above steps are repeated until the rudder surface stops and the test ends. When position control mode is selected, the loading system switches to follow-up mode. The loading cylinder actuator follows the movement of the rudder surface to the designated position. The loading system switches to loading mode and adaptively adjusts the loading force to keep the current position unchanged. It then determines whether the jamming test is completed. If it is completed, the test ends. If it is not completed, it determines whether to change the jamming position. If it is changed, all the above steps are repeated. If it is not changed, the loading force is adaptively adjusted to keep the current position unchanged until the jamming test is completed.

[0007] As a further aspect of the present invention: before loading, the flap loading load spectrum is calculated according to the test load requirements; during loading, the flap control surface movement drives the loading cylinder piston rod to move and generate displacement. The loading system queries the load spectrum according to the corresponding displacement and outputs the corresponding force as a command, so that the flap is subjected to different loads in real time during the movement.

[0008] As a further aspect of the present invention: the flap loading load spectrum is calculated, specifically as follows: Based on the installation position of the loading cylinder and the motion trajectory of the loading cylinder and the flap, the relationship between the output force and displacement of the flap loading cylinder and the deflection of the flap control surface is obtained through the principle of aerodynamic hinge torque conversion as follows:

[0009]

[0010]

[0011]

[0012] In the formula: —Displacement of the loading cylinder piston rod, mm; —Flap hinge torque, Nm; —Loading cylinder output force, N; — The distance from the loading cylinder mounting point to the rocker arm rotation center, in mm; — The distance from the loading cylinder mounting point to the loading point on the rocker arm, in mm, where L0 is the initial value; —Rocker arm rotation radius, mm; —Loading lever arm, mm; —Flap deflection angle, This is the initial deflection angle of the flap.

[0013] Secondly, the present invention provides a ground-integrated experimental flap control surface loading system for amphibious aircraft, comprising: A loading cylinder, the tail of which is fixed to the base; A rocker arm, one end of which is hinged to a fixed base, with the hinge point serving as the center of rotation, and the other end of which is hinged to the output end of the loading cylinder. Two tie rods, one end of which is hinged to the other end of the rocker arm, and the other end is connected through the front axle; One earring, which is installed at the center of the front axle, is used to connect the flap suspension.

[0014] As a further aspect of the present invention: the distance between the hinge point of the loading cylinder output end and the rocker arm and the distance between the hinge point of the two tie rods and the rocker arm are equal.

[0015] As a further embodiment of the present invention: the four points of the front axle center, the suspension rotation center, the intersection of the tie rod and the rocker arm, and the rocker arm rotation center form a parallelogram.

[0016] As a further aspect of the present invention: the bottom end of the rocker arm is hinged to the fixed base via a connecting shaft, and the top end is provided with three pairs of connecting lugs, with a connecting shaft between each pair of connecting lugs for hinge connection.

[0017] As a further embodiment of the present invention: two pull rods are arranged in parallel, and each pull rod has a connector at both ends, which is sleeved on the connecting shaft.

[0018] As a further aspect of the present invention: the earring has a collar and a connecting part, the collar being sleeved on the center position of the front axle, and the connecting part being fixedly connected to the flap suspension by bolts.

[0019] As a further aspect of the present invention: the output end of the loading cylinder is connected to a connector via a coupling, and the connector is sleeved on the connecting shaft.

[0020] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. This invention is simple to operate and highly accurate, and is suitable for loading various types (including unconventional types) of flap control surfaces; it avoids the risk of control surface damage that may be caused by direct loading of "point to surface" by using a "point-to-point" loading method; at the same time, it solves the installation problem caused by the limited loading space.

[0021] 2. This invention not only significantly improves the efficiency and realism of the test, but also provides a reliable technical guarantee for testing and verifying the function and performance of flaps in the flight control system of large amphibious aircraft.

[0022] 3. The present invention designs a parallel loading mechanism consisting of a rocker arm, a tie rod and a loading cylinder. During flight control ground tests, the loading cylinder drives the parallelogram mechanism to simulate the aerodynamic hinge torque acting on the control surface during real flight, based on a pre-set flap load spectrum.

[0023] 4. This invention uses a parallelogram mechanism to transmit force, enabling convenient and efficient installation even under limited space conditions, while ensuring precise and reliable loading control.

[0024] 5. The present invention connects to the suspension through the front axle and lug structure, ensuring the accuracy of load application in functional performance verification tests and avoiding test errors caused by inaccurate loading positions.

[0025] 6. This invention achieves precise "point-to-point" loading, effectively avoiding the risk of damage to the control surface during "point-to-area" loading, and significantly improving the safety and reliability of the test; 7. This invention can simulate the aerodynamic hinge torque of the control surface in real time and accurately, making the flight control ground integration test more realistic and reliable.

[0026] 8. This invention provides a reliable technical means for testing and verifying the function and performance of flaps in flight control systems, effectively improving the development efficiency and safety of large amphibious aircraft.

[0027] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the process for loading flap control surfaces in a ground integrated test of an amphibious aircraft according to the present invention. Figure 2 This is a schematic diagram of the flap loading system of the present invention; Figure 3 This is a line diagram of the movement of the flap loading cylinder of the present invention; Figure 4 This is a side view of the flap loading cylinder of the present invention. Figure 5 This is a top view of the flap loading cylinder of the present invention.

[0029] The attached diagram is labeled as follows: 1. Earring; 2. Front axle; 3. Tie rod; 4. Rocker arm; 5. Loading cylinder; 6. Base. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below with reference to the accompanying drawings.

[0031] In the accompanying drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present invention.

[0032] The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0033] The following is in conjunction with the appendix Figures 1-5 The embodiments of the present invention will be described in detail below.

[0034] Example 1 This invention provides a method for loading flap control surfaces in ground integrated testing of amphibious aircraft, which includes the following steps: Select the loading method according to the test requirements; When force control mode is selected, the loading system switches to loading mode. The loading cylinder actuator follows the movement of the rudder surface. The loading computer queries the load spectrum based on the current displacement of the loading cylinder and outputs force control commands. The electro-hydraulic servo valve controls the opening according to the force control commands. The loading cylinder actuator moves and outputs loading force to the rudder surface. It is determined whether the rudder surface stops moving. If it stops, the test ends. If it does not stop, the above steps are repeated until the rudder surface stops and the test ends. When position control mode is selected, the loading system switches to follow-up mode. The loading cylinder actuator follows the movement of the rudder surface to the designated position. The loading system switches to loading mode and adaptively adjusts the loading force to keep the current position unchanged. It then determines whether the jamming test is completed. If it is completed, the test ends. If it is not completed, it determines whether to change the jamming position. If it is changed, all the above steps are repeated. If it is not changed, the loading force is adaptively adjusted to keep the current position unchanged until the jamming test is completed.

[0035] Furthermore, before loading, the flap loading load spectrum is calculated based on the test load requirements; during loading, the movement of the flap control surface drives the piston rod of the loading cylinder to move and generate displacement. The loading system queries the load spectrum according to the corresponding displacement and outputs the corresponding force as a command, so that the flap is subjected to different loads in real time during the movement.

[0036] Furthermore, the flap loading load spectrum was calculated, specifically as follows: Based on the installation position of the loading cylinder and the motion trajectory of the loading cylinder and the flap, the relationship between the output force and displacement of the flap loading cylinder and the deflection of the flap control surface is obtained through the principle of aerodynamic hinge torque conversion as follows: ············(1) ············(2) ············(3) ···········(4) In the formula: —Displacement of the loading cylinder piston rod, mm; —Flap hinge torque, Nm; —Loading cylinder output force, N; — The distance from the loading cylinder mounting point to the rocker arm rotation center, in mm; — The distance from the loading cylinder mounting point to the loading point on the rocker arm, in mm, where L0 is the initial value; —Rocker arm rotation radius, mm; —Loading lever arm, mm; —Flap deflection angle, This is the initial deflection angle of the flap.

[0037] In this invention, the flap control surfaces are driven to move by actuators. The loading system calculates the load corresponding to the current flap angle in real time based on a pre-set control surface hinge moment-control surface deflection database, and sends control command signals to the electro-hydraulic servo valve. Subsequently, the loading actuator outputs the corresponding loading force and follows the movement of the control surfaces, thereby simulating the aerodynamic hinge moment experienced by the control surfaces in actual flight.

[0038] This invention employs two different loading methods: force-controlled mode and position-controlled mode. In position-controlled mode, the loading cylinder actuator extends or retracts to the target position according to displacement commands, keeping the control surface in the currently set position. This method is mainly used to simulate flap jamming. In force-controlled mode, the system uses a passive loading method, where the applied load force dynamically adjusts with displacement according to the load spectrum variation. This is typically used for conventional flap loading tests. The entire loading process is clear and straightforward, with specific steps as follows: Figure 1 As shown.

[0039] The present invention also provides a ground-integrated experimental flap control surface loading system for amphibious aircraft, comprising: A loading cylinder 5 is fixed at its tail to a base 6; A rocker arm 4 has one end hinged to a fixed base, with the hinge point serving as the rotation center, and the other end hinged to the output end of the loading cylinder 5. Two tie rods 3, one end of which is hinged to the other end of the rocker arm 4, and the other end is connected through the front axle 2; An earring 1 is installed at the center of the front axle 2 and is used to connect the flap suspension.

[0040] Furthermore, the distances between the output end of the loading cylinder 5 and the hinge point of the rocker arm 4, and between the two tie rods 3 and the hinge point of the rocker arm 4 are equal.

[0041] Furthermore, the center of the front axle 2, the center of the suspension rotation, the intersection of the tie rod 3 and the rocker arm 4, and the center of the rocker arm 4 form a parallelogram.

[0042] Furthermore, the bottom end of the rocker arm 4 is hinged to the fixed base via a connecting shaft, and the top end is provided with three pairs of connecting lugs, with a connecting shaft between each pair of connecting lugs for hinge connection.

[0043] Furthermore, the two pull rods 3 are arranged in parallel, and each pull rod 3 has a connector at both ends, which is sleeved on the connecting shaft.

[0044] Furthermore, the earring 1 has a collar and a connecting part. The collar is sleeved on the center position of the front axle 2, and the connecting part is fixedly connected to the flap suspension by bolts.

[0045] Furthermore, the output end of the loading cylinder 5 is connected to a connector via a coupling, and the connector is sleeved on the connecting shaft.

[0046] The flap loading point is located on the flap suspension and is connected to the loading cylinder 5 via tie rod 3 and rocker arm 4, see... Figure 2 The flap control system, which integrates the flap control surface and suspension, uses a torsion bar to rotate and drive the actuator. The actuator then moves the suspension, causing displacement of the control surface above the suspension. Simultaneously, the loading cylinder 5 actuator moves synchronously with the suspension. The loading system structure mainly includes the following parts: 11 (ear loop), 22 (front shaft), 33 (pull rod), 44 (rocker arm), 55 (loading cylinder), and 66 (base). The pull rod 3 is connected to the flap suspension via the front shaft 2 and 1 (ear loop). The other end of the pull rod 3 is connected to the rocker arm 4. The pull rod 3 avoids confined spaces. The loading cylinder 5 is connected to the other end of the rocker arm 4, and its tail is fixed to the base 6.

[0047] See the schematic diagram of the loading motion of the flap loading cylinder. Figure 3 As shown. Front axle 2 center. With the center of rotation of the suspension The intersection of lever 3 and rocker arm 4 Rocker arm 4 rotation center The parallelogram is formed so that the loading force of the loading cylinder 5 on the rocker arm 4 is equal to the force of the front axle 2 on the suspension.

[0048] Before loading, the flap loading load spectrum is calculated using formulas (1) to (4) according to the test load requirements. During loading, the flap control surface movement drives the piston rod of the loading cylinder to move and generate displacement. The loading system queries the load spectrum according to the corresponding displacement and outputs the corresponding force as the command, so that the flap is subjected to different loads in real time during the movement.

[0049] Example 2 The flight control hydraulics laboratory has successfully applied this method in the research and development testing of a certain aircraft model. In the test, the loading of the flap control surfaces was simulated by the loading cylinder 5 acting on the rotating rocker arm 4. The arrangement of the flap loading cylinder is shown in [details omitted]. Figure 4 and 5 As shown. This model of aircraft has 4 flap control surfaces, each with 2 suspensions. Each suspension has a loading point. When the flaps move, the control surfaces and suspensions rotate around the rotation center. The loading cylinder 5 moves through the pull rod 3 and the rotating rocker arm 4. The loading cylinder 5 outputs a load according to the preset load spectrum and transmits it in the opposite direction to the loading point of the suspension, thereby simulating the aerodynamic hinge torque on the flaps.

[0050] According to the test requirements, the maximum aerodynamic hinge torque of the four flap control surfaces converted to the loading point of the loading system is shown in Table 1.

[0051] Table 1 Maximum Pneumatic Hinge Torque

[0052] The loading parameters of each control surface of the flap were calculated according to formulas (1) to (4) and are shown in Table 2. The output stroke and output force of the loading cylinder are the flap load spectrum of the loading system.

[0053] Table 2 Calculation Table of Flange Loading Parameters

[0054] Currently, flap loading tests are an indispensable and crucial part of the research, development, testing, and airworthiness certification of large aircraft. However, there are many types of loading devices corresponding to different flap structures. The loading method in this invention can be applied to the functional performance testing requirements of most flap loading states. Its flexible adaptability allows for convenient and efficient installation even under limited space conditions, while ensuring precise and reliable loading control. It can also avoid the risk of control surface damage during the test and has good applicability in flap loading tests of other aircraft.

[0055] This invention was experimentally verified in the AG600 iron bird flap loading test, supplementing and improving the iron bird control surface loading technology.

[0056] Thus, the objective of this invention has been achieved.

[0057] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for loading flap control surfaces in ground integrated testing of amphibious aircraft, characterized in that, Includes the following steps: Select the loading method according to the test requirements; When force control mode is selected, the loading system switches to loading mode. The loading cylinder actuator follows the movement of the rudder surface. The loading computer queries the load spectrum based on the current displacement of the loading cylinder and outputs force control commands. The electro-hydraulic servo valve controls the opening according to the force control commands. The loading cylinder actuator moves and outputs loading force to the rudder surface. It is determined whether the rudder surface stops moving. If it stops, the test ends. If it does not stop, the above steps are repeated until the rudder surface stops and the test ends. When position control mode is selected, the loading system switches to follow-up mode. The loading cylinder actuator follows the movement of the rudder surface to the designated position. The loading system switches to loading mode and adaptively adjusts the loading force to keep the current position unchanged. It then determines whether the jamming test is completed. If it is completed, the test ends. If it is not completed, it determines whether to change the jamming position. If it is changed, all the above steps are repeated. If it is not changed, the loading force is adaptively adjusted to keep the current position unchanged until the jamming test is completed.

2. The method for loading flap control surfaces in ground integrated testing of amphibious aircraft according to claim 1, characterized in that, Before loading, the flap loading load spectrum is calculated based on the test load requirements. During loading, the flap control surface moves, causing the loading cylinder piston rod to move and generate displacement. The loading system queries the load spectrum based on the corresponding displacement and outputs the corresponding force as a command, so that the flap is subjected to different loads in real time during the movement.

3. The method for loading flap control surfaces in ground integrated testing of amphibious aircraft according to claim 2, characterized in that, The calculated flap loading load spectrum is as follows: Based on the installation position of the loading cylinder and the motion trajectory of the loading cylinder and the flap, the relationship between the output force and displacement of the flap loading cylinder and the deflection of the flap control surface is obtained through the principle of aerodynamic hinge torque conversion as follows: In the formula: —Displacement of the loading cylinder piston rod, mm; —Flap hinge torque, Nm; —Loading cylinder output force, N; — The distance from the loading cylinder mounting point to the rocker arm rotation center, in mm; — The distance from the loading cylinder mounting point to the loading point on the rocker arm, in mm, where L0 is the initial value; —Rocker arm rotation radius, mm; —Loading lever arm, mm; —Flap deflection angle, This is the initial deflection angle of the flap.

4. A ground-integrated experimental flap and control surface loading system for amphibious aircraft, characterized in that, include: A loading cylinder, the tail of which is fixed to the base; A rocker arm, one end of which is hinged to a fixed base, with the hinge point serving as the center of rotation, and the other end of which is hinged to the output end of the loading cylinder. Two tie rods, one end of which is hinged to the other end of the rocker arm, and the other end is connected through the front axle; One earring, which is installed at the center of the front axle, is used to connect the flap suspension.

5. The amphibious aircraft ground integrated test flap control surface loading system according to claim 4, characterized in that, The distances between the output end of the loading cylinder and the hinge point of the rocker arm and the hinge points of the two tie rods and the rocker arm are equal.

6. The amphibious aircraft ground integrated test flap control surface loading system according to claim 4, characterized in that, The center of the front axle, the center of the suspension rotation, the intersection of the tie rod and the rocker arm, and the center of the rocker arm rotation form a parallelogram.

7. The amphibious aircraft ground integrated test flap control surface loading system according to claim 4, characterized in that, The bottom end of the rocker arm is hinged to the fixed base via a connecting shaft, and the top end is provided with three pairs of connecting lugs, with a connecting shaft between each pair of connecting lugs for hinge connection.

8. The amphibious aircraft ground integrated test flap control surface loading system according to claim 7, characterized in that, Two tie rods are set in parallel, and each tie rod has a connector at both ends, which is sleeved on the connecting shaft.

9. The amphibious aircraft ground integrated test flap control surface loading system according to claim 4, characterized in that, The earring has a collar and a connecting part. The collar is fitted onto the center position of the front axle, and the connecting part is fixedly connected to the flap suspension by bolts.

10. The amphibious aircraft ground integrated test flap control surface loading system according to claim 8, characterized in that, The output end of the loading cylinder is connected to the connector via a coupling, and the connector is sleeved on the connecting shaft.

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