CN115649479A

CN115649479A - Low-cost test device and test method for flap system of unmanned aerial vehicle

Info

Publication number: CN115649479A
Application number: CN202211570105.1A
Authority: CN
Inventors: 常庆春; 游进; 吴博; 刘斯佳
Original assignee: Sichuan Tengfeng Technology Co ltd; Sichuan Tengdun Technology Co Ltd
Current assignee: Sichuan Tengfeng Technology Co ltd; Sichuan Tengdun Technology Co Ltd
Priority date: 2022-12-08
Filing date: 2022-12-08
Publication date: 2023-01-31
Anticipated expiration: 2042-12-08
Also published as: CN115649479B

Abstract

The invention discloses a low-cost test device and a test method for a flap system of an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicle tests; the test device comprises: the wing system test device comprises a wing fake part, a wing flap system test part, a first position control actuator cylinder, a second position control actuator cylinder, a load actuator cylinder and a load transmission component; the wing dummy piece is a test system support piece; the flap system test piece is arranged on a rear beam of the wing dummy piece; the first position control actuator cylinder is arranged on the lower wing surface of the wing dummy piece and is used for applying normal forced displacement to two sections of the wing dummy piece so as to simulate real-time global deformation of a real wing; the load actuator cylinder is arranged above the flap test piece and is connected with the flap test piece through a load transmission assembly, and real-time flight load is applied to the flap test piece; based on the test device, the invention provides a flap system test method, and provides test technical support for low-cost development of a flap system of a large unmanned aerial vehicle.

Description

Low-cost test device and test method for flap system of unmanned aerial vehicle

Technical Field

The invention relates to the technical field of unmanned aerial vehicle tests, and particularly discloses a low-cost test device and a test method for a flap system.

Background

The statements in this section merely provide background information related to the present disclosure and may not constitute prior art.

The large unmanned aerial vehicle which is more and more widely applied in the military and civil fields has the characteristics of low structural weight coefficient, ultra-long endurance and excellent short take-off and landing performance; in order to obtain excellent aerodynamic performance, wings of the unmanned aerial vehicle have a large aspect ratio and can generate large deformation in flight; the flap system hung on the trailing edge of the wing is used as a high lift device, the wing lift is obviously increased by enlarging the wing area and the camber of the aircraft, and meanwhile, the resistance is controlled, and the short-distance take-off and landing of the unmanned aerial vehicle are realized.

The existing trailing edge flap and the test technology thereof are basically applied to the field of civil aircraft development, and the functional reliability and the strength conformance of a flap system are directly related to the flight safety of the civil aircraft. In the design stage, in order to research the potential failure mode of the flap system and optimize the design, a function test and a static strength test of the flap system are required; the key technology of the flap system test is to accurately simulate the boundary support condition of the flap system and realize the following loading of the test load meeting the engineering precision requirement.

Studies have shown that wing deformation has a non-negligible effect on both the functional realization and the loaded response of the flap system. However, the existing civil aircraft testing technology does not consider wing deformation, or simply considers the flexural deformation of a wing back beam and carries out static loading, or adopts a real wing 1 test section to carry out static loading, the former two methods cannot simulate the global deformation of the wing, so that the real-time supporting state of a flap system and the real loading condition of a structural mechanism in the service process cannot be reflected, the third method needs a wing test section with higher cost, the test scale and the wing load loading difficulty are high, and only the wing static deformation in a specific state is simulated in the test.

For engineering tests, the load loading error is controlled within 5 percent to be proper; the existing civil aircraft flap test loading scheme is designed with a huge follow-up loading mechanism and precise load distribution for pursuing high-precision test load loading, so that a test loading system and a control system are complex, multiple loading points are provided, the coordination control difficulty is high, and the test cost is high.

Disclosure of Invention

The invention aims to: aiming at the problems that the flap boundary support state is not simulated in real time, the flap test load loading method and system are complex, the civil aircraft development test cost is high and the like in the flap system test method and the test device applied in the civil aircraft development process at present, the low-cost test device and the test method for the flap system of the unmanned aerial vehicle are provided by combining the development requirements and characteristics of the large unmanned aerial vehicle, and the test technical support is provided for the low-cost development of the trailing edge flap system of the large unmanned aerial vehicle.

The technical scheme of the invention is as follows:

a low cost test device for a flap system of a drone, comprising:

the wing dummy piece is a support piece of a flap system test piece, and the normal forced displacement is applied to the wing dummy piece to simulate the global deformation of a real wing, so that the real-time boundary support condition of a flap system is accurately simulated;

the inner and outer flap system test piece is arranged on the rear beam of the wing dummy piece;

the first position control actuating cylinders are four in number, are arranged on the lower wing surfaces of two sections of the wing dummy piece in two groups and are used for applying normal forced displacement to the wing dummy piece;

carry the subassembly, carry and carry the subassembly and include: a guide slide rail and a guide slide block; the guiding slide rail is positioned above the flap body, and the posture of the guiding slide rail in a horizontal plane is adjustable so as to adapt to the larger range change of a load action point; the guide sliding block is arranged in the guide sliding rail;

the four load actuating cylinders are arranged above the inner and outer flap system test pieces in two groups, are connected with the inner and outer flap system test pieces after bypassing the guide sliding block through a steel wire rope, and apply flight loads to the inner and outer flap system test pieces;

and the two second position control actuating cylinders are respectively connected with the guide sliding block through a steel wire rope, and the loading direction of the test load is changed by controlling the position of the guide sliding block.

Further, the inner and outer flap system test pieces comprise:

a flap body, the flap body comprising: the wing comprises an inner flap and an outer flap, wherein the inner flap and the outer flap are arranged in parallel and are respectively arranged on a rear beam of a wing dummy piece through a sliding rail pulley frame type movement mechanism;

the ball screw actuator is arranged on a rear beam of the wing dummy piece through a mounting support and is used as a motion driving device of the flap body; one end of a lead screw of the ball screw actuator is in spherical hinge connection with the flap body and can drive the inner flap and the outer flap to move along the respective sliding rail pulley frame type movement mechanisms.

Furthermore, the number of the ball screw actuators is four, wherein two sets of the ball screw actuators are connected with the inner flap and two sets of the ball screw actuators are connected with the outer flap; the four sets of ball screw actuators are connected with the driving unit PDU through a torsion bar system transmission system and are driven by the driving unit PDU in a unified mode.

Further, the carry subassembly still includes:

the lower end of the lever system is connected with a plurality of loading points on the flap body through adhesive tapes;

one end of the steel wire rope is connected with the load actuating cylinder, the other end of the steel wire rope penetrates through a hole position on the guide sliding block and then is connected with the upper end of the lever system, and the traction force generated by the load actuating cylinder is transmitted to a plurality of loading points of the flap body through the lever system and the adhesive tape.

Furthermore, one guide slide rail and two load actuators are respectively arranged above the inner flap and the outer flap;

the two load actuating cylinders corresponding to the inner flap penetrate through different hole positions on a guide sliding block in a guide sliding rail above the inner flap through independent steel wire ropes respectively, the two steel wire ropes are connected with one lever system respectively, and the two lever systems are connected to different loading wires on the inner flap through adhesive tapes;

the two load actuating cylinders corresponding to the outer flap penetrate through different hole positions on a guide sliding block in a guide sliding rail above the outer flap through independent steel wire ropes respectively, the two steel wire ropes are connected with one lever system respectively, and the two lever systems are connected to different loading wires on the outer flap through adhesive tapes.

Furthermore, a plurality of stay wire type displacement sensors are arranged between the wing dummy piece and the ground and are used for measuring the normal displacement of each section of the wing dummy piece;

and a stay wire type displacement sensor is arranged above the ball screw actuator along the axial direction of a screw rod of the ball screw actuator and is used for measuring the elongation delta L of the screw rod of the ball screw actuator.

A flap flight load simulation method meeting engineering error requirements is based on the low-cost test device for the flap system of the unmanned aerial vehicle, and specifically comprises the following steps:

two loading lines are determined at the front and the back of a single flap along the chord length direction of the flap, a plurality of adhesive tapes are sequentially arranged on each loading line, and the adhesive tapes on the same loading line are connected with a steel wire rope through a lever system; finally, two steel wire ropes distributed along the chord length direction of the flap are connected to the two load actuating cylinders;

the number of the adhesive tapes is adjusted to reduce the test load of a single adhesive tape and simulate the distribution condition of the flap flight load;

the span-wise occupying change of the pneumatic pressure center caused by the deflection of the flap under the flight working condition is small, the span-wise occupying of the steel wire rope is taken as the span-wise occupying midpoint of the load resultant force of each flight working condition of the inner flap and the outer flap, and the length of the steel wire rope is adjusted to ensure that the loading error caused by the span-wise occupying error is less than 5%;

the occupation in the chord length direction of the acting point of the loading resultant force is controlled to be in dynamic accordance with the resultant force of the flap flight load by adjusting the load size of the two loading lines;

in the deflection process of the flap, the second position control actuator cylinder controls the guide slide block to move along the guide slide rail so as to change the direction of the steel wire rope, and the load loading directions of the two loading lines are dynamically consistent with the resultant force direction of the flap flight load.

A method for simulating real wing global deformation through a wing dummy piece is based on the low-cost test device for the flap system of the unmanned aerial vehicle, and specifically comprises the following steps:

step S1: establishing a flap multi-deflection full-aircraft finite element model to analyze the real wing deformation;

step S2: establishing a finite element model of a test system to analyze the deformation of the wing dummy piece;

and step S3: calculating the deformation error and intersection point load error of the real wing and the wing dummy piece, and judging whether the deformation error and the intersection point load error are less than 5%; if the deformation rate is less than 5%, the wing dummy piece can simulate the global deformation of the wing, so that the test requirement is met, the dummy piece can be manufactured and tested, the step S4 is skipped, and the step S5 is carried out; otherwise, performing step S4;

and step S4: and adjusting the rigidity of the wing dummy piece. According to the analysis of the deformation error and the intersection point load error, adjusting the section torsional rigidity of the wing dummy piece or the mounting support rigidity of a back beam slide rail to ensure that the wing deformation and the intersection point load error are less than 5 percent;

step S5: a pre-test is carried out and the normal forced displacement spectrum of the wing dummy piece is adjusted according to the condition.

Further, the step S1 includes:

step S11: establishing an unmanned aerial vehicle full-airplane finite element model with the inner and outer flaps at deflection positions of 0 degrees, 5 degrees, 10 degrees, 12.5 degrees, 15 degrees, 20 degrees, 25 degrees, 30 degrees and 35 degrees, applying full-airplane flight loads of all flight conditions in a take-off and landing stage, and analyzing true wing deformation;

step S12: extracting all-directional displacement of the front and rear beam edge strips of the real wing at the mounting sections of the four sliding rails of the inner flap and the outer flap and at the position where the wing dummy piece is forced to displace and load the occupying position of the ribs; the each directional displacement includes: spanwise displacement, course displacement and normal displacement;

step S13: calculating a real wing section torsion angle at the installation position of the slide rail, a rotation angle at the installation occupation position of the back beam slide rail, wing deflection difference and section torsion angle difference at the inner slide rail and the outer slide rail of the single flap, and extracting the installation intersection point load of the back beam flap slide rail;

the step S2 includes:

step S21: calculating the normal displacement of the front sparcap of the wing dummy at the two forced displacement loading ribs by utilizing the linear interpolation of the deformation data of the real wing front sparcap, and forming a normal forced displacement spectrum of the wing dummy of the test system by combining the normal displacement of the real wing rear sparcap extracted in the step S12 at the occupying position of the wing dummy forced displacement loading ribs;

step S22: establishing a finite element model of the test system, applying a normal forced displacement spectrum of the wing dummy formed in the step S21 under each wing deflection under each flight condition and corresponding flight loads of the inner flap and the outer flap, and analyzing the deformation of the wing dummy of the flap test system;

step S23: extracting all-directional displacement of the front and rear beam edge strips of the wing dummy at the four slide rail mounting sections of the inner and outer flaps under each working condition and the load of the flap slide rail mounting intersection point of the rear beam of the wing dummy of the test system from the analysis result in the step S22; the each directional displacement includes: spanwise displacement, course displacement and normal displacement;

step S24: calculating a section torsion angle of a wing dummy piece at a slide rail installation position of the flap test system, a rotation angle at an installation occupation position of a wing dummy piece back beam slide rail, and a wing dummy piece deflection difference and a section torsion angle difference at an inner slide rail and an outer slide rail of a single flap;

step S51: performing a preliminary test on severe working conditions of wing deformation, and coordinately applying the normal forced displacement spectrum of the wing dummy piece formed in the step S21 to two sections of the wing dummy piece through the four first position control actuating cylinders during the test; and at the flap in take-off skewness

And landing offset

Measuring the normal displacement of the wing dummy piece at the mounting sections of the four sliding rails of the inner flap and the outer flap and the occupying position of the forced displacement loading rib of the wing dummy piece at the position;

step S52: detecting the deformation of the wing dummy piece, and adjusting a normal forced displacement spectrum of the wing dummy piece according to the deformation condition to ensure that the deformation of the wing dummy piece can approach the global deformation of a real wing after the deformation error is less than 5 percent;

the wing dummy simulates the global deformation of a real wing and comprises the following steps: bending deflection and torsional deformation of the whole wing.

A flap system function test method is based on the low-cost test device for the flap system of the unmanned aerial vehicle, and specifically comprises the following steps:

step A: inputting the displacement spectrum and the load spectrum of the first position control actuator cylinder, the second position control actuator cylinder and the load actuator cylinder into an MTS multi-channel coordinated loading control system according to the functional test working condition;

and B, step B: after adjusting the inner flap and the outer flap to zero deflection and guiding the sliding block to corresponding initial positions, eliminating the deformation of the wing dummy part caused by the dead weight of the test system through a first position control actuator cylinder connected with the wing dummy part, and setting the measurement system and the loading system to zero;

step C: operating an MTS multi-channel coordinated loading control system, triggering a driving unit PDU to push a flap to move according to a flap moving program in a take-off stage, carrying out real-time coordinated synchronous loading on forced displacement of a wing dummy part and test loads of an inner flap and an outer flap according to a real-time measurement result of the extension delta L of a lead screw of a ball screw actuator corresponding to the inner flap and the outer flap, and completing take-off moving operation when the flap returns to a zero-deviation position;

step D: after the flap motion operation in the primary takeoff stage is finished, the drive unit PDU pushes the flap to move according to the landing stage flap motion program, the forced displacement of the wing dummy and the test load of the inner flap and the outer flap are synchronously loaded in real time according to the real-time measurement result of the elongation delta L of the lead screw of the ball screw actuator corresponding to the inner flap and the outer flap, and the functional test of the flap system is finished after the flap returns to the zero-offset position;

and E, step E: repeating the test operations of the step B to the step D for 6 times to obtain 1 group of functional tests, and carrying out 3 groups of functional tests in total;

step F: analyzing the 3 groups of functional test data, and judging whether the flap system test piece can realize the design function and whether the motion rule can meet the design requirement;

g: and further, repeating the functional test of the flap system in the steps B to D for 4 multiplied by 12000 times, judging the success or the failure of each functional test according to the functional realization condition and the motion rule conforming condition of the flap system, and calculating the functional reliability of the flap system.

Further, the judgment basis in the step F includes:

the judgment basis that the flap system test piece can realize the design function is as follows:

and D, if the drive unit PDU can drive the flap system test piece to smoothly complete the 3 groups of function tests in the step E within the specified time, the phenomenon of unsmooth movement or clamping stagnation does not exist, and the states of the take-off skewness and the landing skewness of the flap can be kept for 1 minute or more respectively, then the flap system is judged to realize the design function.

The judgment basis that the motion rule of the flap system test piece meets the design requirement is as follows:

if the screw rods of the two actuating cylinders of the inner flap can synchronously extend to push the inner flap to move, the screw rods of the two actuating cylinders of the outer flap can keep equal proportion to extend to push the outer flap to move, and the deflection angle error of the inner flap and the deflection angle error of the outer flap are less than or equal to 3%, the motion rule of the flap system can be judged to meet the design requirement.

Compared with the prior art, the invention has the beneficial effects that:

1. a low-cost test device for an unmanned aerial vehicle flap system simulates real-time global deformation of a real wing by designing a low-cost wing dummy piece and applying a method of two section normal forced displacements to the low-cost wing dummy piece, wherein the global deformation of the real wing comprises bending deflection and torsional deformation of the whole wing, so that the device can simulate a boundary support state and a real loaded condition of a structural mechanism in the flap motion process under the full-flight working condition, and provides an accurate boundary support condition for a flap system test.

2. Compared with the complex loading system and control method in the prior art, the low-cost test device for the flap system, provided by the invention, adopts the loading mechanism loaded by the double actuating cylinders guided by the slide block to apply the follow-up test load to the inner flap and the outer flap, and has the advantages of simple loading system, no additional motor and a plurality of control and feedback units on the premise of ensuring that the loading precision of an engineering test is met, few loading points, accurate control of the loading direction and capability of realizing the real-time follow-up loading of the test load in the full deflection range of the flap.

3. A functional test method for a flap system is used for carrying out real-time coordinated synchronous loading on wing dummy deformation and flap test load, truly simulating boundary support conditions and flight load of an inner flap and an outer flap in the operation process of the flap system, is easy to implement, has clear and effective test criteria, can comprehensively evaluate the function and strength conformity of the flap system, and is beneficial to finding out a potential failure mode and improving the potential failure mode.

4. A wing dummy piece of the low-cost test device for a flap system is made of a simple structural form and low-cost material, a guide sliding block and a sliding rail for changing the loading direction are made of common steel and channel steel, and the coordinated control is realized by means of a mature MTS multi-channel coordinated loading system, so that the test system is simple, and the test cost can be reduced.

5. The low-cost test device and the test method for the flap system have strong applicability, and can be also applied to the test of other movable parts of the airplane.

Drawings

Fig. 1 is a schematic structural diagram of a low-cost test device for a flap system of a drone.

FIG. 2 is a schematic illustration of a wing dummy and its forced displacement application scheme in a low cost test setup for a flap system of a drone;

FIG. 3 is a flow chart of a method of simulating global deformation of a real wing in a low cost test setup for a flap system;

FIG. 4 is a schematic view of a flap load following loading mechanism in a low cost test setup for a flap system of a drone;

FIG. 5 is a schematic view of the relationship between the elongation Δ L of the screw of the ball screw actuator and the flap deflection angle;

FIG. 6 is a flow chart of a flap system testing method implemented based on a flap system low-cost testing apparatus.

Reference numerals: 1-a wing dummy part, 2-a first position control actuator cylinder, 3-a load actuator cylinder, 4-a sliding rail pulley frame type motion mechanism, 5-a ball screw actuator, 6-a guide sliding rail, 7-a guide sliding block, 8-a wing root joint, 9-a steel wire rope, 10-a second position control actuator cylinder, 11-a lever system, 12-an adhesive tape belt, 13-an inner wing flap, 14-an outer wing flap, 15-a torsion bar system transmission system, 16-a driving unit PDU and 18-a pulley.

Detailed Description

It is noted that relational terms such as "first" and "second," and the like, may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising one of 8230; \8230;" 8230; "does not exclude the presence of additional like elements in a process, method, article, or apparatus that comprises the element.

The features and properties of the present invention are described in further detail below with reference to examples.

In the existing flap system test implementation technology, wing deformation is usually not considered, or only flexural deformation of a wing back beam is simply considered and static loading is carried out, or a real wing 1.

For engineering tests, the load loading error is controlled within 5 percent to be proper; in the loading scheme of the existing flap test technology, a huge follow-up loading mechanism and precise load distribution are designed for pursuing high-precision test load loading, so that a test loading system and a control system are complex, multiple loading points are provided, the coordination control difficulty is high, and the test cost is high.

Aiming at the problems in the prior art, the invention provides a low-cost test device which can effectively simulate the real-time global deformation of wings and can realize the following loading of flap loads meeting the engineering precision requirement, and a flap system function test and a multi-deflection static strength test method implemented based on the test device, so as to provide test technical support for the low-cost development of a trailing edge flap system of a large unmanned aerial vehicle.

Example one

Firstly, the invention relates to a low-cost test device for a flap system of an unmanned aerial vehicle, which simulates the global deformation of a real wing by designing a low-cost wing dummy and carries out real-time load simulation on a flap flight load by designing a set of loading mechanism loaded by double actuating cylinders guided by sliding blocks.

Referring to fig. 1-6, the present embodiment provides a low-cost testing apparatus for a flap system of a drone, including the following structure:

the wing dummy part 1 is a support part of a flap system test part, and the normal forced displacement is applied to the wing dummy part 1 to simulate the global deformation of a real wing, so that the real-time boundary support condition of a flap system is accurately simulated; preferably, the wing dummy piece 1 is used as a supporting device for a flap system test at the same time, and the wing dummy piece 1 is designed with low cost and is installed on a bearing wall by a wing root joint 8 for fixed installation; wherein, the low-cost design is as follows: the wing dummy part 1 is in a single-block structural form and is provided with a front beam, a rear beam, upper and lower wing surface skins, ribs and a stringer; the box section of the wing dummy part 1 adopts a straight wing shape with a rectangular section, the size of the rectangular section can be determined independently without being limited by a real wing, a wing flap motion mechanism and a transmission system need to be installed on a back beam of the wing dummy part, the geometrical form and the size of the back beam are the same as those of the back beam of the real wing, the wing dummy part 1 is provided with two machined ribs for loading forced displacement, and a position control actuator cylinder connecting joint is arranged on the lower edge strip of the front beam and the back beam at the ribs; the front beam, the rear beam and the ribs are all formed by bending 6061 aluminum alloy plates with equal thickness, the upper skin and the lower skin are made of 6061 aluminum alloy plates with equal thickness, and the upper skin and the lower skin are connected into the wing dummy part 1 by using domestic fasteners; compared with the civil aircraft flap function test, the method comprises the following steps of 1:1, the wing dummy part 1 can greatly reduce the test cost and shorten the test period;

the inner and outer flap system test piece is arranged on the rear beam of the wing dummy 1;

the first position control actuating cylinders 2 are four in number, are arranged on the lower wing surfaces of two sections of the wing dummy piece 1 in two groups, and are used for applying normal forced displacement to the wing dummy piece 1; to simulate the global deformation of a real wing; specifically, the lower wing surface of the wing dummy part 1 is provided with two first position control actuating cylinders 2 which are rigidly connected with the lower wing surface according to two cross sections;

carry the subassembly, carry and carry the subassembly and include: a guide slide rail 6 and a guide slider 7; the guide slide rail 6 is positioned above the flap body, and the posture of the guide slide rail is adjustable in a horizontal plane so as to adapt to the larger range change of a load action point; the guide slide block 7 is arranged in the guide slide rail 6;

the four load actuating cylinders 3 are arranged above the inner flap system test piece and the outer flap system test piece in two groups, bypass the guide slider 7 through a steel wire rope 9 and then are connected with the inner flap system test piece and the outer flap system test piece, and apply flight loads to the inner flap system test piece and the outer flap system test piece;

two second position control actuating cylinders 10 are provided, the two second position control actuating cylinders 10 are respectively connected with the guide sliding block 7 through a steel wire rope 9, and the loading direction of the test load is changed by controlling the position of the guide sliding block 7; preferably, the second position control actuator cylinder 10 is arranged along the extension line of the guide rail 6, and the second position control actuator cylinder 10 controls the position of the guide slider 7 to change the direction of the loading wire rope 9.

It should be noted that the first position-control actuator cylinder 2, the second position-control actuator cylinder 10 and the load actuator cylinder 3 in this embodiment are all fixedly connected to a wall or other fixed device at the base corresponding to the working end.

In this embodiment, specifically, the inner and outer flap system test piece includes:

a flap body, the flap body comprising: the wing comprises an inner flap 13 and an outer flap 14, wherein the inner flap 13 and the outer flap 14 are arranged in parallel and are respectively arranged on a rear beam of the wing dummy part 1 through a sliding rail pulley frame type movement mechanism 4;

the ball screw actuator 5 is arranged on a back beam of the wing dummy piece 1 through a mounting support and is used as a motion driving device of the flap body; one end of a lead screw of the ball screw actuator 5 is connected with the flap body in a spherical hinge manner, and the inner flap 13 and the outer flap 14 can be driven to move along the respective sliding rail pulley frame type movement mechanisms 4.

In the present embodiment, in particular, the ball screw actuators 5 have four sets, two of which are connected to the inner flap 13 and two of which are connected to the outer flap 14; the four sets of ball screw actuators 5 are connected with a driving unit PDU16 through a torsion bar system transmission system 15 and are driven by the driving unit PDU16 in a unified manner.

In this embodiment, specifically, the load transferring assembly further includes:

the lower end of the lever system 11 is connected with a plurality of loading points through an adhesive tape 12;

one end of the steel wire rope 9 is connected with the load actuator cylinder 3, the other end of the steel wire rope penetrates through a hole position on the guide sliding block 7 and then is connected with the upper end of the lever system 11, and the traction force generated by the load actuator cylinder 3 is transmitted to a plurality of loading points of the flap body through the lever system 11 and the adhesive tape 12; preferably, a pulley 18 is arranged at the hole position on the guide slider 7 for the steel cable 9 to pass around.

In the present embodiment, in particular, one guide rail 6 and two load actuators 3 are arranged above the inner flap 13 and the outer flap 14;

the two load actuators 3 corresponding to the inner flap 13 respectively pass through different hole positions on a guide slider 7 in a guide slide rail 6 above the inner flap 13 through separate steel wire ropes 9, the two steel wire ropes 9 are respectively connected with one lever system 11, and the two lever systems 11 are connected to different loading wires on the inner flap 13 through adhesive tapes 12; it should be noted that the loading line is composed of a plurality of loading points; namely, two loading lines are determined in a single flap in the front and back direction along the chord length direction of the flap, a plurality of adhesive tapes 12 are sequentially arranged on each loading line, and the adhesive tapes 12 on the same loading line are connected with a steel wire rope 9 through a lever system 11;

the two load actuators 3 corresponding to the outer flap 14 respectively pass through different hole positions on a guide slide block 7 in a guide slide rail 6 above the outer flap 14 through separate steel wire ropes 9, the two steel wire ropes 9 are respectively connected with one lever system 11, and the two lever systems 11 are connected to different loading lines on the outer flap 14 through adhesive tapes 12.

In this embodiment, specifically, a plurality of stay wire displacement sensors (not shown in the figure) are arranged between the wing dummy 1 and the ground, and are used for measuring the normal displacement of each section of the wing dummy 1;

and a stay wire type displacement sensor is arranged above the ball screw actuator 5 along the axial direction of the screw of the ball screw actuator 5 and is used for measuring the elongation delta L of the screw of the ball screw actuator 5.

Example two

Referring to fig. 3, a specific method and process for simulating global deformation of a real wing by designing a low-cost wing dummy according to a low-cost test apparatus for a flap system in an embodiment includes the following steps:

step S1: establishing a flap multi-deflection full-aircraft finite element model to analyze the real wing deformation, and specifically comprising the following substeps:

step S11: establishing an unmanned aerial vehicle full-aircraft finite element model with the inner and outer flaps at deflection positions of 0 degree, 5 degrees, 10 degrees, 12.5 degrees, 15 degrees, 20 degrees, 25 degrees, 30 degrees and 35 degrees, applying full-aircraft flight loads of all flight conditions in a take-off and landing stage, and analyzing real wing deformation;

step S12: extracting all-directional displacement of the front and rear beam edge strips of the real wing at the mounting sections of the four sliding rails of the inner flap and the outer flap and at the position where the wing dummy piece is forced to displace and load the occupying position of the ribs; the each-directional displacement includes: spanwise displacement, course displacement and normal displacement;

step S13: and calculating a real wing section torsion angle at the mounting position of the slide rail, a rotation angle at the mounting position of the back beam slide rail, wing deflection difference and section torsion angle difference at the inner slide rail and the outer slide rail of the single flap, and extracting the mounting intersection point load of the back beam flap slide rail.

Step S2: establishing a finite element model of a test system to analyze the deformation of a wing dummy part, and specifically comprising the following substeps:

step S22: establishing a finite element model of a test system, applying a normal forced displacement spectrum of the wing dummy formed in the step S21 under each wing deflection under each flight condition and corresponding flight loads of the inner flap and the outer flap, and analyzing the deformation of the wing dummy of the flap test system;

step S23: extracting all-directional displacement of the front and rear beam edge strips of the wing dummy at the four slide rail mounting sections of the inner and outer flaps under each working condition and the load of the flap slide rail mounting intersection point of the rear beam of the wing dummy of the test system from the analysis result in the step S22; the each-directional displacement includes: spanwise displacement, course displacement and normal displacement;

step S24: and calculating the section torsion angle of the wing dummy piece at the slide rail installation position, the rotation angle of the wing dummy piece back beam slide rail installation occupation position, the wing dummy piece deflection difference and the section torsion angle difference at the inner slide rail and the outer slide rail of the single flap test system.

And step S3: calculating the deformation error and intersection point load error of the real wing and the wing dummy piece, and judging whether the deformation error and the intersection point load error are less than 5%;

if the total deformation of the wing dummy piece is less than 5%, simulating the overall deformation of the wing, meeting the test requirement, manufacturing and testing the dummy piece, skipping the step S4, and performing the step S5; otherwise, performing step S4;

and step S4: and adjusting the rigidity of the wing dummy piece. According to the analysis of the deformation error and the intersection point load error, adjusting the section torsional rigidity of the wing dummy piece or the mounting support rigidity of the back beam sliding rail to ensure that the wing deformation and the intersection point load error are less than 5 percent;

step S5: carrying out a pre-test and adjusting a normal forced displacement spectrum of the wing dummy part according to the condition, and specifically comprising the following substeps:

step S51: performing a preliminary test on severe working conditions of wing deformation, and coordinately applying the normal forced displacement spectrum of the wing dummy piece formed in the step S21 to two sections of the wing dummy piece through the four first position control actuating cylinders during the test; and at the flap at take-off skewness

And landing skewness

step S52: detecting the deformation of the wing dummy piece, and adjusting a normal forced displacement spectrum of the wing dummy piece according to the deformation condition to ensure that the deformation of the wing dummy piece can approach the global deformation of the real wing after the deformation error is less than 5 percent;

the wing dummy piece simulates the global deformation of a real wing and comprises the following steps: bending deflection and torsional deformation of the whole wing.

Based on the method and the implementation steps thereof, the low-cost wing dummy part designed by the invention simulates real-time global deformation of the wing by applying a double-section forced displacement method, wherein the global deformation comprises integral bending deflection and torsion deformation of the wing, so that the boundary support state and the real loading condition of a structural mechanism in the movement process of the flap under the full-flight working condition can be simulated, and accurate boundary support conditions can be provided for the flap system test.

EXAMPLE III

Referring to fig. 4, based on a low-cost test apparatus of a flap system in the first embodiment, the present invention provides a set of following loading mechanisms for loading a dual-servo actuator with slider guidance, which can realize flap flight load real-time simulation in a full-deflection range of full-condition flaps and meet engineering error requirements, and the specific method includes:

two loading lines are determined at the front and the back of a single flap along the chord length direction of the flap, a plurality of adhesive tapes are sequentially arranged on each loading line, and the adhesive tapes on the same loading line are connected with a steel wire rope through a lever system; finally, two steel wire ropes distributed along the chord length direction of the flap are connected to the two load actuating cylinders; namely, a row of adhesive tapes are arranged at the occupied positions of the inner and outer flap frameworks;

the number of the adhesive tapes can be adjusted to reduce the test load of a single adhesive tape and simulate the distribution condition of the flap flight load;

the span-wise occupying change of the pneumatic pressure core caused by the deflection of the wing flap under the flight working condition is small, the span-wise occupying of the steel wire rope is taken as the span-wise occupying midpoint of the load resultant force of each flight working condition of the inner wing flap and the outer wing flap, and the length of the steel wire rope is adjusted to ensure that the loading error caused by the span-wise occupying error is less than 5%;

meanwhile, the dynamic consistency of the occupation in the chord length direction of a loading resultant force action point and the flap flying load resultant force is controlled by adjusting the load sizes of the two loading lines;

meanwhile, in the deflection process of the flap, the second position control actuator cylinder controls the guide slide block to move along the guide slide rail so as to change the direction of the steel wire rope, and the load loading directions of the two loading lines are dynamically consistent with the resultant force direction of the flap flight load;

therefore, the method can meet the test load loading within the flap full-deflection range of the engineering test precision requirement.

Compared with the loading method of the flap load in the existing flap function test, the flap test load real-time simulation method has the advantages that the loading system is simple, additional motors and a plurality of control and feedback units are not needed, the loading points are few, the load direction can be accurately controlled, and the real-time follow-up loading of the test load in the flap full-deflection range can be realized on the premise of ensuring the loading precision of the engineering test.

Example four

Referring to fig. 6, the invention proposes a functional test method for a flap system, the basic test principle of which is as follows:

based on the flap system low-cost test device in the first embodiment, the method for simulating the global deformation of the real wing by the test device in the second embodiment, and the follow-up loading method for simulating the flap test load by the test device in the third embodiment, the coordinated loading control system of the MTS multichannel coordinated loading widely applied in the field of the current mechanical test is utilized to perform the coordinated operation of the multipoint load loading, the displacement control and the test measurement of the flap test; the forced displacement spectrum of the wing dummy part, the flap load spectrum and the displacement spectrum of the guide sliding block are input into a multi-channel coordinated loading control system in advance, after the inner flap and the outer flap are adjusted to the initial deflection theta =0 degrees and the guide sliding block is adjusted to the initial position, the MTS multi-channel coordinated loading control system is started, after the wing dummy part deformation caused by the dead weight of the test system is eliminated, a PDU (protocol data Unit) is triggered to drive the flap to move, the multi-channel coordinated loading system simultaneously outputs a displacement loading instruction and a load loading instruction according to the elongation delta L of a lead screw of a ball screw actuator, and simultaneously carries out closed-loop negative feedback control on a position control actuator and a load actuator in the test system, so that the real-time coordinated loading and test control targets in the flap full deflection range can be achieved.

In the present embodiment, in particular, the low-cost test method for the flap system, first to be explained is:

a complete flap system function test is defined as that a drive unit PDU pushes flaps to complete flap motion operation in a take-off stage and a landing stage in sequence;

the flap movement in the takeoff stage is the flap deviation from the initial degree

Movement to take-off deflection of =0 DEG

=

=12.5 °, held in this state for 1 minute, and then recovered to the initial skewness

Position of =0 °;

the flap motion in the landing stage is the flap deviation from the initial degree

Off-set from 0 ° motion to landing

=

=35 deg. keep this state for 1 minute, then recover to initial skewness

Position =0 °.

Secondly, the low-cost function test method for the flap system specifically comprises the following steps:

step A: inputting the displacement spectrums and the load spectrums of the first position-control actuator cylinder, the second position-control actuator cylinder and the load actuator cylinder into an MTS multi-channel coordinated loading control system according to the functional test working condition;

and B: after adjusting the inner and outer flaps to zero deflection and guiding the sliding block to a corresponding initial position, eliminating the deformation of the wing dummy part caused by the dead weight of the test system through four first position control actuating cylinders connected with the wing dummy part, and zeroing the measurement system and the loading system;

step D: after the flap motion operation in the take-off stage is completed, the drive unit PDU drives the flap to move according to the flap motion program in the landing stage, the forced displacement of the wing dummy and the test load of the inner flap and the outer flap are synchronously loaded in real time according to the real-time measurement result of the elongation delta L of the lead screw of the ball screw actuator corresponding to the inner flap and the outer flap, and the function test of the flap system is completed once after the flap returns to the zero-deviation position;

and E, step E: repeating the test operations of the steps B-D for 6 times to obtain 1 group of functional tests, and carrying out 3 groups of functional tests in total;

step F: analyzing the 3 groups of functional test data, and judging whether the design function of the flap system test piece can be realized and whether the motion rule can meet the design requirement;

step G: further, repeating the functional tests of the flap system of the steps B to D for 4 multiplied by 12000 times, judging the success or the failure of each functional test according to the functional realization condition and the motion rule conforming condition of the flap system, and recording the failure times N _fail Calculating the functional reliability P = N of the flap system _fail /N, where N =4 × 12000.

In this embodiment, specifically, the judgment criterion in the step F includes:

In this embodiment, it should be described in detail that the method for generating the test real-time position control spectrum and the load spectrum is as follows:

firstly, the motion track of the flap is roundArc, see FIG. 5, elongation Δ L of lead screw and flap deflection angle

The functional relationship exists as follows:

=f(ΔL)=arcos(

)-

after the elongation of the screw rod is measured by using the stay wire type displacement sensor, the flap real-time deflection angle can be calculated

；

Secondly, based on the relationship between the flap deflection angle and the actuator cylinder screw elongation, the real-time position control spectrum and load spectrum generation method comprises the following steps:

analyzing the real wing deformation under the states of flap skewness of 0 degrees, 5 degrees, 10 degrees, 12.5 degrees, 15 degrees, 20 degrees, 25 degrees, 30 degrees and 35 degrees respectively by using a full-machine finite element model, and obtaining forced displacement spectrums of four first position control actuating cylinders connected with a wing fake piece through further calculation;

calculating the resultant force of the flap flight load under the flap deflection, and performing equivalent load distribution to obtain a test load spectrum of two loading lines of the inner flap and the outer flap

(j=1、2),

(k=1、2)；

The intersection point position of the action line of the wing flap load resultant force under each wing flap deflection and the guide slide rail is solved by utilizing three-dimensional modeling software CATIA (computer-aided three-dimensional Interactive application)Guide slide displacement spectrum in load loading direction

、

；

And the real-time position control spectrum and the load spectrum under other flap skewness are generated by linear interpolation.

The functional test method for the flap system of the unmanned aerial vehicle is implemented based on the low-cost test device, can realize real-time simulation of global deformation of a real wing by a wing dummy part, including bending deflection and torsional deformation of the whole wing, and the coordinated following loading of test load in flap motion of the flap test part, and truly simulates the real-time boundary support state of the flap system and the real loading condition of a structural mechanism in the flap motion process.

EXAMPLE five

Referring to fig. 6, based on the low-cost test apparatus for the flap system of the unmanned aerial vehicle according to the first embodiment, a static strength test method of a flap and a moving mechanism thereof at multiple skewness positions is provided in consideration of global deformation of a wing, and specifically includes the following steps:

step 1: starting an MTS multi-channel coordinated loading control system, driving the inner flap and the outer flap to corresponding flap deflection positions through a driving unit PDU according to the requirements of the working conditions of each static strength test, powering down the PDU, and adjusting the PDU to the corresponding positions through a second position control actuator cylinder connected with a guide sliding block and then keeping the PDU;

and 2, step: operating an MTS multi-channel coordination loading control system, eliminating the deformation of a wing fake piece caused by the self weight of a test system by using a first position control actuator cylinder, and setting zero to a measurement system and a loading system;

and 3, step 3: performing a 100% load limiting test; performing coordinated synchronous loading on forced displacement of the wing dummy part and test loads of the inner flap and the outer flap according to 5% of primary level by using an MTS multi-channel coordinated loading control system, collecting strain displacement data, and synchronously unloading to 0 after loading is maintained for 30s when the forced displacement data and the test loads of the inner flap and the outer flap are loaded to 100% of limited load deformation of the wing dummy part and 100% of limited load of the flap are loaded, thereby completing a 100% limited load test;

and 4, step 4: a 150% limit load test was performed. And carrying out coordinated synchronous loading on forced displacement of the wing dummy part and test loads of an inner flap and an outer flap by utilizing an MTS multi-channel coordinated loading control system, acquiring strain displacement data, loading the test loads to 120% of limit load and the forced displacement according to 5% of first class, loading the test loads to 150% of limit load deformation of the wing dummy part and 150% of limit load of the flap according to 2% of first class, keeping the loads for 3s, and synchronously unloading the test loads to 0 to finish the 150% limit load test.

Further, according to the static strength test method, if the check flap and the movement mechanism thereof are not permanently deformed after the 100% load limiting test and the flap and the movement mechanism thereof are not damaged after the 150% load limiting test, the static strength of the flap and the movement mechanism thereof is judged to meet the design requirements.

Compared with the prior flap static test technology, the flap and the static test method of the motion mechanism thereof provided by the invention have the advantages that by utilizing the low-cost flap system test device provided by the embodiment I of the invention, the global deformation of a real wing is simulated by designing a low-cost wing dummy and applying a double-section normal forced displacement method to the low-cost wing dummy, the overall bending deflection and torsional deformation of the whole wing can be simulated, the boundary support state of the real wing at each deflection angle position of the flap to the flap system and the real loading condition of the flap system structure mechanism can be simulated, and the method is not realized in the prior art and is obviously different from the method of only simulating the relative deflection difference between the flap installation slide rail occupation of the rear wing beam in the prior art.

The above-mentioned embodiments only express the specific embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the present application. It should be noted that, for those skilled in the art, without departing from the technical idea of the present application, several changes and modifications can be made, which are all within the protection scope of the present application.

The background section is provided to present the context of the invention in general, and work of the presently named inventors, to the extent it is described in this background section, as well as aspects of the description that may not otherwise qualify as prior art at the time of filing, are neither expressly nor impliedly admitted as prior art against the present invention.

Claims

1. A low-cost test device for a flap system of a drone, comprising:

the first position control actuator cylinder is arranged on the lower wing surface of the wing dummy piece and is used for applying normal forced displacement to the wing dummy piece;

the load actuator cylinder is arranged above the inner and outer flap system test piece, is connected with the inner and outer flap system test piece after bypassing the guide slide block through a steel wire rope, and applies flight load to the inner and outer flap system test piece;

and the second position control actuator cylinder is connected with the guide sliding block through a steel wire rope, and the loading direction of the test load is changed by controlling the position of the guide sliding block.

2. The low-cost test device for a flap system of a drone of claim 1, wherein the inner and outer flap system trial comprises:

the ball screw actuator is arranged on a rear beam of the wing dummy piece through a mounting support and serves as a motion driving device of the flap body; one end of a lead screw of the ball screw actuator is in spherical hinge connection with the flap body and can drive the inner flap and the outer flap to move along the respective sliding rail pulley frame type movement mechanisms;

the ball screw actuators are four in number, wherein two sets of the ball screw actuators are connected with the inner flap and two sets of the ball screw actuators are connected with the outer flap; the four sets of ball screw actuators are connected with the driving unit PDU through a torsion bar system transmission system and are driven by the driving unit PDU in a unified mode.

3. The low-cost test device for a flap system of a drone of claim 2, wherein the load carrying assembly further comprises:

one end of the steel wire rope is connected with the load actuator cylinder, the other end of the steel wire rope penetrates through a hole position on the guide sliding block and then is connected with the upper end of the lever system, and the traction force generated by the load actuator cylinder is transmitted to a plurality of loading points of the flap body through the lever system and the adhesive tape.

4. The low-cost test device for the flap system of the unmanned aerial vehicle of claim 3, wherein one guide rail and two load actuators are arranged above the inner flap and the outer flap;

the two load actuating cylinders corresponding to the inner flap penetrate through different hole positions on a guide sliding block in a guide sliding rail above the inner flap through independent steel wire ropes respectively, the two steel wire ropes are connected with one lever system respectively, and the two lever systems are connected to different loading lines on the inner flap through adhesive tapes;

the two load actuating cylinders corresponding to the outer flap penetrate through different hole positions on a guide sliding block in a guide sliding rail above the outer flap through independent steel wire ropes respectively, the two steel wire ropes are connected with one lever system respectively, and the two lever systems are connected to different loading lines on the outer flap through adhesive tape.

5. The low-cost test device for the flap system of the unmanned aerial vehicle as claimed in claim 4, wherein a plurality of stay wire type displacement sensors are arranged between the wing dummy and the ground for measuring the normal displacement of each section of the wing dummy;

6. A flap flight load simulation method meeting engineering error requirements, which is characterized in that the low-cost test device for the flap system of the unmanned aerial vehicle is based on any one of claims 1 to 5 and comprises the following steps:

meanwhile, the number of the adhesive tapes is adjusted to reduce the test load of a single adhesive tape and simulate the distribution condition of the flap flight load;

meanwhile, the span-wise occupying change of the pneumatic pressure center caused by the deflection of the flap under the flight working condition is small, the span-wise occupying of the steel wire rope is taken as the span-wise occupying midpoint of the load resultant force of each flight working condition of the inner flap and the outer flap, and the length of the steel wire rope is adjusted to ensure that the loading error caused by the span-wise occupying error is less than 5%;

meanwhile, the occupation in the chord length direction of a loading resultant force action point is controlled to be dynamically consistent with the wing flap flying load resultant force by adjusting the load sizes of the two loading lines;

meanwhile, in the deflection process of the flap, the second position control actuator cylinder controls the guide slide block to move along the guide slide rail so as to change the direction of the steel wire rope, and the load loading directions of the two loading lines are dynamically consistent with the resultant force direction of the flying load of the flap.

7. A method for simulating real wing global deformation through a wing dummy, which is characterized in that the low-cost test device for the flap system of the unmanned aerial vehicle based on any one of claims 1-5 comprises:

and step S3: calculating the deformation error and intersection point load error of the real wing and the wing dummy piece, and judging whether the deformation error and the intersection point load error are less than 5%; if the deformation rate is less than 5%, the wing dummy piece can simulate the global deformation of the wing, so that the test requirement is met, the dummy piece can be manufactured and tested, the step S4 is skipped, and the step S5 is carried out; otherwise, performing the step S4;

and step S4: adjusting the rigidity of the wing dummy piece; according to the analysis of the deformation error and the intersection point load error, adjusting the section torsional rigidity of the wing dummy piece or the mounting support rigidity of the back beam sliding rail to ensure that the wing deformation and the intersection point load error are less than 5 percent;

8. The method for simulating the global deformation of the real wing by the wing dummy according to claim 7, wherein the step S1 comprises:

step S12: extracting all-directional displacement of the front and rear beam edge strips of the real wing at the mounting sections of the four slide rails of the inner flap and the outer flap and at the occupying position of the forced displacement loading rib of the wing dummy; the each-directional displacement includes: spanwise displacement, course displacement and normal displacement;

step S13: calculating a real wing section torsion angle at the mounting position of the slide rail, a rotation angle at the mounting position of the back beam slide rail, wing deflection difference and section torsion angle difference at the inner slide rail and the outer slide rail of the single flap, and extracting the mounting intersection point load of the back beam flap slide rail;

the step S2 includes:

step S21: calculating the normal displacement of the front beam edge strip of the wing dummy at the two forced displacement loading ribs by utilizing the deformation data linear interpolation of the real wing front beam edge strip, and forming a normal forced displacement spectrum of the wing dummy of the test system by combining the normal displacement of the real wing rear beam edge strip extracted in the step S12 at the occupying position of the wing dummy forced displacement loading ribs;

step S23: extracting all-directional displacements of the front and rear beam edge strips of the wing dummy at the four mounting sections of the inner and outer wing flap sliding rails under various working conditions and the load of the wing flap sliding rail mounting intersection point of the rear beam of the wing dummy of the test system from the analysis result in the step S22; the each-directional displacement includes: spanwise displacement, course displacement and normal displacement;

step S24: calculating a section torsion angle of a wing dummy piece at the slide rail installation position of the flap test system, a rotation angle of an installation occupation position of a wing dummy piece back beam slide rail, and a wing dummy piece deflection difference and a section torsion angle difference at the inner slide rail and the outer slide rail of a single flap;

the step S5 includes:

step S51: carrying out a preliminary test on the severe working condition of wing deformation, and passing four first position controls during the testThe actuator cylinder applies the normal forced displacement spectrum of the wing dummy piece formed in the step S21 to the two sections of the wing dummy piece in a coordinated manner; and at the flap in take-off skewness

And landing skewness

Measuring the normal displacement of the wing dummy piece at the mounting sections of the four sliding rails of the inner flap and the outer flap and at the position where the wing dummy piece is forced to displace and load the occupying part of the rib at the position;

9. A flap system function test method, characterized in that, based on any one of claims 1-5, the low-cost test device for the flap system of the unmanned aerial vehicle comprises:

and B: after adjusting the inner and outer flaps to zero deflection and guiding the sliding block to a corresponding initial position, eliminating the deformation of the wing dummy part caused by the self weight of the test system through a first position control actuator cylinder connected with the wing dummy part, and setting the measurement system and the loading system to zero;

step C: operating an MTS multi-channel coordinated loading control system, triggering a driving unit PDU to drive a flap to move according to a flap moving program in a take-off stage, carrying out real-time coordinated synchronous loading on forced displacement of a wing fake part and test loads of an inner flap and an outer flap according to a real-time measurement result of the elongation delta L of a lead screw of a ball screw actuator corresponding to the inner flap and the outer flap, and completing take-off moving operation when the flap returns to a zero-deviation position;

step E: repeating the test operations of the step B to the step D for 6 times to obtain 1 group of functional tests, and carrying out 3 groups of functional tests in total;

step G: and further, repeating the functional test of the flap system in the steps B to D for 4 multiplied by 12000 times, judging the success or the failure of each functional test according to the functional realization condition and the motion rule conforming condition of the flap system, and calculating the functional reliability of the flap system.

10. The flap system function test method according to claim 9, wherein the judgment in the step F comprises:

the judgment basis that the flap system can realize the design function is as follows:

if the drive unit PDU can drive the flap system test piece to smoothly complete the 3 groups of function tests in the step E within the specified time, the phenomenon of unsmooth movement or clamping stagnation does not exist, and the states of the take-off skewness and the landing skewness of the flap can be kept for 1 minute or more respectively, the flap system is judged to realize the design function;

the judgment basis that the motion rule of the flap system meets the design requirement is as follows:

if the screw rods of the two actuating cylinders of the inner flap can synchronously extend to push the inner flap to move, the screw rods of the two actuating cylinders of the outer flap can keep equal proportion to extend to push the outer flap to move, and the deflection angle error of the inner flap and the outer flap is less than or equal to 3 percent, the motion rule of the flap system is judged to meet the design requirement.