CN109490114B - Full-size fatigue test flap load loading method - Google Patents
Full-size fatigue test flap load loading method Download PDFInfo
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- CN109490114B CN109490114B CN201811520576.5A CN201811520576A CN109490114B CN 109490114 B CN109490114 B CN 109490114B CN 201811520576 A CN201811520576 A CN 201811520576A CN 109490114 B CN109490114 B CN 109490114B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
Abstract
The invention belongs to the technical field of fatigue tests, and relates to a full-size fatigue test flap load loading method. According to the method, from the technical field of fatigue tests, according to the force transmission characteristics of the three-slit flap, the flap fatigue loads of a plurality of components in various angle states are all processed to be applied in the main direction of the main bearing component under the key angle theta. And aiming at the distribution load characteristics and the structural characteristics of the main bearing part, the partition processing is carried out, according to the principle that the design state of the connecting point of the flap and the wing and the test state are not larger than a target error and the fatigue damage of the check part is equivalent, the optimal flap load applying scheme is realized through iterative calculation on the basis of ensuring the accuracy of the flap in the load transmission and check on the wing, namely, the number of actuating cylinders is minimum under the same effect. The method has the advantages of correct theoretical basis, clear and simple analysis steps and convenient computer automatic iterative computation in the computation process.
Description
Technical Field
The invention belongs to the technical field of fatigue tests, and relates to a full-size fatigue test flap load loading method.
Background
The flap is an important high lift device of an airplane structure, for a large airplane, in order to pursue a high lift coefficient, the flap adopts a three-slit flap which comprises an inner front flap, an inner main flap, an inner rear flap, an outer front flap, an outer main flap and an outer rear flap, the flap is connected with the wing, the damage safety is considered, a structure without multiple force transmission paths is designed, and the flap needs to swing at different positions due to different aerodynamic requirements of the airplane in different stages such as take-off, cruise, landing/fly-back and the like. The flaps are therefore complex in structure and movement, resulting in a complex load. In the verification test planning of the structural life of the airplane, a fatigue test of a flap part is generally arranged for checking the service life of a flap structure and a mechanism, and a full-airplane fatigue test is arranged for checking the main structures of the airplane such as wings and a fuselage. In the full-aircraft fatigue test, if the flap load is applied according to the actual situation, huge manpower and material resources are consumed, more importantly, the time cost is greatly increased, the service life evaluation of the aircraft is delayed, and the flight safety is influenced.
At present, most of all-aircraft tests at home and abroad mostly adopt a mode of applying bending moment of the flap on the wing in order to simplify the loading of the flap, the total load is accurate, but wing boxes between ribs corresponding to the connection of the flap and the connection joints of the wing and the flap are not checked really, and component tests cannot effectively check the checked parts, so that the checking of the fatigue performance of the aircraft structure is influenced, and the authenticity of the service life evaluation is further influenced. Therefore, in the full-aircraft fatigue test, how to simply and accurately apply the fatigue load of the flap on the premise of meeting the assessment requirement is very important.
Disclosure of Invention
The purpose of the invention is: a full-scale fatigue test flap load loading design method can simply and accurately apply a flap fatigue load so as to solve the technical problem that the application complexity of the flap load is contradictory to the checking authenticity.
In order to solve the technical problem, the technical scheme of the invention is as follows:
according to the technical field of fatigue tests, according to the force transmission characteristics of a three-slit flap, flap fatigue loads of a plurality of components in various angle states are all processed to be under a key angle theta, a main bearing component is used, and the loading is applied in the main direction. And aiming at the distribution load characteristics and the structural characteristics of the main bearing part, the design load applying scheme of the flap is optimized through iterative calculation according to the principle that the main direction load error of the flap and wing connecting point in the design state and the test state is not more than the target error and the fatigue damage of the check part is equivalent, and on the basis of ensuring the accuracy of the flap in the load transmission and check of the wing.
The full-size fatigue test flap load loading method comprises the following specific steps:
1. analyzing fatigue load characteristics of each component of the three-slit flap, and determining a main bearing component with the maximum fatigue load, a key angle theta and a main direction;
2. the fatigue loads of all parts are equivalent to the main bearing part under the key angle theta according to the minimum strain energy theory, and the error before and after the equivalence is calculated;
3. according to the structure and the force transmission characteristics, under the state of a key angle theta, the main bearing component distributes load subareas, and the pressure center distribution of the fatigue load distributed load under each fatigue load working condition in each subarea is calculated;
4. analyzing the load pressure center distribution of each fatigue load working condition in each partition, and preliminarily determining the load points and the load sizes of each partition of the main bearing component by taking the load sizes of each fatigue working condition and the contribution to the rise and fall damage as weights;
5. carrying out full-machine solution according to the initial loading point and the load size, and confirming the main direction load error of the design state and the test state of the connecting point of the flap and the wing under the key angle theta;
6. iteratively calculating and determining the load coefficient of each loading point until the main direction load error of the design state and the test state of the flap and wing connection point meets the target load error under the state of the key angle theta;
7. fatigue comparison analysis is carried out on the key structure of the examination and the load transmission, the design state is confirmed to be equivalent to the test implementation state, the fatigue damage is equivalent, and the number of the loading actuating cylinders is minimum;
8. calculating the unbalance amount between the design state and the test state of the connecting point of the wing flap and the wing, and equivalently processing the unbalance amount to the corresponding ribs of the wing box of the wing according to the corresponding load transmission relationship.
The step 6 specifically comprises the following steps:
and determining the load coefficient of each loading point according to the main direction load error calculated in the previous step, wherein the specific method comprises the following steps: 1-main direction load error%, and re-performing full-machine solution and error calculation, wherein if the main direction load error of the design state and the test state of a connecting point of the flap and the wing is under a key angle theta, and if the requirement of a load target error is met, performing the next step, and if the load coefficient is not adjusted, performing iterative calculation.
The step 7 specifically comprises the following steps:
according to the assessment part determined by the full-machine fatigue test mission book, calculating the DFR value of the key structure for assessment and load transmission, carrying out fatigue analysis, and confirming that the fatigue damage of the key structure in the design state is equivalent to that in the test implementation state and the number of the loading actuating cylinders is minimum; if not, iterating the calculation from step 3.
The method for judging the minimum number of the loading actuating cylinders comprises the following steps:
if the state impairment after the current number of rams-i is comparable to the state impairment of the current number of rams, the number of rams may be reduced, otherwise the number of rams may not be reduced, which is the minimum number of rams, where i is any integer less than the current number of rams.
The invention has the beneficial effects that: the invention provides a simple and accurate full-size fatigue test flap load loading method, which treats flap fatigue loads of a plurality of components in various angle states to be applied in the main direction of a main bearing component under a key angle theta according to the force transmission characteristics of a three-slit flap from the technical field of fatigue tests. And aiming at the distribution load characteristics and the structural characteristics of the main bearing part, the partition processing is carried out, according to the two principles that the load error in the main direction of the design state and the test state of the connecting point of the flap and the wing is not more than the load target error and the fatigue damage of the check part is equivalent, the optimal design flap load applying scheme is realized on the basis of ensuring the accuracy of the flap in the load transmission and check on the wing through iterative calculation, namely, the number of actuating cylinders is minimum under the same effect. The calculation process of the invention is convenient for computer automated iterative calculation.
Drawings
FIG. 1 is a flow chart of a method of the present invention;
FIG. 2 is a schematic view of a left flap key angle determination;
FIG. 3 is a schematic view of a left inner flap loading scheme.
Detailed Description
The invention is further illustrated with reference to the following figures and examples:
according to the full-scale fatigue test flap load loading method, from the technical field of fatigue tests, according to the force transmission characteristics of the three-slit flap, the flap fatigue loads of a plurality of components in various angle states are all processed to be applied in the main direction of the main bearing component under the key angle theta. And aiming at the distribution load characteristics and the structural characteristics of the main bearing part, the design load applying scheme of the flap is optimized through iterative calculation according to the principle that the main direction load error of the flap and wing connecting point in the design state and the test state is not more than the target error and the fatigue damage of the check part is equivalent, and on the basis of ensuring the accuracy of the flap in the load transmission and check of the wing.
The method is applied to the flap load loading design of a certain type of airplane full-aircraft fatigue test, and the specific steps of loading the flap are specifically described as follows:
1. analyzing fatigue load characteristics of each component of a three-slit flap of a certain type of airplane, and determining a main bearing component with the maximum fatigue load, a key angle theta and a main direction:
analyzing fatigue load characteristics of each part of a three-slit flap of a certain airplane, and confirming that the fatigue load of all the fatigue load working conditions of an inner flap and an outer flap is a main flap which is the main force bearing part at the maximum in a total of 195 types under the same angle; confirming that the fatigue load is the maximum landing configuration of the flap under all the fatigue load working conditions of the inner flap and the outer flap under the same component, wherein the critical angle theta is 37 degrees; and confirming that the maximum fatigue load direction is normal and the load is vertical to the airfoil surface under all fatigue load working conditions of the inner flap and the outer flap in all angle states, wherein the schematic diagram is shown in FIG. 2.
2. And (3) carrying out main bearing on the parts under the condition of equivalence to a key angle theta by fatigue loads of all the parts together according to a minimum strain energy theory, and calculating errors before and after equivalence:
the aerodynamic distribution load of the front flap, the main flap and the rear flap in the states of 0 degrees, 21 degrees and 37 degrees of the flap in a local coordinate system is converted into a full-machine coordinate system, the aerodynamic distribution load and the inertial distribution load are equivalent to the upper wing surfaces of the inner flap and the outer flap at the key angle of 37 degrees according to the minimum strain energy theory, the equivalent front and rear errors are calculated, the total load error is not more than 3 percent, the load distribution has certain change, and the error values are calculated for 0 degrees, 21 degrees and 37 degrees.
3. As the wing surface of the main flap is of a rib-thinning structure, the load is transmitted to the wing box section through the three slide rails, so that the distributed load is divided into 3 regions, and the pressure center distribution of the fatigue load distributed load in each region under the working condition is calculated.
4. Analyzing the load pressure center distribution of each fatigue load working condition in each subarea, preliminarily determining 6 areas of the main bearing part by taking the load size of each fatigue working condition and the contribution to the rise and fall damage as weights, and calculating the loading point and the load size of each subarea:
analyzing the load pressure center distribution of each fatigue load working condition in each subarea, mainly determining the loading point and the load size of each subarea by taking the fatigue working conditions corresponding to the mission sections of the flap lowering approach, the roll maneuver and the yaw maneuver in the 37-degree state and combining the fatigue load working condition weights in other angle states, wherein the number of the actuating cylinders in the primary scheme is 6 respectively.
5. Converting the preliminarily determined load and the loading position thereof into a FORCE card for NASTRAN calculation, and carrying out full-machine solution to obtain normal load errors of front and rear points of connection of the flap 1#, 2#, 3# slide rails and the wing;
6. determining the load coefficient of each loading point to be 1-main direction load error according to the main direction load error calculated in the previous step, carrying out full-machine solution and error calculation again, if the main direction load error of the design state and the test state of the connecting point of the flap and the wing meets the requirement of load target error under the key angle theta, carrying out the next step, if the load coefficient is not adjusted, carrying out iterative calculation:
according to the calculated normal load error, preliminarily determining the load coefficient of each loading point, wherein the number of actuating cylinders is 1.02, 1.05, 1.0, 1.2, 1.0 and 1.1, namely the coefficient with large error is reduced and the coefficient with small error is increased, aiming at approaching to a reference 1, carrying out full-machine solution again, calculating the error of the connecting point of the flap and the wing to be 8 percent, which does not meet the requirement, confirming the load coefficient again, carrying out iterative calculation, and finally confirming that the error of the normal load of the design state and the test state of the connecting point of the flap and the wing is 3 percent and meets the requirement of target error of 5 percent when the load coefficient is 1.05, 1.0, 1.05, 1.1, 1.2 and 1.1.
7. Fatigue comparison analysis is carried out on the key structure of the examination and the load transmission, the design state is confirmed to be equivalent to the test implementation state, the fatigue damage is equivalent, and the number of the loading actuating cylinders is minimum; the judgment conditions are as follows: if the state impairment after the current number of rams-i is comparable to the state impairment of the current number of rams, the number of rams may be reduced, otherwise the number of rams may not be reduced, which is the minimum number of rams, where i is any integer less than the current number of rams
Calculating the DFR value of the lug of the front and rear structure of the connection of the flap 1#, 2#, 3# slide rails and the wing, wherein the formula is DFR ═ DFRbase·K·B·Lt·Ld·Ls·Lθ·RCAnd the calculation results are respectively 121MPa, 116MPa and 95MPa, fatigue comparison analysis is confirmed, the maximum change of the fatigue margin is confirmed to be the joint of the 2# slide rail and the front lug plate connected with the wing, 0.56 is changed into 0.61, the requirement is met, but the number of the actuating cylinders is not met by 6 actuating cylinders through analysis.
Therefore, from the iteration of the step 4, the main flap is changed into 3 subareas again, 1 actuator cylinder is used for each, the load scheme of 3 actuator cylinders is finally calculated, the error is 4 percent, the target error of 5 percent is met, the fatigue margin 0.56 is changed into 0.62, the equivalent damage requirement is met, and the number of the actuator cylinders is judged to be the minimum.
8. Determining a flap loading scheme, calculating the load unbalance amount of front and rear points of the connection of the flaps 1#, 2#, 3# slide rails and the wings as shown in fig. 3, and equivalently processing the load unbalance amount to wing boxes of the wings according to the rib positions corresponding to the slide rails.
The design method for loading the wing flap load in the full-size fatigue test is successfully used for the full-aircraft fatigue test of a certain type of airplane, realizes the optimal designed wing flap load application scheme on the basis of ensuring the accuracy of the wing flap in the load transmission and examination, and solves the technical problem that the complexity of the wing flap load application is contradictory to the authenticity of the examination.
Claims (4)
1. A full-scale fatigue test flap load loading method is characterized in that: according to the flap load loading method, flap fatigue loads of a plurality of components in various angle states are all processed to be applied to a key angle theta, a main bearing component and a main direction; partitioning the main bearing part, and applying a flap load according to the principle that the load error in the main direction of a connecting point of the flap and the wing is not more than a target error and the fatigue damage of an assessment part is equivalent to two; the method comprises the following specific steps:
1.1, analyzing fatigue load characteristics of each component of the three-slit flap, and determining a main bearing component with the maximum fatigue load, a key angle theta and a main direction;
1.2, enabling fatigue loads of all parts to be equivalent to main bearing parts under a key angle theta, and calculating equivalent front and rear errors;
1.3, according to the structure and force transmission characteristics, dividing the load distribution of the main bearing component in a key angle theta state into subareas, and calculating the pressure center distribution of the fatigue load distribution load in each subarea under the working condition of each fatigue load;
1.4, preliminarily determining the loading points and the loads of all the subareas of the main bearing part by taking the load magnitude of each fatigue working condition and the contribution to the rise and fall damage as weights;
1.5, carrying out full-machine solution according to the initial loading point and the load size, and confirming the main direction load error of the design state and the test state of the connecting point of the flap and the wing under the key angle theta;
1.6, iteratively calculating and determining the load coefficient of each loading point until the main direction load error of the design state and the test state of the connecting point of the flap and the wing meets the target load error under the state of the key angle theta;
1.7, carrying out fatigue comparative analysis on the key structure of the examination and the load transmission, and confirming that the design state is equivalent to the test implementation state, the fatigue damage is equivalent, and the number of the loading actuating cylinders is minimum;
and 1.8, calculating the unbalance amount of the design state and the test state of the connecting point of the flap and the wing, and equivalently processing the unbalance amount to the corresponding ribs of the wing box of the wing according to the corresponding load transmission relationship.
2. The full-scale fatigue test flap load loading method of claim 1, characterized in that: the step 1.6 is specifically as follows:
according to the load error in the main direction calculated in the step 1.5, the load coefficient of each loading point is preliminarily determined as follows: 1-main direction load error%, carrying out full-machine solution and error calculation again, if the main direction load error of the design state and the test state of the connecting point of the flap and the wing under the key angle theta meets the requirement of a load target error, carrying out the next step, and if the load coefficient is not adjusted, carrying out iterative calculation.
3. The full-scale fatigue test flap load loading method of claim 1, characterized in that: the step 1.7 is specifically as follows:
according to the assessment part determined by the full-machine fatigue test mission book, calculating the DFR value of the key structure for assessment and load transmission, carrying out fatigue analysis, and confirming that the fatigue damage of the key structure in the design state is equivalent to that in the test implementation state and the number of the loading actuating cylinders is minimum; if not, step 1.3.
4. The full-scale fatigue test flap load loading method of claim 3, wherein: the method for judging the minimum number of the loading actuating cylinders comprises the following steps:
if the state impairment after the current number of rams-i is comparable to the state impairment of the current number of rams, the number of rams may be reduced, otherwise the number of rams may not be reduced, which is the minimum number of rams, where i is any integer less than the current number of rams.
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| CN109977556B (en) * | 2019-03-28 | 2023-04-07 | 中国飞机强度研究所 | Load optimization method based on least square method |
| CN111422375B (en) * | 2020-04-15 | 2023-04-18 | 中国飞机强度研究所 | Active control method and system for load of vertical constraint point of airplane |
| CN113138068B (en) * | 2021-03-31 | 2023-09-05 | 中国飞机强度研究所 | Fatigue test device and method for flap movement mechanism |
| CN113720707B (en) * | 2021-08-23 | 2023-09-05 | 中国飞机强度研究所 | Design method for large deformation loading point of structural fatigue test |
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