CN118182861A - Yaw fatigue rolling test method and device for aircraft wheel - Google Patents
Yaw fatigue rolling test method and device for aircraft wheel Download PDFInfo
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Abstract
The invention relates to a yaw fatigue rolling test method and device for an aircraft wheel, belonging to the technical field of fatigue rolling tests for aircraft wheels; the method comprises the following steps: performing fatigue test on the wheel to be tested according to the setting; collecting side load and radial load, and calculating the side-to-diameter ratio; drawing a yaw angle-side diameter ratio curve, and fitting to obtain a linear relationship between the yaw angle and the side diameter ratio; calculating a predicted yaw angle when the side diameter ratio is a target value, and performing a yaw fatigue rolling test under the predicted yaw angle to obtain a corresponding actual side diameter ratio; determining an effective yaw angle of the side-to-diameter ratio within a target value tolerance range; drawing a curve of the side diameter ratio and the rolling distance under the effective yaw angle, and fitting to obtain a linear relation of the side diameter ratio and the rolling distance; calculating an effective rolling distance interval of the side diameter ratio within a target value tolerance range, namely determining an effective rolling distance; and finishing the examination target. The invention overcomes the defect that the prior art can not meet the requirement of the side diameter ratio in the yaw fatigue rolling test of the aircraft wheel.
Description
Technical Field
The invention belongs to the technical field of aircraft wheel fatigue rolling tests, and particularly relates to an aircraft wheel yaw fatigue rolling test method and device.
Background
The life of an aircraft wheel is primarily affected by its operational load size, tire pressure increases due to tire heating, and corrosion sites in critical areas of the wheel. To ensure wheel safety, two factors must be met. Firstly, aircraft wheels must have reached the expected fatigue life in the qualification test and secondly, in the event of defects such as corrosion pits, the retarded crack propagation speed is slow enough that a crack is detected before failure occurs. The fatigue rolling test specified in the national aviation wheel test standard GJB 1184A-2010 and CTSO-C135a requires the working conditions of inward deflection and outward deflection of the aircraft. The factors forming the fatigue test under the working condition are many, and when the crucian back phenomenon exists on the road or the lateral wind force is large, the machine body can generate certain lateral deviation; for a braking pair, if the initial selection is improper or the abrasion is uneven, the difference value between the left braking moment and the right braking moment is larger, and the side deviation can also occur; when the aircraft turns, lateral forces are generated, and in the U.S. wheel characteristic report, it can be seen that the lateral forces are generated with radial loads during the turn. The lateral force generated by the aircraft can be transmitted to the aircraft wheel through the tire shoulder, tire wall and other parts of the tire, and the aircraft wheel can bear the lateral force in rolling, so the fatigue rolling test under the inward deflection and outward deflection working conditions is an important test in the aircraft wheel identification test.
At present, the fatigue rolling test under the working conditions of inward deflection and outward deflection is carried out at home, namely, a machine wheel shaft and a drum wheel shaft are deflected by an angle to form a side deflection angle, and a side load is generated through vector decomposition of a vertical force, so that the requirement that the side diameter ratio in GJB 1184A is equal to 0.25 (civil aircraft is 0.15) is met, the fatigue rolling mode of the side deflection is described in the literature of an aircraft wheel diameter side combined load test and rolling test side loading analysis, T is a hydraulic cylinder load, Y is a radial load, N is a reaction force of the drum wheel to the machine wheel, f is a friction force of the drum wheel to the machine wheel, fy is a side force applied to the machine wheel, and alpha is a yaw angle. FIG. 4 is a plot of yaw-to-roll ratio versus yaw angle for an aircraft wheel under a design rated load, where the abscissa represents the yaw angle and the ordinate is the ratio of the lateral load to the radial load.
FIG. 5 is a graph of side diameter ratio versus roll distance in the standard SAE ARP 4955A recommended practice guidelines for static and dynamic characterization of aircraft tires, where the ordinate is the side diameter ratio and the abscissa is the ratio of roll distance to tire diameter, and the yaw angles from high to low are 18 °, 15 °, 12 °, 9 °,6 °,3 degrees in order. FIG. 6 is a plot of lateral force versus yaw angle for a standard SAE AIR 5797 program development and implementation for laboratory testing of aircraft tire wear, where the ordinate is the side load and the abscissa is the yaw angle value. Side loads can be generated by applying yaw angles in both documents, but are not applied in the field of aircraft wheel yaw fatigue roll tests.
As can be seen by comparing fig. 4 with fig. 5 and fig. 6, in the actual fatigue rolling test, the fatigue rolling cannot be performed simply according to the wheel yaw method shown in fig. 3.
The deep analysis is carried out by combining the practical contralateral fatigue rolling test results, which can be known as follows: the side loads generated by the aircraft wheels during rolling are due to friction of the wheels with the drum or the ground, the conclusion of which is described in the civil aviation standard CTSO-C26C. During the rolling process of the wheels, because the braking force which can be provided to the wheels by the tires is limited, when the aircraft has a sideslip or turning trend, the drum wheel or the ground force must apply a certain lateral reaction force to the wheels so as to promote the aircraft to reach the balance of the lateral force. As can be seen from the analysis of the previous FIGS. 3 and 4, the lateral force generated by the lateral fatigue rolling test is composed of the components of the ground reaction force and the friction force applied by the wheel, and deviates from the standard CTSO-C26C; while the lateral force generated by yaw rolling is only composed of the component of friction experienced by the wheels. Different models of wheels and tires can reach a side-to-side ratio of 0.25 (0.15) at a yaw angle of a few degrees, and the yaw angle and the side-to-side ratio should be calculated and processed by what method. The invention provides a yaw fatigue rolling test method for an aircraft wheel, by which a side diameter ratio of 0.25 (0.15) times can be generated, and a relatively accurate unique yaw angle can be found.
Disclosure of Invention
The technical problems to be solved are as follows:
In order to avoid the defects of the prior art, the invention provides a yaw fatigue rolling test method and a yaw fatigue rolling test device for an aircraft wheel, wherein the method is characterized in that the linear relation between a yaw angle and a side diameter ratio is fitted through a yaw angle-side diameter ratio curve, the linear relation between the side diameter ratio and a rolling distance is fitted through a side diameter ratio-rolling distance curve, and then the effective yaw angle and the rolling distance of the side diameter ratio under a target value (0.25/0.15) are obtained through calculation and correction; the invention overcomes the defect that the prior art can not meet the requirement of the side diameter ratio in the yaw fatigue rolling test of the aircraft wheel.
The technical scheme of the invention is as follows: a yaw fatigue rolling test method for an aircraft wheel comprises the following specific steps:
Mounting a wheel to be tested on a three-dimensional force measuring platform;
The radial load force application module applies set radial load to the wheel to be tested, and a yaw mode is adopted to carry out a wheel fatigue test of a yaw angle in a set range;
The method comprises the steps of collecting real side load and radial load generated in the test process through a force load sensor, and calculating corresponding side-to-diameter ratio; the side diameter ratio is equal to the ratio of the side load to the vertical load;
drawing a yaw angle-side diameter ratio curve, and fitting to obtain a linear relationship between the yaw angle and the side diameter ratio;
calculating a predicted yaw angle when the side diameter ratio is a target value through a linear relation of the yaw angle and the side diameter ratio, and performing a yaw fatigue rolling test under the predicted yaw angle to obtain a corresponding actual side diameter ratio;
judging whether the actual side diameter ratio is within a tolerance range of a target value, if the actual side diameter ratio is beyond the tolerance range, correcting the predicted yaw angle until the corresponding actual side diameter ratio meets the requirement, namely determining an effective yaw angle of the side diameter ratio within the tolerance range of the target value;
drawing a curve of the side diameter ratio and the rolling distance under the effective yaw angle, and fitting to obtain a linear relation of the side diameter ratio and the rolling distance;
calculating an effective rolling distance interval of the side diameter ratio within a target value tolerance range through a linear relation between the side diameter ratio and the rolling distance, namely determining the effective rolling distance;
and carrying out a wheel fatigue test by adopting the determined effective yaw angle and the determined effective rolling distance to finish the assessment target.
The invention further adopts the technical scheme that: when the yaw mode is adopted for carrying out the fatigue test of the machine wheels, the set range of the yaw angle is-5 degrees to +5 degrees.
The invention further adopts the technical scheme that: the linear relation between the yaw angle and the side diameter ratio is as follows:
SDR＝kx+α
wherein SDR is the side-to-diameter ratio; x is the yaw angle; k is the slope of the curve; alpha is the deflection of the side load caused by steering, conicity of the tire cord layer and asymmetry of the tire.
The invention further adopts the technical scheme that: the tolerance of the target value 0.25 of the side diameter ratio is +/-0.025, namely the actual side diameter ratio is between 0.225 and 0.275, which meets the requirement.
The invention further adopts the technical scheme that: the method for correcting the predicted yaw angle comprises the following steps:
When SDR true is more than 0.275, performing yaw fatigue rolling test under the yaw angle x-a, and stopping the test if SDR true is obtained to be within the [0.225,0.275] interval; if the SDR true is still larger than 0.275, continuing the yaw fatigue rolling test under the yaw angle x-a-b, if the SDR true is obtained to be within the [0.225,0.275] interval, stopping the test, otherwise, continuing to repeat the process;
When SDR true is less than 0.225, performing yaw fatigue rolling test under the yaw angle x+c, and stopping the test if SDR true is obtained to be within the [0.225,0.275] interval; if the SDR true is still smaller than 0.225, continuing the yaw fatigue rolling test under the yaw angle x-c-d, if the SDR true is obtained to be within the [0.225,0.275] interval, stopping the test, otherwise, continuing to repeat the process;
wherein a, b, c, d is a yaw angle correction coefficient set according to a deviation of the actual side diameter ratio from a side diameter ratio target value.
The invention further adopts the technical scheme that: the yaw angle correction coefficients a, c are 0.5, and b, d are 0.25.
The invention further adopts the technical scheme that: the linear relation between the side diameter ratio and the rolling distance is as follows:
L＝(SDR-β)/k’
Wherein: SDR is the side diameter ratio; l is the effective roll distance; k' is the slope of the curve; beta is the curve intercept.
An aircraft wheel driftage fatigue rolling test device which is characterized in that: the device comprises a three-dimensional force measuring platform, an inclination angle sensor and a radial load force application module;
The three-dimensional force measuring platform is used as a rotatable carrying platform of the machine wheel to be measured, and can measure the lateral load, the heading load and the radial load of the machine wheel to be measured;
The radial load force application module applies radial load to the wheel to be tested;
the inclination sensor is used for measuring the yaw angle of the machine wheel to be measured.
The invention further adopts the technical scheme that: the three-dimensional force measuring platform comprises a base, a loading head, a force bearing seat and a hydraulic cylinder, wherein the base is arranged on the test bed; the hydraulic cylinder is installed along the tangential direction of the periphery of the base, the output end of the hydraulic cylinder is hinged with the periphery of the base, and the base is driven to rotate through telescopic control:
Three-way force load sensors are fixedly arranged between the bearing seat and the base, and the four three-way force load sensors are arranged on the table top of the base in a square array.
The invention further adopts the technical scheme that: the output signals of the four three-way force load sensors S 1,S2,S3,S4 are Fx1、Fy1、Fz1、Fx2、Fy2、Fz2、Fx3、Fy3、Fz3、Fx4、Fy4、Fz4, respectively, which represent load values of the four sensors S 1,S2,S3,S4 in the X, Y, Z three directions respectively; the sensor always keeps the same posture as the machine wheel, and the loads in X, Y, Z directions are respectively as follows:
Fx＝Fx1+Fx2+Fx3+Fx4 (1)
Fy＝Fy1+Fy2+Fy3+Fy4 (2)
Fz＝Fz1+Fz2+Fz3+Fz4 (3)
Where F x is the heading load, F y is the side load, and F z is the radial load.
Advantageous effects
The invention has the beneficial effects that: according to the invention, the linear relation between the yaw angle and the side diameter ratio is fitted through the yaw angle-side diameter ratio curve, the real side diameter ratio can be calculated by adopting the linear relation between the yaw angle and the side diameter ratio, and then the effective yaw angle can be determined by correcting the yaw angle so that the side diameter ratio is within the tolerance range of the target value; and fitting a linear relation between the side diameter ratio and the rolling distance through a side diameter ratio-rolling distance curve, and calculating to obtain the effective rolling distance of the side diameter ratio under the target value, so that fatigue tests with the side diameter ratio of different models of wheels and tires as the target value can be carried out.
Compared with the existing fatigue rolling technology, the yaw type fatigue rolling test has the characteristics that the lateral force value is stable, the lateral diameter ratio can meet the standard requirement, and the like.
Because the aircraft has different friction characteristics of the tire under different speeds, different loads and different combination coefficients, the working steps according to the invention under different conditions can obtain more accurate lateral force and lateral diameter ratio, so that the fatigue rolling test achieves the required assessment target, namely the lateral diameter ratio=0.25 (0.15).
The test device comprises a three-dimensional force measuring platform (a measuring platform for lateral load, radial load and radial load of a machine wheel), an inclination angle sensor and the like, wherein the three-dimensional force measuring platform can synchronously yaw rotation with a loading head, and the lateral load value F y1、Fy2、Fy3、Fy4 output by four signals is overlapped to obtain the lateral load born by the machine wheel.
In conclusion, the fatigue rolling test method can effectively check the fatigue rolling test of the aircraft wheel, and can truly evaluate the reliability and fatigue resistance of the aircraft wheel. The invention can be widely applied to fatigue rolling tests of aircraft wheels.
Drawings
FIG. 1 is a front view of a stereoscopic force measurement platform of the present invention.
FIG. 2 is a schematic view of a test bed loading head of the present invention.
Fig. 3 is a schematic diagram of a rolling mode of cornering fatigue in the background art.
FIG. 4 is a graph of yaw-fatigue-roll test for aircraft wheels under a designed rated load versus a yaw angle, wherein the abscissa represents the yaw angle and the ordinate is the ratio of the lateral load to the radial load.
FIG. 5 is a plot of side-to-roll distance in the background of the invention standard SAE ARP 4955A recommended practice guidelines for aircraft tire static and dynamic characteristics testing.
FIG. 6 is a plot of lateral force versus yaw angle for a standard SAE AIR 5797 program development and implementation for laboratory testing of aircraft tire wear in the background art.
FIG. 7 is a flow chart of a yaw fatigue rolling test method for an aircraft wheel.
FIG. 8 is a yaw angle-to-side aspect ratio curve (yaw angle on the abscissa and side aspect ratio on the ordinate) for an embodiment of the present invention.
FIG. 9 is a graph of roll distance versus side diameter ratio (roll distance on the abscissa and side diameter ratio on the ordinate) for an embodiment of the present invention.
Reference numerals illustrate: 1. the hydraulic machine comprises a fixed pin shaft, a base, an inclination angle sensor, a hydraulic cylinder, a loading head, a bearing seat, a three-way force load sensor and a wheel to be tested.
Detailed Description
The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Based on the problems in the prior art, the invention provides an aircraft wheel yaw fatigue rolling test method, which comprises the following specific steps:
step 1: mounting a wheel to be tested on a three-dimensional force measuring platform;
Step 2: the radial load force application module applies set radial load to the wheel to be tested, and a yaw mode is adopted to carry out a wheel fatigue test of a yaw angle in a set range;
Step 3: the method comprises the steps of collecting real side load and radial load generated in the test process through a force load sensor, and calculating corresponding side-to-diameter ratio; the side diameter ratio is equal to the ratio of the side load to the vertical load;
Step 4: drawing a yaw angle-side diameter ratio curve, and fitting to obtain a linear relationship between the yaw angle and the side diameter ratio;
Step 5: calculating a predicted yaw angle when the side diameter ratio is a target value through a linear relation of the yaw angle and the side diameter ratio, and performing a yaw fatigue rolling test under the predicted yaw angle to obtain a corresponding actual side diameter ratio;
Step 6: judging whether the actual side diameter ratio is within a tolerance range of a target value, if the actual side diameter ratio is beyond the tolerance range, correcting the predicted yaw angle until the corresponding actual side diameter ratio meets the requirement, namely determining an effective yaw angle of the side diameter ratio within the tolerance range of the target value;
step 7: drawing a curve of the side diameter ratio and the rolling distance under the effective yaw angle, and fitting to obtain a linear relation of the side diameter ratio and the rolling distance;
Step 8: calculating an effective rolling distance interval of the side diameter ratio within a target value tolerance range through a linear relation between the side diameter ratio and the rolling distance, namely determining the effective rolling distance;
Step 9: and carrying out a wheel fatigue test by adopting the determined effective yaw angle and the determined effective rolling distance to finish the assessment target.
The embodiment of the device for testing yaw fatigue rolling of the aircraft wheel comprises a three-dimensional force measuring platform, an inclination angle sensor and a radial load force application module; the three-dimensional force measuring platform is used as a rotatable carrying platform of the machine wheel to be measured, and can measure the lateral load, the heading load and the radial load of the machine wheel to be measured; the radial load force application module applies radial load to the wheel to be tested; the inclination sensor is used for measuring the yaw angle of the machine wheel to be measured.
Specifically, the three-dimensional force measuring platform comprises a base, a loading head, a bearing seat and a hydraulic cylinder, wherein the base, the loading head, the bearing seat and the hydraulic cylinder are arranged on the test bed, and a wheel to be tested is arranged on the base sequentially through the loading head and the bearing seat; the hydraulic cylinder is arranged along the tangential direction of the periphery of the base, the output end of the hydraulic cylinder is hinged with the periphery of the base, and the base is driven to rotate by telescopic control; three-way force load sensors are fixedly arranged between the bearing seat and the base, and the four three-way force load sensors are arranged on the table top of the base in a square array; the inclination sensor is arranged at the bottom center of the base.
Specifically, the output signals of the four three-way force load sensors S 1,S2,S3,S4 are Fx1、Fy1、Fz1、Fx2、Fy2、Fz2、Fx3、Fy3、Fz3、Fx4、Fy4、Fz4, respectively, which represent load values of the four sensors S 1,S2,S3,S4 in three directions X, Y, Z respectively; the sensor always keeps the same posture as the machine wheel, and the loads in X, Y, Z directions are respectively as follows:
Fx＝Fx1+Fx2+Fx3+Fx4 (1)
Fy＝Fy1+Fy2+Fy3+Fy4 (2)
Fz＝Fz1+Fz2+Fz3+Fz4 (3)
Where F x is the heading load, F y is the side load, and F z is the radial load.
The technical scheme is further described below with reference to examples and drawings:
In the embodiment, the fatigue rolling test is carried out according to the requirement of a certain host farm on the aircraft wheel under the condition that the radial load is 108kN, and the ratio of the lateral load to the radial load is equal to 0.25. The specific experimental process is as follows:
step 1: mounting a wheel to be tested on a three-dimensional force measuring platform; determining the installation form of the aircraft wheel, the rotation direction of the drum wheel and the surface state of the drum wheel;
Referring to fig. 1, the yaw fatigue rolling test device for an aircraft wheel according to the embodiment includes an aircraft wheel three-dimensional force measuring platform and an inclination sensor 5, wherein four three-dimensional force load sensors S 1,S2,S3,S4 are arranged between a force bearing plate and a base of the three-dimensional force measuring platform and are used for measuring and collecting heading load, radial load and side load when the aircraft wheel dynamically rolls; the inclination sensor 5 is arranged at the bottom of the base and is positioned on the central axis of the test bed body and the loading head and used for angle feedback of the yaw adjusting mechanism.
The fixed pin shaft 1 connected with the test bed is detached, the base 2 is allowed to rotate relative to the test bed, the base is connected with the hydraulic cylinder 4, the hydraulic cylinder is pushed to drive the test bed loading head 5 to rotate by utilizing the principle of a crank rocker mechanism, the yaw angle is detected by using the inclination sensor 3, and the required position is accurately reached by a control system. Four three-way force load sensors 7 are arranged between the base and the bearing seat 6 and distributed on four corners of a square base with the side length of 800 mm.
Step 2: the radial load force application module applies set radial load to the wheel to be tested, and a yaw mode is adopted to carry out a wheel fatigue test of a yaw angle in a set range;
The product is arranged on a loading head of a test bed according to a load spectrum required by a host machine, and a yaw angle is respectively adjusted to-5 degrees, -4 degrees, -3 degrees, -2 degrees, -1 degrees, -0 degrees, +1 degrees, +2 degrees, +3 degrees, +4 degrees and +5 degrees through a loading cylinder and a yaw angle sensor, so that the loading head applies a specified radial load of 100kn. The drum wheel is driven and rotated, the movement speed of the drum wheel is kept to be 20km/h, and the drum wheel is stopped to be driven after the drum wheel rolls for 40S. A total of 11 test data acquisitions were completed.
Step 3: the method comprises the steps of collecting real side load and radial load generated in the test process through a force load sensor, and calculating corresponding side-to-diameter ratio; the side diameter ratio is equal to the ratio of the side load to the vertical load;
The output signals of the four three-way force load sensors S 1,S2,S3,S4 are Fx1,Fy1,Fz1,Fx2,Fy2,Fz2,Fx3,Fy3,Fz3,Fx4,Fy4,Fz4,, respectively, which represent the load values of the four sensors S 1,S2,S3,S4 in the three directions X, Y, Z, respectively. The sensor always keeps the same posture as the machine wheel, and the loads in X, Y, Z directions are respectively as follows:
Fx＝Fx1+Fx2+Fx3+Fx4 (1)
Fy＝Fy1+Fy2+Fy3+Fy4 (2)
Fz＝Fz1+Fz2+Fz3+Fz4 (3)
Where F x is the heading load, F y is the side load, and F z is the cylinder load (radial load).
Step 4: drawing a yaw angle-side diameter ratio curve, and fitting to obtain a linear relationship between the yaw angle and the side diameter ratio;
Establishing a linear model of the side-to-diameter ratio and the yaw angle:
SDR＝kx+α(-5°≤x≤+5°) (4)
wherein: SDR is the ratio of side load to radial load; x is the yaw angle; k is the slope of the curve, and the value is-0.052; alpha is the lateral load deflection caused by steering, conicity and asymmetry of the tire cord layer, and the value is-0.017, and the obtained relational expression is as follows:
SDR＝-0.052x-0.017 (5)
Step 5: calculating a predicted yaw angle when the target side diameter ratio is 0.25 through a linear relation of the yaw angle and the side diameter ratio, and performing a yaw fatigue rolling test under the predicted yaw angle to obtain a corresponding actual side diameter ratio;
The yaw angle value is:
x＝(SDR-(0.017))/(-0.052) (6)
Let sdr=0.25
Solving for x=4.5; i.e. the yaw angle value is +4.5 deg..
Yaw roll test was performed at x= +4.5, yielding a true side-to-side ratio SDR ture =0.278.
Step 6: judging whether the actual side diameter ratio is within a tolerance range of a target value of 0.25 (the tolerance is +/-0.025), and if the actual side diameter ratio is beyond the tolerance range, correcting the predicted yaw angle until the corresponding actual side diameter ratio meets the requirement, namely determining an effective yaw angle of which the side diameter ratio is within the tolerance range of 0.25; the method for correcting the predicted yaw angle comprises the following steps:
When SDR true is more than 0.275, performing yaw fatigue rolling test under the yaw angle x-a, and stopping the test if SDR true is obtained to be within the [0.225,0.275] interval; if the SDR true is still larger than 0.275, continuing the yaw fatigue rolling test under the yaw angle x-a-b, if the SDR true is obtained to be within the [0.225,0.275] interval, stopping the test, otherwise, continuing to repeat the process;
When SDR true is less than 0.225, performing yaw fatigue rolling test under the yaw angle x+c, and stopping the test if SDR true is obtained to be within the [0.225,0.275] interval; if the SDR true is still smaller than 0.225, continuing the yaw fatigue rolling test under the yaw angle x-c-d, if the SDR true is obtained to be within the [0.225,0.275] interval, stopping the test, otherwise, continuing to repeat the process;
wherein a, b, c, d is a yaw angle correction coefficient set according to a deviation of the actual side diameter ratio from a side diameter ratio target value.
In the step 5, if the SDR ture =0.278 is obtained, that is, if the lower side diameter ratio of the yaw angle x= +4.5 is greater than the upper limit of the qualified zone, the yaw rolling test is continuously performed under the yaw angle of (x-0.5), so as to obtain SDR ture =0.253. Then the SDR can be satisfied within a qualified interval [0.225,0.275] under the yaw angle of 4.0 degrees.
Step 7: drawing a curve of the side diameter ratio and the rolling distance under the effective yaw angle, and fitting to obtain a linear relation of the side diameter ratio and the rolling distance;
Performing long-distance roll test under the condition that the yaw angle x is 4.0 degrees, establishing the relation between the side diameter ratio and the roll distance, and determining the effective roll distance:
L＝(SDR-β)/k’ (7)
wherein: SDR is the ratio of side load to radial load, k' is the slope of the curve, L is the roll distance, and β is the intercept of the curve.
Step 8: calculating an effective rolling distance interval with the side diameter ratio within a tolerance range of 0.25 through a linear relation between the side diameter ratio and the rolling distance, namely determining the effective rolling distance;
Calculating a relation between the average side diameter ratio and the rolling distance through actual measurement data fitting: the curve intercept beta is 0.264, and the curve slope k' is (3.06E-5); the specific expression is:
L＝(SDR-0.264)/(3.06E-5) (8)
setting the side-to-side ratio SDR tolerance to be + -0.025, namely a reasonable side-to-side ratio range of [0.225,0.275], and calculating the roll distance when sdr=0.225:
L＝(0.225-0.264)/(3.06E-5)＝-1274 (9)
Step 9: and carrying out a wheel fatigue test by adopting the determined effective yaw angle and the determined effective rolling distance to finish the assessment target.
Finally, under the conditions that the radial load is 100kN and the rolling speed is 20km/h, the yaw fatigue rolling test with the yaw angle of 4.0 degrees and the single rolling distance of 1274m is carried out.
Although embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations may be made in the above embodiments by those skilled in the art without departing from the spirit and principles of the invention.
Claims (10)
1. The yaw fatigue rolling test method for the aircraft wheels is characterized by comprising the following specific steps of:
Mounting a wheel to be tested on a three-dimensional force measuring platform;
The radial load force application module applies set radial load to the wheel to be tested, and a yaw mode is adopted to carry out a wheel fatigue test of a yaw angle in a set range;
The method comprises the steps of collecting real side load and radial load generated in the test process through a force load sensor, and calculating corresponding side-to-diameter ratio; the side diameter ratio is equal to the ratio of the side load to the vertical load;
drawing a yaw angle-side diameter ratio curve, and fitting to obtain a linear relationship between the yaw angle and the side diameter ratio;
calculating a predicted yaw angle when the side diameter ratio is a target value through a linear relation of the yaw angle and the side diameter ratio, and performing a yaw fatigue rolling test under the predicted yaw angle to obtain a corresponding actual side diameter ratio;
judging whether the actual side diameter ratio is within a tolerance range of a target value, if the actual side diameter ratio is beyond the tolerance range, correcting the predicted yaw angle until the corresponding actual side diameter ratio meets the requirement, namely determining an effective yaw angle of the side diameter ratio within the tolerance range of the target value;
drawing a curve of the side diameter ratio and the rolling distance under the effective yaw angle, and fitting to obtain a linear relation of the side diameter ratio and the rolling distance;
calculating an effective rolling distance interval of the side diameter ratio within a target value tolerance range through a linear relation between the side diameter ratio and the rolling distance, namely determining the effective rolling distance;
and carrying out a wheel fatigue test by adopting the determined effective yaw angle and the determined effective rolling distance to finish the assessment target.
2. The aircraft wheel yaw fatigue rolling test method according to claim 1, wherein: when the yaw mode is adopted for carrying out the fatigue test of the machine wheels, the set range of the yaw angle is-5 degrees to +5 degrees.
3. The aircraft wheel yaw fatigue rolling test method according to claim 1, wherein: the linear relation between the yaw angle and the side diameter ratio is as follows:
SDR＝kx+α
wherein SDR is the side-to-diameter ratio; x is the yaw angle; k is the slope of the curve; alpha is the deflection of the side load caused by steering, conicity of the tire cord layer and asymmetry of the tire.
4. The aircraft wheel yaw fatigue rolling test method according to claim 1, wherein: the tolerance of the target value 0.25 of the side diameter ratio is +/-0.025, namely the actual side diameter ratio is between 0.225 and 0.275, which meets the requirement.
5. The aircraft wheel yaw fatigue rolling test method according to claim 1, wherein: the method for correcting the predicted yaw angle comprises the following steps:
When SDR true is more than 0.275, performing yaw fatigue rolling test under the yaw angle x-a, and stopping the test if SDR true is obtained to be within the [0.225,0.275] interval; if the SDR true is still larger than 0.275, continuing the yaw fatigue rolling test under the yaw angle x-a-b, if the SDR true is obtained to be within the [0.225,0.275] interval, stopping the test, otherwise, continuing to repeat the process;
when SDR true is less than 0.225, performing yaw fatigue rolling test under the yaw angle x+c, and stopping the test if SDR true is obtained to be within the [0.225,0.275] interval; if the SDR true is still smaller than 0.225, continuing the yaw fatigue rolling test under the yaw angle x-c-d, if the SDR true is obtained to be within the [0.225,0.275] interval, stopping the test, otherwise, continuing to repeat the process;
wherein a, b, c, d is a yaw angle correction coefficient set according to a deviation of the actual side diameter ratio from a side diameter ratio target value.
6. The aircraft wheel yaw fatigue rolling test method according to claim 5, wherein the method comprises the following steps of: the yaw angle correction coefficients a, c are 0.5, and b, d are 0.25.
7. The aircraft wheel yaw fatigue rolling test method according to claim 1, wherein: the linear relation between the side diameter ratio and the rolling distance is as follows:
L＝(SDR-β)/k’
Wherein: SDR is the side diameter ratio; l is the effective roll distance; k' is the slope of the curve; beta is the curve intercept.
8. An aircraft wheel driftage fatigue rolling test device which is characterized in that: for carrying out the aircraft wheel yaw fatigue roll test method of any one of claims 1-7; the device comprises a three-dimensional force measuring platform, an inclination angle sensor and a radial load force application module;
The three-dimensional force measuring platform is used as a rotatable carrying platform of the machine wheel to be measured, and can measure the lateral load, the heading load and the radial load of the machine wheel to be measured;
The radial load force application module applies radial load to the wheel to be tested;
the inclination sensor is used for measuring the yaw angle of the machine wheel to be measured.
9. The aircraft wheel yaw fatigue rolling test device according to claim 8, wherein: the three-dimensional force measuring platform comprises a base, a loading head, a force bearing seat and a hydraulic cylinder, wherein the base is arranged on the test bed; the hydraulic cylinder is arranged along the tangential direction of the periphery of the base, the output end of the hydraulic cylinder is hinged with the periphery of the base, and the base is driven to rotate by telescopic control;
Three-way force load sensors are fixedly arranged between the bearing seat and the base, and the four three-way force load sensors are arranged on the table top of the base in a square array.
10. The aircraft wheel yaw fatigue rolling test device according to claim 8, wherein: the output signals of the four three-way force load sensors S 1,S2,S3,S4 are Fx1、Fy1、Fz1、Fx2、Fy2、Fz2、Fx3、Fy3、Fz3、Fx4、Fy4、Fz4, respectively, which represent load values of the four sensors S 1,S2,S3,S4 in the X, Y, Z three directions respectively; the sensor always keeps the same posture as the machine wheel, and the loads in X, Y, Z directions are respectively as follows:
Fx＝Fx1+Fx2+Fx3+Fx4 (1)
Fy＝Fy1+Fy2+Fy3+Fy4 (2)
Fz＝Fz1+Fz2+Fz3+Fz4 (3)
Where F x is the heading load, F y is the side load, and F z is the radial load.
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