CN113237661B - Device and method for measuring dynamic test load of wing-mounted engine - Google Patents
Device and method for measuring dynamic test load of wing-mounted engine Download PDFInfo
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- CN113237661B CN113237661B CN202110504823.8A CN202110504823A CN113237661B CN 113237661 B CN113237661 B CN 113237661B CN 202110504823 A CN202110504823 A CN 202110504823A CN 113237661 B CN113237661 B CN 113237661B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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Abstract
One aspect of the present disclosure relates to a wing-mounted engine load measuring device, comprising a hanging portion for hanging an engine structure to a wing structure; the pylon portion further comprises load transfer linkages for transferring loads borne by the engine structure to the wing structure, the device further comprising a measurement portion comprising strain sensors arranged on the load transfer linkages for measuring strains of the load transfer linkages. Other aspects of the present disclosure also relate to methods of using the apparatus for wing-mounted engine load measurement, including applying a plurality of known load conditions at the center of gravity of the engine structure; measuring strain data under a known load working condition through a strain sensor; and correlating the strain data with the applied known load conditions.
Description
Technical Field
The present application relates generally to dynamic model testing and more particularly to load measurement of a wing-mounted engine.
Background
Some dynamic model tests, such as wind tunnel test, flying model test, water forced landing test, etc., need to measure the engine load during the test, so as to verify the calculation of the engine load, thereby obtaining the design load of the engine structure.
Currently, in dynamic model tests, a commonly used force measuring device is a force measuring balance. However, the design and modification of the force measuring balance are complex, the balance measuring element needs to be additionally designed, and the connection of related structures needs to be designed.
To this end, there is a need in the art for improved apparatus and methods for measuring engine load during testing.
Disclosure of Invention
One aspect of the present disclosure relates to a wing-mounted engine load measuring device, comprising a hanging portion for hanging an engine structure to a wing structure; the hangar portion further comprises load transfer linkage means for transferring loads carried by the engine structure to the wing structure; and a measurement portion including a strain sensor disposed on the load transfer linkage for measuring strain of the load transfer linkage.
According to an exemplary embodiment, the hanger portion includes a beam structure connected at a front end to the engine structure to transfer loads experienced by the engine structure to the beam structure; and the hanging frame structure is connected with the wing structure, and the beam structure penetrates through the hanging frame structure at the rear end.
According to an exemplary embodiment, the load transfer linkage arrangement comprises a four-strut gimbal arrangement connecting the beam structure and the suspension frame structure for transferring at least a portion of the load transferred to the beam structure to the suspension frame structure; and an adjustable linkage connecting the aft end of the spar structure and the wing structure for transferring at least another portion of the load transferred to the spar structure to the wing structure.
According to an exemplary embodiment, a four-swashplate gimbal arrangement includes a first set of links including an upper link and a lower link; and left and right links, wherein front ends of the upper and lower links are connected to the beam structure, and rear ends of the upper and lower links are connected to the suspension frame structure at a greater distance apart than the front ends, and front ends of the left and right links are connected to the beam structure, and rear ends of the left and right links are connected to the suspension frame structure at a greater distance apart than the front ends.
According to an exemplary embodiment, the adjustable linkage comprises a second set of links comprising a left rear link and a right rear link; a beam joint for connecting lower ends of the left and right rear links to a rear end of the beam structure; and a wing joint for connecting the upper ends of the left and right rear links to the wing structure at a greater distance apart than the lower ends, wherein the wing joint and the spar joint are adjustable in the axial direction of the spar structure.
According to an exemplary embodiment, the strain sensor is arranged near a mid-section of each link.
Another aspect of the present disclosure relates to a method of wing-mounted engine load measurement using a wing-mounted engine load measuring device as described above, comprising applying a plurality of known load conditions at the center of gravity of the engine structure; measuring strain data under the known load working condition through the strain sensor; and correlating the strain data to known applied load conditions.
According to an exemplary embodiment, establishing the relationship of the strain data to the applied known load regime comprises establishing a load matrix based on the known load regime; establishing a strain matrix based on the strain data; establishing a multiple linear regression equation between the strain matrix and the load matrix; and determining a correlation coefficient matrix of the multiple linear regression equation through matrix operation.
According to an exemplary embodiment, the method further comprises collecting, by the strain sensor, trial strain data at one or more particular times in the trial measurement; establishing a test strain vector or matrix based on the test strain data; and determining a trial load vector or matrix based on the trial strain vector or matrix and the matrix of correlation coefficients of the multiple linear regression equation.
According to an exemplary embodiment, the method further comprises taking a wing-mounted engine load measurement after adjusting one or more of the following or any combination thereof: the angle of the link; the front and rear positions of the hanging frame structure; and the axial position of the wing joint and the spar joint along the spar structure.
Drawings
FIG. 1 shows a schematic diagram of an engine load measurement device according to an aspect of the present disclosure.
FIG. 2 shows a schematic diagram of an installation of an engine load measuring device according to an aspect of the present disclosure.
FIG. 3 illustrates a schematic diagram of a four-swashplate gimbal arrangement of an engine load measurement device, according to an aspect of the present disclosure.
FIG. 4 illustrates a schematic diagram of an adjustable linkage arrangement of an engine load measuring device according to an aspect of the present disclosure.
Fig. 5 shows an oblique view of a mounting structure of an engine load measuring device according to an aspect of the present disclosure.
FIG. 6 illustrates a schematic diagram of load transfer of an engine load measurement device according to an aspect of the present disclosure.
FIG. 7 illustrates a schematic diagram of a force analysis of an engine load measurement device according to an aspect of the present disclosure.
FIG. 8 illustrates a flow chart of a method of engine load measurement in accordance with an aspect of the present disclosure.
Detailed Description
The invention relates to a hanging device designed between a wing hanging engine and a wing structure model, a certain number of strain sensors are arranged on a key connecting member, a high-precision load-strain correlation equation is established through calibration, and acquired strain data are substituted into the correlation equation after a test, so that the engine load of a dynamic model test is obtained. Specific embodiments of the present disclosure will be described below with reference to the accompanying drawings.
Fig. 1 shows a schematic diagram of an engine load measurement device 100 according to an aspect of the present disclosure. As shown in the figure, the engine load measuring device 100 may include a hanging portion and a measuring portion. According to an exemplary embodiment, the hangar portion of the engine load measurement device 100 may include, for example, a beam structure 121 for connection with an engine structure and a hanger frame structure 124 for connection with a wing structure, etc., wherein the beam structure 121 passes through the hanger frame structure 124. According to an exemplary embodiment, the beam structure 121 may transfer at least a portion of the load experienced by the engine to the hanger frame structure 124 through a load transfer linkage 122 described below. The drop frame structure 124 may further transfer loads to the wing structure.
The hanger portion of engine load measurement device 100 may also include, for example, a load transfer linkage 122. According to an exemplary embodiment, the load transfer linkage 122 may include a first set of links. One end of the first set of links is connected to the beam structure 121 and the other end is connected to the hanger frame structure 124. According to an exemplary embodiment, the load transfer linkage arrangement 122 may also include a second set of links. One end of the second set of links is connected to the rear end of the beam structure 121 and the other end is connected to the wing structure. At least a portion of the loads experienced by the engine may be transferred from the spar structure 121 to the wing structure via the second set of links.
The measurement portion of the engine load measurement device 100 may include a strain sensor (not shown). According to an exemplary embodiment, one or more strain sensors may be arranged at the load transfer linkage 122 between the engine structure and the wing structure for acquiring respective strain values.
In this way, by applying a plurality of load conditions at the center of gravity of the engine and calibrating the load conditions, a multiple linear regression equation between the strain and the engine load can be established. Thereafter, the acquired strain data is substituted into the correlation equation, and the engine load corresponding thereto can be obtained.
Fig. 2 shows a schematic diagram of an installation 200 of an engine load measuring device according to an aspect of the present disclosure. As shown in FIG. 2, an engine load measurement device 202, such as the engine load measurement device 100 shown in FIG. 1, may be mounted between an engine structure 204 and a wing structure 206 for suspending the engine structure 204 from the wing structure 206.
According to an exemplary embodiment, as described in connection with engine load measurement device 100 of FIG. 1, beam structure 210 of the hanger portion of engine load measurement device 202 may be connected at a forward end to engine structure 204 for transferring loads carried by the engine to the beam structure. The attachment may include, but is not limited to, for example, bolting.
According to an exemplary embodiment, the drop frame structure 212 of the drop portion of the engine load measurement device 202 may be coupled to the wing structure 206 for transferring loads carried by the drop frame structure 212 to the wing structure 206, as described in connection with the engine load measurement device 100 of FIG. 1.
According to an exemplary embodiment, as described in connection with engine load measurement device 100 of FIG. 1, a first set of links 214 of the load transfer linkage of the hanger portion of engine load measurement device 202 may be connected at both ends to beam structure 210 and hanger frame structure 212, respectively. Such connections may include, but are not limited to, for example, by way of a pin connection.
According to an exemplary embodiment, as described in connection with the engine load measurement device 100 of FIG. 1, the second set of links 216 of the load transfer linkage of the pylon portion of the engine load measurement device 202 may be connected to the spar structure 210 and the wing structure 206. For example, one end of the second set of links 216 may be connected to the aft end of the spar structure 210 via a spar joint, while the other end may be connected to the wing structure 206 via a wing joint. Such attachment may include, but is not limited to, for example, bolting. The wing joints and spar joints are adjustable along the axis of the spar structure 210.
Loads experienced by the engine may be transferred to the spar structure 210, a portion of which is transferred from the spar structure 210 to the hanger frame structure 212 and thus to the wing structure 206, and another portion of which is transferred from the spar structure 210 to the wing structure 206 via the second set of links 216 of the load transfer linkage.
According to an aspect of the present disclosure, the first set of links of the load transfer linkage arrangements 100 and/or 202 described above in connection with fig. 1 and 2 may include, for example, four links, i.e., an upper link, a lower link, a left link, and a right link, respectively located on the upper side, lower side, left side, and right side of the beam structure (as viewed from the rear end to the front end), constituting a four-strut universal joint arrangement.
Fig. 3 illustrates a schematic diagram of a four-swashplate gimbal assembly 300 of an engine load measurement device according to an aspect of the present disclosure. The four-swashplate gimbal assembly 300 of the engine load measuring device may include an upper link 302, a lower link 304, a left link 306, and a right link (not shown).
According to an exemplary embodiment, the upper and lower links 302, 304 may be connected in a V-shape, wherein the front ends of the upper and lower links 302, 304 may be connected 308 to the beam structure by, for example, a pin connection, and the rear ends of the upper and lower links 302, 304 may be spaced a greater distance apart than the front ends and connected to the drop frame structure 310 by, for example, a pin connection.
According to an exemplary embodiment, 306 the left and right links (not shown) may be connected in a V-shape, wherein the front ends of the left and right links 306 and 306 may be connected to the beam structure 308 by, for example, a pin connection, and the rear ends of the left and right links 306 and 306 may be spaced apart a greater distance than the front ends and connected to the drop frame structure 310 by, for example, a pin connection.
According to an exemplary embodiment, engine loads are transferred to the beam structure 308 and to the drop frame structure via the upper 302, lower 304, left 306 and right links.
According to an aspect of the present disclosure, the four-diagonal-bar gimbal assembly 300, which is comprised of the upper link 302, the lower link 304, the left link 306, and the right link 308 in the first set of links of the load transfer linkage assembly, may enable independent measurement of vertical and/or lateral orthogonal loads; and the structural strain of the test point can be amplified through the oblique design (i.e. V-shaped connection) of the first group of connecting rods, so that the accurate control of the strain is realized through applying a simple force measuring element two-force rod. In this manner, the four-diagonal-rod gimbal assembly 300 is implemented to be able to control the magnitude of the load at the local survey point.
According to an aspect of the present disclosure, the second set of links of the load transfer linkage described above in connection with fig. 1 and 2 may include, for example, two links, a left rear link and a right rear link, located at the rear end of the beam structure. The left and right rear links of the second set of links of the load transfer linkage may together with the wing and spar joints form an adjustable linkage.
FIG. 4 illustrates a schematic diagram of an adjustable linkage arrangement 400 of an engine load measuring device according to an aspect of the present disclosure. The adjustable linkage arrangement 400 of the engine load measuring device may include a left rear link 402 and a right rear link 404. Adjustable linkage 400 may further include a spar joint 406 and a wing joint 408.
Left and right rear links 402, 404 may be connected in a V-shape, where the lower ends of left and right rear links 402, 404 may be connected to the rear end of the spar structure by spar joints 406, and the upper ends of left and right rear links 402, 404 may be spaced a greater distance apart than the lower ends and connected to the wing structure by wing joints 408. Such attachment may include, but is not limited to, for example, bolting.
In an adjustable linkage 400 comprising a left rear link 402, a right rear link 404, a wing joint 408 and a beam joint 406 of the second set of links of the load transfer linkage according to an aspect of the present disclosure, the wing joint 408 and the beam joint 406 may be adjustable along the beam structure axis for adjusting the moment arm to control the magnitude of the strain of the moment balancing load, thereby improving the test accuracy. As such, the adjustable linkage 400 is implemented to control the magnitude of the overall balancing load.
According to an aspect of the present disclosure, on the other hand, the angle of the diagonal member is changed by adjusting the front and rear positions of the hanger frame structure, so that the strain of the diagonal member can be controlled.
Fig. 5 illustrates an oblique view of a mounting structure 500 of an engine load measuring device according to an aspect of the present disclosure. As can be seen, the front end of the beam structure 502 is used to suspend the engine structure and the rear end passes through the hanger frame structure 504. The first set of links 508 of the load transfer linkage have forward ends connected to the beam structure and rearward ends connected to the drop frame structure at a greater distance apart than the forward ends to transfer at least a portion of the load from the engine structure on the beam structure 502 to the drop frame structure 504 through the first set of links 508 for further transfer to the wing structure.
On the other hand, the lower ends of the second set of links 510 of the load transfer linkage 506 may be connected to the aft end of the spar structure 502 by spar joints 514, while the upper ends may be spaced a greater distance apart than the lower ends and connected to the wing structure by wing joints 512.
Fig. 6 illustrates a schematic diagram of a load transfer 600 of an engine load measurement device in accordance with an aspect of the present disclosure. The load may include force and moment. In this solution, the heading force F of the engineXTransmitted through the first set of links 508 (upper, lower, left, right) and the vertical force FZThe lateral force F is transmitted through the upper and lower links of the first set of links 508 and the second set of links 510 (left and right rear links)YThrough the left and right links of the first set of links 508 and the second set of links 510 (left and right rear links).
On the other hand, heading torque M of the engineXFor example, vertical bending moment M may be transferred through left and right links in the first set of links 508 and the second set of links 510 (left and right rear links)YFor example, lateral bending moment M may be transferred through the upper and lower links of the first set of links 508, and the second set of links 510 (left and right rear links)ZFor example, through the left and right links of the first set of links 508, and the second set of links 510 (left and right rear links).
FIG. 7 illustrates a schematic diagram of a force analysis 700 of an engine load measurement device in accordance with an aspect of the present disclosure. For clarity, only force analysis of vertical loads is shown in FIG. 7. However, it will be appreciated by those skilled in the art that the engine load measurement device may also be analyzed for heading, lateral force. As shown in the figure, FEActing force of engine on beam structure, FWFor wing to beam jointThe force arms of the structure are respectively LEAnd LW. Although F is shown in the figureEAnd FWThe direction is shown as upward, but the direction of the vertical force may vary from test scenario to test scenario and is not limited to the direction shown above.
Vertical loads are transferred through the upper and lower links of the first set of links and the second set of links (left and right rear links). P1The force applied to the upper link, R is its horizontal component and S is its vertical component. P2The force experienced by the lower link can also be resolved into a horizontal component and a vertical component (not shown).
According to stress analysis, the engine load measuring device can realize independent measurement of vertical and lateral orthogonal loads; the structural strain of the test point can be amplified through the oblique design of the connecting rod, and the simplest force measuring element two-force rod is applied to realize accurate control of the strain; in addition, the front and back positions of the hanging frame structure are adjusted to change the angle theta of the diagonal rod, so that the strain of the diagonal rod can be controlled.
The wing joint and the beam joint of the engine load measuring device can be axially adjusted along the beam structure, and are used for adjusting the force arm so as to control the strain magnitude of the moment balance load, and thus the test precision is improved.
The adjustable linkage device (namely, the left rear connecting rod, the right rear connecting rod, the wing joint and the beam joint) is used for controlling the size of the total balanced load, and the four-diagonal-rod universal joint device (namely, the upper connecting rod, the lower connecting rod, the left connecting rod and the right connecting rod) is used for controlling the size of the load of the local measuring point.
According to some aspects of the present disclosure, a key force transmission component between the engine and the wing structure, such as the first set of links and the second set of links described above in connection with fig. 1-6, etc., may be chosen for the strain sensor arrangement. Because the connecting rods are of a two-force rod structure, a single connecting rod can be provided with at least 1 strain sensor, and more strain sensors can be arranged for measuring the shaft force.
According to some exemplary embodiments, the scheme of the present disclosure may arrange 2 strain sensors near the cross-sectional position in each connecting rod, and the redundant strain sensors may play a role in mutual backup and improving calibration accuracy.
According to an exemplary aspect of the present disclosure, a plurality (e.g., m) of load conditions (heading forces F) are applied at the center of gravity of the engineXVertical force FZLateral force FYCourse torque MXVertical bending moment MYAnd lateral bending moment MZ) Can be used for strain [ epsilon ]ij]And calibrating a multiple linear regression equation between the load condition and the load working condition, wherein the equation is shown as the formula (1):
wherein
i is 1, 2, … m (m is more than or equal to 2) is the number of the ground calibration test working conditions; j is 1, 2, … n (n is more than or equal to 3) and is the number of the strain sensors. [ epsilon ]ij]The strain matrix is m rows and n columns, and a plurality of working conditions are measured by each strain sensor, wherein each row corresponds to one working condition, and each column corresponds to the strain value measured by a corresponding one of the sensors. [ beta ]]Is a correlation coefficient matrix of n rows and 6 columns. The matrix to the right of the equal sign is a matrix of m rows and 6 columns of load conditions, where each row corresponds to one condition and each column corresponds to one load (e.g., heading force F)XVertical force FZLateral force FYCourse torque MXVertical bending moment MYAnd lateral bending moment MZ) It can be obtained according to the load condition applied at the center of gravity of the engine. The matrix [ beta ] of the correlation coefficients can be solved by matrix operations, e.g. by left-multiplying the matrix of the load conditions by the inverse of the strain matrix]。
After solving the correlation coefficient matrix [ beta ]]Then, the strain vector [ epsilon ] under the action of engine load can be obtained by a strain sensor1 ε2 … εn]And apply the strain vector [ epsilon ]1 ε2 ... εn]Substituting the following formula (2) to determine the total load vector [ F ] acting on the center of gravity of the engineX FY FZ MX MY MZ]。
Of course, in the case where a plurality of strain vectors are measured or obtained, it is also possible to solve the corresponding total load matrix acting at the center of gravity of the engine by constructing a strain matrix from these strain vectors as row vectors.
According to an exemplary embodiment, if the load conditions applied at the center of gravity of the engine are linearly independent, for example, heading force F is applied separately each timeXVertical force FZLateral force FYCourse torque MXVertical bending moment MYAnd lateral bending moment MZIn one of the above, the multiple linear regression equation in the formula (1) can be calibrated only by 6 times of ground calibration test conditions at least.
FIG. 8 illustrates a flow chart of a method 800 of engine load measurement in accordance with an aspect of the present disclosure. Method 800 may include applying a plurality of known load conditions at the center of gravity of the engine at block 810. According to an exemplary embodiment, the load condition may include a heading force FXVertical force FZLateral force FYCourse torque MXVertical bending moment MYAnd lateral bending moment MZOr any combination thereof. These load conditions may be linearly independent, but are not limited thereto, but may also include at least partially linearly dependent load conditions.
At block 820, the method 800 may include measuring strain data with a sensor disposed in a force transfer component between the engine and the wing structure.
According to an exemplary embodiment, engine load measurements may be made by using an engine load measuring device as described above in connection with any of fig. 1-6. The force transfer components between the engine and the wing structure may include, but are not limited to, a first set of links (upper, lower, left, right) and a second set of links (left, right), etc. in the engine load measurement device as described above in connection with any of fig. 1-6. The sensors arranged in the force transmission member between the engine and the wing structure may comprise one or more strain sensors or the like arranged near the mid-section position of each link.
The strain data may include, for example, measurements made by the one or more sensors for a plurality of operating conditions. The measurements for each condition may include the form of a strain vector as previously described. Thus the measurement of a plurality of operating conditions may comprise the form of a strain matrix as previously described.
At block 830, the method 800 may include establishing a relationship of the measured strain data to the applied load regime by calibration.
According to an exemplary embodiment, correlating the measured strain data to the applied load condition may include correlating the strain data to a linear regression equation for the load condition. Establishing the relationship of the measured strain data to the applied load regime by calibration may include determining a matrix of correlation coefficients for the linear regression equation by matrix solving.
At block 840, the method 800 may include collecting, in a test measurement, test strain data at a particular time by a sensor disposed in a force transfer component between the engine and the wing structure. In the test measurements, the load conditions imposed at the center of gravity of the engine are unknown. The strain data at a particular time corresponds to the load condition at that particular time. The particular time of day may include one or more time of day. Accordingly, the collected experimental strain data may include one or more sets of experimental strain data corresponding to the load conditions at the one or more moments in time, respectively. Each set of trial strain data may be in the form of a trial strain vector. The sets of test strain data may be in the form of a test strain matrix, wherein the load conditions at each time correspond to a respective row vector in the test strain matrix.
At block 850, the method 800 may include determining the engine load in the test measurement by substituting the collected test strain data into the determined linear regression equation.
According to an exemplary embodiment, substituting the collected trial strain data into the determined linear regression equation may comprise multiplying a trial strain vector or a trial strain matrix with a matrix of correlation coefficients of the linear regression equation to obtain a trial load vector or a trial load matrix, respectively.
Thus, by using the engine load measurement method 800 as illustrated in fig. 8, the load experienced by the engine structure of the dynamic model test can be accurately obtained, and the accuracy is sufficient to meet the test requirements.
What has been described above is merely exemplary embodiments of the present invention. The scope of the invention is not limited thereto. Any changes or substitutions that may be easily made by those skilled in the art within the technical scope of the present disclosure are intended to be included within the scope of the present disclosure.
The methods disclosed herein comprise one or more steps or actions for achieving the described method. The method steps and/or actions may be interchanged with one another without departing from the scope of the claims. In other words, unless a specific order of steps or actions is specified, the order and/or use of specific steps and/or actions may be modified without departing from the scope of the claims.
It is to be understood that the claims are not limited to the precise configuration and components illustrated above. Various changes, substitutions and alterations in the arrangement, operation and details of the method and apparatus described above may be made without departing from the scope of the claims.
Claims (6)
1. A wing-mounted engine load measuring device comprising:
a hanging portion for hanging the engine structure to the wing structure;
the hangar portion further comprising load transfer linkage means for transferring loads carried by the engine structure to the wing structure; and
a measurement portion including a strain sensor disposed on the load transfer linkage for measuring strain of the load transfer linkage,
wherein the hanging portion includes: a beam structure connected at a front end to the engine structure to transfer loads carried by the engine structure to the beam structure; and a hanging frame structure connected with the wing structure, wherein the beam structure passes through the hanging frame structure at a rear end, and
wherein the load transfer linkage comprises: a four-strut gimbal assembly connecting the beam structure and the suspension frame structure for transferring at least a portion of the load transferred to the beam structure to the suspension frame structure; and an adjustable linkage connecting the aft end of the spar structure and the wing structure for transferring at least another portion of the load transferred to the spar structure to the wing structure,
wherein the four-strut gimbal arrangement comprises a first set of links, the first set of links comprising: an upper link and a lower link; and left and right links, wherein front ends of the upper and lower links are connected to the beam structure, and rear ends of the upper and lower links are connected to the suspension frame structure at a greater distance apart than the front ends, and front ends of the left and right links are connected to the beam structure, and rear ends of the left and right links are connected to the suspension frame structure at a greater distance apart than the front ends,
wherein the adjustable linkage arrangement comprises a second set of links comprising a left rear link and a right rear link; a beam joint for connecting the lower ends of the left and right rear links to the rear end of the beam structure; and a wing joint for connecting the upper ends of the left and right rear links to the wing structure at a greater distance apart than the lower ends, wherein the wing joint and the spar joint are adjustable in the axial direction of the spar structure.
2. A winged-hook engine load measuring device as defined in claim 1, wherein the strain sensor is disposed near a mid-section of each connecting rod.
3. A method of wing crane engine load measurement using a wing crane engine load measuring device as claimed in any of claims 1-2, comprising:
applying a plurality of known load conditions at a center of gravity of the engine structure;
measuring strain data under the known load working condition through the strain sensor; and
and establishing the relation between the strain data and the applied known load condition.
4. A method of making winged-hook engine load measurements as defined in claim 3, wherein correlating the strain data to known load conditions imposed comprises:
establishing a load matrix based on the known load working condition;
establishing a strain matrix based on the strain data;
establishing a multiple linear regression equation between the strain matrix and the load matrix; and
and determining a correlation coefficient matrix of the multiple linear regression equation through matrix operation.
5. The method of making a winged-hook engine load measurement according to claim 4, further comprising:
acquiring test strain data at one or more specific moments in a test measurement through the strain sensor;
establishing a test strain vector or matrix based on the test strain data; and
determining a trial load vector or matrix based on the trial strain vector or matrix and the matrix of correlation coefficients of the multiple linear regression equation.
6. A method of making wing-mounted engine load measurements as claimed in claim 5, further comprising making wing-mounted engine load measurements after adjusting one or more of:
the angle of the connecting rod;
the front and rear positions of the hanging frame structure; and
the axial position of the wing joint and the spar joint along the spar structure.
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| CN113859553A (en) * | 2021-11-18 | 2021-12-31 | 中国商用飞机有限责任公司 | Aircraft hanging interface assembly and aircraft hanging |
| CN114813000A (en) * | 2022-06-23 | 2022-07-29 | 中国飞机强度研究所 | Load monitoring device and method for buffeting test of aircraft key structure |
| CN118032259A (en) * | 2024-04-09 | 2024-05-14 | 中国空气动力研究与发展中心高速空气动力研究所 | Sub-transonic variable-angle concurrent direct-connection wind tunnel test engine bench and design method |
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