CN113581489B - Static balance moment adjusting device and method for airplane control surface - Google Patents
Static balance moment adjusting device and method for airplane control surface Download PDFInfo
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- CN113581489B CN113581489B CN202110820170.4A CN202110820170A CN113581489B CN 113581489 B CN113581489 B CN 113581489B CN 202110820170 A CN202110820170 A CN 202110820170A CN 113581489 B CN113581489 B CN 113581489B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
The invention discloses an aircraft control surface static balance moment adjusting device which comprises a supporting assembly and a balance moment measuring assembly, wherein the balance moment measuring assembly comprises a balance beam, a movable hanging frame and a counterweight sliding block, and the supporting assembly is used for supporting a control surface connecting part; the middle part of the balance beam is provided with an indicating part, and the indicating part is used for balancing the Liang Fencheng first beam body and the second beam body; the movable hanging rack can move and be locked on the first beam body, weight detection equipment and a clamping piece are arranged on the movable hanging rack, and the clamping piece is used for supporting the rear edge of the control surface; the counterweight sliding block can move on the second beam body. The invention can realize the accurate adjustment of the static balance moment of the control surface, and avoids the scrapping and reworking of aircraft materials caused by improper repair. Meanwhile, the invention also discloses a static balance moment adjusting method for the aircraft control surface.
Description
Technical Field
The invention belongs to the technical field of aircraft maintenance, and particularly relates to an adjusting device and an adjusting method for static balance moment of an aircraft control surface.
Background
The flight control surface of the airplane is a movable wing surface hinged on the wings, horizontal tail and vertical tail of the airplane, comprises main control surfaces such as elevators (full-motion horizontal tail), ailerons and rudders and auxiliary control surfaces such as slats and flaps, and is used for controlling the airplane when the airplane flies and runs at high speed on the ground. Compared with main wing surfaces such as wings and the like, the control surface has the characteristics that the aeroelasticity problem is more prominent due to the characteristics of the structure, the complexity of the control, the difficulty in accurate calculation of aerodynamic force and the like. With the increase of the speed of the airplane, the flutter of the control surface and the tail fin becomes the main cause of the aeroelasticity accident, in order to prevent the control surface from fluttering under the normal operation state of the airplane, the maintenance manual of the airplane requires that the static balance measurement must be carried out after the repair or painting of the control surface of the airplane, and the static balance moment value should be within the specified range.
The existing control surface static balance measuring method is relatively original, the level of a neutral surface of an airplane control surface is adjusted in a visual mode, the weight of the control surface is measured by a spring scale or an electronic scale, a force arm is measured by a ruler, and a static balance moment (the weight of the control surface multiplied by the force arm) is calculated, and the measuring method has the following defects:
1) The force arm is generally required to be measured in a state of keeping balance, and the measurement error is large; 2) The method has the advantages that the method is insensitive to environmental factors and human operation errors, has the defects of poor precision, low efficiency, low automation degree and the like, is difficult to meet the high precision and high efficiency requirements of modern aircraft repair, the flight speed of a transport aircraft is high, the aeroelasticity problem is more prominent, the measurement precision requirement on the control surface balance moment is very high, and compared with a transport aircraft large aircraft, although the requirement on the precision of the low-speed aircraft is reduced, the measurement ratio error of the balance moment is increased along with the light weight of the control surface, if the static balance measurement of the control surface with low precision is implemented, the aircraft repair accident can be caused, and the flight safety is endangered; 3) If the measured static balance moment of the control surface does not meet the requirement, the counterweight on the control surface or the wing needs to be adjusted for many times until the static balance moment of the control surface meets the requirement, the process is complicated, and the accuracy is low.
Disclosure of Invention
In order to solve the defects of the prior art, the invention discloses a static balance moment adjusting device and an adjusting method for an airplane control surface, which adopt the following technical scheme:
a static balance moment adjusting device for an airplane control surface comprises a supporting component and a balance moment measuring component, wherein the balance moment measuring component comprises a balance beam, a movable hanging rack and a counterweight sliding block,
the support assembly is for supporting a control surface connection;
the middle part of the balance beam is provided with an indicating part, and the indicating part is used for balancing the Liang Fencheng first beam body and the second beam body;
the movable hanging rack can move and be locked on the first beam body, weight detection equipment and a clamping piece are arranged on the movable hanging rack, and the clamping piece is used for supporting the rear edge of the control surface;
the counterweight slider is movable on the second beam.
Further, the balance moment measuring assembly further comprises a simulated weight slider, and the simulated weight slider can move on the balance beam.
In a further aspect of the present invention,
a first groove is formed in the counterweight sliding block and is matched with the second beam body;
and a second groove is formed in the simulation counterweight sliding block and is matched with the balance beam.
In a further aspect of the present invention,
the number of the counterweight sliding blocks is multiple, and the weights of at least two counterweight sliding blocks are different;
and/or
The simulation counterweight sliding blocks are multiple, and the weights of at least two simulation counterweight sliding blocks are different.
Further, the system also comprises a data acquisition and processing component, wherein the data acquisition and processing component comprises a laser tracker,
the laser tracker is used for measuring position information of the control surface, the balance beam, the movable hanging rack, the counterweight sliding block, the simulation counterweight sliding block and the indicating part.
Further, the data acquisition and processing assembly further comprises a controller, the controller is connected with the laser tracker and the weight detection device,
the laser tracker feeds the position information back to the controller;
the weight detecting device feeds back the measured value to the controller.
Further, the support assembly comprises an operation table and a support arranged on the operation table, the support extends outwards to form a support table, and the support table is used for supporting the control surface connecting portion.
Further, the weight detection device is a weight sensor.
The invention also discloses an aircraft control surface static balance moment adjusting method, which comprises the following steps:
the method comprises the following steps: acquiring position information of a control surface, a balance beam, a counterweight sliding block, a movable hanging rack and a clamping piece sent by a laser tracker, and judging whether the position information meets the requirement of a preset balance state;
step two: if yes, executing the third step; if not, calculating and visualizing the displacement information of the balance beam, the counterweight sliding block, the movable hanging rack and the clamping piece, and executing the step one after the positions of the balance beam, the counterweight sliding block, the movable hanging rack and the clamping piece are adjusted according to the displacement information;
step three: the method comprises the steps of obtaining position information of a movable hanging rack and an indicating part sent by a laser tracker and a detection value sent by weight detection equipment, calculating a control surface static balance moment value, and judging whether the control surface static balance moment value meets the requirement of a preset static balance moment value;
step four: if so, executing a fifth step, otherwise, calculating and visually simulating the weight and the position of the counterweight sliding block, configuring the counterweight sliding block to be simulated according to the weight and the position, and executing the first step again;
step five: and outputting the weight and the position of the simulated counterweight sliding block so as to configure the weight and the position of the actual counterweight according to the weight and the position of the simulated counterweight sliding block.
Further, the balance state requirement in the step one is as follows: the center of the balance beam indicating part is aligned with the control surface rotating shaft, the balance beam and the control surface neutral plane are horizontal, and the balance beam is vertical to the control surface rotating shaft.
By adopting the technical scheme, the invention has the beneficial effects that:
1. according to the invention, the balance is adjusted by moving the counterweight sliding block on the second beam body, so that the adjustment of the balance state is more convenient; the movable hanging rack can be moved and locked on the first beam body, so that the force arm measuring result is accurate, and the static balance moment is accurately measured.
2. According to the invention, the static balance moment can meet the standard requirement by adjusting the weight and the position of the simulation counterweight sliding block, namely, the situation that the counterweight block is rebalanced after being installed is simulated, a basis is provided for the installation of the counterweight block on the wing flap, the aileron or the empennage, the static balance moment of the control surface can be adjusted, and the scrapping and reworking of aircraft materials caused by improper repair can be avoided.
3. According to the invention, the position information of each component on the control surface and the balance moment measuring component is detected by the laser tracker, and the force for keeping the control surface in static balance is detected by the weight detection equipment, so that the detection precision is ensured, and the human error is avoided; the adjusting method is adjusted and controlled through the controller, adjusting time of the static balance moment of the control surface is shortened, and adjusting accuracy is improved.
Drawings
FIG. 1 is a schematic diagram of the overall structure of an embodiment of the present invention
FIG. 2 is a schematic diagram of a balance moment measuring assembly according to an embodiment of the present invention
1-balance beam, 2-movable hanger, 3-counterweight sliding block, 31-first groove, 4-indicating part, 5-weight detection device, 6-clamping piece, 61-fixed part, 62-clamping part, 7-simulation counterweight sliding block, 71-second groove, 81-operation table, 82-support, 83-support table and 9-control surface.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely below, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1 and 2, the invention discloses an aircraft control surface static balance moment adjusting device, which comprises a supporting assembly and a balance moment measuring assembly, wherein the balance moment measuring assembly comprises a balance beam 1, a movable hanging rack 2 and a counterweight sliding block 3,
the support assembly is for supporting a control surface connection; the control surface connecting part refers to a connecting part for connecting the control surface with the wing, the control surface is hinged to the wing of the airplane under the normal condition, and at the moment, a hinge pin or a bolt for connecting the control surface with the wing is the control surface connecting part;
the balance beam 1 is provided with an indicating part 4 in the middle, and the indicating part 4 is used for indicating a control surface rotating shaft, namely the indicating part 4 is used for aligning with the control surface rotating shaft during measurement; when the control surface is connected with the wing, the control surface can rotate around a fixed shaft, namely the control surface rotating shaft, for example, when the control surface is hinged on the wing, the control surface can rotate around a hinged shaft, namely the control surface rotating shaft, as shown in a dotted line in fig. 1;
the indication part 4 divides the balance beam 1 into a first beam body and a second beam body (in fig. 1, the left side of the indication part 4 is the first beam body, and the right side is the second beam body);
the movable hanging rack 2 can move and be locked on the first beam body, a weight detection device 5 and a clamping piece 6 are arranged on the movable hanging rack 2, the weight detection device 5 can be a weight sensor, and the clamping piece 6 is used for supporting the rear edge of the control surface;
the counterweight sliding block 3 can move on the second beam body to balance the balance beam 1.
Further, the number of the counterweight sliding blocks 3 is multiple, and the weights of at least two counterweight sliding blocks 3 are different, preferably the weights of the counterweight sliding blocks 3 are all different, so as to adapt to various types of control surfaces.
Further, the clamping member 6 comprises a fixing portion 61 and a clamping portion 62, the fixing portion 61 is connected with the lower end of the movable support 2, the clamping portion 62 is used for clamping the rear edge of the control surface and can move and be locked on the fixing portion 61, when the clamping member 6 supports the rear edge of the control surface, the position of the clamping portion 62 on the fixing portion 61 can be adjusted, so that the control surface median plane is parallel to the balance beam 1, wherein the control surface median plane refers to a plane which passes through the center line of the rear edge of the control surface and the control surface rotation axis at the same time.
In one embodiment, the fixing portion 61 is provided with an adjusting channel, the clamping portion 62 is provided with an adjusting bolt, the adjusting bolt can move in the adjusting channel to adjust the position, and after the position is adjusted, the adjusting bolt is fixed on the fixing portion 61 by a nut, so that the clamping portion 62 can move and be locked on the fixing portion 61.
The movable support 2 is provided with a sleeve establishing portion, the sleeve establishing portion is used for being sleeved on the first beam body and can move on the first beam body to adjust the position, the sleeve establishing portion is provided with a threaded hole, and the bolt is screwed up on the threaded hole to lock the movable support 2 and the first beam body.
The mounting method of the support assembly and the balance moment measuring assembly comprises the following steps:
1) The control surface connecting part is arranged on the support component, so that the control surface rotating shaft is parallel to the horizontal plane, and the control surface 9 can freely rotate around the control surface rotating shaft, namely, the control surface connecting part is consistent with the installation constraint state;
2) The balance beam 1 is arranged above the control surface and is vertical to the control surface rotating shaft, so that the center of the indicating part 4 is aligned with the control surface rotating shaft;
3) Adjusting the horizontal position of the movable hanger 2 according to the width of the control surface, supporting the rear edge of the control surface by using the clamping piece 6, and adjusting the vertical position of the clamping part 62 on the fixing part 61 so that the neutral plane of the control surface is parallel to the balance beam 1;
4) The position of the movable balance weight 3 is adjusted to make the balance beam 1 horizontal, and the level of the neutral plane of the control surface is also in a horizontal state.
In the prior art, the articulated shaft of the control surface is usually arranged on a supporting seat, and a supporting block is arranged on an electronic scale or a spring scale to support the rear edge of the control surface, so that the control surface reaches a static balance state to calculate the size of a static balance moment. In the method, the moment arm is the vertical distance from the rotating shaft of the control surface to the supporting block fulcrum, and in actual measurement, due to the complexity of the structure of the control surface, the measurement error of the vertical distance is large, so that the measurement error of the final static balance moment is also large.
According to the balance moment measuring assembly, a static balance moment is measured in a hanging mode, the force arm is the distance between the middle part of the indicating part 4 on the balance beam 1 and the middle part of the movable hanging rack 2, and compared with the prior art, the force arm is measured and transferred from a control surface which is complex in structure and multiple in irregular shape to a measuring tool which is simple in structure, so that the measuring error of the force arm is reduced, and the measuring result of the static balance moment is more accurate; meanwhile, the adjusting device is suitable for various control surfaces by moving the movable hanging rack 2, and static balance moment measurement can be carried out on the control surfaces (including ailerons, flaps, elevators, rudders and the like) of the airplanes of different types of transport planes or navigation airplanes; balance is adjusted by moving the counterweight sliding block 3 on the second beam body, so that the adjustment of a balance state is more convenient.
In a preferred embodiment of the present invention, as shown in fig. 2, the balance moment measuring assembly further comprises a dummy weight slider 7, and the dummy weight slider 7 is movable on the balance beam 1 for position adjustment.
Further, the number of the simulated weight sliders 7 is multiple, at least two of the simulated weight sliders 7 have different weights, and preferably, the weights of the simulated weight sliders 7 are all different, so as to simulate different weights.
The situation of rebalancing after installing a balancing weight on a control surface or a wing can be simulated by simulating the counterweight sliding block 7, the measured static balance moment can meet the standard requirement by adjusting the weight and the position of the simulated counterweight sliding block 7, the balancing weights with the same weight are configured on the control surface or the wing according to the weight of the simulated counterweight sliding block 7 when the static balance moment meets the requirement, and the balancing weights are configured at corresponding positions on the control surface or the wing according to the position of the simulated counterweight sliding block 7 when the static balance moment meets the requirement, wherein the corresponding positions refer to the same vertical distance from the same side of a rotating shaft of the control surface to the rotating shaft of the control surface.
According to the invention, through the arrangement of the simulated counterweight sliding block 7, a theoretical basis is provided for the installation of the counterweight blocks on the control surface or the wing, so that the static balance moment of the control surface can be accurately adjusted, and the scrapping and reworking of aircraft materials caused by improper repair can be avoided.
In an embodiment of the present invention, as shown in fig. 2, a first groove 31 is provided on the counterweight sliding block 3, and the first groove 31 is adapted to the second beam body, so as to realize the combination of the first groove 31 and the second beam body, so that the counterweight sliding block 3 can slide on the second beam body; the simulated weight sliding block 7 is provided with a second groove 71, and the second groove 71 is matched with the balance beam 1 so as to realize the combination of the second groove 71 and the balance beam 1, so that the simulated weight sliding block 7 can slide on the balance beam 1.
In a preferred embodiment of the invention, the adjustment device further comprises a data acquisition and processing assembly, said data acquisition and processing assembly comprising a laser tracker,
the laser tracker is used for measuring the position information of the control surface 9, the balance beam 1, the movable hanger 2, the counterweight sliding block 3, the simulation counterweight sliding block 7 and the indicating part 4.
In another preferred embodiment of the present invention, the data collecting and processing component further comprises a controller, the controller is connected with the laser tracker and the weight detecting device 5, and the laser tracker feeds back the position information to the controller; the weight detecting device 5 feeds back the measured value to the controller, the controller performs calculation of the static equilibrium moment of the control surface around the control surface rotation axis and judgment of whether the equilibrium state and the static equilibrium moment meet the requirements according to the position information and the measured value information, and the controller can calculate an adjustment scheme when a certain judgment result does not meet the requirements.
According to the invention, by arranging the laser tracker, manual measurement errors are avoided, so that the measurement result is relatively accurate; through setting up the controller, can guarantee the accuracy of measurement condition and equilibrium moment measuring result, further avoid human error, guarantee the degree of accuracy, still accelerated detection speed simultaneously.
In one embodiment of the present invention, as shown in fig. 1, the support assembly includes a console 81 and a support 82 disposed on the console 81, the support 82 extends outward to form a support platform 83 for supporting the control surface connecting portion, and the number of the console and the support is not limited by the present invention.
In conclusion, the aircraft control surface static balance moment adjusting device has universality, different control surfaces of various types can be measured by changing the size of the balance moment measuring component and the weight of the movable counterweight, the operation is simple, the automation degree is high, the precision is high, the device is far superior to the traditional mode, and the control surface static balance measuring time can be greatly shortened. If the balance moment does not meet the requirement, calculating and simulating the rebalance condition after repair, and avoiding the scrapping and reworking of the aviation material caused by improper repair.
The invention also discloses an aircraft control surface static balance moment adjusting method, which comprises the following steps:
before the adjustment, the following preparation work is also included:
checking whether relevant information is preset in the controller, namely whether balance state requirements (the balance beam 1 and the control surface neutral plane are horizontal, the balance beam 1 is vertical to the control surface rotating shaft), static balance moment value requirements and rebalancing measures (the static balance moment value standard requirements and the rebalancing measures in an airplane flight manual), weights of a movable hanging rack, weight measuring equipment and a clamping piece and the like are preset;
checking whether the laser tracker is corrected;
checking whether the control surface is in a flight configuration state (sprayed paint, an electrostatic brush, an adjusting sheet, an operating rod and the like are installed) or not, and whether the adjusting sheet (if any) of the control surface is in a neutral position or not;
and installing a static balance moment adjusting device of the airplane control surface.
After the preparation is completed, entering the regulating program
The method comprises the following steps: acquiring position information of a control surface 9, a balance beam 1, a counterweight sliding block 3, a movable hanger 2 and a clamping piece 6 sent by a laser tracker, and judging whether the position information meets the requirement of a preset balance state;
namely, whether the center of the indication part of the balance beam is aligned with the control surface rotating shaft, whether the balance beam 1 and the control surface neutral plane are horizontal and whether the balance beam 1 and the control surface rotating shaft are vertical are judged according to the position information.
Step two: if yes, executing the third step; if not, calculating and visualizing the displacement information of the balance beam 1, the counterweight sliding block 3, the movable hanging frame 2 and the clamping piece 6, and executing the step one after the positions of the balance beam 1, the counterweight sliding block 3, the movable hanging frame 2 and the clamping piece 6 are adjusted according to the displacement information;
when the preset balance state requirement is not met, the controller calculates the displacement information of the better balance beam 1, the counterweight sliding block 3, the movable hanging frame 2 and the clamping piece 6 according to the position information of the current control surface 9 and the balance beam 1 so that the position information of the control surface 9 and the balance beam 1 meets the preset balance state requirement, adjusts the positions of the balance beam 1, the counterweight sliding block 3, the movable hanging frame 2 and the clamping piece 6 according to the displacement information calculated by the controller, and performs the step one again until the finally adjusted position information meets the preset balance requirement;
step three: the method comprises the steps of obtaining position information of a movable hanger 2 and an indicating part 4 sent by a laser tracker and a detection value sent by a weight detection device 5, calculating a static balance moment value of a control surface, and judging whether the static balance moment value of the control surface meets the requirement of a preset static balance moment value;
control surface static equilibrium moment value = force (i.e. detected value of weight detecting device) for keeping control surface static equilibrium X force arm (i.e. distance from middle of indication part 4 to middle of moving hanger 2) for keeping control surface static equilibrium-equilibrium moment value of equilibrium moment measuring assembly itself
Moment of balance measuring assembly self moment of balance = arm of total weight X of the mobile hanger 2, the weight detecting device 5 and the clamp 6 (arm of force keeping the control surface in static balance)
Step four: if yes, executing a fifth step, otherwise, calculating and visualizing the weight and the position of the simulation counterweight sliding block 7, configuring the counterweight sliding block 7 to be simulated according to the weight and the position, and executing the first step again;
that is, when the control surface static balance moment value does not meet the standard requirement, the simulated weight slider 7 is needed to simulate the installation weight and position of the actual counterweight so as to enable the control surface static balance moment to meet the requirement, and the weight and position of the simulated weight slider 7 can be calculated by the controller according to the balance moment deviation data and the counterweight weight allowable increase/decrease data (namely related regulations of rebalancing measures) specified by the manual.
For example, when the static balance moment value of the control surface is larger than the standard requirement, the controller calculates that a counterweight sliding block with a certain weight is installed at a certain position on the opposite side of the control surface; when the static balance moment value of the control surface is smaller than the standard requirement, the controller calculates that a counterweight sliding block with certain weight is arranged at a certain position of the control surface,
configuring the weight and the position of the simulation sliding block 7 according to the calculation result of the controller, slightly adjusting according to the actual situation in the process, and executing the step one again after the configuration is finished;
step five: and outputting the weight and the position of the simulated counterweight sliding block 7, so as to configure the weight and the position of the actual counterweight block according to the weight and the position of the simulated counterweight sliding block 7.
If the static balance moment value of the control surface is within the preset static balance moment requirement range in the fourth step, and the weight of the simulated counterweight sliding block output in the fifth step is 0, the weight of the actual counterweight block to be configured is 0, namely the actual counterweight block does not need to be configured;
if the simulated counterweight sliding block 7 exists, when the static balance moment value of the control surface meets the requirement of the preset static balance moment, the weight and the position of the simulated counterweight sliding block 7 are used for configuring the weight and the position of the actual counterweight block.
By the adjusting method, the mounting weight and the mounting position of the actual counter weight can be accurately calculated when the static balance moment of the control surface meets the standard requirement, so that the static balance moment of the control surface can be accurately adjusted, and aircraft material scrapping and reworking caused by improper repair are avoided.
The above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art may still modify the technical solutions described in the foregoing embodiments, or may equally substitute some or all of the technical features; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.
Claims (10)
1. An aircraft control surface static balance moment adjusting device is characterized in that: comprises a supporting component and a balance moment measuring component, the balance moment measuring component comprises a balance beam, a movable hanging frame and a counterweight sliding block,
the support assembly is used for supporting a control surface connection, which refers to a connection of a control surface for connection with a wing;
the middle part of the balance beam is provided with an indicating part, the indicating part is used for indicating a control surface rotating shaft, namely, during measurement, the indicating part is used for aligning with the control surface rotating shaft, when the control surface is connected with the wing, the indicating part can rotate around a certain fixed shaft, the fixed shaft is the control surface rotating shaft, and the indicating part enables the balance Liang Fencheng to be a first beam body and a second beam body;
the movable hanging rack can move on the first beam body and be locked, a weight detection device and a clamping piece are arranged on the movable hanging rack, the clamping piece is used for supporting the rear edge of the control surface, the clamping piece comprises a fixing portion and a clamping portion, the fixing portion is connected with the lower end of the movable support, the clamping portion is used for clamping the rear edge of the control surface and can move on the fixing portion and be locked, when the clamping piece supports the rear edge of the control surface, the position of the clamping portion on the fixing portion is adjusted, so that a control surface center plane is parallel to the balance beam, and the control surface center plane refers to a plane which passes through the center line of the rear edge of the control surface and a control surface rotating shaft at the same time;
the counterweight slider is movable on the second beam.
2. The adjustment device of claim 1, wherein: the balance moment measuring assembly further comprises a simulated counterweight sliding block, and the simulated counterweight sliding block can move on the balance beam.
3. The adjustment device according to claim 2, characterized in that:
a first groove is formed in the counterweight sliding block and is matched with the second beam body;
and a second groove is formed in the simulation counterweight sliding block and is matched with the balance beam.
4. The adjustment device according to claim 2, characterized in that:
the number of the counterweight sliding blocks is multiple, and the weights of at least two counterweight sliding blocks are different;
and/or
The simulation counterweight sliding blocks are multiple, and the weights of at least two simulation counterweight sliding blocks are different.
5. The adjustment device according to claim 2, characterized in that: further comprising a data acquisition and processing component comprising a laser tracker,
the laser tracker is used for measuring position information of the control surface, the balance beam, the movable hanging rack, the counterweight sliding block, the simulation counterweight sliding block and the indicating part.
6. The adjustment device of claim 5, wherein: the data acquisition and processing assembly further comprises a controller connected with the laser tracker and the weight detection device,
the laser tracker feeds the position information back to the controller;
the weight detecting device feeds back the measured value to the controller.
7. The adjustment device of claim 1, wherein: the support assembly comprises an operating platform and a support arranged on the operating platform, a support platform extends outwards to form the support, and the support platform is used for supporting the control surface connecting part.
8. The adjustment device of claim 1, wherein: the weight detecting device is a weight sensor.
9. An aircraft control surface static balance moment adjusting method is characterized by comprising the following steps: with the adjustment device according to claim 2, the adjustment is carried out by the following steps:
the method comprises the following steps: acquiring position information of a control surface, a balance beam, a counterweight sliding block, a movable hanging rack and a clamping piece sent by a laser tracker, and judging whether the position information meets the requirement of a preset balance state;
step two: if yes, executing the third step; if not, calculating and visualizing the displacement information of the balance beam, the counterweight sliding block, the movable hanging rack and the clamping piece, and executing the step one after the positions of the balance beam, the counterweight sliding block, the movable hanging rack and the clamping piece are adjusted according to the displacement information;
step three: the method comprises the steps of obtaining position information of a movable hanging rack and an indicating part sent by a laser tracker and a detection value sent by weight detection equipment, calculating a control surface static balance moment value, and judging whether the control surface static balance moment value meets the requirement of a preset static balance moment value;
step four: if so, executing a fifth step, otherwise, calculating and visually simulating the weight and the position of the counterweight sliding block, configuring the counterweight sliding block to be simulated according to the weight and the position, and executing the first step again;
step five: and outputting the weight and the position of the simulated counterweight sliding block so as to configure the weight and the position of the actual counterweight according to the weight and the position of the simulated counterweight sliding block.
10. The adjustment method according to claim 9, characterized in that: the balance state requirement in the first step is as follows: the center of the balance beam indicating part is aligned with the control surface rotating shaft, the balance beam and the control surface neutral plane are horizontal, and the balance beam is vertical to the control surface rotating shaft.
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| CN113998144A (en) * | 2021-11-26 | 2022-02-01 | 昌河飞机工业（集团）有限责任公司 | Measuring device of adjustable counter weight |
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| ES2540935T3 (en) * | 2012-07-20 | 2015-07-14 | Airbus Operations S.L. | Measurement of the inertial properties of a movable control surface |
| US9297719B2 (en) * | 2013-04-26 | 2016-03-29 | Honda Patents & Technologies North America, Llc | Flight control system loading test apparatus and method |
| FR3061135B1 (en) * | 2016-12-23 | 2019-05-24 | Safran Electronics & Defense | FLYING MOBILE SURFACE HAVING AT LEAST ONE INTEGRATED ACTUATOR |
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| CN109341948A (en) * | 2018-11-28 | 2019-02-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft wing rudder face and rudder rotational inertia measuring device and measurement method |
| CN110567641B (en) * | 2019-08-15 | 2021-07-13 | 北京航天控制仪器研究所 | Isomer radial static balance adjusting method and device |
| CN112478197A (en) * | 2020-12-07 | 2021-03-12 | 中国民用航空上海航空器适航审定中心 | Dynamic measurement method for clearance of airplane control surface |
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