Helicopter dynamic balance detection verification platform and method
By designing a helicopter maneuver balance detection and verification platform including the platform body, drive mechanism and detection mechanism, the problem of large error in helicopter maneuver balance detection in the prior art is solved, and efficient and low-cost helicopter vibration simulation and detection are achieved.
Patent Information
- Application Number
- CN202311811986.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-12-26
- Publication Date
- 2025-06-27
AI Technical Summary
In the prior art, the helicopter maneuver balance detection equipment cannot effectively simulate the actual helicopter vibration, resulting in large detection errors, and the experimental device platform that simulates working conditions is too large and consumes high, which is not conducive to experimental research.
A low-cost helicopter maneuver balance inspection and verification platform is designed, which includes the platform body, drive mechanism and inspection mechanism. Through the combination of the adapter shaft, blade mounting disc and counterweight disc, the vibration of the helicopter under different working conditions is simulated, and the acceleration sensor, photoelectric sensor and dynamic balance detection device are used for detection and calibration.
The platform can simulate helicopter vibration close to the actual working conditions, improve detection efficiency, reduce errors, reduce experimental costs, and facilitate systematic research on the helicopter vibration situation.
Smart Images
Figure CN120213337A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of helicopter design, and in particular to a helicopter dynamic balance detection and verification platform and method. Background Art
[0002] Helicopters require regular maintenance and overhaul, and helicopter rotor vibration and dynamic balance are very important detection links. Improper rotor dynamic balance debugging can reduce the riding comfort of pilots and passengers at best, or increase the force on related parts of the fuselage, thereby accelerating wear and reducing lifespan, and even causing crashes in severe cases. In related technologies, the detection solution for maintenance and servicing is to use equipment to detect and adjust the dynamic balance of the rotor. The helicopter dynamic balance simulation experimenter cannot simulate the vibration of an actual helicopter, and there are large errors, and the helicopter dynamic balance detection and adjustment equipment cannot be calibrated well. The experimenter designed to simulate actual working conditions has a platform size that is too large and costs too much, which is not conducive to experimental research. Summary of the invention
[0003] The present invention aims to solve one of the technical problems in the related art at least to a certain extent. To this end, an embodiment of the present invention proposes a low-cost platform that can simulate the vibration of an actual helicopter. The helicopter dynamic balance detection and verification platform and method have the advantages of a simulation effect close to the actual working condition and high verification efficiency.
[0004] According to the helicopter dynamic balance detection and verification platform of the embodiment of the present invention, the helicopter dynamic balance detection and verification platform includes a platform body, a driving mechanism and a detection mechanism, the platform body is provided with a transfer shaft, the transfer shaft passes through the platform body and is pivotally connected to the platform body, the blade mounting plate and the counterweight plate are sequentially sleeved on the transfer shaft along a preset direction, a plurality of blade mounting holes are arranged on the blade mounting plate, a plurality of counterweight holes are arranged on the counterweight plate, the driving mechanism is located on the platform body and is transmission-connected to the transfer shaft, the detection mechanism includes an acceleration sensor, a photoelectric sensor and a dynamic balance detection device, and the acceleration sensor and the photoelectric sensor are electrically connected to the dynamic balance detection device.
[0005] The helicopter dynamic balance detection and verification platform according to the embodiment of the present invention has the advantages of simulation effect close to the actual working condition and high verification efficiency. This application designs a vibration test bench for simulating helicopter vibration in view of the vibration caused by the rotation of the helicopter main rotor. The test bench can simulate the vibration of the helicopter under different working conditions, intuitively provide a balancing verification scheme, verify the effectiveness of the balancing scheme, and combine the balancing scheme provided by the dynamic balancing detection equipment to test the effectiveness of the helicopter dynamic balancing detection equipment.
[0006] In some embodiments, the counterweight holes are distributed along the radial direction of the counterweight plate, and a mounting hole is provided at the center of the counterweight plate for the adapter shaft to pass through.
[0007] In some embodiments, the counterweight holes are divided into multiple groups, and the multiple groups of counterweight holes are distributed around the center of the counterweight plate, and the interval between each group of counterweight holes and the adjacent group of counterweight holes is the same.
[0008] In some embodiments, a plurality of adjustment holes are provided on the blade, and the adjustment holes are evenly spaced along the length direction of the blade.
[0009] In some embodiments, the platform body includes a platform frame, a mounting plate and a moving portion, the mounting plate is located at a first end of the platform frame, and the moving portion is located at a second end of the platform frame.
[0010] In some embodiments, a center-of-gravity counterweight is further included, and the center-of-gravity counterweight is located on one side of the platform frame adjacent to the second end.
[0011] In some embodiments, the driving mechanism includes a motor, the motor is located on a side of the mounting plate adjacent to the second end of the platform frame, and the motor is drivingly connected to the transfer shaft.
[0012] In some embodiments, the blades on the blade mounting disk are blades with one attack angle or a combination of blades with several attack angles.
[0013] According to the helicopter dynamic balance detection and verification method of the embodiment of the present invention, the helicopter dynamic balance detection and verification method comprises the following steps:
[0014] The motor of the driving mechanism on the dynamic balance detection and verification platform is started, and the motor drives the connecting shaft to rotate, and the connecting shaft drives the blades on the blade mounting plate to rotate and drives the counterweight plate to rotate;
[0015] The acceleration sensor of the detection mechanism obtains the vibration data of the platform body, the photoelectric sensor of the detection mechanism obtains the blade speed data, and the dynamic balance detection device of the detection mechanism receives the vibration data and the speed data and outputs the balancing phase and quality data;
[0016] Select the counterweight points and arrange the counterweights on the counterweight plate on the dynamic balancing test and verification platform according to the trim phase and mass data;
[0017] Start the motor to drive the blades, counterweight plate and counterweight to rotate, and collect and receive vibration data and speed data;
[0018] Select counterweight points on the blades and arrange the counterweights to simulate vibrations under different working conditions;
[0019] The starting motor drives the blades, counterweight plate and counterweight to rotate, and collects and receives vibration data and speed data.
[0020] In some embodiments, different numbers of blades are installed on the blade mounting disc to simulate the vibrations of a helicopter with different numbers of rotor blades, or blades with different angles of attack are selected to simulate various operating conditions of the helicopter, and vibration data and rotational speed data are collected and received.
[0021] In view of the vibrations caused by the rotation of the main rotor of a helicopter, the present application designs a vibration test bench for simulating helicopter vibrations, which has the following beneficial effects:
[0022] This test bench can simulate the vibrations of a helicopter under different operating conditions, intuitively give a trim verification plan, verify the effectiveness of the trim plan, and in combination with the trim plan given by the dynamic balance detection equipment, test the effectiveness of the helicopter dynamic balance detection equipment.
[0023] The reasonable arrangement of counterweight holes on the counterweight disc provides a definite reference during dynamic balance research, facilitating the verification of the trim plan;
[0024] The adjustment holes provided on the blades facilitate the adjustment of the blade counterweights and the calculation of moment balance;
[0025] By matching the number and shape of the blades, more helicopter vibration data under different operating conditions can be obtained, facilitating the systematic study of the vibration situation. BRIEF DESCRIPTION OF THE DRAWINGS
[0026] Figure 1 is a schematic structural diagram of a helicopter dynamic balance detection and verification platform according to an embodiment of the present invention.
[0027] Figure 2 is Figure 1 a cross-sectional schematic diagram of
[0028] Figure 3 is Figure 1 a top view schematic diagram of
[0029] Figure 4 is Figure 3 a schematic structural diagram of the counterweight disc in
[0030] Reference numerals: 1, blade mounting disc; 2, counterweight disc; 21, counterweight screw; 22, counterweight hole; 3, blade; 31, adjustment hole; 4, photoelectric sensor; 5, mounting plate; 6, platform frame; 7, acceleration sensor; 8, center of gravity counterweight; 9, caster; 10, dynamic balance detection device; 11, adapter shaft; 12, fixing nut; 13, motor; 14, mounting hole. DETAILED DESCRIPTION OF THE EMBODIMENTS
[0031] The embodiments of the present invention will be described in detail below, and the examples of the embodiments are shown in the drawings. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present invention, but should not be construed as limiting the present invention.
[0032] According to the helicopter dynamic balance detection and verification platform of the embodiments of the present invention, the helicopter dynamic balance detection and verification platform includes a platform body, a driving mechanism and a detection mechanism. A transfer shaft is provided on the platform body. The transfer shaft passes through the platform body and is pivotally connected to the platform body. A blade mounting disc and a counterweight disc are sequentially sleeved on the transfer shaft along a preset direction, and the preset direction is Figure 2 the up-and-down direction shown in
[0033] Multiple blade mounting holes are provided on the blade mounting disc, and multiple counterweight holes are provided on the counterweight disc. The driving mechanism is located on the platform body and is in transmission connection with the transfer shaft. The detection mechanism includes an acceleration sensor, a photoelectric sensor and a dynamic balance detection device. The acceleration sensor and the photoelectric sensor are electrically connected to the dynamic balance detection device. The driving mechanism drives the transfer shaft on the platform body to rotate, thereby driving the blade mounting disc and the counterweight disc to rotate. Installing blades on the blade mounting disc can simulate the helicopter vibration caused by blade rotation, uneven blade mass distribution, blade air resistance and engine vibration, etc. in the actual helicopter working process. Adjusting the counterweight points on the counterweight disc can simulate the counterweight situation. According to the balancing schemes at various parts of the detection mechanism, balancing is carried out to verify the effectiveness of the scheme given by the dynamic balance detection device. The verification error is small and the cost is low, which is beneficial to experimental research on helicopter vibration and the effectiveness of detection equipment, improves the efficiency and reduces the on-board operation time.
[0034] According to the helicopter dynamic balance detection and verification platform of the embodiments of the present invention, it has the advantages of close simulation effect to the actual working conditions and high verification efficiency.
[0035] In some embodiments, the counterweight holes are distributed along the radial direction of the counterweight disc, and a mounting hole is provided in the center of the counterweight disc for the transfer shaft to pass through.
[0036] Specifically, the counterweight holes are distributed along the radius direction of the circular disc of the counterweight disc, which is convenient for calculating the distance from the counterweight holes to the center of the counterweight disc and for carrying out balancing adjustment. The transfer shaft passes through the central mounting hole to drive the counterweight disc to rotate accordingly. The mounting hole can be a D-shaped hole, and the cross-section of the transfer shaft is also a D-shaped cross-section. The relative positions of the transfer shaft and the counterweight disc are determined, which is convenient for having a definite reference during dynamic balance research.
[0037] In some embodiments, the counterweight holes are divided into multiple groups, and the multiple groups of counterweight holes are distributed around the center of the counterweight disc, and the interval between each group of counterweight holes and the adjacent group of counterweight holes is the same.
[0038] Specifically, the counterweight holes are divided into multiple groups. The number of counterweight holes in each group can be the same. The multiple counterweight holes in each group are in the same radial direction of the counterweight disc and are arranged in a straight line. The groups are in different radial directions of the counterweight disc, and the interval between each group and any adjacent group is the same, so that the groups are evenly distributed at equal angles on the counterweight disc, which is convenient for adjusting the counterweight position. In some embodiments, multiple adjustment holes are provided on the blade, and the adjustment holes are equally spaced along the length direction of the blade.
[0039] Specifically, the equal-spaced distribution of the adjustment holes on the blade facilitates the study of the vibration of the blade under different conditions. The counterweight screw can be screwed into the adjustment hole to fix the counterweight to the blade, and changing the position of the adjustment hole where the counterweight is installed can change the vibration of the blade. The equal-spaced arrangement of the adjustment holes facilitates the adjustment of the blade counterweight and the calculation of the moment balance.
[0040] In some embodiments, the platform body includes a platform frame, a mounting plate and a moving portion, wherein the mounting plate is located at a first end of the platform frame and the moving portion is located at a second end of the platform frame.
[0041] Specifically, the platform frame is a frame structure, and a mounting plate is provided in the first section of the frame structure. Two sensors of the detection mechanism are arranged on the mounting plate. The adapter shaft passes through the mounting plate and can rotate relative to the mounting plate. The blade mounting plate and the counterweight plate are sleeved on the adapter shaft. The first side of the mounting plate is adjacent to the blade mounting plate and the counterweight plate, and the second side of the mounting plate is adjacent to the second end of the frame structure. The movable part is placed at the second end of the platform frame and in contact with the ground. When the platform frame needs to be moved, the movable part facilitates the movement of the platform body.
[0042] In some embodiments, the platform further includes a center of gravity counterweight, which is located on one side of the platform frame adjacent to the second end.
[0043] Specifically, the center of gravity counterweight is used to adjust the center of the platform body. The center of gravity counterweight is placed near the second end of the platform frame to adjust the center of gravity so that the center of gravity of the platform body is below the vertical position of the adapter shaft, thereby avoiding the platform frame from tipping over due to the center of gravity offset and improving safety.
[0044] In some embodiments, the driving mechanism includes a motor, which is located on a side of the mounting plate adjacent to the second end of the platform frame, and the motor is drivingly connected to the transfer shaft.
[0045] Specifically, the output end of the motor is drivingly connected to the adapter shaft, the motor is located on the second side of the mounting plate, the motor and the counterweight plate and the blade mounting plate are separated by the mounting plate, and the motor places the center of gravity of the platform within the platform frame.
[0046] In some embodiments, the blades on the blade mounting disk are blades with one attack angle or a combination of blades with several attack angles.
[0047] Specifically, the blades on the blade mounting plate can be composed of blades with the same angle of attack, or can be composed of two or three blades with different angles of attack. This can simulate the common taper of the helicopter rotor at different angles of attack. The difference in the angle of attack between the blades increases or decreases, which can simulate the difference in the common taper of the helicopter blades.
[0048] In some embodiments, the moving portion includes three casters connected to the second end of the platform frame.
[0049] Specifically, three casters are used to simulate the three wheels of a helicopter, facilitating the movement of the platform body when it needs to be moved.
[0050] According to the helicopter dynamic balance detection and verification method of an embodiment of the present invention, the helicopter dynamic balance detection and verification method includes the following steps:
[0051] Start the motor of the drive mechanism on the dynamic balance detection and verification platform. The motor drives the connecting shaft to rotate, and the connecting shaft drives the blades on the blade mounting disc to rotate and drives the counterweight disc to rotate;
[0052] The acceleration sensor of the detection mechanism acquires the vibration data of the platform body, the photoelectric sensor of the detection mechanism acquires the blade rotation speed data, and the dynamic balance detection device of the detection mechanism receives the vibration data and rotation speed data and outputs the balancing phase and mass data;
[0053] Select the balancing points on the counterweight disc on the dynamic balance detection and verification platform according to the balancing phase and mass data and arrange the counterweights;
[0054] Start the motor to drive the blades, the counterweight disc and the counterweights to rotate, and collect and receive the vibration data and rotation speed data;
[0055] Select the balancing points on the blades and arrange the counterweights to simulate the vibrations under different working conditions;
[0056] Start the motor to drive the blades, the counterweight disc and the counterweights to rotate, and collect and receive the vibration data and rotation speed data.
[0057] As Figure 3 shown, the distance between the adjustment hole on the blade and the axis of the blade mounting disc is r1, r1 can be measured, the distance between the counterweight hole on the counterweight disc and the center of gravity of the counterweight disc is r2, r2 can be measured, and the angle θ between the counterweight hole and the adjustment hole on the blade can be measured. The dynamic balance detection device gives the balancing information.
[0058] The counterweight calculation is mainly carried out with reference to the angular momentum and centrifugal force formulas of the rotating body, as follows:
[0059]
[0060] The balancing principle is moment balance, as follows:
[0061] |F1| = |F2|
[0062] The calculation example is as follows: The blade counterweight is m1, the distance from the balancing point to the axis is r1, the rotational speed of the platform motor is ω. According to the dynamic balance principle, the required counterweight information on the counterweight disc can be theoretically calculated. The counterweight weight is m2, and the distance from the balancing point to the axis is r2. Then there is
[0063] m1r1w 2 = m1r2w2
[0064] The counterweight m2 is calculated by the above calculation formula. Comparing with the recommended values of the theoretical calculation for the vertical and dynamic balance detection device can test the accuracy of the equipment. Operating and starting the platform according to the aforementioned values can verify the data validity.
[0065] In some embodiments, different numbers of blades are installed on the blade mounting disc to simulate the vibrations of helicopters with different numbers of blades or blades with different angles of attack are selected to simulate various operating conditions of the helicopter, and vibration data and rotational speed data are collected and received.
[0066] Specifically, installing different numbers of blades can simulate the vibration conditions of helicopters with different numbers of blades. The blades can be designed with different angles of attack to study the coning situation of the helicopter rotor at different angles of attack. When the angles of attack of the blades are α1, α2, and α3 respectively, the rotation of the simulated rotor causes vibration of the platform at this time. The storage capacity of the dynamic balance detection device is limited. The photoelectric sensor and the acceleration sensor can be connected to a PC device, and the vibration data under different operating conditions are collected and stored by the PC device to collect a large amount of data for studying the dynamic balance, and the vibration situation can be systematically studied.
[0067] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be construed as a limitation to the present invention.
[0068] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise specifically defined.
[0069] In the present invention, unless otherwise clearly specified or limited, terms such as "installed", "connected", "coupled", "fixed", etc. shall be construed in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral one; it may be a mechanical connection, an electrical connection, or communicable with each other; it may be directly connected, or indirectly connected through an intermediate medium, and it may be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0070] In the present invention, unless otherwise clearly specified or limited, the first feature being "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may be that the first feature is directly above or obliquely above the second feature, or merely indicates that the first feature has a higher horizontal height than the second feature. The first feature being "under", "beneath" and "underneath" the second feature may be that the first feature is directly below or obliquely below the second feature, or merely indicates that the first feature has a lower horizontal height than the second feature.
[0071] In the present invention, terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic descriptions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.
[0072] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Any changes, modifications, substitutions, and variations made by those of ordinary skill in the art to the above embodiments are within the protection scope of the present invention.
Claims
1. A helicopter dynamic balance detection and verification platform, characterized in that Comprising: A platform body, on which a transfer shaft is provided. The transfer shaft passes through the platform body and is pivotally connected to the platform body. A blade mounting disc and a counterweight disc are sequentially sleeved on the transfer shaft along a preset direction. A plurality of blade mounting holes are provided on the blade mounting disc, and a plurality of counterweight holes are provided on the counterweight disc; A driving mechanism, which is located on the platform body and is in transmission connection with the transfer shaft; A detection mechanism, which includes an acceleration sensor, a photoelectric sensor and a dynamic balance detection device. The acceleration sensor and the photoelectric sensor are electrically connected to the dynamic balance detection device.
2. The helicopter dynamic balance detection and verification platform according to claim 1, characterized in that The counterweight holes are distributed along the radial direction of the counterweight disc, and a mounting hole is provided in the center of the counterweight disc for the transfer shaft to pass through.
3. The helicopter dynamic balance detection and verification platform according to claim 2, characterized in that, The counterweight holes are divided into multiple groups, and the multiple groups of counterweight holes are distributed around the center of the counterweight disc. The interval between each group of counterweight holes and the adjacent group of counterweight holes is the same.
4. The helicopter dynamic balance detection and verification platform according to claim 1, characterized in that A plurality of adjustment holes are provided on the blade, and the adjustment holes are equally spaced along the length direction of the blade.
5. The helicopter dynamic balance detection and verification platform according to claim 1, characterized in that The platform body includes a platform frame, a mounting plate and a moving part. The mounting plate is located at the first end of the platform frame, and the moving part is located at the second end of the platform frame.
6. The helicopter dynamic balance detection and verification platform according to claim 5, characterized in that It further includes a center-of-gravity counterweight, which is located on one side of the platform frame adjacent to the second end.
7. The helicopter dynamic balance detection and verification platform according to claim 5, characterized in that The driving mechanism includes a motor, which is located on one side of the mounting plate adjacent to the second end of the platform frame, and the motor is in transmission connection with the transfer shaft.
8. The helicopter dynamic balance detection and verification platform according to claim 7, characterized in that, The blades on the blade mounting disc are a combination of a certain angle of attack blade or several angles of attack blades.
9. Helicopter dynamic balance detection and verification method, characterized in that, Including the following steps: Start the motor of the driving mechanism on the dynamic balance detection and verification platform. The motor drives the connecting shaft to rotate, and the connecting shaft drives the blades on the blade mounting disc to rotate and drives the counterweight disc to rotate; The acceleration sensor of the detection mechanism acquires the vibration data of the platform body, the photoelectric sensor of the detection mechanism acquires the blade rotation speed data, and the dynamic balance detection device of the detection mechanism receives the vibration data and the rotation speed data and outputs the balancing phase and mass data; Select the balancing points on the counterweight disc on the dynamic balance detection and verification platform according to the balancing phase and mass data and arrange the counterweights; Start the motor to drive the blades, the counterweight disc and the counterweights to rotate, and collect and receive the vibration data and the rotation speed data; Select the balancing points on the blades and arrange the counterweights to simulate the vibration under different working conditions; Start the motor to drive the blades, the counterweight disc and the counterweights to rotate, and collect and receive the vibration data and the rotation speed data.
10. The helicopter dynamic balance detection and verification method according to claim 9, wherein Install different numbers of blades on the blade mounting disc to simulate the vibration of a helicopter with different numbers of blades or select blades with different angles of attack to simulate various working conditions of the helicopter, and collect and receive the vibration data and the rotation speed data.