Folding morphing aircraft demonstration device capable of continuously changing angle

Abstract

The utility model discloses a foldable morphing aircraft demonstration device capable of continuously changing angles. The foldable morphing aircraft demonstration device comprises a basic frame, wings, a sensor module and an angle adjusting mechanism, the foundation frame is of a cuboid frame structure and is composed of a bottom plate, a top plate and a supporting frame. The angle adjusting mechanism is arranged between the bottom plate and the top plate; comprising a stepping motor, a worm and worm gear transmission unit and a gear transmission unit, and the stepping motor is fixed to the middle of a bottom plate through a motor mounting base; the worm and worm wheel transmission unit comprises a bearing seat, a bidirectional worm and a worm wheel; the gear transmission unit adopts a three-stage transmission shaft system, the output end of the gear transmission unit penetrates through the top plate and is connected with the wings, and the wings are symmetrically arranged on the two sides of the top plate; and sensor modules are mounted on the wings.

Description

Technical Field

[0001] This utility model relates to the field of dynamic design, and in particular to a foldable variant aircraft demonstration device with continuously variable angles. The device verifies the vibration characteristics and dynamic performance of the foldable variant aircraft in different folded states through design experiments, and uses sensors to monitor vibrations so as to optimize and reduce vibrations in the future. Background Technology

[0002] Currently, the main problem faced by aircraft during flight is that, due to their lightweight and high-strength design requirements, they are prone to high-frequency vibrations under aerodynamic loads or periodic excitations, which may induce flutter in special circumstances, seriously threatening structural safety. Solving this problem requires that the aircraft wings, while achieving automatic locking, continuously adjust their sweep angle through small changes to obtain better aerodynamic performance.

[0003] Existing folding morphing aircraft demonstrator devices with continuously variable angles primarily rely on large experimental platforms or full-function prototypes. These devices are complex in structure, costly, and have long manufacturing and maintenance cycles, making them unsuitable for teaching demonstrations and small-scale displays. Their main shortcomings include:

[0004] The integration is low. The wing folding, sweep angle adjustment and vibration monitoring modules in the demonstration device are mostly independent units, which are cumbersome to assemble and debug, and time-consuming and labor-intensive to maintain and replace parts later.

[0005] The lack of an intuitive demonstration function of the self-locking mechanism makes the wings prone to angular drift under external forces, making it impossible to maintain the required teaching angle for a long time, resulting in unstable demonstration effects.

[0006] Existing miniature demonstration devices are mostly made of conventional plastic or metal parts, which are costly to manufacture and have limited processing precision. This results in increased gaps in the fit during multiple assembly processes, affecting adjustment accuracy and stability.

[0007] Currently, there are few products on the market that can simultaneously demonstrate the vibration characteristics of small folding variant mechanisms, making it impossible to intuitively present the correlation between changes in the folding angle and the corresponding vibration state.

[0008] Therefore, there is an urgent need for a demonstration device with a simple structure, modular design, quick assembly on a small platform, and the ability to continuously adjust the wing folding sweep angle, self-locking, and vibration teaching, in order to meet the needs of university teaching, science popularization, and corporate presentations. Utility Model Content

[0009] The purpose of this invention is to overcome the shortcomings of existing technologies and address the problems of insufficient stability and lack of real-time monitoring and adjustment capabilities in existing folding morphing aircraft due to mechanical vibration during flight. This invention provides a folding morphing aircraft demonstration device with continuously variable angles, and monitors wing vibration through sensor modules mounted on the wings. By integrating high-precision sensors and optimizing the mechanical transmission structure, dynamic acquisition of vibration parameters and dynamic adjustment of wing folding are achieved, significantly improving flight stability and environmental adaptability.

[0010] The objective of this utility model is achieved through the following technical solution:

[0011] A foldable variant aircraft demonstrator with continuously variable angles includes a basic frame, wings, sensor modules, and an angle adjustment mechanism;

[0012] The basic frame is a cuboid frame structure, consisting of a bottom plate, a top plate, and a support frame. The bottom plate has support frames symmetrically arranged on both sides, and the top plate is fixed to the top of the support frames.

[0013] The angle adjustment mechanism is located between the base plate and the top plate; it includes a stepper motor, a worm gear transmission unit and a gear transmission unit, and the stepper motor is fixed to the middle of the base plate by a motor mounting bracket.

[0014] The worm gear transmission unit includes a bearing housing, a bidirectional worm, and a worm wheel. The bearing housing is also fixed in the middle of the base plate and located on one side of the motor mounting base. The rotating shafts at both ends of the bidirectional worm are rotatably connected to the bearing housing. The output shaft of the stepper motor is connected to one end of the bidirectional worm through a coupling. The worm wheel and gear transmission unit are symmetrically arranged on both sides of the bidirectional worm. The bidirectional worm and the worm wheels on both sides are connected by gear meshing transmission.

[0015] The gear transmission unit adopts a three-stage transmission shaft system, including a first transmission shaft, a first gear, a second transmission shaft, a second gear, a third transmission shaft, and a third gear. One end of the first transmission shaft is mounted on the middle of the worm gear, and the other end is mounted on the first gear. A sleeve is provided between the first gear and the worm gear. The base plate is provided with bearings for mounting the second and third transmission shafts. The second and third transmission shafts are respectively mounted on the second and third transmission shafts. The first gear is connected to the second gear and the third gear in sequence by gear meshing.

[0016] The top of the third drive shaft passes through the top plate and connects to the wing, which is symmetrically arranged on both sides of the top plate;

[0017] Sensor modules are installed on the wings.

[0018] Furthermore, both the basic frame and the bidirectional worm gear are manufactured by 3D printing. The 3D printing material is polylactic acid. Three sets of shaft mounting holes are symmetrically arranged on both sides of the longitudinal central axis of the basic frame, and the spacing tolerance between adjacent shaft mounting holes is controlled within ±0.05mm.

[0019] Furthermore, the wing adopts a variable sweep folding structure, and the angle adjustment mechanism enables continuous angle adjustment within the range of 0° to 90°.

[0020] Furthermore, the worm gear transmission unit has a self-locking function to ensure that the wing angle is fixed under the action of external force and to avoid uncontrolled changes; the symmetrically arranged gear transmission units ensure the consistency of the movement of the wings on both sides through synchronous transmission.

[0021] Furthermore, the wing is 3D printed using continuous carbon fiber reinforced PLA material, with a bending strength ≥89MPa and an impact strength ≥22.2kJ / m. 2 .

[0022] Furthermore, the sensor module consists of a signal transmission connector, an anti-interference housing, a mass block, and a base. The mass block is made of tungsten alloy, and the base is made of stainless steel. The base is fixedly connected to the wing surface by double-sided tape or bolts. The mass block is provided on the upper surface of the base. The anti-interference housing is fitted onto the base. The signal transmission connector is installed on the top surface of the anti-interference housing. A gasket is provided between the signal transmission connector and the anti-interference housing.

[0023] Compared with the prior art, the beneficial effects of the technical solution of this utility model are:

[0024] 1. High-precision continuous angle adjustment: The stepper motor and worm gear transmission mechanism, combined with a three-stage gear transmission ratio amplification, enable fine adjustment of the wing sweep angle in the range of 0° to 90°, ranging from 0.1° to 0.5°. The high-precision meshing of the transmission link ensures that there is no obvious gap or lag during the adjustment process, and the demonstrator can accurately set and reproduce any folding state.

[0025] 2. Self-locking stability: The self-locking structure formed by the bidirectional worm gear and worm wheel prevents the output end from driving the input shaft in reverse when the lead angle is less than the friction angle. This ensures that the wing maintains the set angle for a long time without external interference during the demonstration, ensuring stability and controllability and improving the safety and reliability of the demonstration. Furthermore, in the self-locking state, only the worm gear can drive the wing to rotate; the wing cannot deflect on its own, guaranteeing the accuracy of the rotation angle.

[0026] 3. Lightweight modular design: The base frame and components such as worm gears, gears, and wing fasteners are all 3D printed using PLA / continuous carbon fiber reinforced PLA, resulting in a high degree of structural integration, good interchangeability of parts, and an overall weight reduction of more than 30%, making it easy to carry and assemble quickly; the high smoothness of the 3D printed surface reduces motion friction and assembly tolerances, thereby reducing manufacturing costs and manufacturing time.

[0027] 4. Symmetrical layout and synchronous transmission: A three-stage transmission shaft system is symmetrically arranged on both sides of the base. The synchronous gear set in the middle ensures that the wings on both sides move synchronously, avoiding equipment tilting and uneven loading, and improving the uniformity of the demonstration and the visual effect.

[0028] 5. High-sensitivity vibration teaching: Miniature accelerometers are installed on the wing surface. The sensor mass is made of high-density tungsten alloy, and the base and shell are made of high-strength stainless steel and shielding layer design, which significantly improves the signal-to-noise ratio of vibration measurement. With a sampling frequency of more than 1kHz, the vibration frequency and amplitude of the wing can be captured in real time, and the vibration state and sweep angle changes can be demonstrated synchronously.

[0029] 7. Expandability and easy maintenance: The modular design supports quick replacement of different materials and transmission ratios, and different specifications of gear sets or wing styles can be changed according to teaching needs; disassembly and assembly do not require special tools, only an Allen wrench is needed, which improves the maintainability and upgrade potential of the device. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the overall three-dimensional structure of the aircraft demonstration device in this embodiment;

[0031] Figures 2 to 3 This is a half-section three-dimensional structural diagram of the aircraft demonstration device in this embodiment;

[0032] Figure 4 This is a schematic diagram of the wing structure;

[0033] Figure 5 Schematic diagram of the wing fixing component

[0034] Figure 6 This is a schematic diagram of the sleeve structure;

[0035] Figure 7 This is a schematic diagram of a two-way worm gear.

[0036] Figure 8 This is a schematic diagram of the worm gear structure;

[0037] Figure 9 This is a schematic diagram of the motor mounting bracket.

[0038] Figure 10 This is a schematic diagram of the sensor module.

[0039] Figure 11 This is a schematic diagram of the mass block structure;

[0040] Figure 12 This is a structural diagram of the base. Detailed Implementation

[0041] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only for explaining the present invention and are not intended to limit the present invention.

[0042] This embodiment provides a demonstration device for a foldable variant aircraft with continuously variable angles, see [link / reference]. Figures 1 to 3 It includes a basic frame, wings 2, sensor modules 3, and an angle adjustment mechanism;

[0043] The basic frame is a cuboid frame structure, consisting of a base plate 101, a top plate 102 and a support frame 103. The support frame 103 is symmetrically provided on both sides of the base plate 101, and the top plate 102 is fixed to the top of the support frame 103.

[0044] An angle adjustment mechanism is located between the base plate 101 and the top plate 102; it includes a stepper motor 401, a worm gear transmission unit and a gear transmission unit, and the stepper motor 401 is fixed to the middle of the base plate by a motor mounting base 402.

[0045] The worm gear transmission unit includes a bearing housing 502, a bidirectional worm 501, and a worm wheel 503. The bearing housing 502 is also fixed in the middle of the base plate and located on one side of the motor mounting base 402. The rotating shafts at both ends of the bidirectional worm 501 are rotatably connected to the bearing housing 502. The output shaft of the stepper motor 401 is connected to one end of the bidirectional worm 501 through a grooved coupling 403. Worm wheels 503 and gear transmission units are symmetrically arranged on both sides of the bidirectional worm 501. The bidirectional worm 501 and the worm wheels 503 on both sides are connected by gear meshing transmission. The specific shape and structure of the bidirectional worm 501 and worm wheel 503 in this embodiment are shown in [reference needed]. Figure 7 and Figure 8 The structural diagram of motor mounting bracket 402 is shown below. Figure 9 .

[0046] The gear transmission unit adopts a three-stage transmission shaft system, including a first transmission shaft 601, a first gear 602, a second transmission shaft 603, a second gear 604, a third transmission shaft 605, and a third gear 606. One end of the first transmission shaft 601 is mounted on the middle of the worm gear 503, and the other end is mounted on the first gear 602. A sleeve is provided between the first gear 602 and the worm gear 503 (see...). Figure 6The base plate 101 is provided with bearings for mounting the second drive shaft 603 and the third drive shaft 605. The second drive shaft 603 and the third drive shaft 605 are respectively mounted with the second gear 604 and the third gear 606. The first gear 602 is connected to the second gear 604 and the third gear 606 in a gear meshing manner.

[0047] In this embodiment, the pitch circle diameters of the worm gear 503, the first gear 602, the second gear 604, and the third gear 606 are 30mm, 25mm, 36mm, and 40mm, respectively, and the module is 1 for all of them.

[0048] The top of the third drive shaft 605 passes through the top plate 102 and connects to the wing 2, which is symmetrically positioned on both sides of the top plate 102; see Figure 4 and Figure 5 In this embodiment, each wing 2 is provided with four fixing holes and one shaft hole, and the top end of the third drive shaft 605 passes through... Figure 5 The wing fixing component is connected to the wing 2. The upper and lower sides of the wing fixing component are symmetrically and protrudingly provided with fastening sleeves that engage with the third drive shaft 605. The upper surface of the wing fixing component is tightly attached to the lower surface of the wing 2 and secured with bolts. The fastening sleeves on the upper part of the wing fixing component extend into the shaft hole. In this embodiment, the wing is 3D printed using high-strength continuous carbon fiber reinforced PLA material, with a bending strength ≥89MPa and an impact strength ≥22.2kJ / m. 2 It combines lightweight and high toughness, and can withstand dynamic loads under complex working conditions.

[0049] Each wing 2 is equipped with a sensor module 3, see Figures 10-12 The sensor module 3 consists of an M5 signal transmission connector 301, a waterproof gasket 302, an anti-interference housing 303, a mass block 304, and a base 305. During installation, a circular through-hole is drilled in the top of the anti-interference housing 303, and the signal transmission connector 301 is inserted into it. The waterproof gasket 302 is installed between the signal transmission connector 301 and the anti-interference housing 303. Simultaneously, the mass block 304, piezoelectric ceramics, and other main components are installed into the anti-interference housing 303. The base 305 is fixed to the surface of the wing 2 using double-sided tape or bolts. The mass block is bolted to the upper surface of the base 305, and the anti-interference housing 303 is fitted over the base 305. The mass block is made of a high-density tungsten alloy. The anti-interference housing 303 has a shielding layer to block signal interference. Considering the large vibration amplitude and easy wear of the main body of the device, the base needs to be made of corrosion-resistant, wear-resistant, and high-strength materials; high-strength stainless steel is selected as the base material.

[0050] Specifically, the self-locking effect is mainly provided by the mechanical characteristics of the worm gear itself. When the lead angle of the bidirectional worm is less than the equivalent friction angle between the meshing teeth, the mechanism has self-locking properties and can achieve reverse self-locking, meaning that only the worm can drive the worm wheel, and the worm wheel cannot drive the worm. In this example, the bidirectional worm acts as the driving component, transmitting the torque input from the stepper motor to two symmetrically distributed worm wheels. Through a series of gear transmissions, the torque is transmitted to the wing, causing it to rotate. When the wing is subjected to external disturbances or experiences overshoot due to its own inertia during movement, the torque generated by the wing is transmitted to the worm gear through the gears. However, due to its self-locking function, the worm wheel cannot drive the worm, ultimately causing the torque to act between the worm gear and worm until it cancels out.

[0051] The specific working process of the overall device is as follows: A data communication channel is established between the computer and the demonstration device. The stepper motor enters standby mode, and the transmission shaft system maintains its initial zero position. The sensor module is connected to the computer, driving the stepper motor to run. The output shaft drives the bidirectional worm to rotate synchronously through a flexible coupling. The worm meshes with the worm wheel at both ends, and drives the active gear to perform synchronous angular displacement through the first transmission shaft. The intermediate gear set performs secondary transmission ratio amplification, and drives the end long shaft to perform precise angular deflection through the third transmission shaft. The rigidly connected wing module generates periodic motion with a predetermined amplitude, forming a vibration excitation source. The sensor module array collects the dynamic acceleration distribution on the wing surface at a sampling frequency of ≥1kHz, and then processes it into vibration parameters. The feedback control quantity is generated through a PID algorithm, and the acceleration and deceleration S-curve speed planning mode of the stepper motor is dynamically adjusted. The wing vibration parameters are corrected through the three-stage transmission system, and the final experimental data is presented on the computer.

[0052] The stepper motor output speed adopts an S-curve speed planning, which allows it to quickly enter the working speed while running smoothly during the start-stop phase, preventing motor step loss and wing overshoot, and facilitating more precise angle control.

[0053] Control commands can be developed based on embedded systems, performing basic motor control while receiving sensor data and generating control commands through a proportional-integral-derivative (PID) algorithm, and displaying the real-time rotation angle and speed on a screen; alternatively, the stepper motor drive can be manually controlled based on data measured by the sensor module and information displayed on a computer.

[0054] This utility model is not limited to the embodiments described above. The above description of specific embodiments is intended to illustrate and explain the technical solution of this utility model. The specific embodiments described above are merely illustrative and not restrictive. Without departing from the spirit and scope of protection of this utility model and the claims, those skilled in the art can make many specific modifications based on the teachings of this utility model, and these modifications all fall within the protection scope of this utility model.

Claims

1. A foldable variant aircraft demonstration device with continuously variable angles, characterized in that, Includes the basic frame, wings, sensor modules, and angle adjustment mechanism; The basic frame is a cuboid frame structure, consisting of a bottom plate, a top plate, and a support frame. The bottom plate has support frames symmetrically arranged on both sides, and the top plate is fixed to the top of the support frames. The angle adjustment mechanism is located between the base plate and the top plate; it includes a stepper motor, a worm gear transmission unit and a gear transmission unit, and the stepper motor is fixed to the middle of the base plate by a motor mounting bracket. The worm gear transmission unit includes a bearing housing, a bidirectional worm, and a worm wheel. The bearing housing is also fixed in the middle of the base plate and located on one side of the motor mounting base. The rotating shafts at both ends of the bidirectional worm are rotatably connected to the bearing housing. The output shaft of the stepper motor is connected to one end of the bidirectional worm through a coupling. The worm wheel and gear transmission unit are symmetrically arranged on both sides of the bidirectional worm. The bidirectional worm and the worm wheels on both sides are connected by gear meshing transmission. The gear transmission unit adopts a three-stage transmission shaft system, including a first transmission shaft, a first gear, a second transmission shaft, a second gear, a third transmission shaft, and a third gear. One end of the first transmission shaft is mounted on the middle of the worm gear, and the other end is mounted on the first gear. A sleeve is provided between the first gear and the worm gear. The base plate is provided with bearings for mounting the second and third transmission shafts. The second and third transmission shafts are respectively mounted on the second and third transmission shafts. The first gear is connected to the second gear and the third gear in sequence by gear meshing. The top of the third drive shaft passes through the top plate and connects to the wing, which is symmetrically arranged on both sides of the top plate; Sensor modules are installed on the wings.

2. The folding variant aircraft demonstration device with continuously variable angles according to claim 1, characterized in that, Both the basic frame and the bidirectional worm gear are manufactured using 3D printing with polylactic acid as the printing material. Three sets of shaft mounting holes are symmetrically arranged on both sides of the longitudinal central axis of the basic frame, with the spacing between adjacent shaft mounting holes controlled within ±... 0.05mm.

3. The folding variant aircraft demonstration device with continuously variable angles according to claim 1, characterized in that, The wing adopts a variable sweep folding structure, and the angle can be continuously adjusted within the range of 0° to 90° through an angle adjustment mechanism.

4. The folding variant aircraft demonstration device with continuously variable angles according to claim 1, characterized in that, The worm gear transmission unit has a self-locking function to ensure that the wing angle is fixed under the action of external force and to avoid uncontrolled changes; the symmetrically arranged gear transmission unit ensures the consistency of the movement of the wings on both sides through synchronous transmission.

5. A folding variant aircraft demonstration device with continuously variable angles according to claim 1, characterized in that, The wing is 3D printed from PLA material, with a bending strength ≥89MPa and an impact strength ≥22.2kJ / m. 2 .

6. A folding variant aircraft demonstration device with continuously variable angles according to claim 1, characterized in that, The sensor module consists of a signal transmission connector, an anti-interference housing, a mass block, and a base. The mass block is made of tungsten alloy, and the base is made of stainless steel. The base is fixed to the wing surface by double-sided tape or bolts. The mass block is located on the upper surface of the base. The anti-interference housing is attached to the base. The signal transmission connector is installed on the top surface of the anti-interference housing. A gasket is provided between the signal transmission connector and the anti-interference housing.

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