Landing damping baffle for aeromodelling wings

Abstract

The invention relates to the technical field of model airplane flight control, and particularly discloses a landing damping baffle plate for a model airplane wing, which comprises a shell, a driving motor, a screw rod-sliding sleeve transmission mechanism and a connecting rod type movable top plate assembly. The driving motor drives the screw to rotate through the gear set, the sliding sleeve moves linearly, the movable top plate is driven to rise through the connecting rod to increase air resistance, and stable landing of the model airplane is achieved. The baffle is compact in structure and reliable in work.

Description

Technical Field

[0001] This invention belongs to the field of aircraft model flight control technology, specifically relating to a landing damping baffle for aircraft model wings. Background Technology

[0002] During landing, fixed-wing model aircraft require effective deceleration methods to achieve a smooth and safe landing due to their high inertia and airspeed. Current technologies commonly employ low-altitude flybys to dissipate energy or rely on elevator manipulation for a "pull-down" landing. These methods demand high operator skill and pose a significant risk of landing failure in confined spaces or when encountering crosswinds. Some advanced model aircraft borrow from real aircraft, using deflectable flaps or independent speed brakes to increase drag. However, these devices are typically complex in structure, occupy significant internal wing space, are heavy, and require sophisticated servo control systems, making them difficult to deploy effectively on ordinary fixed-wing model aircraft where lightweight, low-cost design and extremely limited space are paramount.

[0003] Therefore, in view of the above-mentioned shortcomings in the existing technology, there is an urgent need to develop a special landing damping device that is compact, lightweight, highly reliable, and easy to integrate into small aircraft wings. Summary of the Invention

[0004] This invention aims to address the aforementioned shortcomings in the existing technology by providing a landing damping baffle for model aircraft wings. The technical problem it addresses is how to design a compact, lightweight, reliable, and easily integrated dedicated landing drag-increasing device that can be installed within the space-constrained wings of fixed-wing model aircraft, thereby reducing the difficulty of landing operations and improving landing stability and safety.

[0005] To solve the above-mentioned technical problems, the present invention is implemented as follows: This invention provides a landing damping baffle for a model aircraft wing, comprising: case; The drive motor is installed inside the housing; A transmission mechanism is installed inside the housing, with its input end connected to the output end of the drive motor; the transmission mechanism includes a screw and a sliding sleeve that is threadedly engaged with the screw, and the drive motor can drive the screw to rotate so that the sliding sleeve moves linearly along the screw; The movable top plate assembly includes a base, a movable top plate, and a linkage mechanism; the base is used to fix to the wing, and the linkage mechanism is connected between the sliding sleeve and the movable top plate, converting the linear motion of the sliding sleeve into the rising or closing motion of the movable top plate relative to the base.

[0006] Furthermore, the transmission mechanism also includes a gear set, which includes motor teeth fixedly connected to the output shaft of the drive motor. The gear set is used to transmit power to the screw and achieve deceleration.

[0007] Furthermore, the gear set also includes a first gear meshing with the motor teeth and a second gear meshing with the first gear, the second gear being coaxially and fixedly connected to the screw.

[0008] Furthermore, the linkage mechanism includes a connecting piece hinged to the sliding sleeve, and connecting rods hinged to the connecting piece and the movable top plate, respectively.

[0009] Furthermore, it also includes a position detection mechanism for detecting the raised position of the movable top plate; the position detection mechanism is connected to the sliding sleeve in a transmission manner.

[0010] Furthermore, the position detection mechanism includes a potentiometer, and the rotating shaft of the potentiometer is connected to the sliding sleeve via the rotating shaft, so that the linear motion of the sliding sleeve can drive the rotating shaft to rotate.

[0011] Furthermore, the movable top plate assembly also includes a movable upper plate disposed between the base and the movable top plate.

[0012] Furthermore, the housing includes a detachably connected upper cover and a lower cover.

[0013] Furthermore, it also includes a positioning bracket for supporting the screw.

[0014] Compared with the prior art, the advantages of this invention are as follows: (1) Highly compact structure and high integration: By adopting a “screw-sliding sleeve” linear transmission combined with a compact linkage conversion mechanism, the drive, transmission and execution components are highly integrated into a small housing, which greatly saves valuable space inside the wing and is particularly suitable for model aircraft applications in small spaces.

[0015] (2) Reliable operation and precise control: The screw drive has self-locking properties, which can reliably keep the movable top plate in any raised position and has strong resistance to airflow interference. Combined with the optional position detection mechanism, it can achieve precise feedback and control of the opening degree of the movable top plate.

[0016] (3) Significant drag increase effect, which is conducive to smooth landing: The movable top plate can be raised quickly during landing, significantly increasing the drag of the wing, effectively reducing the airspeed and glide ratio of the model aircraft, thereby shortening the landing distance, reducing the over-reliance on the operator's instantaneous control skills, and improving the landing success rate and safety.

[0017] (4) Modular design, easy to install and maintain: The entire device can be installed as an independent module in the preset position of the wing. The shell is detachable, which facilitates the assembly, debugging and maintenance of internal components. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort, wherein: Figure 1 A three-dimensional structural schematic diagram of a landing damping baffle for a model aircraft wing provided by the present invention; Figure 2 An exploded structural diagram of a landing damping baffle for a model aircraft wing provided by the present invention; Figure 3 The diagram shows the working state of the landing damping baffle for the wing of a model aircraft provided by the present invention. Detailed Implementation

[0019] The technical solutions in the embodiments of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the present invention, and not all of it.

[0020] It should be noted that in the description of this invention, the terms "upper", "lower", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and do not indicate or imply that the device or element referred to must have a specific orientation. Therefore, they should not be construed as limiting this invention.

[0021] like Figure 1 and Figure 2 As shown, the landing damping baffle in this embodiment is a whole module, mainly including a housing, a driving part, a transmission part, an execution part, and a detection part.

[0022] The housing consists of an upper cover 1 and a lower cover 2, which are detachably connected by screws to form a sealed cavity for housing and protecting the internal mechanisms. The housing is designed to be flat to fit the limited space inside the wing of a model aircraft.

[0023] The core of the drive unit is the drive motor 13, which is fixed inside the housing via a mounting bracket. The transmission unit mainly includes a gear reduction mechanism and a screw linear transmission mechanism. The gear reduction mechanism consists of meshing motor teeth 5, a first gear 6, and a second gear 7. The motor teeth 5 are fixed to the output shaft of the drive motor 13, and the first gear 6 and the second gear 7 are mounted inside the housing via bearings. The second gear 7 is coaxially and fixedly connected to a screw 8, forming the final stage of the transmission.

[0024] The linear drive mechanism includes a screw 8 and a sliding sleeve 17 that is threadedly engaged with it. Both ends of the screw 8 are supported within the housing by positioning brackets 3. When the drive motor 13 is energized and rotates, the power is transmitted sequentially through the motor teeth 5, the first gear 6, and the second gear 7, ultimately driving the screw 8 to rotate. The rotational motion of the screw 8 is converted into precise linear motion of the sliding sleeve 17 along the screw axis through the threaded joint.

[0025] The actuator is a movable top plate assembly, used to convert the linear motion of the sliding sleeve into the opening and closing action of the drag plate on the wing surface. This assembly includes a base 10, a movable upper plate 11, a movable top plate 12, and a linkage mechanism. The base 10 is used to fix itself to a pre-set opening on the model aircraft wing by adhesive or screws. The movable upper plate 11 and movable top plate 12 are connected sequentially by hinges and ultimately hinged to the base 10, forming a foldable and deployable multi-segment structure. The linkage mechanism includes a connecting piece 9 and two connecting rods 4. One end of the connecting piece 9 is hinged to the sliding sleeve 17, and the other end is hinged to one end of each of the two connecting rods 4. The other ends of the two connecting rods 4 are respectively hinged to different positions on the movable top plate 12.

[0026] The detection section provides real-time feedback on the position of the movable top plate. It includes a PCB (printed circuit board) 14 and a potentiometer 15. The potentiometer 15 is mounted on the PCB 14, and its shaft is connected to the sliding sleeve 17 via a shaft 16. When the sliding sleeve 17 moves linearly, it rotates the shaft of the potentiometer 15 via the shaft 16, thereby changing the potentiometer's resistance value. This resistance value signal is acquired and processed by the circuitry on the PCB 14, and converted into a corresponding movable top plate opening position signal for the model aircraft's flight control system to read, achieving closed-loop control.

[0027] The working principle of this invention is as follows: When the model aircraft needs to land, the flight control system or receiver sends a command to the drive motor 13 to rotate it in the forward direction. Motor 13 drives the screw 8 to rotate via gear sets (5, 6, 7), which in turn drives the sliding sleeve 17 to... Figure 1 The sliding sleeve 17 moves in a straight line to the left (or other designated direction) via the connecting piece 9. The connecting piece 4 then pushes the movable top plate 12, causing it and the movable plate 11 to rotate outward and rise around their hinge point with the base 10, eventually protruding from the upper surface of the wing (e.g., ...). Figure 3 (Illustrative state) to create an obstacle to significantly increase air resistance. During this process, potentiometer 15 detects and feeds back the position signal in real time. When it is necessary to retract the baffle, the drive motor 13 is controlled to rotate in the opposite direction, and the components move in the reverse order described above, so that the movable top plate 12 is smoothly retracted into the wing surface.

[0028] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A landing damping baffle for a model aircraft wing, characterized in that, include: case; The drive motor (13) is installed inside the housing; A transmission mechanism is installed inside the housing, and its input end is connected to the output end of the drive motor (13). The transmission mechanism includes a screw (8) and a sliding sleeve (17) that is threadedly engaged with the screw (8). The drive motor (13) drives the screw (8) to rotate so that the sliding sleeve (17) moves linearly along the screw (8). The movable top plate assembly includes a base (10), a movable top plate (12), and a linkage mechanism; the base (10) is used to fix to the wing, and the linkage mechanism is connected between the sliding sleeve (17) and the movable top plate (12) to convert the linear motion of the sliding sleeve (17) into the raising or closing motion of the movable top plate (12) relative to the base (10).

2. The landing damping baffle for a model aircraft wing according to claim 1, characterized in that, The transmission mechanism also includes a gear set, which includes motor teeth (5) fixedly connected to the output shaft of the drive motor (13). The gear set is used to transmit power to the screw (8) and achieve deceleration.

3. The landing damping baffle for a model aircraft wing according to claim 2, characterized in that, The gear set also includes a first gear (6) meshing with the motor teeth (5) and a second gear (7) meshing with the first gear (6), wherein the second gear (7) is coaxially and fixedly connected to the screw (8).

4. The landing damping baffle for a model aircraft wing according to claim 1, characterized in that, The linkage mechanism includes a connecting piece (9) hinged to the sliding sleeve (17), and a connecting rod (4) hinged to the connecting piece (9) and the movable top plate (12) respectively.

5. The landing damping baffle for a model aircraft wing according to claim 1, characterized in that, It also includes a position detection mechanism for detecting the raised position of the movable top plate (12); the position detection mechanism is connected to the sliding sleeve (17) in a transmission manner.

6. The landing damping baffle for a model aircraft wing according to claim 5, characterized in that, The position detection mechanism includes a potentiometer (15), and the rotating shaft of the potentiometer (15) is connected to the sliding sleeve (17) through a rotating shaft (16), so that the linear motion of the sliding sleeve (17) can drive the rotating shaft to rotate.

7. The landing damping baffle for a model aircraft wing according to claim 1, characterized in that, The movable top plate assembly also includes a movable plate (11) disposed between the base (10) and the movable top plate (12).

8. The landing damping baffle for a model aircraft wing according to claim 1, characterized in that, The housing includes a detachably connected upper cover (1) and a lower cover (2).

9. The landing damping baffle for a model aircraft wing according to claim 1, characterized in that, It also includes a positioning bracket (3) for supporting the screw (8).

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