Auxiliary wing for adjusting gravity center of unmanned aerial vehicle
By designing the auxiliary wings for center of gravity adjustment on the drone, and using the coordination of the mobile plate and auxiliary wings to dynamically adjust the center of gravity of the drone, the problems of small adjustment range of the center of gravity and unstable flight are solved, and the flight stability and handling are improved.
Patent Information
- Application Number
- CN202510566328.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-30
- Publication Date
- 2025-06-06
AI Technical Summary
Existing drones are difficult to effectively adjust the center of gravity under load changes or airflow, resulting in unstable flight and poor handling.
A drone center of gravity adjustment auxiliary wing is designed, including auxiliary wings, adjustment components and detection components at the bottom of the fuselage. Through the coordination of the moving plate and auxiliary wing, the center of gravity is dynamically adjusted using the motor and sensor system, and the auxiliary wing can be deployed or combined to adjust the upper and lower center of gravity of the fuselage.
The dynamic adjustment of the center of gravity of the drone is realized, the range of center of gravity is expanded, and the flight stability and handling are improved, especially in the case of complex airflow or load changes.
Smart Images
Figure CN120096849A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to an auxiliary wing for adjusting the center of gravity of an unmanned aerial vehicle. Background Art
[0002] The center of gravity of a drone refers to the point where all its mass is concentrated. It is the point where the drone can maintain balance under the action of gravity. It determines the stability and controllability of the drone during flight. If the center of gravity is in the right position, the drone can fly more smoothly and respond to operating instructions more accurately; while an incorrect center of gravity position may cause the drone to be unstable or even lose control and other dangerous situations.
[0003] When the weight of the load carried by the drone is different from usual, such as carrying a different number of items or equipment, such as cameras, measuring instruments, etc., the center of gravity will shift and need to be adjusted to ensure stable flight. Nowadays, the center of gravity is changed by adjusting the position of the battery, but the battery has a limited movable position and the center of gravity of the fuselage cannot be adjusted over a large range.
[0004] When a drone flies from a relatively calm environment to an area with strong airflow, such as mountains, the seaside, or between high-rise buildings in a city, the complex airflow may affect the flight stability of the drone. At this time, properly lowering the center of gravity can help the drone better resist airflow interference. However, today's drones lack the structure to lower the center of gravity, and cannot adjust the center of gravity up and down. Summary of the invention
[0005] The purpose of the present invention is to overcome the deficiencies of the above-mentioned prior art and to provide a drone center of gravity adjustment auxiliary wing, which is intended to solve the technical problems in the prior art that the drone center of gravity adjustment range is small and there is a lack of a low center of gravity adjustment mechanism.
[0006] To achieve the above-mentioned purpose, the present invention proposes an auxiliary wing for adjusting the center of gravity of a drone, comprising a fuselage, four wings are mounted on the fuselage, and auxiliary wings, an adjustment component and a detection component are arranged at the bottom of the fuselage; The adjustment assembly comprises a movable plate, the movable plate slides on the bottom of the fuselage, and the auxiliary wing is installed in the movable plate; The detection assembly comprises a detection plate, the detection plate is located above the moving plate, a support ball and a trigger plate are arranged inside the detection plate, and the trigger plate abuts against the support ball; The auxiliary wing comprises two main wing panels and an aileron panel, and the aileron panel slides inside the main wing panel.
[0007] Preferably, a synchronous gear is fixed on one side of the main wing plate, and the two are rotatably connected to the movable plate and mesh with each other. A long gear is fixed on one side of the synchronous gear, and a wing plate groove is opened on one end face of the main wing plate, and the auxiliary wing plate slides in the wing plate groove.
[0008] Preferably, a wing screw is rotatably connected inside the main wing panel, the wing screw extends into the aile wing panel and is threadedly connected to the aile wing panel, a second motor is also installed inside the main wing panel, the second motor is power-connected to the wing screw through a bevel gear, and the long gear extends outward.
[0009] Preferably, one side end surface of the main wing panel and the aileron panel is arc-shaped, and a counterweight is provided at the end of the aileron panel.
[0010] Preferably, a connecting hole is opened at the bottom of the fuselage, a bracket motor is fixedly installed at the connecting hole, a bracket gear is fixed to the bracket motor through a rotating shaft, and the bracket gear is meshed with the long gear.
[0011] Preferably, a mounting block is fixed at the bottom of the fuselage, and the movable plate is buckled on the mounting block, that is, it slides on the mounting block, and a connecting push rod is fixed to one side end face of the movable plate. A first motor is also installed in the mounting block, and a threaded screw is provided on the first motor. The threaded screw extends to the inside of the connecting push rod and cooperates with the thread of the connecting push rod.
[0012] Preferably, the detection plate is fixed at the bottom of the fuselage, a detection cavity is opened inside the detection plate, the support ball is installed at the center of the bottom of the detection cavity, and the trigger plate is also located in the detection cavity.
[0013] Preferably, the supporting ball is a hemispherical body, and a hemispherical groove is provided at the bottom of the trigger plate, and the groove of the trigger plate matches with the supporting ball.
[0014] Preferably, four groups of contact sensors are arranged at the bottom of the detection cavity, abutting against the trigger plate.
[0015] Compared with the prior art, the beneficial effects of the auxiliary wing for adjusting the center of gravity of a drone provided by the present invention are as follows: 1. The first motor, the second motor and the bracket motor can be controlled by sensors to drive the auxiliary wing to move. The center of gravity of the drone body can be adjusted by the auxiliary wing, so that the drone can dynamically adjust or statically adjust the center of gravity offset to restore it to the center position. In addition, the auxiliary wing is longer and the adjustable range of its center of gravity is larger.
[0016] 2. Adjust the auxiliary wings to open to about 60° on both sides. Since the mobile board is at the center of gravity of the drone, the auxiliary wings can be used temporarily instead of the drone bracket. When the drone lands, it can support the drone standing on the ground for the user to pick up, and it also prevents the drone's blades from directly hitting the ground and causing damage.
[0017] 3. The auxiliary wings on both sides are driven by the bracket motor to expand to both sides or merge to the middle at the same time to adjust the upper and lower center of gravity of the fuselage. When encountering specific environments and operations such as strong winds and complex airflows, especially when the drone is taking aerial photos at high altitudes, the auxiliary wings can be merged to move the overall center of gravity of the fuselage downward, making the drone more stable and not easily shaken.
[0018] The features and advantages of the present invention will be described in detail through embodiments in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 It is a top view of an embodiment of the present invention.
[0020] Figure 2 is a bottom view of an embodiment of the present invention.
[0021] Figure 3 It is a half-section view of an embodiment of the present invention.
[0022] Figure 4 Embodiment of the present invention Figure 3 Enlarged view of point A in the figure.
[0023] Figure 5 4 is a view of an auxiliary wing according to an embodiment of the present invention.
[0024] Figure 6 4 is a bottom view of the auxiliary wing according to an embodiment of the present invention.
[0025] Figure 7 It is a view of a detection component according to an embodiment of the present invention.
[0026] Figure 8 FIG. 4 is a diagram showing the internal sensor distribution of the detection component according to an embodiment of the present invention.
[0027] Fig. 9 2 is a view of a moving plate according to an embodiment of the present invention.
[0028] Fig.10 3 is a view of the stent morphology of an embodiment of the present invention.
[0029] Fig.11 is a low center of gravity view of an embodiment of the present invention.
[0030] in: 10-fuselage; 11-wing; 12-mounting block; 13-connecting hole; 20-moving plate; 21-connecting push rod; 22-first motor; 30-main wing panel; 31-auxiliary wing panel; 32-wing panel screw rod; 33-second motor; 34-wing panel slot; 35-synchronous gear; 36-long gear; 40-bracket motor; 41-bracket gear; 50-detection disk; 51-detection chamber; 52-support ball; 53-trigger plate. DETAILED DESCRIPTION
[0031] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is further described in detail below through the accompanying drawings and embodiments. However, it should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the scope of the present invention. In addition, in the following description, the description of known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.
[0032] In the description of the present invention, it should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it may be directly on the other element or indirectly on the other element. When an element is referred to as being "connected to" another element, it may be directly connected to the other element or indirectly connected to the other element.
[0033] In the description of the present invention, it should be noted that the terms "center", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or the positions or positional relationships in which the invention product is usually placed when in use, 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 therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", "third" and the like are only used to distinguish descriptions, and cannot be understood as indicating or implying relative importance. Thus, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined. The meaning of "several" is one or more, unless otherwise clearly and specifically defined.
[0034] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0035] See also Figure 1-11 The embodiment of the present invention provides an auxiliary wing for adjusting the center of gravity of a drone, comprising a fuselage 10, on which four wings 11 are mounted, and the bottom of the fuselage 10 is provided with an auxiliary wing, an adjustment component and a detection component, the adjustment component comprising a moving plate 20, the moving plate 20 slides at the bottom of the fuselage 10, the auxiliary wing is mounted in the moving plate 20, a mounting block 12 is fixed at the bottom of the fuselage 10, the moving plate 20 is buckled on the mounting block 12, that is, it slides on the mounting block 12, a connecting push rod 21 is fixed to one side end surface of the moving plate 20, a first motor 22 is further mounted in the mounting block 12, the first motor 22 is electrically connected to the sensor signal in the detection disk 50, a threaded screw is arranged on the first motor 22, the threaded screw extends to the inside of the connecting push rod 21, and is threadedly matched with the connecting push rod 21, the threaded screw is driven to rotate by the first motor 22, and the first motor 22 and the auxiliary wing can be driven to move forward and backward by the connecting push rod 21 to adjust the center of gravity position in the front and rear directions.
[0036] The auxiliary wing includes two main wing panels 30 and aileron panels 31. The aileron panels 31 slide in the main wing panels 30. A synchronous gear 35 is fixed on one side of the main wing panels 30. The two are rotatably connected to the movable plate 20, and the two are meshed with each other. A long gear 36 is fixed on one side of the synchronous gear 35. A wing panel groove 34 is provided on one side end surface of the main wing panel 30. The aileron panels 31 slide in the wing panel groove 34. A connecting hole 13 is provided at the bottom of the fuselage 10. A bracket motor 40 is fixedly installed at the connecting hole 13. The bracket motor 40 is fixed with a bracket gear 41 through a rotating shaft. The bracket motor 40 is separately connected to the flight control module of the drone by electrical signals. The bracket gear 41 meshes with the long gear 36. The long gear 36 can be driven by the bracket motor 40 and the bracket gear 41. The wheel 36 rotates, thereby rotating the synchronous gear 35, so that the main wing panels 30 on both sides can be simultaneously unfolded to both sides or merged to the middle, so as to adjust the position of the upper and lower center of gravity of the fuselage. When encountering specific environments and operations such as strong winds, especially when the drone is taking aerial photos at high altitudes, the auxiliary wings can be merged to move the overall center of gravity of the fuselage downward, so that the drone is more stable and will not shake easily. By adjusting the auxiliary wings to open to about 60° on both sides, since the movable plate 20 is at the center of gravity of the drone, the auxiliary wings can be used to temporarily replace the drone bracket. When the drone lands, the drone can be supported to stand on the ground for the user to pick up, while also preventing the drone's blades from directly hitting the ground and causing damage.
[0037] A wing screw 32 is rotatably connected inside the main wing panel 30, and the wing screw 32 extends into the aileron panel 31 and is threadedly connected to the aileron panel 31. A second motor 33 is also installed inside the main wing panel 30. The second motor 33 is power-connected to the wing screw 32 through a bevel gear, and the second motor 33 is electrically connected to the sensor in the detection disk 50 through a signal wire. The long gear 36 extends outward, and one side end surface of the main wing panel 30 and the aileron panel 31 is arc-shaped. A counterweight is provided at the end of the aileron panel 31. Through the setting of the counterweight, the auxiliary wing moves a smaller distance, and its center of gravity changes greatly, so that it can be precisely controlled. The main wing panel 30 and the aileron panel 31 with arc surfaces cut the airflow when the drone is flying, which greatly reduces its flight resistance. Moreover, when it flies forward, the flow rate of the airflow is different, which will generate a certain lift, reduce the weight of the drone, and increase the controllability of the drone.
[0038] The detection assembly includes a detection plate 50, which is located above the moving plate 20. A support ball 52 and a trigger plate 53 are arranged inside the detection plate 50. The trigger plate 53 abuts against the support ball 52. The detection plate 50 is fixed to the bottom of the fuselage 10, and the detection plate 50 is located at the center of gravity of the drone. A detection cavity 51 is opened inside the detection plate 50. The support ball 52 is installed at the center of the bottom of the detection cavity 51. The trigger plate 53 is also located in the detection cavity 51. The support ball 52 is a hemispherical body. The bottom of the trigger plate 53 is provided with a hemispherical groove. The groove of the trigger plate 53 is in contact with the support ball 51. 2 cooperate with each other, and the two also have slight magnetism, which keeps the trigger plate 53 and the support ball 52 always connected, and also makes a certain friction between the two, so that when the trigger plate 53 deflects, the center of gravity of the drone has a certain error margin. Four groups of contact sensors are arranged at the bottom of the detection cavity 51, namely a, b, c, and d, and each group is arranged with a number of sensors. When the trigger plate 53 causes the drone body to deflect due to the center of gravity offset, the trigger plate 53 will fall and contact the sensor. When the trigger plate 53 deflects and contacts a, it means that the center of gravity of the fuselage is deflected to the left front. At this time, the sensor will start the second motor 33 and the first motor 22, wherein the right second motor 33 and the left second motor 33 both drive the aileron plate 31 to move rightward, so that the center of gravity gradually moves to the right, and the first motor 22 will drive the entire movable plate 20 to move backward, so that the center of gravity of the fuselage moves backward at the same time, and gradually restore the problem of the offset center of gravity of the fuselage to the center position. When the trigger plate 53 contacts point b due to deflection, it means that the center of gravity of the fuselage deflects to the left rear. At this time, the sensor will cause the right second motor 33 and the left second motor 33 to drive the aileron plate 31 to move rightward. The first motor 22 will drive the entire movable plate 20 to move forward until the trigger plate 53 is separated from the contact sensor again and is parallel to the bottom of the detection chamber 51. Similarly, when the trigger plate 53 contacts point c, the sensor will cause the right second motor 33 and the left second motor 33 to drive the aileron plate 31 to move leftward, and the first motor 22 will drive the entire movable plate 20 to move backward. When the trigger plate 53 contacts point d, the sensor will cause the right second motor 33 and the left second motor 33 to drive the aileron plate 31 to move leftward, and the first motor 22 will drive the entire movable plate 20 to move forward.
[0039] Therefore, the first motor 22, the second motor 33 and the bracket motor 40 can be controlled by sensors to drive the auxiliary wing to move, and the center of gravity of the drone body can be adjusted by the auxiliary wing, so that the drone can dynamically adjust or statically adjust the center of gravity offset and restore it to the center position.
[0040] Working principle: When in use, the drone stops horizontally in the air or is placed on the ground, and the center of gravity offset adjustment button is activated. At this time, the sensor in the detection plate 50 can be used. Then, if there is a problem with the center of gravity offset of the fuselage, the trigger plate 53 will deflect and contact the bottom of the detection cavity 51 and contact the sensor at the corresponding position. The sensor will drive the first motor 22 and the second motor 33 to start. According to the deflection position of the trigger plate 53, the first motor 22 and the second motor 33 drive the auxiliary wing to move in the opposite direction of the center of gravity offset, so as to gradually restore the problem of the center of gravity offset of the fuselage to the center position.
[0041] When the UAV needs high stability in the air, the bracket motor 40 can be started to merge the auxiliary wings inward to form a whole. At this time, since the auxiliary wings are located below the fuselage, the overall center of gravity of the fuselage moves downward, thereby increasing the stability of the UAV. When high stability is not required, the auxiliary wings can be fully deployed and their center of gravity is restored, thereby increasing the controllability and maneuverability of the UAV.
[0042] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modification, equivalent substitution or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims
1. An auxiliary wing for adjusting the center of gravity of an unmanned aerial vehicle, comprising a fuselage (10), on which four wings (11) are mounted, characterized in that: The bottom of the fuselage (10) is provided with auxiliary wings, an adjustment component and a detection component; The adjustment assembly comprises a movable plate (20), the movable plate (20) slides on the bottom of the fuselage (10), and the auxiliary wing is installed in the movable plate (20); The detection assembly comprises a detection plate (50), the detection plate (50) being located above the movable plate (20), a support ball (52) and a trigger plate (53) being arranged inside the detection plate (50), the trigger plate (53) being in contact with the support ball (52); The auxiliary wing comprises two main wing panels (30) and an aileron panel (31), and the aileron panel (31) slides inside the main wing panel (30).
2. The auxiliary wing for adjusting the center of gravity of a drone as claimed in claim 1, characterized in that: A synchronous gear (35) is fixed on one side of the main wing plate (30), and the two are rotatably connected to the movable plate (20), and the two are meshed with each other. A long gear (36) is fixed on one side of the synchronous gear (35). A wing plate groove (34) is formed on one end surface of the main wing plate (30), and the auxiliary wing plate (31) slides in the wing plate groove (34).
3. The center of gravity adjustment auxiliary wing of a UAV as claimed in claim 2, characterized in that: A wing screw (32) is also rotatably connected inside the main wing plate (30), and the wing screw (32) extends into the aile wing plate (31) and is threadedly connected to the aile wing plate (31). A second motor (33) is also installed inside the main wing plate (30), and the second motor (33) is connected to the wing screw (32) through a bevel gear. The long gear (36) extends outward.
4. The auxiliary wing for adjusting the center of gravity of a drone as claimed in claim 3, characterized in that: One side end surface of the main wing plate (30) and the aileron plate (31) is arranged in an arc shape, and a counterweight block is arranged at the end of the aileron plate (31).
5. The auxiliary wing for adjusting the center of gravity of an unmanned aerial vehicle according to claim 2, characterized in that: A connection hole (13) is provided at the bottom of the body (10), a support motor (40) is fixedly mounted at the connection hole (13), a support gear (41) is fixed to the support motor (40) via a rotating shaft, and the support gear (41) is meshed with the long gear (36).
6. The auxiliary wing for adjusting the center of gravity of a drone as claimed in claim 1, characterized in that: A mounting block (12) is fixed to the bottom of the body (10); the movable plate (20) is buckled on the mounting block (12), that is, it slides on the mounting block (12); a connecting push rod (21) is fixed to one end surface of the movable plate (20); a first motor (22) is also installed in the mounting block (12); a threaded screw is provided on the first motor (22); the threaded screw extends into the interior of the connecting push rod (21) and is threadably matched with the connecting push rod (21).
7. The auxiliary wing for adjusting the center of gravity of an unmanned aerial vehicle according to claim 1, characterized in that: The detection plate (50) is fixed to the bottom of the body (10); a detection cavity (51) is provided inside the detection plate (50); the support ball (52) is mounted at the center of the bottom of the detection cavity (51); and the trigger plate (53) is also located in the detection cavity (51).
8. The auxiliary wing for adjusting the center of gravity of an unmanned aerial vehicle according to claim 7, characterized in that: The supporting ball (52) is in the form of a hemispherical body, and a hemispherical groove is provided at the bottom of the trigger plate (53), and the groove of the trigger plate (53) matches the supporting ball (52).
9. The auxiliary wing for adjusting the center of gravity of an unmanned aerial vehicle according to claim 8, characterized in that: Four groups of contact sensors are arranged at the bottom of the detection cavity (51) and abut against the trigger plate (53).