Flapping-wing aircraft launcher

Abstract

The present invention relates to a launcher for a flapping-wing aircraft, wherein a steel plate is provided for connecting the flapping-wing aircraft, the launcher comprising a base, a release lever, and an angle adjustment assembly. The base comprises a vertical rod, the release lever comprises an electromagnet for the steel plate, and the angle adjustment assembly is used to adjust the launch angle of the flapping-wing aircraft. The angle adjustment assembly comprises an angle adjustment rod and two angle adjustment plates. The angle adjustment rod is loosely and tightly connected to the two angle adjustment plates on either side, one of which is connected to the vertical rod, and the other is connected to the release lever. The present invention achieves flexible control of adjustable launch angles without significantly increasing the weight of the aircraft or changing its structure. This facilitates a simple launch process and is applicable to flapping-wing aircraft of most sizes and weights.

Description

Technical Field

[0001] The invention relates to a flapping-wing aircraft launching rack, belonging to the technical field of aircraft take-off. Background Art

[0002] Traditional flapping-wing aircraft require human assistance and throwing to launch. This launch method limits their autonomous capabilities, especially the fact that they are easily disturbed by human shaking during the launch process, and cannot maintain a stable pitch angle during takeoff. In order to solve the above problems, some aircraft use catapults to assist takeoff. For example, Ma Dongfu and others from the School of Aeronautics at Northwestern Polytechnical University designed a bird-like leg bouncing mechanism model and a bouncing takeoff flapping-wing aircraft system based on the crow's take-off method. The device catapults the flapping-wing aircraft to a safe height at a certain angle and accelerates it to the take-off speed. However, installing a bouncing device on the outside of the bird-like flapping-wing aircraft will increase the overall weight of the aircraft, making its dynamic model when flying in the air more complicated and difficult to maintain flight balance. For example, the pneumatic catapult device developed by Li Degeng and others from Xi'an Aisen UAV Technology Co., Ltd. uses the catapult device to simulate the takeoff of bird-like flapping-wing aircraft. Its advantage is that it does not increase the weight of the flapping-wing aircraft and there is no need to consider the impact of external devices on flight. However, before launching, the system usually needs to be inflated to reach a preset air pressure value. After the inflation is completed, the safety pin needs to be removed, and then the release mechanism is opened to release the pulley carrying the aircraft. The entire launching process is relatively cumbersome and is only suitable for small aircraft.

[0003] Existing takeoff systems place extremely high demands on the size, weight, and output power of flapping-wing aircraft. However, as aircraft scale, these requirements become difficult to achieve or severely impact other aspects of the aircraft's performance, such as payload capacity, endurance, and maneuverability. To address this issue, a flapping-wing aircraft launcher has been designed. This device is suitable for launching aircraft of most current sizes and weights and has promising applications in studying the takeoff process of birds under natural conditions. Summary of the Invention

[0004] The present invention provides a flapping-wing aircraft launcher designed to address at least one of the technical problems existing in the prior art. To this end, the present invention proposes a flapping-wing aircraft launcher that achieves flexible control with adjustable launch angles without significantly increasing the weight or changing the structure of the aircraft. This facilitates a simple launch process and is adaptable to flapping-wing aircraft of most sizes and weights.

[0005] One aspect of the technical solution of the present invention relates to a launcher for a flapping-wing aircraft, wherein the flapping-wing aircraft is provided with a steel plate, comprising:

[0006] A base, the base including a vertical pole;

[0007] a release lever comprising an electromagnet for engaging the steel plate;

[0008] An angle adjustment assembly is used to adjust the launch angle of a flapping-wing aircraft. The angle adjustment assembly includes an angle adjustment rod and two angle adjustment plates. The two sides of the angle adjustment rod are respectively loosely connected to the two angle adjustment plates, one of the angle adjustment plates is connected to the vertical pole, and the other angle adjustment plate is connected to the release rod.

[0009] Furthermore, the angle adjustment rod is provided with an adjustment groove, and the angle adjustment rod is connected to the angle adjustment plate through the cooperation of the adjustment groove and the bolt.

[0010] Furthermore, the angle adjustment rod is an aluminum profile.

[0011] Furthermore, the launch angle of the flapping-wing aircraft can be adjusted in a range of 0° to 180°.

[0012] Furthermore, the release lever is provided with a movable slider, and the electromagnet is provided on the slider.

[0013] Furthermore, the number of the electromagnets and the number of the steel plates are both two.

[0014] Furthermore, the number of the angle adjustment components is two groups, and the two angle adjustment plates are respectively connected to the two sides of the release rod.

[0015] Furthermore, the base includes an inclined support rod, one end of which is connected to the vertical rod.

[0016] Another aspect of the technical solution of the present invention relates to a method for taking off a flapping-wing aircraft, which is applied to the flapping-wing aircraft launcher of the above embodiment. The method according to the present invention comprises the following steps:

[0017] S100, loosening the two angle adjustment plates, adjusting the angle of the release rod by moving the angle adjustment rod, thereby making the launch angle of the flapping-wing aircraft reach a set value, and locking the angle adjustment rod on the vertical pole through the angle adjustment plates;

[0018] S200, tightening the steel plate by the electromagnet to fix the flapping-wing aircraft on the release rod;

[0019] S300: driving the flapping-wing aircraft and continuously increasing the flapping frequency to separate the steel plate from the electromagnet, thereby enabling the flapping-wing aircraft to take off autonomously.

[0020] Furthermore, when the power of the flapping-wing aircraft reaches a limited value, the steel plate is separated from the electromagnet by cutting off the power.

[0021] The beneficial effects of the present invention are as follows.

[0022] The flapping-wing aircraft launcher of the present invention achieves flexible control of adjustable launch angles without significantly increasing the weight of the aircraft or changing its structure, and is conducive to meeting the simplicity of the launch process, and is applicable to flapping-wing aircraft of most sizes and weights. In the implementation of the present invention, the flapping-wing aircraft relies on its own flapping to overcome the suction between the electromagnet and the steel plate to achieve autonomous takeoff. It only requires the installation of a steel plate on the aircraft, which is conducive to allowing the flapping-wing aircraft to maintain its original weight and structure to a greater extent. The electromagnet is set on the release lever, and the angle of the release lever is adjusted by the provided angle adjustment component, thereby adjusting the angle of the flapping-wing aircraft, thereby facilitating flexible control of the launch angle while meeting the simplicity of the launch process. The flapping-wing aircraft launcher of the embodiment of the present invention is suitable for the launch of most flapping-wing aircraft of current sizes and weights, and has good application prospects in studying the takeoff process of birds under natural conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 1 is a schematic structural diagram of a flapping-wing aircraft launcher according to an embodiment of the present invention.

[0024] Figure 2 yes Figure 1 A magnified schematic diagram of the front view at point A in the middle.

[0025] Figure 3 1 is a schematic structural diagram of a flapping-wing aircraft according to an embodiment of the present invention.

[0026] Figure 4 1 is a schematic structural diagram of a flapping-wing aircraft launcher according to an embodiment of the present invention applied to a flapping-wing aircraft.

[0027] Reference numerals:

[0028] 100 flapping-wing aircraft launcher; 110 base; 111 vertical pole; 112 support pole; 113 chassis; 120 release lever; 121 electromagnet; 130 angle adjustment assembly; 131 angle adjustment rod; 132 angle adjustment plate; 133 adjustment groove; 134 arc-shaped through groove;

[0029] 200 Flapping-wing aircraft; 210 Steel plate. DETAILED DESCRIPTION

[0030] The following will be combined with the embodiments and drawings to clearly and completely describe the concept, specific structure and technical effects of the present invention so as to fully understand the purpose, scheme and effect of the present invention. It should be noted that the embodiments and features in the embodiments of this application can be combined with each other unless there is a conflict.

[0031] It should be noted that, unless otherwise specified, when a feature is referred to as being "fixed" or "connected" to another feature, it may be directly fixed or connected to the other feature or indirectly fixed or connected to the other feature. Furthermore, terms such as "upper," "lower," "left," "right," "top," and "bottom" used in this disclosure are intended solely to describe the relative positions of the components of the disclosure as shown in the accompanying drawings.

[0032] In addition, unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art. The terms used in this specification are only for describing specific embodiments and are not intended to limit the present invention. The term "and / or" as used herein includes any combination of one or more of the related listed items.

[0033] It should be understood that although the terms first, second, third, etc. may be used to describe various elements in the present disclosure, these elements should not be limited to these terms. These terms are only used to distinguish elements of the same type from each other. For example, a first element may also be referred to as a second element, and similarly, a second element may also be referred to as a first element without departing from the scope of the present disclosure.

[0034] See also Figures 1 to 4 The flapping-wing aircraft launcher 100 of the technical solution of the present invention, wherein the flapping-wing aircraft 200 is provided with a steel plate 210, the flapping-wing aircraft launcher 100 includes a base 110, a release rod 120 and an angle adjustment assembly 130, and the base 110 includes a vertical rod 111. The release rod 120 includes an electromagnet 121 for connecting to the steel plate 210. The angle adjustment assembly 130 is used to adjust the launch angle of the flapping-wing aircraft 200, and the angle adjustment assembly 130 includes an angle adjustment rod 131 and two angle adjustment plates 132. The two sides of the angle adjustment rod 131 are respectively loosely connected to the two angle adjustment plates 132, one of the angle adjustment plates 132 is connected to the vertical rod 111, and the other angle adjustment plate 132 is connected to the release rod 120.

[0035] For details, see Figure 3 and Figure 4The electromagnet 121 draws the steel plate 210 on the flapping-wing aircraft 200 tightly, thereby securing the flapping-wing aircraft 200 to the flapping-wing aircraft launcher 100. The angle of the release lever 120 matches the launch angle of the flapping-wing aircraft 200. Simultaneously, the two angle adjustment plates 132 loosen or lock the angle adjustment lever 131 on the vertical pole 111. By adjusting the angle of the release lever 120, the launch angle of the flapping-wing aircraft 200 can be flexibly adjusted. This system is applicable to flapping-wing aircraft 200 of any shape. The system relies on the enormous thrust generated by the flapping of the flapping-wing aircraft 200 to separate the steel plate 210 from the electromagnet 121, thereby enabling the flapping-wing aircraft 200 to autonomously take off at the initial pitch angle, thereby simplifying the launch process.

[0036] In the embodiment of the present invention, the flapping-wing aircraft 200 achieves autonomous takeoff by overcoming the suction force between the electromagnet 121 and the steel plate 210 through its own flapping motion. This only requires the steel plate 210 to be added to the aircraft, which helps to maintain the original weight and structure of the flapping-wing aircraft 200 to a greater extent. Furthermore, the electromagnet 121 is disposed on the release lever 120, and the angle of the release lever 120 is adjusted by the provided angle adjustment assembly 130, thereby adjusting the angle of the flapping-wing aircraft 200. This facilitates flexible control of the launch angle while ensuring a simple launch process. The flapping-wing aircraft launcher 100 of the embodiment of the present invention is suitable for launching flapping-wing aircraft 200 of most current sizes and weights, and has good application prospects in studying the takeoff process of birds under natural conditions.

[0037] In some specific embodiments of the present invention, see Figure 1 The base 110 of the embodiment of the present invention includes a base frame 113 and a vertical rod 111. The base frame 113 is a square frame formed by a plurality of rods. The vertical rod 111 is arranged at the center of the square frame and extends upward. Specifically, the base frame 113 is composed of a plurality of cross bars and a plurality of vertical rods, and the cross bars and the vertical rods are connected by right-angle connectors. The vertical rod 111 is vertically arranged and perpendicular to the upper plane of the base frame 113. Furthermore, the base frame 113 also includes an obliquely arranged support rod 112, one end of the support rod 112 is connected to the vertical rod 111, and the other end is connected to the base frame 113. Specifically, the upper end of the support rod 112 is connected to the upper side of the vertical rod 111, and the lower end of the support rod 112 is connected to the upper side of the base frame 113, so that the support rod 112, the vertical rod 111 and one of the rods of the base frame 113 form a triangle, which is conducive to improving the stability of the base 110. In some specific embodiments, the uprights 111, support rods 112, and base frame 113 of the present invention are all made of aluminum profiles with grooves on all four sides for easy installation and connection. The base 110 of the present invention helps ensure that the flapping-wing aircraft 200 is virtually free of vibrations that could interfere with the experiment during autonomous takeoff.

[0038] In some specific embodiments of the present invention, see Figure 2 and Figure 4 The flapping-wing aircraft launcher 100 of the present invention includes a release lever 120 equipped with an electromagnet 121. The electromagnet 121 attracts a steel plate 210 on the flapping-wing aircraft 200, securing the flapping-wing aircraft 200 to the launcher 100 and maintaining the flapping-wing aircraft 200 in a predetermined initial position on the launcher 100. The present invention utilizes the electromagnet 121 and the steel plate 210 in conjunction with each other, allowing the flapping-wing aircraft 200 to be placed on the release lever 120 in a predetermined initial position simply by attaching two low-carbon steel plates to the aircraft body, without excessive restrictions on the aircraft's size and weight.

[0039] In some embodiments of the present invention, the release lever 120 is provided with a movable slider, and the electromagnet 121 is fixed to the slider, thereby adjusting the position of the electromagnet 121 on the release lever 120 via the slider. In some embodiments of the present invention, the release lever 120 is made of an aluminum profile, and the slider is provided with a protrusion that engages with a sliding groove in the aluminum profile, thereby achieving a sliding connection between the slider and the release lever 120. In some embodiments of the present invention, there are two electromagnets 121, the number of steel plates 210 is equal to the number of electromagnets 121, and the number of sliders is equal to the number of electromagnets 121. Therefore, the position of the electromagnet 121 on the release lever 120 and the distance between the electromagnets 121 can be appropriately adjusted according to the installation position of the steel plates 210 on the flapping-wing aircraft 200, thereby improving the adaptability of the flapping-wing aircraft launcher 100. It is understood that the number of electromagnets 121 in the embodiments of the present invention can be set to more than two, and the number of steel plates 210 and the number of sliders can be adjusted accordingly. It should be noted that the electromagnet 121 of the embodiment of the present invention generates magnetic force to attract the steel plate 210 when it is powered on, and when the electromagnet 121 is powered off, the steel plate 210 can be separated from the electromagnet 121. Furthermore, the steel plate 210 of the embodiment of the present invention is a low-carbon steel plate.

[0040] In some specific embodiments of the present invention, see Figure 1 and Figure 2The flapping-wing aircraft launcher 100 of the embodiment of the present invention includes an angle adjustment assembly 130 for adjusting the launch angle of the flapping-wing aircraft 200. The angle adjustment assembly 130 includes an angle adjustment rod 131 and two angle adjustment plates 132. The angle adjustment plate 132 is used to loosen or tighten the angle adjustment rod 131 and the vertical rod 111, thereby adjusting the angle of the release rod 120. Specifically, the angle adjustment rod 131 of the embodiment of the present invention is provided with an adjustment groove 133, and the angle adjustment plate 132 is provided with an arcuate through-slot 134. A bolt passing through the arcuate through-slot 134 can abut against the bottom wall of the adjustment groove 133. Thus, by unscrewing the bolt, the bottom end of the bolt is disengaged from the bottom wall of the adjustment groove 133, causing the angle adjustment rod 131 to release the vertical rod 111 and the release rod 120, thereby adjusting the contact position between the angle adjustment rod 131 and the vertical rod 111 and adjusting the angle of the release rod 120. Then, by tightening the screw so that the bottom end of the screw abuts against the bottom wall of the adjustment groove 133, the angle adjustment rod 131 is fixed to the vertical rod 111, and the release rod 120 is fixed to the base 110 at a desired angle. In some specific embodiments of the present invention, the angle adjustment rod 131 is an aluminum profile, which is made of aluminum profile.

[0041] Furthermore, there are two angle adjustment assemblies 130, one of which is disposed above the other. The right angle adjustment plates 132 of the two angle adjustment assemblies 130 are connected to the upper and lower ends of the release lever 120, respectively, and the left angle adjustment plates 132 of the two angle adjustment assemblies 130 are connected to the upper side of the vertical rod 111. This improves the convenience of angle adjustment, strengthens the stability of the release lever 120, and increases the angle adjustment range. Specifically, one side of two angle adjustment plates 132 is fixedly connected to the vertical rod 111 and disposed on the side of the vertical rod 111 facing the release lever 120, while one side of the other two angle adjustment plates 132 is fixedly connected to the release lever 120 and disposed on the side of the release lever 120 facing the vertical rod 111. A bolt is inserted into the arcuate slot 134 of each angle adjustment plate 132. By tightening the bolt, the angle adjustment rod 131 is fixed to the vertical rod 111 and the release lever 120. When the launch angle of the flapping-wing aircraft 200 needs to be adjusted, first loosen the bolts on the four angle adjustment plates 132, then adjust the contact position between the angle adjustment rod 131 and the vertical rod 111, and adjust the contact position between the angle adjustment rod 131 and the release rod 120 to change the angle of the release rod 120, and then tighten the four bolts so that the release rod 120 maintains the adjusted angle, thereby changing the initial pitch angle of the flapping-wing aircraft 200 when taking off.

[0042] It should be noted that the angle adjustment assembly 130 of the embodiment of the present invention can adjust the launch angle of the flapping-wing aircraft 200 between 0° and 180°. Figure 4In some specific implementations, two steel plates 210 are set on the straight rod of the flapping-wing aircraft 200. When the electromagnet 121 attracts the steel plates 210, the release rod 120 is parallel to the straight rod of the flapping-wing aircraft 200, so that the angle of the release rod 120 is consistent with the launch angle of the flapping-wing aircraft 200. For example, when the release rod 120 is set vertically, that is, when the angle of the release rod 120 is 90°, the flapping-wing aircraft 200 can achieve autonomous takeoff at an initial pitch angle of 90°. In this embodiment of the present invention, the angle of the release rod 120 matches the launch angle of the flapping-wing aircraft 200, thereby achieving a simple process for adjusting the initial launch angle.

[0043] See also Figures 1 to 4 The flapping-wing aircraft 200 takeoff method of the technical solution of the present invention is applied to the flapping-wing aircraft launcher 100 of the embodiment of the present invention, and the method includes at least the following steps:

[0044] S100, loosen the two angle adjustment plates 132, move the angle adjustment rod 131 to adjust the angle of the release rod 120, and thereby make the launch angle of the flapping-wing aircraft 200 reach a set value, and lock the angle adjustment rod 131 on the vertical pole 111 through the angle adjustment plates 132;

[0045] S200, tightening the steel plate 210 by the electromagnet 121 to fix the flapping-wing aircraft 200 on the release rod 120;

[0046] S300 , driving the flapping-wing aircraft 200 and continuously increasing the flapping frequency to separate the steel plate 210 from the electromagnet 121 , thereby enabling the flapping-wing aircraft 200 to take off autonomously.

[0047] The method for taking off a flapping-wing aircraft 200 according to an embodiment of the present invention is to suck the steel plate 210 on the flapping-wing aircraft 200 tightly by the electromagnet 121, and to flexibly adjust the launch angle of the flapping-wing aircraft 200 by the angle adjustment component 130, thereby relying on the huge thrust generated by the flapping of the flapping-wing aircraft 200 itself to make the steel plate 210 separate from the electromagnet 121, thereby realizing the autonomous takeoff of the flapping-wing aircraft 200 at the initial pitch angle. The method is applicable to flapping-wing aircraft 200 of any form.

[0048] Here we use a specific embodiment to illustrate, for example, see Figure 3 and Figure 4There are two electromagnets 121 and two steel plates 210, each mounted on the bottom of the flapping-wing aircraft 200. The spacing between the two electromagnets 121 is adjusted based on the positions of the two steel plates 210. When the electromagnets 121 firmly hold the steel plates 210, the wings of the flapping-wing aircraft 200 are positioned on the side of the release lever 120 facing away from the vertical rod 111, and the flapping-wing aircraft 200 is at a set launch angle. When the flapping-wing aircraft 200 flaps its wings to take off, as the flapping frequency of the flapping-wing aircraft 200 increases, the huge thrust generated by the flapping of the tail portion of the aircraft will separate from the electromagnets 121 before the aircraft's head. Subsequently, the aircraft's head and the electromagnets 121 will also be instantly separated due to the resulting tangential force, thereby enabling the flapping-wing aircraft 200 to autonomously take off at the set initial upward angle.

[0049] In some specific embodiments of the present invention, in the takeoff method for a flapping-wing aircraft 200 of the present invention, when the power of the flapping-wing aircraft 200 reaches a limit, the steel plate 210 is separated from the electromagnet 121 by powering off. Specifically, for some flapping-wing aircraft 200 with low power, which cannot separate from the electromagnet 121 through its own thrust, the electromagnet 121 can be de-energized to eliminate the suction force exerted by the electromagnet 121 on the steel plate 210, thereby enabling the flapping-wing aircraft 200 to take off autonomously after separating from the release lever 120. It will be appreciated that when the flapping-wing aircraft 200 reaches takeoff speed, the magnetic force of the electromagnet 121 can be eliminated by manual power-off or automatic power-off by a program, thereby enabling the flapping-wing aircraft 200 to take off autonomously.

[0050] The above description is merely a preferred embodiment of the present invention. The present invention is not limited to the aforementioned embodiments. As long as the technical effects of the present invention are achieved by the same means, any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present disclosure shall be included within the scope of protection of the present disclosure. Within the scope of protection of the present invention, its technical solutions and / or implementation methods may be modified and varied in various ways.

Claims

1. A flapping-wing aircraft launcher, characterized in that: The flapping-wing aircraft (200) is provided with a steel plate (210) comprising: A base (110), the base (110) comprising a vertical pole (111); a release rod (120), the release rod (120) comprising an electromagnet (121) for connecting to the steel plate (210); An angle adjustment assembly (130) is used to adjust the launch angle of the flapping-wing aircraft (200), the angle adjustment assembly (130) comprising an angle adjustment rod (131) and two angle adjustment plates (132), both sides of the angle adjustment rod (131) being loosely connected to the two angle adjustment plates (132), one of the angle adjustment plates (132) being connected to the vertical rod (111), and the other angle adjustment plate (132) being connected to the release rod (120); The angle adjustment rod (131) is provided with an adjustment groove (133), and the angle adjustment rod (131) is connected to the angle adjustment plate (132) through the adjustment groove (133) and the bolt; the release rod (120) is provided with a movable slider, and the electromagnet (121) is provided on the slider.

2. The flapping-wing aircraft launcher according to claim 1, characterized in that: The angle adjustment rod (131) is an aluminum profile.

3. The flapping-wing aircraft launcher according to claim 1, characterized in that: The launch angle of the flapping-wing aircraft (200) can be adjusted in a range of 0° to 180°.

4. The flapping-wing aircraft launcher according to claim 1, characterized in that: The number of the electromagnet (121) and the number of the steel plates (210) are both two.

5. The flapping-wing aircraft launcher according to claim 1, characterized in that: The number of the angle adjustment components (130) is two groups, and the two angle adjustment plates (132) are respectively connected to the two sides of the release rod (120).

6. The flapping-wing aircraft launcher according to claim 1, characterized in that: The base (110) comprises a support rod (112) arranged obliquely, one end of the support rod (112) being connected to the vertical rod (111).

7. A method for taking off a flapping-wing aircraft (200), applied to the flapping-wing aircraft launcher according to any one of claims 1 to 6, the method comprising the following steps: S100, loosening the two angle adjustment plates (132), adjusting the angle of the release rod (120) by moving the angle adjustment rod (131), thereby making the launch angle of the flapping-wing aircraft (200) reach a set value, and locking the angle adjustment rod (131) on the vertical rod (111) through the angle adjustment plates (132); S200, tightening the steel plate (210) by the electromagnet (121) to fix the flapping-wing aircraft (200) on the release rod (120); S300: driving the flapping-wing aircraft (200) and continuously increasing the flapping frequency to cause the steel plate (210) to separate from the electromagnet (121), thereby causing the flapping-wing aircraft (200) to take off autonomously.

8. The method according to claim 7, characterized in that The following steps are also included: When the power of the flapping-wing aircraft (200) reaches a limited value, the steel plate (210) is separated from the electromagnet (121) by powering off.

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