A new type of hand-thrown UAV tail support rod folding mechanism

Abstract

The present invention relates to a novel hand-thrown UAV tail support rod folding mechanism, comprising a first connecting seat, a second connecting seat, a bare rod screw, a torsion spring, a gasket, and a nut, wherein the first connecting seat comprises a first connecting seat shell, a first sub-rotating ear piece, a second sub-rotating ear piece, and a first replaceable adsorption module; the second connecting seat comprises a second connecting seat shell, a third sub-rotating ear piece, a fourth sub-rotating ear piece, and a second replaceable adsorption module; the torsion spring comprises a torsion spring body; the bare rod screw sequentially passes through the third sub-rotating ear piece, the first sub-rotating ear piece, the torsion spring body, the second sub-rotating ear piece, the fourth sub-rotating ear piece, and the gasket, and the nut is fixed on the bare rod screw by rotation. The hand-thrown UAV tail support rod folding mechanism proposed by the present invention can fold the tail support rod to release force after the UAV lands, thereby avoiding the problem of damage to the fuselage structure caused by stress concentration, and the mechanism is simple in composition. After being installed on the fuselage, the tail support rod and the fuselage can be separated by disassembling the rotating shaft.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicle design, and in particular relates to a novel hand-thrown unmanned aerial vehicle tail support rod folding mechanism. Background Art

[0002] Hand-thrown UAVs are characterized by light weight, small size, easy operation, no site restrictions for takeoff and landing, strong environmental adaptability, strong scalability, and low price. In the civilian sector, they can be used for dangerous situation monitoring and environmental monitoring, mainly for forestry departments, aerial survey units, and for large-scale operations such as disaster detection, fire risk monitoring, national geographic data aerial surveys, and environmental protection departments; in the military sector, they can be used for continuous intelligence reconnaissance and surveillance, mainly for squad-level combat units for single-soldier combat, and for battlefield reconnaissance, border patrols, counter-terrorism and other combat missions.

[0003] Most of the existing hand-thrown UAVs are theoretically designed for deep stall landings, and after landing, the wings and tail struts share the force equally to ensure the integrity of the fuselage structure. However, in most cases in actual engineering, the wings and tail struts cannot be equally divided according to the theoretical design ideas. In particular, the tail struts are mostly connected to the fuselage through electric plugs and carbon tubes for the convenience of disassembly and power supply. At the same time, because the tail struts are designed to be long and at an angle to the fuselage, after deep stall landings under various complex environmental conditions, the turbulence causes the tail struts to be subjected to too much force, especially the stress concentration at the connection with the fuselage causes fracture. Summary of the invention

[0004] In order to solve the deficiencies in the prior art, the present invention provides a novel hand-thrown UAV tail support rod folding mechanism, the novel hand-thrown UAV tail support rod folding mechanism comprising:

[0005] It includes a first connecting seat, a second connecting seat, a bare rod screw, a torsion spring, a gasket, and a nut, wherein:

[0006] The first connection seat comprises a first connection seat shell, a first rotating ear piece and a first replaceable adsorption module, the first rotating ear piece is fixed outside the first connection seat shell, the first replaceable adsorption module is fixed inside the first connection seat shell, and the first rotating ear piece comprises a first sub-rotating ear piece and a second sub-rotating ear piece;

[0007] The second connection seat includes a second connection seat shell, a second rotating ear piece and a second replaceable adsorption module, the second rotating ear piece is fixed outside the second connection seat shell, the second replaceable adsorption module is fixed inside the second connection seat shell, and the second rotating ear piece includes a third sub-rotating ear piece and a fourth sub-rotating ear piece;

[0008] The torsion spring comprises a torsion spring body, a first torsion spring fixed end, and a second torsion spring fixed end, wherein the first torsion spring fixed end is fixed to the outside of the first connecting seat housing, and the second torsion spring fixed end is fixed to the outside of the second connecting seat housing;

[0009] The bare rod screw passes through the third sub-rotation ear, the first sub-rotation ear, the torsion spring body, the second sub-rotation ear, the fourth sub-rotation ear, and the gasket in sequence, and the nut is fixed on the bare rod screw by rotation.

[0010] In one embodiment of the present invention, the first connecting seat and the second connecting seat are respectively fixedly sleeved on the outer side of the connecting pipe by gluing or screw locking.

[0011] In one embodiment of the present invention, the first replaceable adsorption module includes a first adsorption mounting seat and a first permanent magnet. The first adsorption mounting seat is fixed in the first connecting seat shell by gluing or screw locking, and the first permanent magnet is fixed in the first adsorption mounting seat by gluing.

[0012] In one embodiment of the present invention, the second replaceable adsorption module includes a second adsorption mounting seat and a second permanent magnet. The second adsorption mounting seat is fixed in the second connecting seat shell by gluing or screw locking, and the second permanent magnet is fixed in the second adsorption mounting seat by gluing.

[0013] In one embodiment of the present invention, the first permanent magnet and the second permanent magnet have opposite magnetic properties, and the first replaceable adsorption module and the second replaceable adsorption module are adsorbed together without a gap through the first permanent magnet and the second permanent magnet.

[0014] In one embodiment of the present invention, the nut is a self-locking nut.

[0015] In one embodiment of the present invention, the nut is a common nut, and a fuse is installed at one end of the bare rod screw close to the nut.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] The novel hand-thrown UAV tail strut folding mechanism provided by the present invention can fold the tail strut to release force after the UAV lands, thereby avoiding the problem of damage to the fuselage structure caused by stress concentration. The mechanism is simple in composition and basically does not change the original design scheme. After being installed on the fuselage, the tail strut and the fuselage can be separated by disassembling the rotating shaft. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 A schematic diagram of the structure of a new hand-thrown UAV tail support rod folding mechanism provided by an embodiment of the present invention;

[0019] Figure 2 A schematic diagram of the exploded structure of a new hand-thrown UAV tail strut folding mechanism provided by an embodiment of the present invention;

[0020] Figure 3 A schematic structural diagram of a first connecting seat in a folding mechanism of a tail support rod of a new hand-thrown UAV provided by an embodiment of the present invention;

[0021] Figure 4 A schematic structural diagram of a second connecting seat in a folding mechanism of a tail support rod of a new hand-thrown UAV provided by an embodiment of the present invention;

[0022] Figure 5 A schematic structural diagram of a novel hand-thrown UAV tail support rod folding mechanism provided by an embodiment of the present invention, in which a first connecting seat and a second connecting seat are respectively connected to a connecting pipe;

[0023] Figure 6 A schematic structural diagram of a novel hand-thrown UAV tail support rod folding mechanism provided by an embodiment of the present invention, in which a first connecting seat is connected to a first replaceable adsorption module, and a second connecting seat is connected to a second replaceable adsorption module;

[0024] Figure 7 A structural schematic diagram of a novel hand-thrown UAV tail strut folding mechanism installation provided in an embodiment of the present invention.

[0025] Description of reference numerals:

[0026] 1-first connecting seat; 2-second connecting seat; 3-bare rod screw; 4-torsion spring; 5-gasket; 6-nut; 7-fuse; 8-first fixing hole; 9-second fixing hole; 101-first sub-rotating ear; 102-second sub-rotating ear; 103-first adsorption mounting seat; 104-first permanent magnet; 201-third sub-rotating ear; 202-fourth sub-rotating ear; 203-second adsorption mounting seat; 401-torsion spring body; 402-first torsion spring fixed end; 403-second torsion spring fixed end. DETAILED DESCRIPTION

[0027] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and understandable, the specific embodiments of the present invention are described in detail below with reference to the accompanying drawings, but the embodiments of the present invention are not limited thereto.

[0028] Embodiment 1

[0029] This embodiment relates to a new type of hand-thrown UAV tail support rod folding mechanism. Figure 1 , Figure 2 , Figure 1 A schematic diagram of a novel hand-thrown UAV tail support rod folding mechanism provided by an embodiment of the present invention. Figure 2 The exploded structural diagram of a novel hand-thrown UAV tail support rod folding mechanism provided by an embodiment of the present invention. Specifically, the novel hand-thrown UAV tail support rod folding mechanism provided by this embodiment includes:

[0030] First connecting seat 1, second connecting seat 2, bare rod screw 3, torsion spring 4, gasket 5, nut 6, specifically:

[0031] In order to prevent the connection pipe from being split due to force after installation inside the connection pipe, the first connection seat 1 and the second connection seat 2 are mounted on the outside of the connection pipe to protect the connection pipe, and the first connection seat 1, the second connection seat 2 and the connection pipe are installed by gluing or symmetrically locking with two screws, which is simple and reliable. Figure 3 , Figure 3 This is a schematic diagram of the structure of the first connecting seat in a novel hand-thrown UAV tail support rod folding mechanism provided by an embodiment of the present invention. In this embodiment, the first connecting seat 1 includes a first connecting seat shell, a first rotating ear piece and a first replaceable adsorption module. The first rotating ear piece is fixed to the outside of the first connecting seat shell, and the first replaceable adsorption module is fixed to the inside of the first connecting seat shell 101. The first rotating ear piece includes a first sub-rotating ear piece 101 and a second sub-rotating ear piece 102; please refer to Figure 4 , Figure 4 A schematic structural diagram of a second connecting seat in a novel hand-thrown UAV tail strut folding mechanism provided in an embodiment of the present invention, wherein the second connecting seat 2 in this embodiment includes a second connecting seat shell, a second rotating ear and a second replaceable adsorption module, the second rotating ear is fixed outside the second connecting seat shell, the second replaceable adsorption module is fixed inside the second connecting seat shell, and the second rotating ear includes a third sub-rotating ear 201 and a fourth sub-rotating ear 202.

[0032] Please see again Figure 1 In this embodiment, the bare rod screw 3 passes through the third sub-rotation ear piece 201, the first sub-rotation ear piece 101, the second sub-rotation ear piece 102, the fourth sub-rotation ear piece 202, and the gasket 5 in sequence, and the nut 6 is fixed on the bare rod screw 3 by rotation, and then the rear bare rod screw 3 is connected as a rotation axis, wherein the nut 6 can be an ordinary nut or a self-locking nut. When it is an ordinary nut, a fuse 7 is installed at one end of the bare rod screw 3 close to the nut 6. When it is a self-locking nut, the fuse 7 does not need to be installed.

[0033] To prevent increased stress at the connection between the tail strut and the fuselage, please refer to Figure 1In this embodiment, a torsion spring 4 is added to the mechanism. The torsion spring 4 includes a torsion spring body 401, a first torsion spring fixed end 402, and a second torsion spring fixed end 403. The first torsion spring fixed end 402 is fixed to the outside of the first connection seat shell, and the second torsion spring fixed end 403 is fixed to the outside of the second connection seat shell. At this time, the light rod screw 3 passes through the third sub-rotation ear 201, the first sub-rotation ear 101, the torsion spring body 401, the second sub-rotation ear 102, the fourth sub-rotation ear 202, and the gasket 5 in sequence. The nut 6 is fixed to the light rod screw 3 by rotation, and then connected to the rear light rod screw 3 as a rotation axis. The introduced torsion spring 4 can effectively prevent the problem of the tail support rod rotating too much and damaging the body structure, and at the same time can absorb and release the ground rebound force, further preventing the problem of the tail support rod being excessively stressed and broken due to the turbulence of deep stall landing. The torsion spring 4 installed on the mechanism can be adapted by theoretical calculation and test adaptation based on the adsorption force of the first replaceable adsorption module and the adsorption force of the second replaceable adsorption module.

[0034] For further information, see Figure 3 In this embodiment, the first replaceable adsorption module includes a first adsorption mounting seat 103 and a first permanent magnet 104. The first adsorption mounting seat 103 is fixed in the first connection seat housing by gluing or screw locking, and the first permanent magnet 104 is fixed in the first adsorption mounting seat 103 by gluing. The adsorption force of the first replaceable adsorption module can be theoretically calculated and experimentally adapted according to the specific parameters of the drone landing, and then adapted to the first permanent magnet 104.

[0035] Please see again Figure 4 In this embodiment, the second replaceable adsorption module includes a second adsorption mounting seat 203 and a second permanent magnet (not marked, see the structure of the first permanent magnet 104 in the first adsorption mounting seat 103 for details), the second adsorption mounting seat 203 is fixed in the second connection seat shell by gluing or screw locking, and the second permanent magnet is fixed in the second adsorption mounting seat 203 by gluing. The adsorption force of the second replaceable adsorption module can be theoretically calculated and experimentally adapted according to the specific parameters of the drone landing, and then adapted to the second permanent magnet.

[0036] In this embodiment, the first permanent magnet 104 and the second permanent magnet have opposite magnetic properties, that is, the first permanent magnet 104 is S polarity and the second permanent magnet is N polarity, or the first permanent magnet 104 is N polarity and the second permanent magnet is S polarity. The first replaceable adsorption module is specifically installed on the end face of the first connecting seat 1, and the second replaceable adsorption module is specifically installed on the end face of the second connecting seat 2. The first replaceable adsorption module and the second replaceable adsorption module are in a horizontally aligned state. After installation, they can be adsorbed together by the first permanent magnet 104 and the second permanent magnet, with no gap in between. In this embodiment, the tail support rod can be folded to release stress after the drone lands through permanent magnet adsorption, which has the function of buffering and protecting the body structure, and is simple and durable.

[0037] See also Figure 5 , Figure 6 , Figure 5 A schematic diagram of a structure in which a first connecting seat and a second connecting seat are respectively connected to a connecting pipe in a new hand-thrown UAV tail support rod folding mechanism provided by an embodiment of the present invention, Figure 6 A schematic structural diagram of a novel hand-thrown UAV tail support rod folding mechanism provided by an embodiment of the present invention, in which the first connecting seat is connected to the first replaceable adsorption module, and the second connecting seat is connected to the second replaceable adsorption module. When the first connecting seat 1 and the connecting tube, and the second connecting seat 2 and the connecting tube are respectively fixed by screw locking, the first connecting seat 1 and the connecting tube, and the second connecting seat 2 and the connecting tube are screwed through the first fixing hole 8 shown in 5 in this embodiment. When the first connecting seat 1 and the first replaceable adsorption module, and the second connecting seat 2 and the second replaceable adsorption module are respectively fixed by screw locking, the first connecting seat 1 and the first replaceable adsorption module, and the second connecting seat 2 and the second replaceable adsorption module are screwed through the first fixing hole 8 shown in 5. Figure 6 The second fixing hole 9 shown is connected.

[0038] The working principle of the new hand-thrown UAV tail support rod folding mechanism provided in this embodiment is as follows:

[0039] See also Figure 7 , Figure 7 The present invention is a schematic structural diagram of a novel hand-thrown UAV tail strut folding mechanism installation. During production and assembly of the hand-thrown UAV, the first connecting seat 1 (second connecting seat 2) is directly installed outside the tail connecting tube of the fuselage, with the first sub-rotating ear 101 and the second sub-rotating ear 102 facing upwards, and then the second connecting seat 2 (first connecting seat 1) is installed outside the front connecting tube of the tail strut, with the third sub-rotating ear 201 and the fourth sub-rotating ear 202 facing upwards.

[0040] When the UAV needs to work, the first connecting seat 1 and the second connecting seat 2 are connected through the first sub-rotating ear 101, the second sub-rotating ear 102, the third sub-rotating ear 201 and the fourth sub-rotating ear 202 with a bare screw 3, a torsion spring 4, a gasket 5, a common nut (self-locking nut), and a fuse 7 (not required when installing the self-locking nut). The bare screw 3 serves as a rotating axis, and the first replaceable adsorption module in the first connecting seat 1 and the second replaceable adsorption module in the second connecting seat 2 are adsorbed together by the opposite magnetic properties of the first permanent magnet 104 and the second permanent magnet, that is, the principle of attraction between the S pole and the N pole. Since the rotating axis is at the uppermost end of the installation axis, the front and rear parts connected by the folding mechanism can only rotate upward, and cannot rotate downward due to the structural limit of the folding mechanism of the present application.

[0041] After the installation of the UAV is completed, it is debugged and flown. After the mission is completed, it is recovered through a deep stall landing. The landing energy absorption device touches the ground to absorb part of the elastic force. Due to the turbulence, the tail of the tail strut touches the ground. After touching the ground, the remaining elastic force that is not absorbed disconnects the adsorbed first connecting seat 1 (second connecting seat 2) and the second connecting seat 2 (first connecting seat 1). Since the fuselage part accounts for most of the weight of the entire UAV, it can be regarded as fixed. The weight of the tail strut part is very light. Due to the action of inertia force, the first connecting seat 1 (second connecting seat 2) and the second connecting seat 2 (first connecting seat 1) are adsorbed and disconnected. When the first connecting seat 1 (second connecting seat 2) and the second connecting seat 2 (first connecting seat 1) are adsorbed and disconnected, they rotate upward around the rotation axis. During the rotation process, the torsion spring 4 applies a downward buffering force to prevent the rotation angle from being too large to damage the body structure. At this point, all the elastic force touching the ground is released to ensure the safety of the body mechanism.

[0042] In summary, this embodiment provides a new type of hand-thrown UAV tail strut folding mechanism. After the UAV lands, the tail strut can be folded to release force, avoiding the problem of stress concentration causing damage to the fuselage structure. The mechanism is simple in composition and basically does not change the original design scheme. After being installed on the fuselage, the tail strut and the fuselage can be separated by removing the rotating shaft 3.

[0043] It should be noted that the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more features. In the description of this application, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0044] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine different embodiments or examples described in this specification.

[0045] Although the present invention is described herein in conjunction with various embodiments, in the process of implementing the claimed invention, those skilled in the art may understand and implement other variations of the disclosed embodiments by viewing the drawings, the disclosure, and the appended claims. In the claims, the word "comprising" does not exclude other components or steps, and "one" or "an" does not exclude multiple situations. A single processor or other unit may implement several functions listed in the claims. Certain measures are recorded in different dependent claims, but this does not mean that these measures cannot be combined to produce good results.

[0046] The above contents are further detailed descriptions of the present invention in combination with specific preferred embodiments, and it cannot be determined that the specific implementation of the present invention is limited to these descriptions. For ordinary technicians in the technical field to which the present invention belongs, several simple deductions or substitutions can be made without departing from the concept of the present invention, which should be regarded as falling within the protection scope of the present invention.

Claims

1. A new type of hand-thrown UAV tail support rod folding mechanism, characterized in that: It includes a first connecting seat, a second connecting seat, a bare rod screw, a torsion spring, a gasket, and a nut, wherein the first connecting seat and the second connecting seat are respectively fixedly sleeved on the outside of the connecting pipe by gluing or screw locking; The first connection seat comprises a first connection seat shell, a first rotating ear piece and a first replaceable adsorption module, the first rotating ear piece is fixed to the outside of the first connection seat shell, the first replaceable adsorption module is fixed to the inside of the first connection seat shell, the first replaceable adsorption module comprises a first adsorption mounting seat and a first permanent magnet, the first adsorption mounting seat is fixed to the inside of the first connection seat shell by gluing or screw locking, and the first permanent magnet is fixed to the inside of the first adsorption mounting seat by gluing; the first rotating ear piece comprises a first sub-rotating ear piece and a second sub-rotating ear piece; The second connecting seat comprises a second connecting seat shell, a second rotating ear piece and a second replaceable adsorption module, the second rotating ear piece is fixed outside the second connecting seat shell, the second replaceable adsorption module is fixed inside the second connecting seat shell, the second replaceable adsorption module comprises a second adsorption mounting seat and a second permanent magnet, the second adsorption mounting seat is fixed inside the second connecting seat shell by gluing or screw locking, and the second permanent magnet is fixed inside the second adsorption mounting seat by gluing; the second rotating ear piece comprises a third sub-rotating ear piece and a fourth sub-rotating ear piece; The torsion spring comprises a torsion spring body, a first torsion spring fixed end, and a second torsion spring fixed end, wherein the first torsion spring fixed end is fixed to the outside of the first connecting seat housing, and the second torsion spring fixed end is fixed to the outside of the second connecting seat housing; The bare rod screw passes through the third sub-rotation ear, the first sub-rotation ear, the torsion spring body, the second sub-rotation ear, the fourth sub-rotation ear, and the gasket in sequence, and the nut is fixed on the bare rod screw by rotation.

2. The novel hand-thrown UAV tail support rod folding mechanism according to claim 1 is characterized in that: The first permanent magnet and the second permanent magnet have opposite magnetic properties, and the first replaceable adsorption module and the second replaceable adsorption module are adsorbed together without a gap through the first permanent magnet and the second permanent magnet.

3. The novel hand-thrown UAV tail support rod folding mechanism according to claim 1 is characterized in that: The nut is a self-locking nut.

4. The novel hand-thrown UAV tail support rod folding mechanism according to claim 1 is characterized in that: The nut is a common nut, and a fuse is installed at one end of the bare rod screw close to the nut.

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