A hand-made unmanned aerial vehicle suitable for standardized mass production

Abstract

The utility model discloses a hand -throwing unmanned plane suitable for standardization batch production relates to unmanned plane technical field. The utility model discloses three -section foldable fuselage, three -section airfoil and three piece tail fin, through three -section modular fuselage and airfoil design, combine folding hinge positioning, lock catch rigid locking and quick -release dowel down -type locking mechanism, realize the quick disassembly of whole machine in 5 minutes, wherein airfoil carbon tube A inserts the automatic pilot electrical connector of conduction, and tail fin carbon tube B inserts synchronous meshing servo arm, and completely exempts manual wiring step, cooperate task cabin standardization interface, and support function module hot plug replacement. The design replaces traditional cementing technology with full bolt connection, reduces production cost, improves the battlefield deployment efficiency, and through double -insurance locking mechanism and carbon pipe enhanced torsional structure, ensures flight stability, satisfies the standardization batch production demand of military individual soldier carrying and emergency investigation.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, and in particular relates to a hand-launched UAV suitable for standardized mass production that achieves rapid assembly and disassembly and modular functions through structural innovation. Background Technology

[0002] With the development of social technology, drones have been applied to many fields such as military, surveying, and inspection. However, due to their specialized nature as special equipment, they cannot be mass-produced like conventional products to reduce research and development and production costs.

[0003] Traditional drones suffer from complex manufacturing processes (relying on molds and wet layup), time-consuming assembly, and high maintenance costs. Especially for scenarios requiring frequent payload changes, existing structures struggle to balance strength with the need for rapid assembly and disassembly.

[0004] Therefore, we propose a hand-launched drone suitable for standardized mass production. Utility Model Content

[0005] The purpose of this invention is to provide a hand-launched drone suitable for standardized mass production, thereby solving existing problems.

[0006] To solve the above-mentioned technical problems, this utility model is achieved through the following technical solution:

[0007] This utility model relates to a hand-launched unmanned aerial vehicle (UAV) suitable for standardized mass production, comprising a three-section foldable fuselage, a three-section wing, and a three-piece tail fin. The three-section foldable fuselage consists of a mission compartment, an equipment compartment, and a tail compartment, which are fixedly connected by folding components and latches. The three-section wing consists of a middle wing, a left outer wing, and a right outer wing. The left and right outer wings are connected to the mating surfaces of the middle wing via carbon tubes A, which are fixed to the mating surfaces, and the mating surfaces contain electrical connectors. The middle wing is fixedly connected to the equipment compartment via a folding and fixing assembly, and all three tail fins are connected to the rear end of the tail compartment via carbon tubes B.

[0008] In one embodiment, the folding component consists of a hinge seat and a fixed seat rotatably connected by a pivot. The hinge seat is fixed to the lower arc surface at the front end of the equipment compartment and the upper arc surface at the front end of the tail compartment by bolts. The fixed seat is fixed to the lower arc surface at the rear end of the mission compartment and the upper arc surface at the rear end of the equipment compartment by bolts.

[0009] In one embodiment, the latch consists of a movable locking ring and a fixed hook that matches the movable locking ring. The movable locking ring is fixed to the upper arc surface at the rear end of the mission compartment and the lower arc surface at the rear end of the equipment compartment by bolts. The fixed hook is fixed to the upper arc surface at the front end of the equipment compartment and the lower arc surface at the front end of the stern compartment by bolts.

[0010] In one embodiment, the folding fixing assembly includes a fixing plate and a locking mechanism. The locking mechanism includes a quick-release insert rod, a round nut fixed below the quick-release insert rod, and a round nut fixing member with a round nut limiting groove and a positioning boss. The round nut fixing member has a round nut through groove in the middle.

[0011] In one embodiment, both the fixing plate and the middle of the rear end of the middle wing have through holes for quick-release inserts to move. The front end of the fixing plate is hinged to the upper arc surface of the front end of the equipment compartment. The upper surface of the fixing plate is fixedly connected to the middle wing by screws. A round nut is installed on the screw in the middle of the rear end of the equipment compartment.

[0012] In one embodiment, when the three tail fins are inserted into the tail section, the control surface automatically connects to the servo rocker arm.

[0013] This utility model has the following beneficial effects:

[0014] This invention utilizes a three-section modular fuselage (mission compartment / equipment compartment / tail compartment) and wing (middle wing / left outer wing / right outer wing) design, combined with hinged positioning of folding parts, rigid locking of latches, and a quick-release plug-in locking mechanism, enabling rapid assembly and disassembly of the entire aircraft within 5 minutes. Specifically, the wing's carbon tube A connects to an automatically conductive electrical connector, and the tail's carbon tube B connects to a synchronously engaging servo rocker arm, completely eliminating manual wiring steps. Combined with the standardized interface of the mission compartment, it supports hot-swappable replacement of functional modules. This design replaces traditional gluing with all-bolted connections, reducing production costs and improving battlefield deployment efficiency. Simultaneously, the double-safety locking mechanism (rotating shaft + latch) and the carbon tube-reinforced anti-torsional structure ensure flight stability, meeting the standardized mass production requirements for military individual soldier carrying and emergency reconnaissance.

[0015] Of course, any product implementing this utility model does not necessarily need to achieve all of the advantages described above at the same time. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this utility model, 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 this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 A schematic diagram of the overall structure of a hand-launched drone suitable for standardized mass production;

[0018] Figure 2 An exploded view of a hand-launched drone suitable for standardized mass production;

[0019] Figure 3This is a schematic diagram of the folding of the three-section foldable body in this utility model;

[0020] Figure 4 This is a schematic diagram of the unfolded three-section foldable body of this utility model;

[0021] Figure 5 This is an enlarged view of the connection between the leading edge of the wing and the fuselage in this utility model;

[0022] Figure 6 This is an enlarged view of the locking mechanism at the connection between the rear end of the wing and the fuselage in this utility model;

[0023] Figure 7 This is a schematic diagram of the connection structure between the connecting plate and the equipment compartment in this utility model;

[0024] Figure 8 This is a schematic diagram of the structure of the round nut fastener in this utility model;

[0025] Figure 9 This is a schematic diagram of the fuselage and wings after folding in this utility model;

[0026] Figure 10 This is a schematic diagram of the overall structure of this utility model after folding and packing.

[0027] The attached diagram lists the components represented by each number as follows:

[0028] 1. Three-section foldable fuselage; 101. Mission bay; 102. Equipment bay; 103. Tail bay; 2. Three-section wing; 201. Center wing; 202. Left outer wing; 203. Right outer wing; 204. Carbon fiber tube A; 205. Electrical connector; 3. Tail fin; 301. Carbon fiber tube B; 302. Vertical stabilizer; 303. Left horizontal stabilizer; 304. Right horizontal stabilizer; 4. Folding components; 401. Hinge base; 402. Fixing base; 5. Lock; 501. Movable locking ring; 502. Fixing hook; 6. Folding fixing assembly; 601. Fixing plate; 602. Locking mechanism; 603. Quick-release insert; 604. Round nut; 605. Round nut fixing component; 606. Round nut limiting groove; 607. Positioning boss; 608. Round nut passage groove. Detailed Implementation

[0029] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0030] In the description of this utility model, it should be understood that the terms "upper", "middle", "outer", "inner", etc., which indicate orientation or positional relationship, are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the components or elements referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0031] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "connected," etc., should be interpreted broadly. For example, "connection" 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 an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0032] Example 1

[0033] Please see Figures 1-10 As shown, this utility model is a hand-launched unmanned aerial vehicle suitable for standardized mass production, comprising a three-section foldable fuselage 1, a three-section wing 2, and a three-piece tail wing 3. The three-section foldable fuselage 1 consists of a mission compartment 101, an equipment compartment 102, and a tail compartment 103, which are fixedly connected by folding parts 4 and locking buckles 5. The three-section wing 2 consists of a middle wing 201, a left outer wing 202, and a right outer wing 203. 3. Carbon tubes A204, which are fixed to the docking surface, are inserted into the docking surfaces on both sides of the middle wing 201, and the docking end face includes electrical connectors 205; the middle wing 201 and the equipment compartment 102 are fixedly connected by the folding fixing component 6, and the three tail wings 3 are all inserted into the rear end of the tail compartment 103 by carbon tubes B301; among them, the outer wing is fixed by friction fixing. When the outer wing is subjected to upward pull during the flight of the UAV, the torque of the carbon tube A204 increases, and the friction also increases, so the outer wing cannot be detached.

[0034] like Figure 3 As shown, the folding component 4 consists of a hinge seat 401 and a fixed seat 402 rotatably connected by a pivot. The hinge seat 401 is fixed to the lower arc surface at the front end of the equipment compartment 102 and the upper arc surface at the front end of the tail compartment 103 by bolts. The fixed seat 402 is fixed to the lower arc surface at the rear end of the mission compartment 101 and the upper arc surface at the rear end of the equipment compartment 102 by bolts. The bolted connection facilitates future maintenance.

[0035] like Figure 4 and Figure 5As shown, the latch 5 consists of a movable locking ring 501 and a fixed hook 502 that matches the movable locking ring 501. The movable locking ring 501 is fixed to the upper arc surface at the rear end of the mission compartment 101 and the lower arc surface at the rear end of the equipment compartment 102 by bolts. The fixed hook 502 is fixed to the upper arc surface at the front end of the equipment compartment 102 and the lower arc surface at the front end of the tail compartment 103 by bolts.

[0036] like Figure 6 and Figure 7 As shown, the folding fixing assembly 6 includes a fixing plate 601 and a locking mechanism 602. The locking mechanism 602 includes a quick-release insert 603, a round nut 604 fixed below the quick-release insert 603, and a round nut fixing member 605 with a round nut limiting groove 606 and a positioning boss 607. The round nut fixing member 605 has a round nut through groove 608 in the middle. The fixing plate 601 has a positioning groove on one surface that matches the positioning boss 607 to help the fixing plate 601 to be quickly positioned.

[0037] Both the fixed plate 601 and the middle wing 201 have through holes in the middle of their rear ends for the quick-release insert rod 603 to move. The front end of the fixed plate 601 is hinged to the upper arc surface of the front end of the equipment compartment 102. The upper surface of the fixed plate 601 is fixedly connected to the middle wing 201 by screws. The middle of the rear end of the equipment compartment 102 is fitted with a round nut fastener 605.

[0038] The wings are fixed to the fuselage using two methods, one at the front and one at the rear, such as... Figure 5 As shown, the U-shaped slot at the leading edge of the wing aligns with the mounting screw on the fuselage. The wing rotates along the axis of the mounting screw, simultaneously inserting the quick-release lever 603 at the rear of the wing into the fuselage. Figure 6 As shown; after the wing and fuselage are in place, rotate the handle of the wing rear quick-release lever 603 horizontally 90° and then press it down to lock it.

[0039] Furthermore, when the three tail fins 3 are inserted into the tail section 103, the control surface automatically connects to the servo rocker arm.

[0040] Example 2

[0041] Please see Figures 1-10 As shown, this embodiment illustrates an assembly method for a hand-launched drone suitable for standardized mass production:

[0042] Three-section wing assembly:

[0043] First, insert the carbon tube A204 of the outer wing into the corresponding hole of the middle wing 201. After it is inserted tightly, the electrical interface will automatically connect and complete the electrical connection.

[0044] Secondly, the fixing plate 601 is positioned by inserting it into the pin at the front end of the equipment compartment 102 through its front U-shaped slot;

[0045] Then, the assembled wing is fixed to the fixing plate 601 with screws. Next, the round nut 604 fixed at the lower end of the quick-release rod 603 passes through the round nut through slot 608 of the round nut fixing piece 605. Then, the quick-release rod 603 is rotated laterally to 90° and the handle hinged at the upper end of the quick-release rod 603 is pressed down, so that the fixing plate 601 and the wing are quickly locked to the equipment compartment 102 through the locking mechanism 602.

[0046] Three-section foldable body assembly:

[0047] First, unfold the mission compartment 101, equipment compartment 102 and tail compartment 103, and then lock the fuselage by fastening the movable locking ring 501 with the corresponding fixed hook 502 to complete the fuselage assembly;

[0048] Mission compartment 101 is a standard component, which supports quick replacement of different functional compartments;

[0049] Tail wing 3 assembly:

[0050] The carbon fiber tube B301 of the three tail fins 3 is inserted into the corresponding hole of the tail section 103. At this time, the control surface automatically engages with the servo rocker arm, and the internal locking device is activated.

[0051] It should be further noted that this method relies entirely on modular design, and the time for a single complete assembly can be controlled within 5 minutes, making it suitable for rapid deployment scenarios such as battlefields and the field. All connectors (folding component 4 / locking buckle 5 / folding fixing component 6) are universal interfaces, supporting pre-installation on assembly lines. The cylindrical fuselage is made of standard circular composite material tubes machined by CNC machining center, and its machining accuracy is far higher than that of traditional UAV mold wet layup processing technology.

[0052] In the description of this specification, references to terms such as "an embodiment," "example," and "specific example" indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0053] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this utility model, thereby enabling those skilled in the art to better understand and utilize it. This utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A hand-launched unmanned aerial vehicle suitable for standardized mass production, comprising a three-section foldable fuselage (1), a three-section wing (2), and a three-piece tail fin (3), characterized in that: The three-section foldable fuselage (1) consists of a mission compartment (101), an equipment compartment (102), and a tail compartment (103). The mission compartment (101), equipment compartment (102), and tail compartment (103) are fixedly connected to each other by folding parts (4) and latches (5). The three-section wing (2) consists of a middle wing (201), a left outer wing (202), and a right outer wing (203). The left outer wing (202) and the right outer wing (203) are connected to the mating surfaces on both sides of the middle wing (201) by carbon tubes A (204) fixed to the mating surfaces, and the mating surfaces contain electrical connectors (205). The middle wing (201) is fixedly connected to the equipment compartment (102) by folding fixing components (6). The three tail wings (3) are all connected to the rear end of the tail compartment (103) by carbon tubes B (301).

2. The hand-launched drone suitable for standardized mass production according to claim 1, characterized in that, The folding component (4) consists of a hinge seat (401) and a fixed seat (402) rotatably connected by a pivot. The hinge seat (401) is fixed to the lower arc surface at the front end of the equipment compartment (102) and the upper arc surface at the front end of the tail compartment (103) by bolts. The fixed seat (402) is fixed to the lower arc surface at the rear end of the mission compartment (101) and the upper arc surface at the rear end of the equipment compartment (102) by bolts.

3. A hand-launched drone suitable for standardized mass production according to claim 1, characterized in that, The latch (5) consists of a movable locking ring (501) and a fixed hook (502) that matches the movable locking ring (501). The movable locking ring (501) is fixed to the upper arc surface of the rear end of the mission compartment (101) and the lower arc surface of the rear end of the equipment compartment (102) by bolts. The fixed hook (502) is fixed to the upper arc surface of the front end of the equipment compartment (102) and the lower arc surface of the front end of the tail compartment (103) by bolts.

4. A hand-launched drone suitable for standardized mass production according to claim 1, characterized in that, The folding fixing assembly (6) includes a fixing plate (601) and a locking mechanism (602). The locking mechanism (602) includes a quick-release insert (603), a round nut (604) fixed below the quick-release insert (603), and a round nut fixing member (605) with a round nut limiting groove (606) and a positioning boss (607). The round nut fixing member (605) has a round nut through groove (608) in the middle.

5. A hand-launched drone suitable for standardized mass production according to claim 4, characterized in that, Both the fixed plate (601) and the middle wing (201) have through holes at the middle of their rear ends for the quick-release insert (603) to move. The front end of the fixed plate (601) is hinged to the upper arc surface of the front end of the equipment compartment (102). The upper surface of the fixed plate (601) is fixedly connected to the middle wing (201) by screws. A round nut fastener (605) is installed on the screw at the middle of the rear end of the equipment compartment (102).

6. A hand-launched drone suitable for standardized mass production according to claim 1, characterized in that, When the three tail fins (3) are inserted into the tail section (103), the control surface automatically connects to the servo arm.

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