CN119284230A - A stackable folding wing of a patrol drone with a trailing edge rudder - Google Patents
A stackable folding wing of a patrol drone with a trailing edge rudder Download PDFInfo
- Publication number
- CN119284230A CN119284230A CN202411607562.2A CN202411607562A CN119284230A CN 119284230 A CN119284230 A CN 119284230A CN 202411607562 A CN202411607562 A CN 202411607562A CN 119284230 A CN119284230 A CN 119284230A
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- wing
- trailing edge
- control surface
- wings
- edge control
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- 238000009434 installation Methods 0.000 claims description 25
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 15
- 229910052799 carbon Inorganic materials 0.000 claims description 15
- 239000006260 foam Substances 0.000 claims description 11
- 229910052751 metal Inorganic materials 0.000 claims description 8
- 239000002184 metal Substances 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 7
- 230000007246 mechanism Effects 0.000 claims description 6
- 239000000835 fiber Substances 0.000 claims description 5
- 229920000271 Kevlar® Polymers 0.000 claims description 4
- 238000001125 extrusion Methods 0.000 claims description 4
- 239000004761 kevlar Substances 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 239000000314 lubricant Substances 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 3
- 238000003780 insertion Methods 0.000 claims description 2
- 230000037431 insertion Effects 0.000 claims description 2
- 238000012546 transfer Methods 0.000 claims description 2
- 241001264313 Semioptera wallacii Species 0.000 claims 1
- 230000006835 compression Effects 0.000 description 8
- 238000007906 compression Methods 0.000 description 8
- 238000013461 design Methods 0.000 description 5
- 238000013016 damping Methods 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 239000003795 chemical substances by application Substances 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003028 elevating effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/54—Varying in area
- B64C3/546—Varying in area by foldable elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
本发明提供一种带后缘舵面的巡飞无人机叠放式折叠机翼，属于新型无人机领域，机身连接结构、内侧半翼、外侧半翼、压紧螺帽、扭转弹簧和锁紧器，内侧半翼和外侧半翼依次套合连接在机身连接结构上，两个半翼共轴叠放并通过压紧螺帽与机身连接结构连接，靠近机身的半翼为内侧半翼，另一个为外侧半翼，两个半翼通过扭转弹簧提供旋转力，通过锁紧器实现位置锁定；本发明填补了特殊布局巡飞无人机，尤其是带后缘舵面的叠放式折叠机翼的空白。
The invention provides a patrol unmanned aerial vehicle with stacked folding wings with trailing edge control surfaces, belonging to the field of new unmanned aerial vehicles, comprising a fuselage connection structure, an inner half wing, an outer half wing, a clamping nut, a torsion spring and a locker. The inner half wing and the outer half wing are sequentially sleeved and connected to the fuselage connection structure, the two half wings are coaxially stacked and connected to the fuselage connection structure through the clamping nut, the half wing close to the fuselage is the inner half wing, and the other is the outer half wing, the two half wings are provided with rotational force by a torsion spring, and position locking is achieved by a locker; the invention fills the gap of patrol unmanned aerial vehicles with special layouts, especially stacked folding wings with trailing edge control surfaces.
Description
Technical Field
The invention belongs to the field of novel unmanned aerial vehicles, and relates to a stacked folding wing of a fly-by-the-flight unmanned aerial vehicle with a trailing edge control surface.
Background
The unmanned aerial vehicle is a novel unmanned aerial vehicle, and is mainly characterized by cruising flight mode, quick response/quick emission, low cost, high efficiency and flexible use. Unmanned aerial vehicle generally adopts a mode of storage and emission of an emission barrel to realize rapid emission, and therefore, a foldable unfolding wing design is generally adopted. The wing folding and unfolding mechanism and the structure are one of key technologies of the unmanned aerial vehicle, and have great influence on the performance of a unmanned aerial vehicle platform. The folding and unfolding mechanism and the structural design of the wing have great difficulty, and the difficulty is great for special layout (such as that a front wing and a rear wing are both arranged on the upper side or the lower side of a machine body) and the wing with a rear edge control surface. The manufacturers of the unmanned aerial vehicle for flying inspection in all countries in the world develop respective airfoil folding and unfolding mechanisms and structural design schemes when developing unmanned aerial vehicle products for flying inspection, and some manufacturers and individuals declare airfoil folding and unfolding mechanisms and structural design patents. However, the research on a special layout of a patrol unmanned aerial vehicle platform, particularly a stacked folding wing with a trailing edge control surface, is insufficient.
Disclosure of Invention
The invention provides a stacked folding wing of an unmanned aerial vehicle for patrol with a trailing edge control surface, which is provided with the trailing edge control surface, such as an elevator, an aileron, an elevating aileron and the like.
A stacked folding wing of an unmanned aerial vehicle for patrol with a trailing edge control surface comprises a body connecting structure, an inner half wing, an outer half wing, a compression nut, a torsion spring and a locker, wherein the inner half wing and the outer half wing are sequentially sleeved and connected to the body connecting structure, the two half wings are coaxially stacked and connected with the body connecting structure through the compression nut, the half wing close to the body is the inner half wing, the other half wing is the outer half wing, the torsion spring is arranged between the two half wings to provide a rotating force, and the locking of an unfolding position is realized through the locker. Specific:
The machine body connecting structure is a hollow cylinder and is used for fixedly connecting the whole stacked folding wing with the main machine body, a platform is symmetrically arranged at the bottom or the top of the machine body connecting structure according to the central symmetry plane of the machine body to serve as a horizontal bottom plate, a cylindrical protruding mounting tube shaft is arranged at the center of the horizontal bottom plate, threads are arranged on the inner wall of the mounting tube shaft and are used for being matched with compression nuts, the mounting tube shaft is used for being connected with a bearing structural member and a folding unfolding center rotating shaft in a mounting mode, openings are formed in the side wall of the mounting tube shaft and the horizontal bottom plate at the bottom of the mounting tube shaft and are used as line passing openings, small-height concentric rings are arranged on the horizontal bottom plate at the outer side of the mounting tube shaft and are used for being attached to the outer surface of a wing root joint of an inner side half wing and are used as a wing surface facing the bearing surface, when the wing surface is unfolded, the annular locating surface and the wing root joint plane move relatively, friction force between the two wing surfaces is reduced by using a lubricant, and a fixing stop block is arranged at the tail end of the rear side of the machine body connecting mechanism along the central symmetry plane.
The inner half wing and the outer half wing are of symmetrical structures, and the outer half wing are basically identical in appearance structure and comprise a basic airfoil surface, a trailing edge control surface, a wing root joint and a control surface actuating system.
The basic airfoil surface is a pneumatic surface, the cross section of the basic airfoil surface is a standard airfoil, the basic airfoil surface and a root joint positioned at the root of the basic airfoil surface are connected in a sleeved mode, and the basic airfoil surface is connected with the trailing edge control surface through a flexible hinge piece.
The wing root joint is an aluminum alloy integral machining part, the basic structure is a disc with a central cylindrical hole, and the disc extends outwards to form a front-back parallel wing surface connecting structure and a steering engine mounting structure which are respectively used for sleeving and connecting a basic wing surface and a fixed control surface actuating system; the central cylindrical hole aperture of the two wing root joints is designed to be opened on one side, namely, two opposite sides are processed to form cylindrical depressions, the surfaces of the wing root joints outside the cylindrical depressions are respectively provided with a concave ring groove and an outer convex ring canal, the ring canal and the ring groove are tightly sleeved to transfer load, after the ring canal is sleeved with the ring groove, the two cylindrical depressions form an approximately closed space for installing a torsion spring, the rear parts of the two wing root joints are respectively provided with movable stop blocks, the inner end surfaces of the two movable stop blocks are respectively matched with the end surfaces of the two fixed stop blocks on the connecting structure, the movable stop blocks rotate along with the half wings when the half wings are unfolded, the inner end surfaces of the two movable stop blocks impact with the fixed stop blocks on the connecting structure, the inner end surfaces of the two wing joint are provided with guide grooves for locking, the two conical surface of the two conical joint can be made into a specific slope, the two conical joint devices are used for absorbing the inner end surfaces of the two conical joint holes, the two conical joint devices are used for making a specific slope, the damping device is used for making a damping device is used for damping the inner side of the machine body, the deployment position lock is achieved.
The steering surface actuating system comprises a steering engine, a rocker arm and an angular lug, wherein the steering engine is arranged on a steering engine mounting structure of a wing root joint, an output shaft of the steering engine is parallel to a rotating shaft of a rear edge steering surface, a certain distance is reserved between the steering engine and the rotating shaft along the longitudinal direction and the height direction of an airplane, a gear is arranged on the output shaft of the steering engine, a multi-tooth sleeve is arranged at the root of the rocker arm, the gear and the multi-tooth sleeve are sleeved and connected into a whole through a standard screw, a pin is arranged on the rocker arm, the pin is in interference fit connection or threaded connection with the rocker arm through a pin hole, the angular lug is arranged at the inner end of the rear edge steering surface, a notch matched with the pin on the rocker arm is formed in the end of the angular lug, the output shaft of the steering engine drives the rocker arm to rotate, and the pin on the rocker arm and the notch on the angular lug are matched with the notch on the angular lug to drive the rear edge steering surface to rotate.
The torsion spring is fixedly arranged in a space formed between cylindrical depressions on the two half wing root joints and sleeved on the mounting tube shaft of the machine body connecting structure.
The locking device comprises a strip-shaped sheet spring and tapered pins fixed at two ends of the strip-shaped sheet spring, wherein the strip-shaped sheet spring is fixed on a fixed stop block of a machine body connecting structure, the strip-shaped sheet spring is horizontally and symmetrically arranged along a symmetrical center plane, the two tapered pins are respectively matched with taper holes on inner side end faces of movable stop blocks on two half wings, and locking of the two half wings at an unfolding position is achieved.
The basic airfoil structure comprises a main airfoil surface and a metal airfoil tip, wherein the main airfoil surface and the metal airfoil tip are connected in a sleeved mode, the main airfoil surface comprises a core and a shell wrapped outside the core, the core comprises a carbon tube beam, a filling material and a foam core, a root joint is inserted into the root part of the inner side of the carbon tube beam and fixedly connected with the root joint through a cementing agent, the carbon tube beam is filled with the filling material, the foam core is arranged on two sides of the carbon tube beam, the inner shape surface of the shell is matched with the outer shape surface of the root joint, the inner shape surface of the shell and the outer shape surface of the root joint are connected in a co-cementing/co-curing mode, the metal airfoil tip comprises an end plate and a connecting block, the connecting block is sleeved in the shell, and a fastener or an integral machine is used for connecting the end plate and the connecting block.
Further, the trailing edge rudder surface comprises a rigid foam core and a carbon fiber panel wrapped outside the rigid foam core.
Further, the flexible hinge piece is made of Kevlar fiber cloth with a certain thickness, and the front part and the rear part of the flexible hinge piece are respectively connected to the inside of the rear edge of the basic airfoil surface and the inside of the front edge of the rear edge rudder surface.
The folding wing with the trailing edge control surface for the unmanned aerial vehicle has the beneficial effects that the folding wing with the trailing edge control surface for the unmanned aerial vehicle fills the blank of the folding wing with the trailing edge control surface for the unmanned aerial vehicle with special layout.
Drawings
Fig. 1 is a general layout of an airfoil in an extended state, wherein (a) is an isometric view from a top view and (b) is an isometric view from a bottom view.
Fig. 2 is a schematic view of a fuselage connection structure.
Fig. 3 is a schematic view of an inner half wing structure, wherein (a) is a schematic view from a top view, (b) is a C-C sectional view, (C) is a D-D sectional view, and (D) is a schematic view from a bottom view.
Fig. 4 is a schematic view of an outer half wing structure, wherein (a) is a schematic view from a top view, (b) is a cross-sectional view F-F, (c) is a cross-sectional view G-G, and (d) is a schematic view from a bottom view.
Fig. 5 is a partial enlarged view of the present invention, in which (a) is a partial enlarged view of the whole wing in the unfolded state, (b) is a sectional view H-H, and (c) is a partial enlarged view of the outer half wing.
Fig. 6 is a cross-sectional view A-A.
FIG. 7 is a sectional view B-B.
1, A fuselage connection structure; 2 inner half wings, 3 outer half wings, 4 compression nuts, 5 lockers, 6 torsion springs, 11 mounting tube shafts, 12 annular locating surfaces, 13 fixed stop blocks, 14 line through holes, 21 inner wing root joints, 211 central cylindrical holes, 212 annular grooves, 22 basic wings, 221 shells, 222 carbon tube beams, 223 foam cores, 224 flexible hinge sheets, 23 trailing edge control surfaces, 24 control surface actuating systems, 241 steering engines, 242 rocker arms, 243 angular lugs, 31 outer wing root joints and 311 annular rings.
Detailed Description
The technical scheme of the invention is clearly and completely described below. It is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments, and that those skilled in the art may improve or adjust all other embodiments based on the embodiments of the present invention, which are within the scope of the present invention.
The embodiment provides a stacked folding wing of an unmanned aerial vehicle for patrol flight with a trailing edge control surface, wherein the stacked folding wing comprises a body connecting structure 1, an inner half wing 2, an outer half wing 3, a compression nut 4, a torsion spring 6 and a locker 5. When folded, the two half wings are stacked one above the other and are retracted into the lower part or the upper part of the machine body, so that the folding state of the whole machine is realized, the section size is minimum, and when unfolded, the two half wings rotate around the two axial sides by a specific angle (generally about 90 degrees, depending on the designed sweepback angle of the front edge of the wing), and the locker 5 locks the two half wings at the unfolding position as shown in figure 1.
As shown in FIG. 2, the fuselage connection structure 1 is a hollow cylinder, and is used for fixedly connecting the whole stacked folding wing with the main fuselage, a platform is symmetrically arranged at the bottom or the top of the fuselage connection structure 1 according to the central symmetry plane of the fuselage as a horizontal bottom plate, a cylindrical protruding installation tube shaft 11 is arranged at the center of the horizontal bottom plate, threads are arranged on the inner wall of the installation tube shaft 11 and are used for being matched with a compression nut 4, the installation tube shaft 11 is used as an installation connection bearing structure part and a folding unfolding center rotating shaft of two half wings, the hollow cylindrical body connection structure has sufficient strength and rigidity, tighter shape and matching dimensional tolerance, an opening is formed on the horizontal bottom plate at the side wall of the installation tube shaft 11 and the bottom of the installation tube shaft as a line passing opening 14, a path for a steering engine 241 line and a plug of the rear edge control surface 23 on the two half wings is formed on the horizontal bottom plate at the outer side of the installation tube shaft 11, a ring plane is used as an annular positioning surface 12 which is concentric in a small height and is used for being attached to the outer surface of a wing root joint of the inner half wing 2, the annular positioning surface 12 is used as a high-directional positioning surface and a bearing surface of the wing surface, when the wing is unfolded, the wing is used for being relatively moving with the root joint plane, a friction force between the wing joint plane is reduced by adopting lubricant, and a stop 13 is symmetrically arranged at the tail end of the fuselage connection structure along the central strip.
As shown in FIG. 3, the inboard half 2 includes a base airfoil 22, a trailing edge control surface 23, an inboard root joint, and a control surface actuation system 24. The basic airfoil 22 is a pneumatic airfoil, the cross section of the basic airfoil 22 is a standard airfoil, the basic airfoil 22 comprises an airfoil, a metal airfoil tip and flexible hinge plates 224, the airfoil and the metal airfoil tip are connected in a sleeved mode, the airfoil comprises a core and a shell 221 wrapped outside the core, the shell 221 is a carbon fiber panel, the core comprises a carbon tube beam 222, a filling material and a foam core 223, the inner root of the carbon tube beam 222 is inserted into an airfoil connecting structure of a root joint positioned at the root of the airfoil and fixedly connected through a cementing agent, the carbon tube beam 222 is filled with the filling material, the filling material is a twisted strip or resin, the foam core 223 is arranged on two sides of the carbon tube beam 222, the metal airfoil tip comprises end plates and connecting blocks, the connecting blocks are sleeved in the shell 221 of the airfoil, the end plates and the connecting blocks are connected by using fasteners or an integral machine, the flexible hinge plates 224 are positioned at the rear edge of the airfoil, the main airfoil, the flexible hinge plates 224 are used for connecting the rear edge of the main airfoil, the flexible hinge plates 224 are Kevlar fiber cloths with certain thickness (thickness is about 0.20mm, 0.30mm and the like), and the flexible hinge plates 224 are respectively connected with the rear edge of the inner surface 23, and the front edge of the rear edge of the main airfoil are respectively connected with the rear edge of the main airfoil by the front edge of the flexible hinge plates and the rear edge of the front edge of the main airfoil respectively
The trailing edge control surface 23 comprises a rigid foam core 223 and carbon fiber panels wrapped around the rigid foam core
The inner wing root joint 21 is an aluminum alloy integral machining part, the basic structure of the inner wing root joint 21 is a disc with a central cylindrical hole 211, and the disc extends outwards to form a front-rear parallel wing surface connecting structure and a steering engine mounting structure which are respectively used for sleeving and connecting a basic wing surface 22 and a fixed connection control surface actuating system 24; the airfoil connection structure at the front part accounts for about 60% of the chord length, the steering engine installation structure at the rear part accounts for about 40% of the chord length, the cross section of the inner airfoil root joint 21 along the chord direction is an airfoil which is the same as that of the basic airfoil 22, the outer surface of the inner airfoil root joint is matched with the inner surface of the shell 221 of the basic airfoil 22, the inner airfoil root joint 21 is connected with the outer surface of the basic airfoil 22 in a co-cementing/co-curing mode, longitudinal and transverse grooves are formed on the surface of the inner airfoil root joint 21 so as to realize high cementing connection strength, holes are formed in the airfoil connection structure and are used for being inserted into carbon tube beams 222 in the basic airfoil 22, in order to further improve the connection strength, the inner airfoil root joint 21 and the shell 221 can be connected through fasteners or in a hole and fiber bundle sewing mode, the steering engine installation structure is matched with the shape of a steering engine 241 in a steering engine actuation system 24, 3 installation bosses with threaded holes are formed on a bottom plate of the steering engine, the positions of the threaded holes are respectively corresponding to the central positions of 3 installation lug pieces of the steering engine, the central cylindrical hole 211 of a disc of the inner airfoil root joint 21 is matched with the installation tube shaft 11 on the machine connection structure 1 so as to realize the insertion of the tube shaft 11, one side of the central cylindrical hole 211 is far away from the body connection structure 1 to form a carbon tube beam 222, the hollow cylindrical hole is used for forming a torsion spring 6 with a concave installation spring 6 with the diameter 6, the diameter of the hollow installation hole 6 is the hollow diameter has the same as the diameter of the hollow spring 6, the surface of the wing root joint outside the cylindrical recess is provided with a recessed ring groove 212, the rear part (the position of the linear rear edge adjacent to the semicircular outline surface) of the inner wing root joint is provided with a movable stop block, the inner side end surface of the movable stop block is matched with the end surface of the side surface of the fixed stop block 13 on the machine body connecting structure 1, when the inner half wing 2 is unfolded, the movable stop block rotates along with the inner half wing 2, and at the end section of the unfolding stroke, the movable stop block collides with the fixed stop block 13 to impact and absorb the rotating energy of the inner half wing 2, thereby playing the roles of a limiting and damping device, the inner side end surface of the movable stop block is provided with a taper hole, the inner side of the taper hole is provided with a guide groove, and the inclined surface at the bottom of the guide groove is provided with a specific gradient angle for being matched with the locker 5, so that the unfolding position is locked.
The control surface actuating system 24 comprises a steering engine 241, a rocker 242 and an angular lug 243, wherein the steering engine 241 is arranged on a steering engine mounting structure of an inner wing root joint 21, an output shaft of the steering engine 241 is parallel to a rotating shaft of a rear edge control surface 23, a certain distance is reserved between the steering engine 241 and the rotating shaft along the longitudinal direction and the height direction of the aircraft, a gear is arranged on the output shaft of the steering engine 241, a multi-tooth sleeve is arranged at the root of the rocker 242, the gear and the multi-tooth sleeve are sleeved and connected into a whole through standard screws, a pin is arranged on the rocker 242, the pin is in pin hole interference fit connection or threaded connection with the rocker 242, the angular lug 243 is arranged on the inner end of the rear edge control surface 23, a notch matched with the pin on the rocker 242 is formed in the end of the angular lug 243, the output shaft of the steering engine 241 drives the rocker 242 to rotate, the pin on the rocker 242 is matched with the notch on the angular lug 243 to drive the rear edge control surface 23 to rotate, and the steering engine 241 is in a relatively open installation connection design, so that maintenance is facilitated.
The outer half wing 3 and the inner half wing 2 are symmetrical structures, and the two outer structures are basically the same, wherein the cylindrical recess on the outer wing root joint 31 of the outer half wing 3 is positioned on one side facing the fuselage connecting structure 1, the outer wing root joint 31 surface outside the cylindrical recess is provided with a convex ring pipe 311 as shown in fig. 4 and 5, the inner half wing 2 and the outer half wing 3 are sequentially sleeved on the mounting tube shaft 11 of the fuselage connecting structure 1 through the central cylindrical hole 211 on the wing root joint, then the compression nut 4 is screwed on the end part of the mounting tube shaft 11, so that the compression nut 4 is tightly attached to the outer half wing 3, thereby fixing the two half wings on the mounting tube shaft 11 and enabling the two half wings to freely rotate and bear the gravity and the load along the vertical axis direction. An organic integral high-efficiency bearing structure is formed by pipe fitting, hole shaft fitting and surface fitting between the wing root joints of the two half wings and the mounting pipe shaft 11 of the machine body connecting structure 1, so that symmetrical complete load balance of the two half wings can be realized, and asymmetric bending load and vertical load can be transmitted to the machine body.
The torsion spring 6 is arranged in a space formed between cylindrical recesses on the two half wing root joints, is sleeved on the mounting tube shaft 11 of the machine body connecting structure 1, and two ends of the torsion spring are matched with mounting holes on the bottom surfaces of the cylindrical grooves through central arms of the torsion spring 6 to realize fixed connection.
The locking device 5 is characterized in that connecting holes are formed in two ends of the long strip-shaped sheet spring, the lower parts of the two conical pins are small-size cylinders and are respectively in interference fit with the two connecting holes and fixedly connected into a whole in a welding or screwing mode, the long strip-shaped sheet spring is fixed on a fixed stop 13 of the machine body connecting structure 1 and is horizontally and symmetrically arranged along a symmetrical center plane, the two conical pins are respectively matched with conical holes on inner side end surfaces of movable stop blocks on two half wings, locking of the two half wings in an unfolding position is achieved, specifically, at the tail section of a half wing unfolding stroke, the conical pins enter a slope surface inlet section at the bottom of a guide groove in the conical holes, the end surfaces of the conical pins are contacted with slope surfaces of the guide groove and slide upwards along the slope to generate extrusion force, the sheet spring is backwards deformed under the action of extrusion force, the two half wings continue to rotate until the conical pins pass through the topmost end of the slope surfaces and are inserted into the conical holes under the action of elastic force of the sheet spring, and the conical pins are matched with the conical holes to lock the two half wings in the unfolding position, and the end surfaces of the movable stop blocks on the two half wings are respectively contacted with the machine body connecting structure 1, and the two half wings are fixedly contacted with the stop blocks 13 at the same time.
The examples described above represent only embodiments of the invention and are not to be understood as limiting the scope of the invention, it being understood that variations and modifications can be made by those skilled in the art without departing from the spirit of the invention, which are all within the scope of the invention.
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411607562.2A CN119284230A (en) | 2024-11-12 | 2024-11-12 | A stackable folding wing of a patrol drone with a trailing edge rudder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411607562.2A CN119284230A (en) | 2024-11-12 | 2024-11-12 | A stackable folding wing of a patrol drone with a trailing edge rudder |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN119284230A true CN119284230A (en) | 2025-01-10 |
Family
ID=94156911
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202411607562.2A Pending CN119284230A (en) | 2024-11-12 | 2024-11-12 | A stackable folding wing of a patrol drone with a trailing edge rudder |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN119284230A (en) |
-
2024
- 2024-11-12 CN CN202411607562.2A patent/CN119284230A/en active Pending
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