CN219806961U - Fixed wing unmanned aerial vehicle folding wing for box type emission - Google Patents
Fixed wing unmanned aerial vehicle folding wing for box type emission Download PDFInfo
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Abstract
The utility model discloses a fixed wing unmanned aerial vehicle folding wing for box type emission, which is divided into an inner section and an outer section along the wingspan direction, and specifically comprises an inner wing, an outer wing and a wing folding mechanism, wherein the inner wing and the outer wing are connected through the wing folding mechanism; the wing folding mechanism adopts a modularized structural design, and is used as a total module to be respectively connected with the inner wing and the outer wing through connectors and clamping grooves and locked by fasteners. The utility model provides a modularized design implementation scheme of a wing folding mechanism, which is used for completing the assembly of the wing folding mechanism and the connection and installation of the wing folding mechanism with an inner wing and an outer wing. The inner wing and the outer wing are folded once after the installation interfaces of the inner wing and the outer wing are positioned in the wing folding mould through the tool.
Description
Technical Field
The utility model belongs to the technical field of aviation, and particularly relates to a fixed wing unmanned aerial vehicle wing folding, automatic unfolding and locking mechanism for box-type emission and a modularized design implementation scheme thereof.
Background
The wing form of the existing fixed-wing unmanned aerial vehicle in the take-off state mainly comprises a full-span state and a folding state. The full span state is widely used, the structure is simple and reliable, the technology is mature, but obvious defects such as large space volume occupancy rate exist. The folding wings can effectively reduce the occupation of the unmanned aerial vehicle to the space, more unmanned aerial vehicle clusters can be arranged in a smaller space, and the unmanned aerial vehicle clusters can be quickly transmitted more conveniently. However, compared with the full-extension wing, the folding wing has obvious defects of complex structure, reduced reliability, high technical difficulty and the like, and aerodynamic force loss is caused by incomplete aerodynamic appearance of the wing in a folding section.
The driving of folding and unfolding the wing generally comprises motor driving, hydraulic driving, elastic component driving and the like, and the motor and the hydraulic driving are often used for large-load wings of carrier-borne aircraft, fighter aircraft and the like, and the unfolding time is long, and the structure is relatively complex. The unmanned aerial vehicle takes off rapidly, including target aircraft, various projectile bodies etc., and the unfolding of the airfoil surface often needs to be realized rapidly in place in a short time by using an elastic element, and can be locked reliably.
In recent years, the demand of the market for cluster emission of unmanned aerial vehicles, particularly target aircraft products, is gradually increased, and the old-fashioned emission mode has long preparation time and high ground occupancy rate and cannot be used for high-density cluster emission. The box type emission is one of important means for solving the problem of high-density cluster emission of unmanned aerial vehicles, the space occupation of the unmanned aerial vehicles is greatly reduced by folding wings, the volume of the emission box is reduced, the density of the emission box is increased, and the box type emission method is one of essential key technologies of box type emission.
Disclosure of Invention
In order to solve the technical problems, the utility model aims to provide a folding, automatic unfolding and locking mechanism for a box-type launching fixed wing unmanned aerial vehicle wing, which can realize the folding operation of the wing on the ground by a single person, and can automatically lock the wing after the wing is automatically unfolded and unfolded in place after the unmanned aerial vehicle is launched and lifted, so that the wing is prevented from rebounding or trembling. The wing folding mechanism provided by the utility model has a sufficient pneumatic shape-preserving function, and can sufficiently reduce the aerodynamic loss of a wing folding area.
In order to achieve the above effects, the present utility model provides a folding wing of a fixed wing unmanned aerial vehicle for box type launching, wherein the folding wing is divided into an inner section and an outer section along a wingspan direction, and specifically comprises an inner wing, an outer wing and a wing folding mechanism, wherein the inner wing and the outer wing are connected through the wing folding mechanism; the wing folding mechanism adopts a modularized structural design, and is used as a total module, and is respectively connected with the inner wing and the outer wing through connectors and clamping grooves and locked by fasteners;
the folding rotation axis and the folding separation surface of the wing folding mechanism are designed in an offset way, and the folding separation surface comprises a section of cylindrical surface coaxial with the folding rotation axis and a section of plane vertical to the wingspan direction, and the plane is tangent to the cylindrical surface; the wing folding mechanism comprises a fixed joint, a rotating joint, an inner mounting rib and an outer mounting rib, wherein the fixed joint, the rotating joint, the inner mounting rib and the outer mounting rib are all provided with structural characteristics of folding separating surfaces, the rotating joint and the outer mounting rib rotate by taking a rotating shaft as a central shaft, and the folding separating surfaces are overlapped with the fixed joint and the inner mounting rib when being unfolded.
Further, the wing folding mechanism comprises a folding rotation and locking module, an installation connection and pneumatic shape-preserving module.
Further, the folding rotation and locking module comprises a torque generating element, a front fixed joint, a front rotation joint, a rear fixed joint, a rear rotation joint and a lock pin assembly, the fixed joint and the rotary joint are arranged in pairs, the front and the rear of the flying direction are named as front and rear, the front fixed joint is connected with the front beam of the inner wing, and the rear fixed joint is connected with the rear beam of the inner wing; the rotary joint is connected with one side of the outer wing and used for driving the outer wing to fold and unfold, the front rotary joint is connected with the front beam of the outer wing, the rear rotary joint is connected with the rear beam of the outer wing and fastened by using a fastener and a conformal nut, and the two ends of the rotating shaft are connected and fastened with the front fixed joint and the rear fixed joint by using fasteners.
Further, the installation connection and pneumatic shape-preserving module comprises an inner installation rib, an outer installation rib, shape-preserving covers, shape-preserving nuts and the like, one end of the torque generating element is connected with the inner installation rib, and the other end of the torque generating element is connected with the outer installation rib to transmit torque;
the torque generating element comprises a sleeve, the sleeve is coaxially connected with the rotating shaft and sleeved on the rotating shaft, and two ends of the torsion spring are respectively connected with the inner mounting rib and the outer mounting rib; the pressure generating element comprises a front pressure spring and a rear pressure spring, the pressure springs correspond to the lock pins one by one, the pressure springs are arranged on the outer sides of the lock pins, and the pressure springs are arranged on the lock pin mounting blocks.
Further, the wing folding mechanism comprises a lock pin assembly, wherein the lock pin assembly is arranged on one side, connected with the inner wing mounting rib, of the fixed joint, a mounting space is reserved in a groove at the corresponding position of the inner wing mounting rib, and the lock pin assembly is used for locking the unfolded state of the outer wing after the outer wing is automatically unfolded in place.
Further, the lock pin assemblies are divided into a front group and a rear group, each lock pin assembly consists of a lock pin, a lock pin installation block and a pressure generating element, the lock pin assemblies are in one-to-one correspondence with the front fixed joint and the rear fixed joint, the lock pins are installed on the outer sides of the fixed joints, and the lock pins penetrate through the corresponding fixed joints and the corresponding rotary joints; the pressure generating element passes through the lock pin tail rod section and is arranged in a sliding groove of the lock pin mounting block, and the lock pin mounting block is connected with a corresponding fixed joint through a threaded fastener.
Furthermore, the lock pin component is in clearance fit with a limiting hole of the fixed joint and is in conical guide fit with the rotary joint.
Further, the torque generating element generates torque and is restrained by the limiting structure of the launching device, the wing is released from restraint after being launched, the torque generating element and the aerodynamic lift force of the outer wing drive the wing to complete automatic unfolding, and the torque is determined by the loading condition of the wing and the index of the folded wing.
The beneficial effects are that:
1) Space occupancy rate during unmanned aerial vehicle transmitting is reduced, transmitting preparation time is shortened, and unmanned aerial vehicle cluster rapid transmitting is realized;
2) The offset design of the folding rotation axis and the folding surface has compact structure, and the integrity of the aerodynamic shape of the wing can be fully ensured through the shape-preserving design, so that the aerodynamic loss of the folding section of the wing is avoided;
3) The force transmission route is short, the force transmission is direct, a double locking mechanism is adopted, the structural strength is good, the weight is light, and the reliability is high;
4) The locking structure directly acts on the rotating joint through the fixed joint, and adopts a hole shaft matching design and a front end conical guide matching design to eliminate the wingtip trembling problem caused by the assembly clearance of the folding mechanism;
5) The modularized design implementation method is adopted, so that the structure is simple, the disassembly and assembly are convenient, the cost is low, and the maintenance and the use are easy;
6) The mechanism has good compatibility, and can be suitable for folding of fixed wings and tail wings with various molded surfaces by simple transformation.
Drawings
In order to more clearly illustrate the technical solutions of the present utility model, the drawings that are needed in the present utility model will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the overall structural composition of a folding wing according to the present utility model;
FIG. 2 is a schematic view of the overall structure of the wing-fold mechanism of the present utility model;
FIG. 3 is a schematic view of a folding rotation and locking module of the folding mechanism according to the present utility model;
FIG. 4 is a schematic diagram of an unlocking and folding operation process of the wing folding mechanism according to the utility model;
FIG. 5 is a schematic diagram of an automatic unfolding and locking working process of the wing folding mechanism according to the utility model;
FIG. 6 is a view showing the structural characteristics of the folding surface of the folding mechanism according to the present utility model;
FIG. 7 is a schematic diagram of a method for implementing a modular design of a wing-fold mechanism according to the present utility model;
wherein, the names corresponding to the marks in the drawings are as follows: a-inner wing, A1-inner wing front beam, A2-inner wing rear beam, B-outer wing, B1-outer wing front beam, B2-outer wing rear beam, 1-folding rotation and locking module, 1.1-front fixed joint, 1.2-front rotation joint, 1.3-rear fixed joint, 1.4-rear rotation joint, 1.5-rotating shaft, 1.6-sleeve, 1.7-torsion spring, 1.8-front lock pin, 1.9-front pressure spring, 1.10-front lock pin mounting block, 1.11-rear lock pin, 1.12-rear pressure spring, 1.13-rear lock pin limiting block, 1.14-threaded fastener, 2.1-inner mounting rib, 2.2-outer mounting rib, 2.3-front edge shape-preserving cover, 2.4-inner rib shape-preserving cover, 2.5-outer shape-preserving cover and 2.6-rear edge shape-preserving cover.
Description of the embodiments
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments of the present utility model. The components of the embodiments of the present utility model generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the utility model, as presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the present utility model, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are directions or positional relationships based on those shown in the drawings, or are directions or positional relationships conventionally put in use of the inventive product, are merely for convenience of describing the present utility model and simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal," "vertical," "overhang," and the like do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present utility model, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be connected inside two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.
Example 1
The utility model provides a fixed wing unmanned aerial vehicle folding wing for box type launching, which can realize the wing folding operation of a single person on the ground, the automatic unfolding of the wing after the unmanned aerial vehicle is launched and lifted, and the automatic locking of the wing after the wing is unfolded to a position, so that the rebound or the tremble of the wing is prevented. The utility model provides a modularized design implementation scheme of a wing folding mechanism, which is used for completing the assembly of the wing folding mechanism and the connection and installation of the wing folding mechanism with an inner wing and an outer wing. The inner wing and the outer wing are folded once after the installation interfaces of the inner wing and the outer wing are positioned in the wing folding mould through the tool.
As shown in fig. 1, the folding wing of the fixed wing unmanned aerial vehicle provided by the embodiment comprises a folding rotation module, a locking module 1, an installation connection, a pneumatic shape keeping module 2 and other modules, and can realize that a single person can carry out wing folding operation on the ground, the wing can be automatically unfolded after the unmanned aerial vehicle is launched and lifted, and the wing can be automatically locked after the wing is unfolded to a position, so that the rebound or tremble of the wing can be prevented.
As shown in fig. 2, the folding rotation and locking module 1 is composed of a torsion spring 1.7, a sleeve 1.6, a rotating shaft 1.5, a front fixed joint 1.1, a front rotating joint 1.2, a rear fixed joint 1.3, a rear rotating joint 1.4, a front lock pin 1.8, a front pressure spring 1.9, a front lock pin mounting block 1.10, a rear lock pin 1.11, a rear pressure spring 1.12, a rear lock pin mounting block 1.13 and the like, wherein the rotating shaft 1.5 is respectively connected and fastened with the front fixed joint 1.1 and the rear fixed joint 1.3 by a threaded fastener 1.14, the wing is folded, the torsion spring 1.7 generates torque and is restrained by a limiting structure of a transmitting device, the wing is released after being transmitted, and the torque of the torsion spring 1.7 and the aerodynamic lift force of an outer wing jointly drive the wing to complete automatic unfolding, and the torque is determined by the wing loading condition and the folding wing index; as shown in fig. 7, the front lock pin 1.8 penetrates through the front fixed joint 1.1 and the front rotary joint 1.2, the front pressure spring 1.9 penetrates through the tail rod section of the front lock pin 1.8 and is installed in the sliding groove of the front lock pin installation block 1.10, the front lock pin installation block 1.10 is connected with the front fixed joint 1.1 through a threaded fastener 1.14, and the installation structures and principles of the rear lock pin 1.11, the rear pressure spring 1.12 and the rear lock pin installation block 1.13 are consistent with those of the front lock pin. When the wing is folded, the lock pin is pulled backwards, the pressure spring produces pressure, and after the wing is unfolded in place, the pressure spring drives the lock pin to penetrate through a round hole of the fixed joint and press into a taper hole of the rotary joint, so that the wing is locked in an unfolded state; the installation connection and pneumatic shape-preserving module consists of an inner installation rib 2.1, an outer installation rib 2.2, a front edge shape-preserving cover 2.3, an inner rib shape-preserving cover 2.4, an outer rib shape-preserving cover 2.5, a rear edge shape-preserving cover 2.6 and the like, is used as an installation and connection basic mechanism of the wing folding mechanism, and maintains the pneumatic shape of the wing in the folding mechanism section to be complete.
The folding wing is divided into an inner section and an outer section along the span direction, and specifically comprises an inner wing, an outer wing and a wing folding mechanism, the inner wing and the outer wing are connected through a wing folding mechanism; the wing folding mechanism adopts a modularized structural design, and is used as a total module, and is respectively connected with the inner wing and the outer wing through connectors and clamping grooves and locked by fasteners;
the folding rotation axis and the folding separation surface of the wing folding mechanism are designed in an offset way, and the folding separation surface comprises a section of cylindrical surface coaxial with the folding rotation axis and a section of plane vertical to the wingspan direction, and the plane is tangent to the cylindrical surface; the wing folding mechanism comprises a fixed joint, a rotating joint, an inner mounting rib and an outer mounting rib, wherein the fixed joint, the rotating joint, the inner mounting rib and the outer mounting rib are all provided with structural characteristics of folding separating surfaces, the rotating joint and the outer mounting rib rotate by taking a rotating shaft as a central shaft, and the folding separating surfaces are overlapped with the fixed joint and the inner mounting rib when being unfolded.
The wing folding mechanism comprises a folding rotation and locking module and an installation connection and pneumatic shape-preserving module; the folding rotation and locking module comprises a torque generating element, a sleeve, a rotating shaft, a front fixed joint, a front rotating joint, a rear fixed joint, a rear rotating joint and a lock pin assembly, wherein the fixed joint and the rotating joint are arranged in pairs, the front and the rear of the rotating joint in the flying direction are named as front and rear, the front fixed joint is connected with a front beam of an inner wing, and the rear fixed joint is connected with a rear beam of the inner wing; the rotary joint is connected with one side of the outer wing and used for driving the outer wing to fold and unfold, the front rotary joint is connected with the front beam of the outer wing, the rear rotary joint is connected with the rear beam of the outer wing and fastened by using a fastener and a conformal nut, and the two ends of the rotating shaft are connected and fastened with the front fixed joint and the rear fixed joint by using fasteners.
The installation connection and pneumatic shape-preserving module comprises an inner installation rib, an outer installation rib, shape-preserving covers, shape-preserving nuts and the like, one end of the torque generating element is connected with the inner installation rib, and the other end of the torque generating element is connected with the outer installation rib to transmit torque;
the torque generating element comprises a sleeve, the sleeve is coaxially connected with the rotating shaft, sleeved on the rotating shaft, and two ends of the torsion spring are respectively connected with the inner mounting rib and the outer mounting rib; the pressure generating element comprises a front pressure spring and a rear pressure spring, the pressure springs correspond to the lock pins one by one, the pressure springs are arranged on the outer sides of the lock pins, and the pressure springs are arranged on the lock pin mounting blocks.
As shown in fig. 3, the wing folding mechanism comprises a locking pin assembly, wherein the locking pin assembly is arranged on one side of the fixed joint connected with the inner wing mounting rib, a groove is reserved at the corresponding position of the inner wing mounting rib to leave an installation space, and the locking pin assembly is used for locking the unfolded state of the outer wing after the outer wing is automatically unfolded in place. The lock pin assemblies are divided into a front group and a rear group, each lock pin assembly consists of lock pins, lock pin installation blocks and pressure generating elements, the lock pin assemblies are in one-to-one correspondence with the front fixed joint and the rear fixed joint, the lock pins are installed on the outer sides of the fixed joints, and the lock pins penetrate through the corresponding fixed joints and the corresponding rotary joints; the pressure generating element passes through the lock pin tail rod section and is arranged in a sliding groove of the lock pin mounting block, and the lock pin mounting block is connected with a corresponding fixed joint through a threaded fastener. The lock pin assembly is in clearance fit with a limiting hole of the fixed joint and is in conical guide fit with the rotary joint.
The torque generating element generates torque and is restrained by a limiting structure of the launching device, the wing is released from restraint after launching, the torque generating element and the outer wing aerodynamic lift force drive the wing to complete automatic unfolding, and the torque is determined by the loading condition of the wing and the index of the folding wing.
The unlocking and folding method for the box-type transmitting fixed wing unmanned aerial vehicle folding wing comprises the following steps of:
before the unmanned aerial vehicle takes off, the wing is manually folded and is arranged in the transmitting device, and the specific steps comprise:
s1.1, manually pulling back a front lock pin, and unlocking the front rotary joint by a front locking structure;
s1.2, manually pulling back the rear lock pin, and unlocking the rear rotary joint by the rear locking structure;
s1.3, the external force overcomes the torque of the torsion spring, so that the outer mounting rib rotates relative to the inner mounting rib, and the rotation angle is determined by the folding angle of the wing; the wing folding state is constrained by a limiting structure of the unmanned aerial vehicle launching device;
after the unmanned aerial vehicle takes off, the launching device is separated from, the constraint of the launching device to the wing is released, the wing is automatically unfolded and locked in an unfolding state, and the method specifically comprises the following steps:
s2.1, the outer mounting ribs are automatically unfolded under the combined action of torsion of the torsion springs and aerodynamic lift of the outer wings;
s2.2, after the wing is unfolded to be in a flat state, the front lock pin is pressed into the front rotary joint taper hole under the pressure of the front pressure spring, and the rear lock pin is pressed into the rear rotary joint taper hole under the pressure of the pressure spring, so that the wing is automatically locked in an unfolded state.
The folding and automatic unfolding locking working process of the wing folding mechanism is as follows:
1) The wing folding mechanism is unlocked and folded in the working process:
as shown in fig. 4, before the unmanned aerial vehicle takes off, the wing is manually folded and loaded into the launching device, and the specific steps include:
(1) The front lock pin 1.8 is manually pulled back, and the front locking structure is used for unlocking the front rotary joint 1.2;
(2) The rear lock pin 1.11 is manually pulled back, and the locking of the rear locking structure to the rear rotary joint 1.4 is released;
(3) The external force overcomes the torque of the torsion spring 1.7, so that the outer mounting rib 2.2 rotates relative to the inner mounting rib 2.1, and the rotation angle is determined by the folding angle of the unmanned aerial vehicle. The wing folding state is constrained by the limiting structure of the unmanned aerial vehicle launching device.
2) The automatic unfolding and locking working process of the wing folding mechanism comprises the following steps:
as shown in fig. 5, after the unmanned aerial vehicle takes off, the launching device is separated from the launching device, the constraint of the launching device on the wing is released, and the wing is automatically unfolded and locked, and the specific steps include:
(1) The outer mounting rib 2.2 is automatically unfolded under the combined action of the torque of the torsion spring 1.7 and the aerodynamic lift force of the outer wing;
(2) After the wing is unfolded to be in a flat state, the front lock pin 1.8 is pressed into the taper hole of the front rotary joint 1.2 under the pressure of the front pressure spring 1.9, and the rear lock pin 1.11 is pressed into the taper hole of the rear rotary joint 1.4 under the pressure of the pressure spring 1.12, so that the automatic locking of the wing in an unfolded state is realized.
As shown in fig. 6, the folding rotation axis and the folding separation surface of the wing folding mechanism adopt an offset design scheme, the folding separation surface consists of a cylindrical surface and a plane, and the axis of the cylindrical surface coincides with the folding rotation axis and is tangent to the plane, so that the folding surface is compact in structure and complete in aerodynamic appearance.
As shown in fig. 3, the aforementioned wing folding mechanism is connected with an inner wing front beam A1 by a front fixed joint 1.1, a rear fixed joint 1.3 is connected with an inner wing rear beam A2, it is connected with an outer wing front beam B1 by a front rotating joint 1.2, a rear rotating joint 1.4 is connected with an outer wing rear beam B2, and the force transmission route of the whole folding wing is as follows: the outer spar B1/B2- & gt rotary joint- & gt rotary shaft 1.5 (and lock pin- & gt fixed joint- & gt inner spar A1/A2- & gt machine body has the advantages of short force transmission route, direct force transmission, good structural strength, light weight and the like; the front lock pin 1.8 penetrates through the front fixed joint 1.1 to directly act on the front rotary joint 1.2, the rear lock pin 1.11 penetrates through the rear fixed joint 1.3 to directly act on the rear rotary joint 1.4, no other force transmission route exists, reliability of a locking structure is improved, clearance fit is adopted between the lock pin 1.8/1.11 and a limiting hole of the fixed joint 1.1/1.3, conical guide fit is adopted between the lock pin 1.8/1.11 and the rotary joint 1.2/1.4, compactness of the locking structure is improved, and accordingly the tremble problem of a folding wing is eliminated; the rear lock pin mounting block 1.13 is connected with the rear fixed joint 1.3 through the threaded fastener 1.14, and the rear lock pin mounting block 1.13 realizes the locking of the inner mounting rib 2.1 and the rear fixed joint 1.3 in the folding axis direction through the design of the hook structure, so that the strength and the reliability of the folding mechanism are greatly improved;
as shown in fig. 7, the foregoing wing-folding mechanism adopts a modularized design implementation method:
(Z1) firstly, the folding rotation and the independent assembly and function debugging of the locking module 1 are finished;
(Z2) positioning and mounting at the corresponding position of the folding rotation and locking module 1 through the clamping groove structures of the inner mounting rib 2.1 and the outer mounting rib 2.2 and locking by using a threaded fastener;
(Z3) installing each conformal cover 2.3-2.6 and locking by using a threaded fastener to complete the integral assembly of the wing folding mechanism;
and (Z4) the wing folding mechanism is used as a total module and is respectively connected with the inner wing A and the outer wing B through the joint and the clamping groove and is locked by a fastener J. The modularized design implementation method improves the assembly manufacturability of the mechanism, is convenient to assemble and disassemble, and is easy to use and maintain. The inner wing A and the outer wing B are positioned in a wing folding mould through a tool to finish folding of the inner wing and the outer wing after the installation interfaces of the inner wing A and the outer wing B are positioned;
the wing folding mechanism can be additionally arranged on a given wing structure, and the wing folding mechanism can be arranged at a proper position of a wing to realize wing folding, automatic unfolding and locking, and can also be suitable for folding of a tail wing through simple transformation.
The utility model provides a fixed wing unmanned aerial vehicle folding wing for box type emission and a thinking of an unlocking folding method thereof, and a method and a way for realizing the technical scheme are numerous, the above description is only a preferred embodiment of the utility model, and it should be pointed out that a plurality of improvements and modifications can be made to a person of ordinary skill in the art without departing from the principle of the utility model, and the improvements and the modifications are also regarded as the protection scope of the utility model. The components not explicitly described in this embodiment can be implemented by using the prior art.
Claims (8)
1. The fixed wing unmanned aerial vehicle folding wing for box type emission is characterized by comprising an inner wing, an outer wing and a wing folding mechanism along the wingspan direction, wherein the inner wing and the outer wing are connected through the wing folding mechanism; the wing folding mechanism adopts a modularized structural design, and is used as a total module, and is respectively connected with the inner wing and the outer wing through connectors and clamping grooves and locked by fasteners;
the folding rotation axis and the folding separation surface of the wing folding mechanism are designed in an offset way, and the folding separation surface comprises a section of cylindrical surface coaxial with the folding rotation axis and a section of plane vertical to the wingspan direction, and the plane is tangent to the cylindrical surface; the wing folding mechanism comprises a fixed joint, a rotating joint, an inner mounting rib and an outer mounting rib, wherein the fixed joint, the rotating joint, the inner mounting rib and the outer mounting rib are all provided with structural characteristics of folding separating surfaces, the rotating joint and the outer mounting rib rotate by taking a rotating shaft as a central shaft, and the folding separating surfaces are overlapped with the fixed joint and the inner mounting rib when being unfolded.
2. A fixed wing unmanned aerial vehicle folding wing for box firing according to claim 1, wherein the wing folding mechanism comprises a folding rotation and locking module, a mounting connection and a pneumatic conformal module.
3. A folding wing of a fixed wing unmanned aerial vehicle for box firing according to claim 2, wherein the folding rotation and locking module comprises a torque generating element, a front fixed joint, a front rotating joint, a rear fixed joint, a rear rotating joint, a locking pin assembly, the fixed joint and the rotating joint being arranged in pairs, which are named front and rear with respect to the direction of flight, the front fixed joint being connected to the front spar of the inner wing, the rear fixed joint being connected to the rear spar of the inner wing; the rotary joint is connected with one side of the outer wing and used for driving the outer wing to fold and unfold, the front rotary joint is connected with the front beam of the outer wing, the rear rotary joint is connected with the rear beam of the outer wing and fastened by using a fastener and a conformal nut, and the two ends of the rotating shaft are connected and fastened with the front fixed joint and the rear fixed joint by using fasteners.
4. A folding wing of a fixed wing unmanned aerial vehicle for box firing according to claim 3, wherein the mounting connection and aerodynamic shape retention module comprises an inner mounting rib, an outer mounting rib, shape retention flaps and shape retention nuts, wherein one end of the torque generating element is connected with the inner mounting rib, and the other end is connected with the outer mounting rib to transmit torque;
the torque generating element comprises a sleeve, the sleeve is coaxially connected with the rotating shaft and sleeved on the rotating shaft, and two ends of the torsion spring are respectively connected with the inner mounting rib and the outer mounting rib; the pressure generating element comprises a front pressure spring and a rear pressure spring, the pressure springs correspond to the lock pins one by one, the pressure springs are arranged on the outer sides of the lock pins, and the pressure springs are arranged on the lock pin mounting blocks.
5. A folding wing of a fixed wing unmanned aerial vehicle for box firing according to claim 3, wherein,
the wing folding mechanism comprises a lock pin assembly, wherein the lock pin assembly is arranged on one side, connected with the inner wing installation rib, of the fixed joint, an installation space is reserved in a groove at the corresponding position of the inner wing installation rib, and the lock pin assembly is used for locking the unfolded state of the outer wing after the outer wing is automatically unfolded in place.
6. The folding wing of a fixed wing unmanned aerial vehicle for box launching according to claim 5, wherein the lock pin assemblies are divided into a front group and a rear group, each of which consists of lock pins, lock pin mounting blocks and pressure generating elements, the lock pin assemblies are in one-to-one correspondence with the front fixed joint and the rear fixed joint, the lock pins are mounted outside the fixed joints, and the lock pins penetrate through the corresponding fixed joints and the rotary joints; the pressure generating element passes through the lock pin tail rod section and is arranged in a sliding groove of the lock pin mounting block, and the lock pin mounting block is connected with a corresponding fixed joint through a threaded fastener.
7. A fixed wing unmanned aerial vehicle folding wing for box firing according to claim 3, wherein the locking pin assembly is in clearance fit with the limiting aperture of the fixed joint and in tapered guiding fit with the rotary joint.
8. A folding wing of a fixed wing unmanned aerial vehicle for box firing according to claim 3, wherein the torque generating element generates torque and is constrained by a limit structure of the firing device, the wing is released from constraint after being launched, the torque generating element and the aerodynamic lift force of the outer wing drive the wing to complete automatic unfolding, and the torque is determined by the loading condition of the wing and the index of the folded wing.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222457411.6U CN219806961U (en) | 2022-09-15 | 2022-09-15 | Fixed wing unmanned aerial vehicle folding wing for box type emission |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222457411.6U CN219806961U (en) | 2022-09-15 | 2022-09-15 | Fixed wing unmanned aerial vehicle folding wing for box type emission |
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| CN219806961U true CN219806961U (en) | 2023-10-10 |
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| CN202222457411.6U Active CN219806961U (en) | 2022-09-15 | 2022-09-15 | Fixed wing unmanned aerial vehicle folding wing for box type emission |
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| CN (1) | CN219806961U (en) |
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