CN113212735B - Air-jet unmanned aerial vehicle - Google Patents
Air-jet unmanned aerial vehicle Download PDFInfo
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- CN113212735B CN113212735B CN202110567622.2A CN202110567622A CN113212735B CN 113212735 B CN113212735 B CN 113212735B CN 202110567622 A CN202110567622 A CN 202110567622A CN 113212735 B CN113212735 B CN 113212735B
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- 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/10—Stabilising surfaces adjustable
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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Abstract
The invention discloses an air-jet unmanned aerial vehicle, which comprises a vehicle body, a main wing assembly and a main wing folding structure, wherein the main wing folding structure comprises a main wing platform, a main wing driving assembly and a main wing limiting assembly, and the main wing assembly comprises a left main wing and a right main wing; when the main wing assembly is folded, the left main wing and the right main wing are stacked along the length direction of the fuselage; when the main wing assembly is unfolded, the left main wing and the right main wing are level in height and extend towards two sides of the fuselage respectively; the main wing limiting component is movably connected with the main wing rotating component so as to limit the main wing component to be in a folded state when the main wing limiting component is effective; the main wing driving assembly is in transmission connection with the main wing rotating assembly so as to drive the main wing rotating assembly to rotate and convert into a unfolding state when the main wing limiting assembly fails. Can realize folding under the small prerequisite of volume, realize simultaneously that the main wing expandes the back and eliminate the difference in height and have the function of dihedral, have more excellent aerodynamic performance when making unmanned aerial vehicle be convenient for store, transport.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an air-jet unmanned aerial vehicle.
Background
Unmanned aerial vehicles have evolved into an irreplaceable piece of equipment that performs long-endurance reconnaissance, regional surveillance, search positioning, firepower guidance, and other tasks. The air-jet unmanned aerial vehicle is an unmanned aerial vehicle which is launched based on an aerial platform such as a fixed-wing airplane, a helicopter or an unmanned aerial vehicle and executes tasks such as aerial monitoring range expansion, bait defense, electronic countermeasure, cluster attack and the like. Air-jet unmanned aerial vehicle usually needs longer duration, requires the existing higher lift-drag ratio of unmanned aerial vehicle, simultaneously, in order to satisfy portable delivery, all requires that unmanned aerial vehicle occupation space is less in unmanned storage, transportation and use stage.
In the unmanned aerial vehicle that discloses at present, dismantled and assembled account for the overwhelming majority, this type of unmanned aerial vehicle dismantles unmanned aerial vehicle into modules such as wing, fuselage when storing and transporting, treats to assemble it again when using. But the size of the disassembled packing box is still large, and the disassembling and assembling process is time-consuming and labor-consuming. There are some few partial collapsible unmanned aerial vehicle schemes, these schemes structure complicacies, the reliability is lower, can't avoid unmanned aerial vehicle's both sides wing height drop problem, and can't compromise high lift-drag ratio aerodynamic configuration and compact accomodation.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the air-jet unmanned aerial vehicle which can simultaneously eliminate the height difference after the main wing is unfolded and meet the requirement of high lift air barrier performance on the premise of realizing small folding volume.
In order to achieve the purpose, the invention provides an air-jet unmanned aerial vehicle which comprises a vehicle body, a main wing assembly and a main wing folding structure, wherein the main wing folding structure comprises a main wing platform, a main wing rotating assembly, a main wing driving assembly and a main wing limiting assembly;
the main wing rotary component comprises a left main wing rotating shaft and a right main wing rotating shaft which are connected on the main wing platform in a parallel and rotating manner, and the main wing component comprises a left main wing and a right main wing;
one end of the left main wing is fixedly connected to the top end of the left main wing rotating shaft, and the other end of the left main wing extends in the direction far away from the left main wing rotating shaft; one end of the right main wing is fixedly connected to the top end of the right main wing rotating shaft, and the other end of the right main wing extends in the direction far away from the right main wing rotating shaft;
the main wing assembly has a folded state and an unfolded state:
when the main wing assembly is in a folded state, the left main wing and the right main wing are stacked above the fuselage along the length direction of the fuselage, and the left main wing is positioned above the right main wing;
when the main wing assembly is in an unfolded state, the left main wing and the right main wing are flush in height and symmetrical with each other along the fuselage, and the left main wing and the right main wing respectively extend towards two sides of the fuselage;
the main wing limiting assembly is arranged on the main wing platform and is movably connected with the main wing rotating assembly so as to limit the main wing rotating assembly to be fixed when the main wing limiting assembly is effective and enable the main wing assembly to be in a folded state;
the main wing drive assembly is in transmission connection with the main wing rotating assembly to be used for driving the main wing rotating assembly to rotate when the main wing limiting assembly fails, and then the main wing assembly is converted into an unfolding state from a folding state.
In one embodiment, the folding type flight wing structure further comprises a flight assembly and a flight folding structure, wherein the flight folding structure comprises a flight platform, a flight rotating assembly, a flight driving assembly and a flight limiting assembly;
the empennage wing platform is fixedly arranged at the tail part of the fuselage, the empennage rotating assembly comprises a left empennage rotating shaft and a right empennage rotating shaft which are connected with the empennage wing platform in a parallel rotating mode, and the empennage assembly comprises a left empennage and a right empennage;
one end of the left empennage is connected to the top end of the left empennage rotating shaft, and the other end of the left empennage extends in the direction far away from the left empennage rotating shaft; one end of the right tail wing is connected to the top end of the right tail wing rotating shaft, and the other end of the right tail wing extends in the direction far away from the right tail wing rotating shaft;
the tail assembly has a folded state and an unfolded state:
when the tail wing assembly is in a folded state, the left tail wing and the right tail wing are symmetrically positioned on two sides of the fuselage along the length direction of the fuselage;
when the tail assembly is in a spreading state, the left tail and the right tail respectively extend towards the lower parts of two sides of the fuselage, and the left tail and the right tail are mutually symmetrical along the fuselage and form an inverted V-shaped structure;
the tail wing limiting assembly is arranged on the tail wing platform and is movably connected with the tail wing rotating assembly so as to limit the tail wing rotating assembly to be fixed when the tail wing limiting assembly is effective and enable the tail wing assembly to be in a folded state;
the tail wing drive assembly with the tail wing rotating assembly transmission links to each other to be used for the spacing subassembly of tail wing drives when failing the tail wing rotating assembly is rotatory, and then makes the tail wing assembly is converted into the expansion state by fold condition.
In one embodiment, the left tail wing and the right tail wing are respectively connected with the left tail wing rotating shaft and the right tail wing rotating shaft in a rotating mode through steering engines.
In one embodiment, an angle between the axial direction of the left main wing rotating shaft and the plane where the main wing platform is located is α 1, and an angle between the axial direction of the right main wing rotating shaft and the plane where the main wing platform is located is α 2, where α 2 is smaller than 0 ° < α 1.
In one embodiment, the air conditioner further comprises a fairing;
when the main wing assembly is in a folded state, one end of the fairing is hinged to the fuselage, and the other end of the fairing is lapped on the main wing assembly;
when the main wing assembly is in an unfolded state, one end of the fairing is hinged to the machine body, the other end of the fairing is in lap joint with the machine body, and the fairing covers the roots of the left main wing and the right main wing.
In one embodiment, a lifting mechanism is disposed on the left main wing shaft or the right main wing shaft, so as to drive the left main wing shaft to descend along the axial direction during the rotation of the left main wing shaft, or drive the right main wing shaft to ascend along the axial direction during the rotation of the right main wing shaft.
In one embodiment, the lifting mechanism comprises a guide rod and a spiral groove, and the spiral groove is arranged on the side wall of the left main wing rotating shaft or the right main wing rotating shaft;
the axial span of the two ends of the spiral groove on the left main wing rotating shaft or the right main wing rotating shaft is equal to the height difference between the left main wing and the right main wing when the main wing assembly is in a folded state;
one end of the guide rod is fixedly connected with the main wing platform or the machine body, and the other end of the guide rod passes through the spiral groove and then is positioned in the left main wing rotating shaft or the right main wing rotating shaft, or passes through the spiral groove and then passes through the left main wing rotating shaft or the right main wing rotating shaft;
the guide rod is connected with the spiral groove in a sliding mode, and when the main wing assembly is in a folded state, the guide rod is located at one end of the spiral groove; when the main wing assembly is in a spreading state, the guide rod is positioned at the other end of the spiral groove.
In one embodiment, the main wing driving assembly comprises a first tension spring, and a first tension spring groove is formed in the side wall of the left main wing rotating shaft along the circumferential direction;
a first tension spring seat is arranged on the first tension spring groove, one end of the first tension spring is fixedly connected with the first tension spring seat, and the other end of the first tension spring passes through part of the first tension spring groove and then is connected with the machine body;
when the main wing assembly is in a folded state, the first tension spring has pretightening force, so that the left main wing rotating shaft has a rotating trend.
In one embodiment, the main wing limiting assembly comprises a first limiting structure, the first limiting structure comprises a first limiting seat, a first limiting rod and a first control rod, and a first limiting groove is formed in the side wall of the left main wing rotating shaft;
the first limiting seat is fixedly connected to the main wing platform, the middle part of the first control rod is hinged to the first limiting seat, and the first limiting rod is connected to the first limiting seat in a sliding mode;
when the main wing assembly is in a folded state, one end of the first limiting rod is hinged with the end of the first control rod, and the other end of the first limiting rod penetrates through the first limiting seat and is embedded into the first limiting groove behind the main wing platform.
Compared with the prior art, the air-jet unmanned aerial vehicle provided by the invention has the following beneficial technical effects:
1. on the premise of realizing small folding volume, the function of eliminating height difference and having dihedral after the main wing is unfolded is realized;
2. the unmanned aerial vehicle is convenient to store and transport, and has better pneumatic performance;
3. the unmanned aerial vehicle can be carried in a cluster in batches, and has long-time-lag air-powered performance;
4. the unmanned aerial vehicle has the advantages that the unmanned aerial vehicle is free of disassembly and assembly processes, manpower and material resource consumption in the use process of the unmanned aerial vehicle is reduced, and the unmanned aerial vehicle is suitable for being used in an aerial launch unmanned aerial vehicle.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
Fig. 1 is a schematic perspective view of a structure of an unmanned aerial vehicle in a folded state according to an embodiment of the present invention;
fig. 2 is a schematic perspective view of the structure of the drone in an unfolded state in an embodiment of the invention;
FIG. 3 is a schematic isometric view of a main wing folded structure in a folded condition in accordance with an embodiment of the present invention;
FIG. 4 is an enlarged schematic view of portion A of FIG. 3;
FIG. 5 is a schematic isometric view of a main wing folded structure in an unfolded state in accordance with an embodiment of the present invention;
FIG. 6 is an enlarged schematic view of section B of FIG. 5;
FIG. 7 is an isometric view of a main wing platform in an embodiment of the present invention;
FIG. 8 is a side view of a main wing platform according to an embodiment of the present invention;
FIG. 9 is an isometric view of the pivot of the left main wing in an embodiment of the present invention;
FIG. 10 is a schematic structural view of a guide rod and a spiral groove on the rotating shaft of the left main wing according to the embodiment of the present invention;
FIG. 11 is an isometric view of the right main wing shaft in an embodiment of the present invention;
FIG. 12 is a schematic isometric view of the arrangement of a stop assembly in an embodiment of the invention;
FIG. 13 is a schematic sectional view showing the arrangement structure of a position limiting assembly in the embodiment of the present invention;
FIG. 14 is a front elevational view schematically illustrating the main wing folded structure in an unfolded state in accordance with an embodiment of the present invention;
FIG. 15 is a schematic top view of a tail folding structure in a folded state according to an embodiment of the present invention;
FIG. 16 is a schematic isometric view of a tail fold structure in accordance with an embodiment of the invention in a folded condition;
FIG. 17 is a schematic top plan view of a tail fold structure in an extended configuration in accordance with an embodiment of the present invention;
FIG. 18 is a schematic isometric view of a tail fold configuration in an extended condition in accordance with an embodiment of the invention;
FIG. 19 is an enlarged schematic view of portion C of FIG. 18;
FIG. 20 is an enlarged schematic view of portion D of FIG. 18;
FIG. 21 is an isometric view of a tail wing platform in an embodiment of the invention;
fig. 22 is a side view of a tail wing platform in an embodiment of the present invention.
Reference numerals;
the machine body 1: a propeller 11, a cowling 12;
main wing platform 21: a left main wing mounting hole 211, a right main wing mounting hole 212;
left main wing shaft 221: a left main wing spindle body 2211, a left main wing top shaft body 2212, a left main wing bottom shaft body 2213, a left main wing clamping piece 2214, a left main wing reinforcing seat 2215, a left main wing reinforcing rod 2216, a first tension spring groove 2217 and a first tension spring seat 2218;
right main wing shaft 222: a right main wing spindle body 2221, a right main wing top shaft body 2222, a right main wing bottom shaft body 2223, a right main wing clamping piece 2224, a right main wing reinforcing seat 2225, a right main wing reinforcing rod 2226, a second tension spring groove 2227 and a second tension spring seat 2228;
a guide rod 231, a spiral groove 232;
first limit structure 241: a first limit seat 2411, a first limit rod 2412 and a first control rod 2413;
the second limiting structure 242: a second limiting seat 2421, a second limiting rod 2422 and a second control rod 2423;
a first tension spring 251 and a second tension spring 252;
a left main wing 31, a right main wing 32;
empennage wing platform 41: a left tail mounting hole 411 and a right tail mounting hole 412;
left empennage rotating shaft 421: a left tail main shaft body 4211, a left tail top shaft body 4212, a left tail bottom shaft body 4213, a left tail clamping piece 4214, a left tail steering gear 4215, a first transmission piece 4216, a third tension spring groove 4217 and a third tension spring seat 4218;
right tail pivot 422: a right tail main shaft body 4221, a right tail top shaft body 4222, a right tail bottom shaft body 4223, a right tail clamping piece 4224, a right tail steering gear 4225, a second transmission piece 4226, a fourth tension spring groove 4227 and a fourth tension spring seat 4228;
a left tail wing 51 and a right tail wing 52.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as upper, lower, left, right, front and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; either directly or indirectly through intervening media, either internally or in any combination, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should be considered to be absent and not within the protection scope of the present invention.
Fig. 1 to 22 show an air-jet drone disclosed in this embodiment, which mainly includes a fuselage 1, a main wing assembly, a main wing folding structure, a tail wing assembly, and a tail wing folding structure. The fuselage 1 is overall cylindrical, and avionics devices, loads and the like are arranged in the fuselage 1, and the tail end of the fuselage 1 is provided with a foldable propeller 11. Wherein, the installation of the interior avionics device of unmanned aerial vehicle fuselage 1 and load and the installation of screw 11 are the conventional technical means of affiliated field, consequently do not give unnecessary details to it in this embodiment.
In this embodiment, the main wing folding structure includes a main wing platform 21, a main wing rotating assembly, a main wing driving assembly, and a main wing limiting assembly. The main wing platform 21 is a basic support for the main wing assembly and the entire main wing folding structure, and is fixedly mounted at the middle position of the fuselage 1 through a fastening structure such as a bolt. Left and right main wing mounting holes 211 and 212 are provided on the main wing platform 21 at intervals in the left-right direction of the fuselage 1, and both the left and right main wing mounting holes 211 and 212 penetrate the main wing platform 21 in the vertical direction.
The main wing rotating assembly includes a left main wing rotating shaft 221 and a right main wing rotating shaft 222 which are connected to the main wing platform 21 in a parallel rotating manner, and the left main wing rotating shaft 221 and the right main wing rotating shaft 222 are both hollow structures to reduce the weight of the main wing folding structure. Specifically, the left main wing rotating shaft 221 includes a left main wing spindle 2211, a left main wing top spindle 2212 and a left main wing bottom spindle 2213, the left main wing top spindle 2212 is coaxially connected to the top of the left main wing spindle 2211, the left main wing bottom spindle 2213 is coaxially connected to the bottom of the left main wing spindle 2211, and the left main wing spindle 2211 is rotatably connected to the left main wing mounting hole 211. The right main wing rotating shaft 222 includes a right main wing main shaft body 2221, a right main wing top shaft body 2222 and a right main wing bottom shaft body 2223, the right main wing top shaft body 2222 is coaxially and fixedly connected to the top of the right main wing main shaft body 2221, the right main wing bottom shaft body 2223 is coaxially and fixedly connected to the bottom of the right main wing main shaft body 2221, and the right main wing main shaft body 2221 is rotatably connected to the right main wing mounting hole 212. The diameters of the left main wing top shaft body 2212 and the left main wing bottom shaft body 2213 are both larger than the diameter of the left main wing main shaft body 2211, and the diameters of the right main wing top shaft body 2222 and the right main wing bottom shaft body 2223 are both larger than the diameter of the right main wing main shaft body 2221, so that the left main wing rotating shaft 221 and the right main wing rotating shaft 222 form an i-shaped structure with a thin middle and thick two ends, and the left main wing rotating shaft 221 and the right main wing rotating shaft 222 are prevented from falling off from the main wing platform 21. In a specific implementation process, the left main wing spindle body 2211 and the left main wing bottom shaft body 2213 may be integrally formed, and the left main wing top shaft body 2212 is fixedly connected to the left main wing spindle body 2211 through a fixing structure. Similarly, the right main wing spindle body 2221 and the right main wing bottom spindle body 2223 may be integrally formed, and the right main wing top spindle body 2222 may be fixedly connected to the right main wing spindle body 2221 by a fixing structure. Wherein, fixed knot constructs can adopt threaded connection structure or bolted connection structure or buckle connection structure etc..
It should be noted that, when the left main wing rotating shaft 221 and the right main wing rotating shaft 222 are rotatably connected to the main wing platform 21, the bottoms of the left main wing rotating shaft 221 and the right main wing rotating shaft 222, i.e. the left main wing bottom shaft 2213 and the right main wing bottom shaft 2223, are both located inside the fuselage 1 and are both supported by a structure such as a bulkhead inside the fuselage 1.
In a preferred embodiment, the left main wing spindle 2211 and the left main wing mounting hole 211 and the right main wing spindle 2221 and the right main wing mounting hole 212 are in clearance fit. Of course, the left main wing spindle 2211 and the left main wing mounting hole 211, and the right main wing spindle 2221 and the right main wing mounting hole 212 may be rotatably connected by a bearing or other structural member, so as to reduce the frictional resistance. As for how to set up the mode that structures such as bearing realized rotating connection is the conventional technical skill section in the field, it is not repeated in this embodiment.
In this embodiment, the main wing assembly includes a left main wing 31 and a right main wing 32. One end of the left main wing 31 is fixedly connected to the top end of the left main wing rotating shaft 221, and the other end extends in a direction away from the left main wing rotating shaft 221; one end of the right main wing 32 is fixedly connected to the top end of the right main wing rotating shaft 222, and the other end extends in a direction away from the right main wing rotating shaft 222. Specifically, a left main wing clamping piece 2214 is fixedly arranged at the top end of the left main wing rotating shaft 221, and a right main wing clamping piece 2224 is fixedly arranged at the top end of the right main wing rotating shaft 222; the root of the left main wing 31 is fixedly connected to the left main wing holder 2214, and the root of the right main wing 32 is fixedly connected to the right main wing holder 2224. Further specifically, the left main wing holder 2214 is provided with a first upper clamping piece and a first lower clamping piece, and the root of the left main wing 31 is held between the first upper clamping piece and the first lower clamping piece and is fixedly connected to the first upper clamping piece and the first lower clamping piece through fasteners such as bolts. The right main wing holder 2224 is provided with a second upper clip and a second lower clip, and the root of the right main wing 32 is held between the second upper clip and the second lower clip and is fixedly connected to the second upper clip and the second lower clip by fasteners such as bolts.
In a preferred embodiment, a left main wing reinforcing seat 2215 and a left main wing reinforcing rod 2216 are further disposed on the top end of the left main wing rotating shaft 221, i.e. the left main wing top shaft body 2212, the left main wing reinforcing seat 2215 is fixedly connected to the left main wing rotating shaft 221, one end of the left main wing reinforcing rod 2216 is fixedly connected to the left main wing reinforcing seat 2215, and the other end is fixedly embedded in the left main wing 31; the top end of the right main wing spindle 222, i.e. the right main wing top shaft 2222, is further provided with a right main wing reinforcement seat 2225 and a right main wing reinforcement rod 2226, the right main wing reinforcement seat 2225 is fixedly connected with the right main wing spindle 222, one end of the right main wing reinforcement rod 2226 is fixedly connected with the right main wing reinforcement seat 2225, and the other end is fixedly embedded into the right main wing 32.
In this embodiment, the main wing assembly has a folded state and an unfolded state:
when the main wing assembly is in a folded state, the left main wing 31 and the right main wing 32 are stacked above the fuselage 1 along the length direction of the fuselage 1, and the left main wing 31 is located above the right main wing 32, as shown in fig. 3-4;
when the main wing assembly is in the unfolded state, the left main wing 31 and the right main wing 32 are level in height and symmetrical to each other along the fuselage 1, and the left main wing 31 and the right main wing 32 extend to both sides of the fuselage 1, respectively, as shown in fig. 5-6.
In this embodiment, the main wing assembly is switched between the folded state and the unfolded state along with the reverse rotation of the left main wing rotating shaft 221 and the right main wing rotating shaft 222, for example, the main wing assembly is initially in the folded state shown in fig. 3-4, and the main wing assembly is turned to the unfolded state shown in fig. 5-6 after the left main wing rotating shaft 221 rotates counterclockwise by 90 ° and the right main wing rotating shaft 222 rotates clockwise by 90 °. It should be noted that the rotation angle is not necessarily 90 ° in the specific implementation process, and other angles smaller than 90 ° may also be used.
In a specific implementation process, the left main wing rotating shaft 221 or the right main wing rotating shaft 222 is provided with a lifting mechanism for driving the left main wing rotating shaft 221 to axially descend in a rotation process of the left main wing rotating shaft 221 or driving the right main wing rotating shaft 222 to axially ascend in a rotation process of the right main wing rotating shaft 222, so that when the main wing assembly is in a folded state, the left main wing 31 and the right main wing 32 are in a stacked state, that is, a height difference exists between the left main wing 31 and the right main wing 32, and the height difference between the left main wing 31 and the right main wing 32 is eliminated while the main wing assembly is unfolded along with the rotation of the left main wing rotating shaft 221 and the right main wing rotating shaft 222.
The following description will further describe the lifting mechanism by taking an example in which the left main wing shaft 221 is driven to descend along the axial direction during the rotation of the left main wing shaft 221. In this example, the lifting mechanism includes a guide bar 231 and a spiral groove 232, and the spiral groove 232 is provided on the side wall of the left main wing rotating shaft 221. Wherein, the circumferential span of the two ends of the spiral groove 232 on the left main wing rotating shaft 221 is related to the rotation angle of the left main wing rotating shaft 221 in the process of converting the main wing assembly from the folded state to the unfolded state, for example, if the rotation angle of the left main wing rotating shaft 221 in this process is 90 °, the circumferential span of the two ends of the spiral groove 232 on the left main wing rotating shaft 221 is one fourth of the circumference of the left main wing rotating shaft 221, that is, the guiding range of the left main wing rotating shaft 221 rotating 90 °; the axial span of the two ends of the spiral groove 232 on the left main wing rotating shaft 221 is equal to the height difference between the left main wing 31 and the right main wing 32 when the main wing assembly is in the folded state. One end of the guide rod 231 is fixedly connected with the main wing platform 21 or the fuselage 1, and the other end of the guide rod passes through the spiral groove 232 and then is positioned on the left main wing rotating shaft 221, wherein the number of the spiral grooves 232 is only one in the case; or the other end passes through the spiral groove 232 and then passes through the left main wing rotating shaft 221, in this case, the number of the spiral grooves 232 is two, and the two spiral grooves 232 are distributed on the side part of the left main wing rotating shaft 221 in a cross-shaped symmetrical manner, namely, one spiral groove 232 is in the 0-90-degree area on the left main wing rotating shaft 221, and the other spiral groove 232 is in the 180-270-degree area. Wherein, the guide rod 231 is slidably connected with the spiral groove 232. When the main wing assembly is in the folded state, the guide bar 231 is located at one end of the spiral groove 232; the guide rod 231 is located at the other end of the helical groove 232 when the main wing assembly is in the deployed state. That is, as the left main wing rotating shaft 221 rotates, since the guiding rod 231 is fixed on the main wing platform 21 or the fuselage 1, the left main wing rotating shaft 221 is caused to descend under the action of the spiral groove 232, and the descending distance is the axial span of the two ends of the spiral groove 232 on the left main wing rotating shaft 221, that is, the height difference between the left main wing 31 and the right main wing 32 when the main wing assembly is in the folded state. Through this process, the height difference between the left and right main wings 31 and 32 can be eliminated. If it is necessary to drive the right main wing rotating shaft 222 to ascend along the axis in the rotation process of the right main wing rotating shaft 222 to realize the function of the elevating mechanism, it is only necessary to set the spiral groove 232 on the right main wing rotating shaft 222 and set the spiral direction thereof in the reverse direction, and therefore details thereof are not repeated in this embodiment.
It should be noted that if the left main wing rotating shaft 221 is driven to axially descend in the rotating process of the left main wing rotating shaft 221, the axial length of the left main wing spindle body 2211 is slightly greater than the hole depth of the left main wing mounting hole 211 in the specific implementation process, so that the left main wing rotating shaft 221 has a lifting space; the axial length of the right main wing spindle body 2221 is set to be equal to the hole depth of the right main wing mounting hole 212 to prevent the right main wing spindle 222 from axially shifting. On the contrary, if the right main wing rotating shaft 222 is driven to move upward along the axial direction during the rotation process of the right main wing rotating shaft 222, the axial length of the right main wing main shaft body 2221 is slightly greater than the hole depth of the right main wing mounting hole 212 during the specific implementation process, so that the right main wing rotating shaft 222 has a lifting space; the axial length of the left main wing spindle body 2211 is set equal to the hole depth of the left main wing mounting hole 211 to avoid axial play of the left main wing spindle 221.
It should be noted that the lifting mechanism in this embodiment is not limited to the above-mentioned embodiments of the guide rod 231 and the spiral groove 232. Alternatively, a thread may be disposed on the left main wing spindle 221 or the right main wing spindle 222, and the left main wing spindle 221 or the right main wing spindle 222 may be screwed to the main wing platform 21 or the fuselage 1, so that the left main wing spindle 221 or the right main wing spindle 222 may be lifted or lowered in accordance with the feeding effect of the thread as the left main wing spindle 221 or the right main wing spindle 222 rotates. Or the lifting can be realized by directly adopting an oil cylinder drive or a motor-driven worm and gear structure, and the embodiment is not repeated one by one.
In this embodiment, the main wing position limiting component is disposed on the main wing platform 21 and movably connected to the main wing rotating component, so as to limit the main wing rotating component from being fixed when the main wing position limiting component is effective, and make the main wing component in a folded state. Specifically, the main wing limiting component includes a first limiting structure 241 and a second limiting structure 242. The first position-limiting structure 241 includes a first position-limiting base 2411, a first position-limiting rod 2412 and a first control rod 2413, and a first position-limiting groove is formed on the side wall of the left main wing rotating shaft 221; the first position-limiting seat 2411 is fixedly connected to the main wing platform 21, the middle part of the first control rod 2413 is hinged to the first position-limiting seat 2411, and the first position-limiting rod 2412 is slidably connected to the first position-limiting seat 2411. When the main wing assembly is in the folded state, one end of the first limit rod 2412 is hinged to the end of the first control rod 2413, and the other end thereof passes through the first limit seat 2411 and the main wing platform 21 and then is embedded into the first limit groove, i.e., the left main wing rotating shaft 221 and the main wing platform 21 are fixedly connected. The second limiting structure 242 includes a second limiting seat 2421, a second limiting rod 2422 and a second control rod 2423, and a second limiting groove is formed on the side wall of the right main wing rotating shaft 222; the second limiting seat 2421 is fixedly connected to the main wing platform 21, the middle part of the second control rod 2423 is hinged to the second limiting seat 2421, and the second limiting rod 2422 is connected to the second limiting seat 2421 in a sliding manner; when the main wing assembly is in a folded state, one end of the second limiting rod 2422 is hinged to the end of the second control rod 2423, and the other end of the second limiting rod passes through the second limiting seat 2421 and the main wing platform 21 and then is embedded into the second limiting groove, i.e., the right main wing rotating shaft 222 and the main wing platform 21 are fixedly connected. When the main wing limiting assembly needs to be out of service, the first limiting rod 2412 and the second limiting rod 2422 can be separated from the first limiting groove and the second limiting groove only by pulling the end parts of the first control rod 2413 and the second control rod 2423, so that the fixed connection state between the left main wing rotating shaft 221, the right main wing rotating shaft 222 and the main wing platform 21 is released. In the specific implementation process, the first control rod 2413 and the second control rod 2423 can be controlled by installing a steering engine and other devices on the machine body 1.
In this embodiment, the main wing driving assembly is in transmission connection with the main wing rotating assembly, so as to drive the main wing rotating assembly to rotate when the main wing limiting assembly fails, and further the main wing assembly is converted from the folded state to the unfolded state, wherein a clamping structure is further disposed between the left main wing rotating shaft 221, the right main wing rotating shaft 222 and the main wing platform 21, so that the rotating amplitudes of the left main wing rotating shaft 221 and the right main wing rotating shaft 222 on the main wing platform 21 have limited values, such as only 90 ° rotation. The locking structure can be realized by a locking groove and a locking block, wherein one of the locking groove and the locking block is arranged on the left main wing rotating shaft 221 and the right main wing rotating shaft 222, and the other locking groove and the locking block is arranged on the main wing platform 21. The specific implementation principle is similar to that of the guide rod 231 and the spiral groove 232, and the detailed description thereof is omitted in this embodiment.
In particular. The main wing driving assembly includes a first tension spring 251, and a first tension spring slot 2217 is circumferentially disposed on a side wall of the left main wing rotating shaft 221, wherein the first tension spring slot 2217 is specifically disposed on the left main wing bottom shaft body 2213. A first tension spring seat 2218 is arranged on the first tension spring groove 2217, one end of the first tension spring 251 is fixedly connected with the first tension spring seat 2218, and the other end of the first tension spring 251 is connected with external fixing pieces such as the machine body 1 after passing through part of the first tension spring groove 2217; when the main wing assembly is in a folded state, the first tension spring 251 has a pretightening force, so that the left main wing rotating shaft 221 has a forward rotation trend, and after the main wing limiting assembly fails, under the action of the pretightening force of the first tension spring 251, the left main wing rotating shaft 221 is rotated forward by 90 degrees under the limitation of the clamping structure. The main wing driving assembly further includes a second tension spring 252, and a second tension spring slot 2227 is circumferentially disposed on a side wall of the right main wing rotating shaft 222, wherein the second tension spring slot 2227 is specifically disposed on the right main wing bottom shaft body 2223. A second tension spring seat 2228 is arranged on the second tension spring groove 2227, one end of the second tension spring 252 is fixedly connected with the second tension spring seat 2228, and the other end passes through part of the second tension spring groove 2227 and then is connected with external fixing parts such as the machine body 1; when the main wing assembly is in a folded state, the second tension spring 252 has a pre-tightening force, so that the right main wing rotating shaft 222 tends to rotate in a reverse direction, and after the main wing limiting assembly fails, the right main wing rotating shaft 222 rotates in a forward direction by 90 degrees under the action of the pre-tightening force of the second tension spring 252 and the limitation of the clamping structure.
It should be noted that the main wing driving assembly in this embodiment is not limited to the above-mentioned embodiment driven by the tension spring, and may also adopt a driving mode of the motor + gear transmission assembly directly, or adopt a driving mode of the motor directly.
In a preferred embodiment, an angle α is formed between the axial direction of the left main wing rotating shaft 221 and the plane of the main wing platform 21, and an angle α is formed between the axial direction of the right main wing rotating shaft 222 and the plane of the main wing platform 21, where α <90 ° is 0 ° < α. Specifically, the axial directions of the left main wing rotating shaft 221 and the right main wing rotating shaft 222 are not perpendicular to the plane where the main wing platform 21 is located, and the top end of the left main wing rotating shaft 221 and the top end of the right main wing rotating shaft 222 both incline to the direction of the tail of the fuselage 1 by the same angle, so that the main wing assembly has a dihedral angle when in the unfolded state, that is, as shown in fig. 14.
In this embodiment, the tail folding structure includes a tail platform 41, a tail rotating assembly, a tail driving assembly, and a tail limiting assembly. The tail wing platform 41 is a foundation support for the tail assembly and the entire tail folding structure, and is fixedly installed at the tail position of the fuselage 1 by fastening structures such as bolts. The empennage wing platform 41 is provided with a left empennage mounting hole 411 and a right empennage mounting hole 412 at intervals in the left-right direction of the fuselage 1, and both the left empennage mounting hole 411 and the right empennage mounting hole 412 penetrate through the wall surface of the empennage wing platform 41 in the vertical direction. In this embodiment, the empennage platform 41 is an integral part of the fuselage 1, i.e. the propellers 11 on the fuselage 1 are arranged at the tail end of the empennage platform 41.
The tail wing rotating assembly comprises a left tail wing rotating shaft 421 and a right tail wing rotating shaft 422 which are connected to the tail wing platform 41 in parallel in a rotating manner, and the left tail wing rotating shaft 421 and the right tail wing rotating shaft 422 are both hollow structures, so that the weight of the tail wing folding structure is reduced. Specifically, the left tail wing rotating shaft 421 includes a left tail wing main shaft 4211, a left tail wing top shaft 4212 and a left tail wing bottom shaft 4213, the left tail wing top shaft 4212 is coaxially connected to the top of the left tail wing main shaft 4211, the left tail wing bottom shaft 4213 is coaxially connected to the bottom of the left tail wing main shaft 4211, and the left tail wing main shaft 4211 is rotatably connected to the left tail wing mounting hole 411. The right tail wing rotating shaft 422 comprises a right tail wing main shaft body 4221, a right tail wing top shaft body 4222 and a right tail wing bottom shaft body 4223, the right tail wing top shaft body 4222 is coaxially and fixedly connected to the top of the right tail wing main shaft body 4221, the right tail wing bottom shaft body 4223 is coaxially and fixedly connected to the bottom of the right tail wing main shaft body 4221, and the right tail wing main shaft body 4221 is rotatably connected to the right tail wing mounting hole 412. The diameters of the left tail top shaft body 4212 and the left tail bottom shaft body 4213 are both larger than the diameter of the left tail main shaft body 4211, and the diameters of the right tail top shaft body 4222 and the right tail bottom shaft body 4223 are both larger than the diameter of the right tail main shaft body 4221, so that the left tail rotating shaft 421 and the right tail rotating shaft 422 form an I-shaped structure with a thin middle part and thick two ends, and the left tail rotating shaft 421 and the right tail rotating shaft 422 are prevented from falling off from the tail wing platform 41. In a specific implementation process, the left tail spindle body 4211 and the left tail bottom spindle body 4213 may be integrally formed, and the left tail top spindle body 4212 is fixedly connected to the left tail spindle body 4211 through a fixing structure. Similarly, the right tail main shaft 4221 and the right tail bottom shaft 4223 may be integrally formed, and the right tail top shaft 4222 may be fixedly coupled to the right tail main shaft 4221 by a fixing structure. Wherein, fixed knot constructs can adopt threaded connection structure or bolted connection structure or buckle connection structure etc..
It should be noted that, when the left tail rotating shaft 421 and the right tail rotating shaft 422 are rotatably connected to the tail wing platform 41, the bottoms of the left tail rotating shaft 421 and the right tail rotating shaft 422, i.e. the left tail bottom shaft body 4213 and the right tail bottom shaft body 4223, are both located inside the fuselage 1 and are supported by structures such as a partition frame inside the fuselage 1.
Preferably, clearance fit is formed between the left tail spindle body 4211 and the left tail mounting hole 411 and between the right tail spindle body 4221 and the right tail mounting hole 412. Of course, the left tail spindle body 4211 and the left tail mounting hole 411, and the right tail spindle body 4221 and the right tail mounting hole 412 may be rotatably connected through a structural member such as a bearing, thereby reducing frictional resistance. As for how to set up the mode that structures such as bearing realized rotating connection is the conventional technical skill section in the field, it is not repeated in this embodiment.
In this embodiment, the tail assembly includes a left tail 51 and a right tail 52. One end of the left tail wing 51 is rotatably connected to the top end of the left tail wing rotating shaft 421, and the other end extends in a direction away from the left tail wing rotating shaft 421; one end of the right tail 52 is rotatably connected to the top end of the right tail rotating shaft 422, and the other end extends in a direction away from the right tail rotating shaft 422. Specifically, the top end of the left tail rotating shaft 421 is rotatably connected with a left tail clamping piece 4214, and the top end of the right tail rotating shaft 422 is rotatably connected with a right tail clamping piece 4224; the root of the left tail 51 is fixedly connected with the left tail clamping piece 4214, and the root of the right tail 52 is fixedly connected with the right tail clamping piece 4224. Further specifically, a third upper clip and a third lower clip are disposed on the left tail clamping member 4214, and the root of the left tail 51 is clamped between the third upper clip and the third lower clip and is fixedly connected to the third upper clip and the third lower clip through fasteners such as bolts. The right tail clamping piece 4224 is provided with a fourth upper clamping piece and a fourth lower clamping piece, and the root of the right tail 52 is clamped between the fourth upper clamping piece and the fourth lower clamping piece and is fixedly connected with the fourth upper clamping piece and the fourth lower clamping piece through fasteners such as bolts. Still more specifically, the side portion of the left tail wing clamping piece 4214 is rotatably connected with the top end of the left tail wing rotating shaft 421 through a bearing, a left tail wing steering engine 4215 is further arranged inside the machine body 1, and the output end of the left tail wing steering engine 4215 is in transmission connection with the left tail wing clamping piece 4214 through a first transmission piece 4216, so that the left tail wing clamping piece 4214 is driven to rotate, and the left tail wing 51 is driven to rotate. Similarly, the side part of the right tail clamping piece 4224 is rotatably connected with the top end of the right tail rotating shaft 422 through a bearing, a right tail steering engine 4225 is further arranged inside the machine body 1, and the output end of the right tail steering engine 4225 is in transmission connection with the right tail clamping piece 4224 through a second transmission piece 4226, so that the right tail clamping piece 4224 is driven to rotate, and the right tail 52 is driven to rotate.
In this embodiment, the fin assembly has a folded state and an unfolded state:
when the tail wing assembly is in the folded state, the left tail wing 51 and the right tail wing 52 are symmetrically positioned at both sides of the fuselage 1 along the length direction of the fuselage 1, as shown in fig. 15-16;
when the tail assembly is in the deployed state, the left tail wing 51 and the right tail wing 52 extend downward from both sides of the fuselage 1, respectively, and the left tail wing 51 and the right tail wing 52 are symmetrical to each other along the fuselage 1 and form an inverted V-shaped structure, as shown in fig. 17 to 18.
In this embodiment, the switch between the folded state and the unfolded state of the tail assembly is performed along with the reverse rotation of the left tail rotating shaft 421 and the right tail rotating shaft 422, for example, the tail assembly is initially in the folded state shown in fig. 15-16, and then rotates 90 ° counterclockwise along with the left tail rotating shaft 421, and the right tail rotating shaft 422 rotates 90 ° clockwise to turn to the unfolded state shown in fig. 17-18. It should be noted that the rotation angle is not necessarily 90 ° in the specific implementation process, and may be other angles smaller than 90 °.
In this embodiment, the tail wing limiting assembly is disposed on the tail wing platform 41 and movably connected to the tail wing rotating assembly, so as to limit the fixing of the tail wing rotating assembly when the tail wing limiting assembly is effective, so that the tail wing assembly is in a folded state. Specifically, the tail limiting assembly comprises a third limiting structure and a fourth limiting structure. The third limiting structure comprises a third limiting seat, a third limiting rod and a third control rod, and a third limiting groove is formed in the side wall of the left empennage rotating shaft 421; the third limiting seat is fixedly connected to the empennage wing platform 41, the middle part of the third control rod is hinged to the third limiting seat, and the third limiting rod is connected to the third limiting seat in a sliding mode. When the tail wing assembly is in a folded state, one end of the third limiting rod is hinged to the end of the third control rod, and the other end of the third limiting rod passes through the third limiting seat and the tail wing platform 41 and then is embedded into the third limiting groove, i.e., the left tail wing rotating shaft 421 and the tail wing platform 41 are fixedly connected. The fourth limiting structure comprises a fourth limiting seat, a fourth limiting rod and a fourth control rod, and a fourth limiting groove is formed in the side wall of the right tail rotating shaft 422; the fourth limiting seat is fixedly connected to the empennage wing platform 41, the middle part of the fourth control rod is hinged to the fourth limiting seat, and the fourth limiting rod is connected to the fourth limiting seat in a sliding mode; when the tail wing assembly is in the folded state, one end of the fourth limiting rod is hinged to the end of the fourth control rod, and the other end of the fourth limiting rod penetrates through the fourth limiting seat and the tail wing platform 41 and then is embedded into the fourth limiting groove, so that the right tail wing rotating shaft 422 and the tail wing platform 41 are fixedly connected. When the tail wing limiting assembly is needed to be out of effect, the third limiting rod and the fourth limiting rod can be separated from the third limiting groove and the fourth limiting groove only by shifting the end parts of the third control rod and the fourth control rod, and then the fixed connection state between the left tail wing rotating shaft 421 and the right tail wing rotating shaft 422 and the tail wing platform 41 is released. In the specific implementation process, the third control rod and the fourth control rod can be controlled by installing a steering engine and other devices on the machine body 1. The above described embodiment of the tail limiting assembly is substantially the same as the embodiment of the main wing limiting assembly described above and therefore it is not illustrated in this embodiment.
In this embodiment, the tail wing driving assembly is in transmission connection with the tail wing rotating assembly, so as to drive the tail wing rotating assembly to rotate when the tail wing limiting assembly fails, and further, the tail wing assembly is converted from a folded state to an unfolded state, wherein a clamping structure is further disposed between the left tail wing rotating shaft 421, the right tail wing rotating shaft 422 and the tail wing platform 41, so that the rotating amplitudes of the left tail wing rotating shaft 421 and the right tail wing rotating shaft 422 on the tail wing platform 41 have limited values, for example, only 90 ° can be rotated. The clamping structure can be realized by a clamping groove and a clamping block, wherein one of the clamping groove and the clamping block is arranged on the left empennage rotating shaft 421 and the right empennage rotating shaft 422, and the other clamping groove and the clamping block is arranged on the empennage wing table 41. The specific implementation principle is similar to that of the guide rod 231 and the spiral groove 232, and the detailed description thereof is omitted in this embodiment.
Specifically. The tail driving assembly comprises a third tension spring, a third tension spring groove 4217 is formed in the side wall of the left tail rotating shaft 421 along the circumferential direction, and the third tension spring groove 4217 is specifically formed in the left tail bottom shaft 4213. A third tension spring seat 4218 is arranged on the third tension spring groove 4217, one end of the third tension spring is fixedly connected with the third tension spring seat 4218, and the other end of the third tension spring passes through part of the third tension spring groove 4217 and then is connected with external fixing pieces such as the machine body 1; when the tail wing assembly is in a folded state, the third tension spring has a pre-tightening force, so that the left tail wing rotating shaft 421 has a forward rotating trend, and after the tail wing limiting assembly fails, under the action of the pre-tightening force of the third tension spring, the left tail wing rotating shaft 421 is limited by the clamping structure to rotate 90 degrees in a forward direction. The tail wing driving assembly further comprises a fourth tension spring, a fourth tension spring groove 4227 is formed in the side wall of the right tail wing rotating shaft 422 along the circumferential direction, wherein the fourth tension spring groove 4227 is specifically formed in two tension spring grooves in the right tail wing bottom shaft body 4223, a fourth tension spring seat 4228 is arranged on each of the two tension spring grooves, one end of the fourth tension spring is fixedly connected with the fourth tension spring seat 4228, and the other end of the fourth tension spring is connected with external fixing pieces such as the fuselage 1 after passing through part of the fourth tension spring groove 4227; when the tail wing assembly is in a folded state, the fourth tension spring has pretightening force so that the right tail wing rotating shaft 422 has a tendency of reversely rotating, and after the tail wing limiting assembly fails, the right tail wing rotating shaft 422 is forwardly rotated by 90 degrees under the limitation of the clamping structure under the action of the pretightening force of the fourth tension spring.
It should be noted that the tail wing driving assembly in this embodiment is not limited to the above-mentioned tension spring driving embodiment, and may also directly adopt a driving mode of a motor + gear transmission assembly, or directly adopt a motor driving mode.
In a preferred embodiment, the drone further comprises a fairing 12. When the main wing assembly is in a folded state, one end of the fairing 12 is hinged on the fuselage 1, and the other end is lapped on the main wing assembly; when the main wing assembly is in the deployed state, one end of the fairing 12 is hinged to the fuselage 1, the other end is lapped on the fuselage 1, and the fairing 12 covers the roots of the left main wing 31 and the right main wing 32.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (8)
1. An air-jet unmanned aerial vehicle is characterized by comprising a vehicle body, a main wing assembly and a main wing folding structure, wherein the main wing folding structure comprises a main wing platform, a main wing rotating assembly, a main wing driving assembly and a main wing limiting assembly;
the main wing rotary component comprises a left main wing rotating shaft and a right main wing rotating shaft which are connected to the main wing platform in a parallel rotating mode, and the main wing component comprises a left main wing and a right main wing;
one end of the left main wing is fixedly connected to the top end of the left main wing rotating shaft, and the other end of the left main wing extends in the direction far away from the left main wing rotating shaft; one end of the right main wing is fixedly connected to the top end of the right main wing rotating shaft, and the other end of the right main wing extends in the direction far away from the right main wing rotating shaft;
the main wing assembly has a folded state and an unfolded state:
when the main wing assembly is in a folded state, the left main wing and the right main wing are stacked above the fuselage along the length direction of the fuselage, and the left main wing is positioned above the right main wing;
when the main wing assembly is in a unfolding state, the left main wing and the right main wing are level in height and symmetrical to each other along the fuselage, and the left main wing and the right main wing respectively extend towards two sides of the fuselage;
the main wing limiting assembly is arranged on the main wing platform and movably connected with the main wing rotating assembly so as to limit the main wing rotating assembly to be fixed when the main wing limiting assembly is effective and enable the main wing assembly to be in a folded state;
the main wing driving assembly is in transmission connection with the main wing rotating assembly and is used for driving the main wing rotating assembly to rotate when the main wing limiting assembly fails, so that the main wing assembly is converted from a folded state to an unfolded state;
an included angle between the axial direction of the left main wing rotating shaft and the plane where the main wing platform is located is α 1, and an included angle between the axial direction of the right main wing rotating shaft and the plane where the main wing platform is located is α 2, wherein 0 ° < α 1 ═ α 2<90 °, specifically:
the axial directions of the left main wing rotating shaft and the right main wing rotating shaft are not perpendicular to the plane where the main wing platform is located, and the top end of the left main wing rotating shaft and the top end of the right main wing rotating shaft are inclined to the direction of the tail of the airplane body by the same angle, so that the main wing assembly is provided with a dihedral angle when in an unfolded state.
2. The airborne unmanned aerial vehicle of claim 1, further comprising a tail assembly and a tail folding structure, wherein the tail folding structure comprises a tail platform, a tail rotating assembly, a tail driving assembly and a tail limiting assembly;
the empennage wing platform is fixedly arranged at the tail part of the fuselage, the empennage rotating assembly comprises a left empennage rotating shaft and a right empennage rotating shaft which are connected to the empennage wing platform in a rotating mode side by side, and the empennage assembly comprises a left empennage and a right empennage;
one end of the left empennage is connected to the top end of the left empennage rotating shaft, and the other end of the left empennage extends in the direction far away from the left empennage rotating shaft; one end of the right tail wing is connected to the top end of the right tail wing rotating shaft, and the other end of the right tail wing extends in the direction far away from the right tail wing rotating shaft;
the tail assembly has a folded state and an unfolded state:
when the tail wing assembly is in a folded state, the left tail wing and the right tail wing are symmetrically positioned at two sides of the machine body along the length direction of the machine body;
when the tail assembly is in a spreading state, the left tail and the right tail respectively extend towards the lower parts of two sides of the fuselage, and the left tail and the right tail are mutually symmetrical along the fuselage and form an inverted V-shaped structure;
the tail wing limiting assembly is arranged on the tail wing platform and is movably connected with the tail wing rotating assembly so as to limit the tail wing rotating assembly to be fixed when the tail wing limiting assembly is effective and enable the tail wing assembly to be in a folded state;
the tail wing drive assembly with the tail wing rotating assembly transmission links to each other to be used for the spacing subassembly of tail wing drives when failing the tail wing rotating assembly is rotatory, and then makes the tail wing assembly is converted into the expansion state by fold condition.
3. The air-jet unmanned aerial vehicle of claim 2, wherein the left tail wing and the right tail wing are rotatably connected with the left tail wing rotating shaft and the right tail wing rotating shaft through steering gears respectively.
4. An air-jet drone according to claim 1, 2 or 3, characterised by further comprising a fairing;
when the main wing assembly is in a folded state, one end of the fairing is hinged to the machine body, and the other end of the fairing is lapped on the main wing assembly;
when the main wing assembly is in an unfolded state, one end of the fairing is hinged to the machine body, the other end of the fairing is connected to the machine body in a lap joint mode, and the fairing covers the roots of the left main wing and the right main wing.
5. The aerial emission unmanned aerial vehicle of claim 1, 2 or 3, wherein a lifting mechanism is provided on the left main wing rotating shaft or the right main wing rotating shaft for driving the left main wing rotating shaft to descend along an axial direction during rotation of the left main wing rotating shaft or driving the right main wing rotating shaft to ascend along an axial direction during rotation of the right main wing rotating shaft.
6. The airborne unmanned aerial vehicle of claim 5, wherein the lifting mechanism comprises a guide rod and a spiral groove, and the spiral groove is formed in a side wall of the left main wing rotating shaft or the right main wing rotating shaft;
the axial span of the two ends of the spiral groove on the left main wing rotating shaft or the right main wing rotating shaft is equal to the height difference between the left main wing and the right main wing when the main wing assembly is in a folded state;
one end of the guide rod is fixedly connected with the main wing platform or the machine body, and the other end of the guide rod passes through the spiral groove and then is positioned in the left main wing rotating shaft or the right main wing rotating shaft, or passes through the spiral groove and then passes through the left main wing rotating shaft or the right main wing rotating shaft;
the guide rod is connected with the spiral groove in a sliding mode, and when the main wing assembly is in a folded state, the guide rod is located at one end of the spiral groove; when the main wing assembly is in a spreading state, the guide rod is positioned at the other end of the spiral groove.
7. The aerial emission unmanned aerial vehicle of claim 1, 2 or 3, wherein the main wing driving assembly comprises a first tension spring, and a first tension spring groove is formed in the side wall of the left main wing rotating shaft along the circumferential direction;
a first tension spring seat is arranged on the first tension spring groove, one end of the first tension spring is fixedly connected with the first tension spring seat, and the other end of the first tension spring passes through part of the first tension spring groove and then is connected with the machine body;
when the main wing assembly is in a folded state, the first tension spring has pretightening force, so that the left main wing rotating shaft has a rotating trend.
8. The aerial emission unmanned aerial vehicle of claim 1, 2 or 3, wherein the main wing limiting assembly comprises a first limiting structure, the first limiting structure comprises a first limiting seat, a first limiting rod and a first control rod, and a first limiting groove is formed in the side wall of the left main wing rotating shaft;
the first limiting seat is fixedly connected to the main wing platform, the middle part of the first control rod is hinged to the first limiting seat, and the first limiting rod is connected to the first limiting seat in a sliding manner;
when the main wing assembly is in a folded state, one end of the first limiting rod is hinged to the end of the first control rod, and the other end of the first limiting rod penetrates through the first limiting seat and is embedded into the first limiting groove behind the main wing platform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110567622.2A CN113212735B (en) | 2021-05-24 | 2021-05-24 | Air-jet unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110567622.2A CN113212735B (en) | 2021-05-24 | 2021-05-24 | Air-jet unmanned aerial vehicle |
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| CN113212735A CN113212735A (en) | 2021-08-06 |
| CN113212735B true CN113212735B (en) | 2022-09-02 |
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| CN210126634U (en) * | 2019-06-18 | 2020-03-06 | 河南趣航科技有限公司 | Wing unfolding and locking device of folding wing unmanned aerial vehicle |
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| US20200079492A1 (en) * | 2018-09-11 | 2020-03-12 | Swift Engineering, Inc. | Systems and methods for aerodynamic deployment of wing structures |
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| JPH0789492A (en) * | 1993-09-27 | 1995-04-04 | Mitsubishi Heavy Ind Ltd | Missile |
| CN108177783A (en) * | 2017-12-28 | 2018-06-19 | 陕西中科博亿电子科技有限公司 | A kind of training type unmanned plane |
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