CN111086633A - Solar foldable aircraft wing imitating coleoptera insects - Google Patents

Solar foldable aircraft wing imitating coleoptera insects Download PDF

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Publication number
CN111086633A
CN111086633A CN202010003235.1A CN202010003235A CN111086633A CN 111086633 A CN111086633 A CN 111086633A CN 202010003235 A CN202010003235 A CN 202010003235A CN 111086633 A CN111086633 A CN 111086633A
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CN
China
Prior art keywords
solar
flapping wing
plate
flapping
wing plate
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CN202010003235.1A
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Chinese (zh)
Inventor
李一浩
张琦
吴昊
李科颉
江伟涛
贾铭哲
刘畅
郑永发
申益宁
袁可帅
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Zhengzhou University of Light Industry
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Zhengzhou University of Light Industry
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Priority to CN202010003235.1A priority Critical patent/CN111086633A/en
Publication of CN111086633A publication Critical patent/CN111086633A/en
Pending legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C33/00—Ornithopters
    • B64C33/02—Wings; Actuating mechanisms therefor
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C33/00—Ornithopters

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Abstract

The invention discloses a solar foldable aircraft wing imitating coleopteran insects.A flapping wing plate driving mechanism achieves normal flapping of a foldable solar battery flapping wing plate; the pitching angle of the solar flapping plate can be adjusted through the pitching angle driving mechanism, the flying posture of the aircraft in different flying environments is guaranteed to be stable, and the folding solar battery flapping wing plate is covered through the flapping wing plate protecting mechanism; the foldable wing plate combines the characteristics that the back wing of a coleopteran insect can be folded and hidden under the coleopteran to be protected, and a solar cell panel is arranged on a small aircraft to be continued for a long time, and two adjacent solar folding wing plates can be conveniently switched back and forth in two vertical planes through the designed complementary electromagnetic alignment anti-loosening clamping groove and the matching of a two-degree-of-freedom limiting pin pair mechanism and an electric telescopic rod based on air pressure driving, so that the safety and reliability are realized, and compared with the folding wings of the same type, the vertical space utilization rate of the folding wings is also saved.

Description

Solar foldable aircraft wing imitating coleoptera insects
Technical Field
The invention relates to the technical field of aircrafts, in particular to a solar foldable aircraft wing imitating coleopteran insects.
Background
The small aircraft has the advantages of small size, high maneuverability, good portability and the like, and has very high application value in both military fields and civil fields. However, the small flapping wing aircraft is limited by the size of the aircraft, the small flapping wing aircraft is limited by the size of the lift force of the small flapping wing during operation, the size and the mass of the aircraft are strictly regulated, and the battery capacity is also limited, so that the cruising ability of the aircraft is greatly shortened, and the working ability of the aircraft is influenced.
The solar cell panel is additionally arranged on the wing, so that the cruising ability of the aircraft can be greatly enhanced, but the solar cell panel needs a large light receiving area to provide enough flight power, so that the wing size of the aircraft is greatly increased, particularly the flapping wings of most aircraft are not foldable, most solar aircraft have large volume and large occupied space when parked, and the loss of the cell panel is aggravated if the solar cell panel is exposed to extreme severe weather conditions such as wind, rain and the like for a long time;
however, most of the existing folding flapping wing aircrafts have single folding mode and complicated folding structure, and the volume and the mass of the folding flapping wing and the whole aircraft can be increased. The protective measures for wings of the aircraft during parking are not provided, for example, if the aircraft is parked outdoors, the wing area of the aircraft is large, and the aircraft is easily corroded by severe or extreme weather after being exposed for a long time;
therefore, how to provide a coleopteran insect-imitated solar foldable aircraft wing which is small in size, strong in cruising ability, convenient to fold and capable of protecting the wing is a problem to be solved by technical personnel in the field.
Disclosure of Invention
The invention provides a solar foldable aircraft wing imitating coleopteran insects, and aims to solve at least one of the technical problems in the prior art to a certain extent.
In order to achieve the purpose, the invention adopts the following technical scheme:
the utility model provides a collapsible aircraft wing of solar energy of imitative sheath wing class insect, includes that frame and symmetry are installed flapping wing board actuating mechanism of frame both sides, flapping wing board actuating mechanism includes:
the foldable solar battery flapping plate is hinged to one side of the rack at the end part;
a first turntable;
the driving motor is fixedly arranged on the rack, and the end part of an output shaft of the driving motor is fixedly connected with the axis of the first rotating disc;
one end of the first driving pull rod is hinged with the first rotating disc at a position far away from the axis, and the other end of the first driving pull rod is hinged with one end of the folding solar cell flapping plate.
Further, the both sides of frame all articulate there is movable support, movable support includes:
the driving motor is horizontally arranged in the motor mounting seat;
the vertical connecting plate is fixedly connected with the motor mounting seat, the bottom end of the vertical connecting plate is hinged with the side plate of the rack, and the top end of the vertical connecting plate is rotatably connected with the end part of the folding solar battery flapping plate.
The flapping wing plate driving mechanism is fixed on the movable support, and the driving mechanism and the folding solar flapping wing plate are integrally rotated.
Further, still including the symmetry setting be in the angle of pitch actuating mechanism of frame afterbody, angle of pitch actuating mechanism includes:
a second turntable;
the pitch angle driving motor is horizontally arranged at the tail part of the rack, and the end part of an output shaft of the pitch angle driving motor is fixedly connected with the axis of the second turntable;
one end of the second driving pull rod is hinged with the second turntable at a position far away from the axis, and the other end of the second driving pull rod is hinged with one side of the vertical connecting plate.
The beneficial effect who adopts above-mentioned scheme is that, pitch angle through this structure adjustment solar energy flapping wing board guarantees that the flight attitude of aircraft in different flight environment is stable.
Further, still including the symmetry setting be in the anterior flapping wing plate protection machanism of frame, flapping wing plate protection machanism includes:
the front part of the frame is provided with a vertical supporting plate, and the end part of one side of the flapping wing protective cover is hinged with the vertical supporting plate;
a third turntable;
the protective cover driving motor is vertically arranged at the front part of the rack, and the end part of an output shaft of the protective cover driving motor is fixedly connected with the axis of the third turntable;
and one end of the third driving pull rod is hinged with the third turntable at a position far away from the axis, and the other end of the third driving pull rod is hinged with one side edge of the flapping wing protective cover.
The solar flapping wing protection cover has the advantages that the flapping wing protection cover can cover the upper position of the folded flapping wing plate to play a role in protection, the solar flapping wing plate can be prevented from being eroded in severe extreme weather, the size of the flapping wing of an aircraft can be reduced, and when the aircraft needs to work, the driving pull rod close to the lower part of the driving motor is pushed by the driving motor of the protection cover to move outwards, namely the position of the flapping wing which normally operates in a vertical flapping mode is not influenced.
Further, the folding solar cell flapping wing plate comprises:
the solar flapping wing plate comprises a first solar flapping wing plate, wherein a connecting hole is formed in one side of the first solar flapping wing plate, a mounting hole corresponding to the connecting hole is formed in the top end of the movable support, and the first solar flapping wing plate is sequentially arranged in the mounting hole and the connecting hole in a penetrating mode through a pin shaft and is rotatably connected with the movable support;
the second solar flapping wing plate is movably connected with the first solar flapping wing plate through a limiting pin pair mechanism, an electric telescopic rod is installed on the outer side of the first solar flapping wing plate, and the driving end of the electric telescopic rod is pivoted with the end part connected with the same side of the second solar flapping wing plate;
the third solar flapping wing plate is movably connected with the second solar flapping wing plate through a limiting pin pair mechanism, the other side of the second solar flapping wing plate is provided with the electric telescopic rod, and the driving end of the electric telescopic rod is pivoted with the end part of the third solar flapping wing plate at the same side.
The beneficial effects of adopting above-mentioned scheme are that, under the shrink state, three solar energy flapping wing plates pile up on vertical plane, begin to expand when solar energy flapping wing plate, electric telescopic handle shortens under the drive of aircraft own electrified source, the promotion third solar energy flapping wing plate is done anticlockwise rotation around the second solar energy flapping wing plate, when the third solar energy flapping wing plate changes to required expansion position, the electric telescopic handle of first solar energy flapping wing plate shortens, the promotion second solar energy flapping wing plate is done clockwise rotation around first solar energy flapping wing plate to required position, foldable solar energy flapping wing plate is whole to be expanded this moment, get into flight preparation state.
Furthermore, a horizontal connecting plate extends from the connecting end of the first solar flapping wing plate and the vertical connecting plate, and the horizontal connecting plate is hinged to the first driving pull rod.
The beneficial effect who adopts above-mentioned scheme is, for the convenience of driving motor drives three solar energy flapping wing panel flapping through first drive pull rod.
Further, the limit pin pair mechanism comprises:
the flapping wing plate rotating position cover plate is fixedly connected with the second solar flapping wing plate or the third solar flapping wing plate, and the bottom of the flapping wing plate rotating position cover plate is connected with an inflation cavity in a sliding manner;
the lower flapping wing plate rotating shaft cylinder and the flapping wing plate rotating position cover plate are of an integrated connecting structure, and the lower flapping wing plate rotating shaft cylinder is sleeved on the outer wall of the inflation cavity and is in sliding connection with the inflation cavity; the outer wall of the inflation cavity is fixedly connected with the first solar flapping wing plate or the second solar flapping wing plate;
the air inlet is arranged at the bottom of the lower flapping wing plate rotating shaft cylinder and is communicated with the lower flapping wing plate rotating shaft cylinder and the inflation cavity; the inflation cavity is inflated and deflated through the inflation port, so that the third solar flapping wing plate can slide up and down on the second solar flapping wing plate, or the second solar flapping wing plate can slide up and down on the first solar flapping wing plate.
The solar flapping wing plate folding mechanism has the advantages that after air in the two-degree-of-freedom limiting pin pair mechanism driven by air pressure is pumped out, the second solar flapping wing plate or the third solar flapping wing plate can fall to the same plane relative to the first solar flapping wing plate or the second solar flapping wing plate under the action of gravity, so that the solar flapping wing plates can move relatively in an axial space in the folding process, the flatness of the flapping wings can be kept under the action of air pressure after the solar flapping wing plates are unfolded, the folding function is realized, the structure is simplified, the weight of the flapping wings is reduced, and the flight performance of an aircraft is influenced to the minimum extent.
Furthermore, a complementary electromagnetic alignment connecting clamping groove is arranged between two adjacent solar flapping wing panels and comprises two convex inserting ports and two concave mooring ports, the concave mooring ports are made of metal materials, the convex inserting ports are matched with the concave mooring ports, and controllable electromagnets are arranged in the convex inserting ports.
The solar flapping wing plate has the advantages that after the solar flapping wing plate is unfolded, the relative positions of two adjacent solar flapping wing plates can be fixed, the connection is reliable, the size of the flapping wing plate can be saved, and the quality of the flapping wing is greatly reduced.
Furthermore, a small air pump is arranged at the front part of the frame and connected with the inflation inlet through a pipeline.
According to the technical scheme, compared with the prior art, the invention has the following beneficial effects:
1. the electric telescopic rod is used as power, and the two-degree-of-freedom limitable pin pair mechanism driven by air pressure in a special design ensures that two adjacent solar folding wing plates can be switched back and forth in two vertical planes, namely the safety and reliability of the wings during working are ensured;
2. the folded area proportion after folding is improved, and the size of the wings of the aircraft is reduced by 40 to 60 percent when the aircraft is parked by dividing the folding solar flapping wing plate into three sections;
3. the designed pneumatic two-degree-of-freedom limiting pin pair mechanism with axial limiting can enable the folded solar flapping wing plate to have axial spatial relative motion in the folding process, ensure that the flatness of the flapping wing can be kept under the air pressure driving after the solar flapping wing plate is unfolded, and influence the flight performance of an aircraft to the minimum extent;
4. the situation that the solar flapping wing plate falls off or becomes loose after being unfolded is guaranteed, the relative position of the folding solar flapping wing plate can be fixed by adopting the complementary electromagnetic alignment anti-loosening clamping groove, the volume of the flapping wing can be saved, and the mass of the flapping wing is greatly reduced;
5. the flapping wing protective cover imitating the coleoptera of the beetle insects can prolong the service life of the flapping wings of the aircraft, can ensure that the internal mechanical structure, the special driving source, the circuit and the like of the wings of the aircraft are not corroded by the natural environment when the aircraft is parked in the open air, can improve the service life of the wings of the aircraft, and ensures the stability of the aircraft during working.
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 description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1-2 are schematic structural views of a coleopteran insect-imitating solar foldable aircraft wing.
Fig. 3-4 are partial top views of the present invention.
Fig. 5 is a schematic structural view of a flapping plate driving mechanism, a pitch angle driving mechanism and a flapping plate protection mechanism according to the present invention.
Fig. 6 is a schematic view of the folding solar energy flapping plate of the invention in a folded state.
Fig. 7 is a schematic structural diagram of a limiting pin pair mechanism of two adjacent solar flapping wing plates on the same plane.
FIG. 8 is a schematic structural diagram of a limiting pin pair mechanism of two adjacent solar flapping wing panels of the invention, which are not on the same plane.
Fig. 9 is a schematic structural view of the limit pin pair mechanism of the present invention.
FIG. 10 is a schematic view of the air duct and cable arrangement of the solar flapping wing panel of the invention in the unfolded state.
FIG. 11 is a schematic view of the air duct and cable distribution of the solar flapping wing panel of the invention in a folded state.
Wherein:
1-a frame; 2-folding solar battery flapping wing plate; 3-a first turntable; 4-a first drive link; 5-a movable support; 6-pitch angle driving mechanism; 7-a flapping wing plate protection mechanism; 8-limiting pin pair mechanism; 9-a power supply; 11-a vertical support plate; 12-an air pump; 21-a first solar flapping plate; 211-horizontal connecting plate; 22-a second solar flapping plate; 23-a third solar flapping plate; 24-an electric telescopic rod; 25-a male socket; 26-concave mooring port; 27-trachea; 28-a drive cable; 51-a motor mount; 52-vertical connection plate; 61-a second carousel; 62-a second drive link; 71-flapping wing shield; 72-a third carousel; 73-a third drive link; 81-flapping wing plate rotating position cover plate; 82-lower flapping wing plate rotating shaft cylinder; 83-inflation lumen.
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.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only 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 one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. 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 the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
The embodiment of the invention discloses a solar foldable aircraft wing imitating coleopteran insects, which comprises a rack 1 and flapping wing plate driving mechanisms symmetrically arranged on two sides of the rack 1, wherein the flapping wing plate driving mechanisms comprise: the foldable solar battery flapping plate comprises a foldable solar battery flapping plate 2, a first rotating disc 3, a driving motor and a first driving pull rod 4; specifically, the end of the foldable solar battery flapping plate 2 is hinged to one side of the rack 1, the driving motor can be MSME 011G1, the driving motor is fixedly mounted on the rack 1, the end of an output shaft of the driving motor is fixedly connected with the axis of the first rotating disc 3, one end of the first driving pull rod 4 is hinged to the first rotating disc 3 at a position far away from the axis, the other end of the first driving pull rod is hinged to one end of the foldable solar battery flapping plate 2, and the first driving pull rod 4 is pushed and pulled by the driving motor to reciprocate up and down, so that the folding solar battery flapping plate 2 can be normally fluttered.
In one embodiment, in order to adjust the pitch angle of the solar flapping plate and ensure the stable flight attitude of the aircraft in different flight environments, the solar flapping plate aircraft further comprises a pitch angle driving mechanism 6 symmetrically arranged at the tail part of the frame 1, and the pitch angle driving mechanism comprises: the pitch angle driving motor is horizontally arranged at the tail of the support, the end part of an output shaft of the pitch angle driving motor is fixedly connected with the axis of the second turntable 61, one end of the second driving pull rod 62 is hinged with the second turntable 61 at a position far away from the axis, and the other end of the second driving pull rod 62 is hinged with one side of the vertical connecting plate 52; wherein, the both sides of frame 1 all articulate there is movable support 5, and movable support 5 includes: the driving motor is horizontally arranged in the motor mounting seat 51, the vertical connecting plate 52 is fixedly connected with the motor mounting seat 51, the bottom end of the vertical connecting plate is hinged with a side plate of the frame 1, and the top end of the vertical connecting plate is rotatably connected with the end part of the folding solar battery flapping plate 2; the motor mounting seat 51 and the vertical connecting plate 52 are driven to rotate together by pushing and pulling the second driving pull rod through the pitch angle driving motor, so that the whole motion of the flapping wing plate driving mechanism is achieved, and the normal flapping of the folding solar battery flapping wing plate 2 cannot be influenced when the pitch angle of the folding solar flapping wing plate 2 is adjusted.
In a specific embodiment, the flapping wing plate protection mechanism 7 is symmetrically arranged at the front part of the frame 1, and the flapping wing plate protection mechanism 7 comprises: a flapping wing shield 71, a third turntable 72, a shield driving motor and a third driving pull rod 73; the front part of the frame 1 is provided with a vertical support plate 11, the height of the vertical support plate 11 is greater than that of the vertical connecting plate 52, so that the flapping wing protective cover 71 can cover the upper position of the folded flapping wing plate to play a protective role, the end part of one side of the flapping wing protective cover 71 is hinged with the vertical support plate to realize the rotation in the horizontal direction, the protective cover driving motor is vertically arranged at the front part of the frame 1, and the end part of an output shaft of the protective cover driving motor is positioned at the top and is fixedly connected with the axis of the third rotary disc; one end of a third driving pull rod 73 is hinged with the third rotary disc 72 at a position far away from the axis, and the other end is hinged with one side edge of the flapping wing protective cover 71; the third turntable 72 is driven to rotate by the shield driving motor, so that the third driving pull rod 73 is pushed and pulled, the flapping wing shield 71 horizontally rotates, and the folding solar cell flapping plate 2 is covered and separated.
Specifically, the folding solar cell flap plate 2 includes: a first solar flapping wing plate 21, a second solar flapping wing plate 22 and a third solar flapping wing plate 23; one end of the first solar flapping wing plate 21 is provided with a connecting hole, the top end of the vertical connecting plate 52 is provided with a mounting hole corresponding to the connecting hole, the mounting hole and the connecting hole are sequentially penetrated through by a pin shaft, and the first solar flapping wing plate 21 is rotatably connected with the vertical connecting plate 52; the second solar flapping wing plate 22 is movably connected with the first solar flapping wing plate 21 through a limiting pin pair mechanism 8, an electric telescopic rod is installed on the outer side of the first solar flapping wing plate 21, and the driving end of the electric telescopic rod 24 is pivoted with the end part of the second solar flapping wing plate 22 connected at the same side; the third solar flapping wing plate 23 is movably connected with the second solar flapping wing plate 22 through a limiting pin pair mechanism 8, an electric telescopic rod 24 is installed on the other side of the second solar flapping wing plate 22, the electric telescopic rod 24 is ANT-35 in type, and the driving end of the electric telescopic rod is pivoted with the end part of the third solar flapping wing plate 23 connected on the same side.
Advantageously, in order to facilitate the driving motor to drive the foldable solar cell flapping plate 2 to flap through the first driving pull rod, a horizontal connecting plate 211 extends from the connecting end of the first solar flapping plate 21 and the vertical connecting plate 52, and the horizontal connecting plate 211 is hinged to the first driving pull rod 4.
In one particular embodiment, as shown in fig. 6-8, the spacing pin pair mechanism 8 includes: a flapping wing plate rotating position cover plate 81, a lower flapping wing plate rotating shaft cylinder 82 and an air inlet; the flapping wing plate rotating position cover plate 81 is fixedly connected with the second solar flapping wing plate 22 or the third solar flapping wing plate 23, and the bottom of the flapping wing plate rotating position cover plate 81 is connected with an inflation cavity 83 in a sliding manner; the lower flapping wing plate rotating shaft cylinder 82 is of an integrated connecting structure, the lower flapping wing plate rotating shaft cylinder 82 and the flapping wing plate rotating position cover plate 81 are of an integrated connecting structure, and the lower flapping wing plate rotating shaft cylinder 82 is sleeved on the outer wall of the inflation cavity 83 and is in sliding connection with the inflation cavity; the outer wall of the inflation cavity 83 is fixedly connected with the first solar flapping wing plate 21 or the second solar flapping wing plate 22; the air inlet is arranged at the bottom of the lower flapping wing plate rotating shaft cylinder 82 and is communicated with the lower flapping wing plate rotating shaft cylinder 82 and the inflation cavity 83; the third solar flapping wing panel 23 can slide up and down on the second solar flapping wing panel 22 or the second solar flapping wing panel 22 can slide up and down on the first solar flapping wing panel 21 by inflating and deflating the inflation cavity 83.
Advantageously, a small air pump 12 is arranged at the front part of the frame 1, the model of which is JYB-C008-9, and the air pump 12 is connected with the inflation cavity 83 through an air pipe 27.
When the second solar flapping wing plate is unfolded, the third solar flapping wing plate can rotate anticlockwise around the two-degree-of-freedom limiting pin pair mechanism based on air pressure driving relative to the second solar flapping wing plate by taking the electric telescopic rod as a driving force, and the second solar flapping wing plate can rotate clockwise around the two-degree-of-freedom limiting pin pair mechanism based on air pressure driving relative to the first solar flapping wing plate by taking the electric telescopic rod as a driving force; the three solar flapping wing plates are respectively arranged on three planes in the rotating process, when two adjacent solar flapping wing plates rotate to the positions below the solar flapping wing plates without barriers, the external air pump can pump air in the inflation cavity out through the inflation inlet, in the process of pumping the air out, the solar flapping wing plates can slide to the bottom end under the action of self gravity, at the moment, the three solar flapping wing plates are arranged in the same plane, then, the electric telescopic rod extends until no gap exists between the two adjacent solar flapping wing plates, and the three solar flapping wing plates finish the unfolding process.
The limit pin pair mechanism adopted by the invention can greatly improve the folding area proportion of the folded solar flapping wing plate, and the conventional rotating pair has the characteristic that the conventional rotating pair can only move in one plane, and the mechanism is applied to the folding solar flapping wing plate of the aircraft, so that the condition that three solar flapping wing plates are not in the same plane when the folding solar flapping wing plate is unfolded can be caused, the flight performance of the aircraft is influenced, and even the flight function of the aircraft can be lost.
More advantageously, a complementary electromagnetic contraposition connecting slot is arranged between two adjacent solar flapping wing panels, and comprises two convex sockets 25 and two concave mooring ports 26, the concave mooring ports 26 are made of metal materials and have good magnetic and electric conductivity, the convex sockets 25 are matched with the concave mooring ports 26, the controllable electromagnet is arranged in the convex jack 25 and can attract the concave port 26 mutually, the aircraft is powered by a self-contained power supply, the rear part of the frame 1 is provided with a small-sized power supply 9, the model can be selected from a DLP-24vl power supply, the charging is carried out during the operation until the charging is enough to ensure that the looseness or the sliding phenomenon cannot be generated between the two solar flap plates, the safe and stable performance of the aircraft during the operation is ensured, the unfolded positions of the two flapping wing plates are fixed, the relative position of the adjacent solar flapping wing plates after unfolding can be fixed, the volume of the flapping wing can be saved, and the mass of the flapping wing is greatly reduced.
As shown in fig. 9-10, the air pipe 27 and the cable direction of the power of the driving mechanism are provided at the back of the solar flapping wing panel when the solar flapping wing panel is unfolded and folded, the cable is made of soft material and can be folded along with the solar flapping wing panel without affecting the folding process of the solar flapping wing panel, and the power line and the signal control line of the electric telescopic rods are respectively contained in the driving cables 28 of the two electric telescopic rods to respectively drive the two electric telescopic rods 24.
The two limit pin pair mechanisms 8 are powered by a small-sized air pump carried by the aircraft, and an air pipe 27 for air supply is made of soft materials and can be folded along with the solar flapping wing plate and hidden below the flapping wing plate.
The invention is composed of a solar cell panel in a flapping wing shape, a complementary electromagnetic alignment anti-loosening clamping groove and a wing-like sheath flapping wing protective cover, combines the characteristics that the back wing of a sheath wing type insect can be hidden under the sheath wing to be protected by folding, and the solar cell panel is arranged on a small aircraft to be continued for a long time, and is matched with a two-degree-of-freedom limiting pin pair mechanism and an electric telescopic rod based on air pressure driving.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (9)

1. The utility model provides a collapsible aircraft wing of solar energy of imitative sheath wing class insect, its characterized in that includes frame (1) and symmetry and installs the flapping wing board actuating mechanism of frame (1) both sides, flapping wing board actuating mechanism includes:
the foldable solar battery flapping plate (2) is hinged to one side of the rack (1) at the end part of the foldable solar battery flapping plate (2);
a first turntable (3);
the driving motor is fixedly arranged on the rack (1), and the end part of an output shaft of the driving motor is fixedly connected with the axis of the first rotating disc (3);
one end of the first driving pull rod (4) is hinged with the first rotary disc (3) at a position far away from the axis, and the other end of the first driving pull rod is hinged with one end of the folding solar battery flapping plate (2).
2. The coleopteran-like solar foldable aircraft wing according to claim 1, characterized in that a movable support (5) is articulated to both sides of the frame (1), the movable support (5) comprising:
a motor mounting seat (51), wherein the driving motor is horizontally mounted in the motor mounting seat (51);
the vertical connecting plate (52) is fixedly connected with the motor mounting seat (51), the bottom end of the vertical connecting plate is hinged with a side plate of the rack (1), and the top end of the vertical connecting plate is rotatably connected with the end part of the folding solar battery flapping wing plate (2).
3. The coleopteran-like solar foldable aircraft wing according to claim 1, further comprising a pitch angle drive mechanism (6) symmetrically disposed at an aft portion of the airframe (1), the pitch angle drive mechanism (6) comprising:
a second turntable (61);
the pitch angle driving motor is horizontally arranged at the tail part of the bracket, and the end part of an output shaft of the pitch angle driving motor is fixedly connected with the axis of the second rotating disc (61);
one end of the second driving pull rod (62) is hinged to the second rotating disc (61) at a position far away from the axis, and the other end of the second driving pull rod (62) is hinged to one side of the vertical connecting plate (52).
4. The coleoptera-like solar foldable aircraft wing as claimed in claim 1, further comprising a flapping plate protection mechanism (7) symmetrically disposed at a front portion of the frame (1), the flapping plate protection mechanism (7) comprising:
the flapping wing protective cover (71), wherein a vertical supporting plate (11) is arranged at the front part of the rack (1), and the height of the vertical supporting plate (11) is greater than that of the vertical connecting plate (52); the end part of one side of the flapping wing protective cover (71) is hinged with the vertical supporting plate;
a third turntable (72);
the protective cover driving motor is vertically arranged at the front part of the rack (1), and the end part of an output shaft of the protective cover driving motor is fixedly connected with the axis of the third turntable (72);
one end of the third driving pull rod (73) is hinged with the third rotary disc (72) at a position far away from the axis, and the other end of the third driving pull rod (73) is hinged with one side edge of the flapping wing protective cover (71).
5. The coleopteran-like solar foldable aircraft wing as claimed in claim 1, characterized in that said folding solar cell flapping wing panel (2) comprises:
the solar flapping wing plate comprises a first solar flapping wing plate (21), wherein a connecting hole is formed in one side of the first solar flapping wing plate (21), a mounting hole corresponding to the connecting hole is formed in the top end of a vertical connecting plate (52), and the first solar flapping wing plate (21) is rotatably connected with the vertical connecting plate (52) by sequentially penetrating through the mounting hole and the connecting hole through a pin shaft;
the second solar flapping wing plate (22) is movably connected with the first solar flapping wing plate (21) through a limiting pin pair mechanism (8), an electric telescopic rod (24) is installed on the outer side of the first solar flapping wing plate (21), and the driving end of the electric telescopic rod (24) is pivoted with the end part of the second solar flapping wing plate (22) connected on the same side;
pterygoid lamina (23) is pounced to third solar energy, third solar energy stamp pterygoid lamina (23) with second solar energy stamp pterygoid lamina (22) and pass through the vice mechanism (8) swing joint of spacer pin, the opposite side that pterygoid lamina (22) was pounced to second solar energy is installed electric telescopic handle (24), the drive end of electric telescopic handle (24) with the tip pin joint that pterygoid lamina (23) homonymy is connected is pounced to third solar energy.
6. The coleoptera-like solar foldable aircraft wing as claimed in claim 1, wherein a horizontal connecting plate (211) extends from a connecting end of the first solar flapping wing plate (21) and the vertical connecting plate (52), and the horizontal connecting plate (211) is hinged to the first driving pull rod (4).
7. The coleoptera-like solar foldable aircraft wing according to claim 1, characterized in that said stop pin pair mechanism (8) comprises:
the flapping wing plate rotating position cover plate (81), the flapping wing plate rotating position cover plate (81) is fixedly connected with the second solar flapping wing plate (22) or the third solar flapping wing plate (23), and the bottom of the flapping wing plate rotating position cover plate (81) is connected with an inflation cavity (83) in a sliding mode;
the lower flapping wing plate rotating shaft cylinder (82), the lower flapping wing plate rotating shaft cylinder (82) and the flapping wing plate rotating position cover plate (81) are of an integrated connecting structure, and the lower flapping wing plate rotating shaft cylinder (82) is sleeved on the outer wall of the inflation cavity (83) and is in sliding connection with the inflation cavity; the outer wall of the inflation cavity (83) is fixedly connected with the first solar flapping-wing plate (21) or the second solar flapping-wing plate (22);
the air inlet is arranged at the bottom of the lower flapping wing plate rotating shaft cylinder (82) and is communicated with the lower flapping wing plate rotating shaft cylinder (82) and the inflation cavity (83); the inflation cavity (83) is inflated and deflated through the inflation port, so that the third solar flapping wing plate (23) can slide up and down on the second solar flapping wing plate (22), or the second solar flapping wing plate (22) can slide up and down on the first solar flapping wing plate (21).
8. The coleoptera-like solar foldable aircraft wing of claim 1, wherein a complementary electromagnetic contraposition connecting slot is arranged between two adjacent solar flapping wing plates, and comprises two convex sockets (25) and two concave mooring ports (26), the concave mooring ports (26) are made of metal materials, the convex sockets (25) are matched with the concave mooring ports (26), and controllable electromagnets are arranged in the convex sockets (25).
9. The coleoptera-like solar foldable aircraft wing as claimed in claim 1, characterized in that a small air pump (12) is arranged in front of the frame (1), and the air pump (12) is connected with the inflation port (83) through a pipeline.
CN202010003235.1A 2020-01-02 2020-01-02 Solar foldable aircraft wing imitating coleoptera insects Pending CN111086633A (en)

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4410911A1 (en) * 1994-03-29 1995-11-09 Gilbert Dr Duong Human powered flight device
CN103950538A (en) * 2014-05-06 2014-07-30 中国计量学院 Goose group flapping wing imitation flight system
CN106585980A (en) * 2016-12-07 2017-04-26 郑州轻工业学院 Four-degree of freedom beetle-imitated foldable flapping-wing micro flying robot
CN108528710A (en) * 2018-04-03 2018-09-14 中国空气动力研究与发展中心计算空气动力研究所 A kind of flapping wing matrix aerodynamic configuration of aircraft
WO2018224033A1 (en) * 2017-06-09 2018-12-13 昆明鞘翼科技有限公司 Aircraft with imitation beetle elytron wings
CN211893640U (en) * 2020-01-02 2020-11-10 郑州轻工业大学 Solar foldable aircraft wing imitating coleoptera insects

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4410911A1 (en) * 1994-03-29 1995-11-09 Gilbert Dr Duong Human powered flight device
CN103950538A (en) * 2014-05-06 2014-07-30 中国计量学院 Goose group flapping wing imitation flight system
CN106585980A (en) * 2016-12-07 2017-04-26 郑州轻工业学院 Four-degree of freedom beetle-imitated foldable flapping-wing micro flying robot
WO2018224033A1 (en) * 2017-06-09 2018-12-13 昆明鞘翼科技有限公司 Aircraft with imitation beetle elytron wings
CN108528710A (en) * 2018-04-03 2018-09-14 中国空气动力研究与发展中心计算空气动力研究所 A kind of flapping wing matrix aerodynamic configuration of aircraft
CN211893640U (en) * 2020-01-02 2020-11-10 郑州轻工业大学 Solar foldable aircraft wing imitating coleoptera insects

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