CN107176289A - Aircraft - Google Patents
Aircraft Download PDFInfo
- Publication number
- CN107176289A CN107176289A CN201710375829.3A CN201710375829A CN107176289A CN 107176289 A CN107176289 A CN 107176289A CN 201710375829 A CN201710375829 A CN 201710375829A CN 107176289 A CN107176289 A CN 107176289A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- connecting rod
- rotor
- clamping jaws
- clamping jaw
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000000712 assembly Effects 0.000 claims abstract description 38
- 238000000429 assembly Methods 0.000 claims abstract description 38
- 230000005611 electricity Effects 0.000 claims abstract description 11
- 230000000694 effects Effects 0.000 claims abstract description 9
- 238000001179 sorption measurement Methods 0.000 claims description 11
- 230000033001 locomotion Effects 0.000 claims description 4
- 238000010248 power generation Methods 0.000 claims description 3
- 208000037873 arthrodesis Diseases 0.000 claims description 2
- 238000010521 absorption reaction Methods 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 12
- 238000000034 method Methods 0.000 description 5
- 230000005484 gravity Effects 0.000 description 3
- 238000005265 energy consumption Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000010295 mobile communication Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L8/00—Electric propulsion with power supply from forces of nature, e.g. sun or wind
- B60L8/006—Converting flow of air into electric energy, e.g. by using wind turbines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L2200/00—Type of vehicles
- B60L2200/10—Air crafts
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Power Engineering (AREA)
- Transportation (AREA)
- Clamps And Clips (AREA)
Abstract
The present invention discloses a kind of aircraft, including frame and rack-mounted rotor assemblies, storage assembly and clamp assemblies, rotor assemblies include rotor and electrically connect the motor of rotor, storage assembly electrically connects motor, clamp assemblies are used for gripping rods thing, so that aircraft stops dwelling in the air, rotor motor under wind-force effect generates electricity.The hang time of above-mentioned aircraft is longer.
Description
Technical field
The present invention relates to airborne vehicle technical field, more particularly to a kind of aircraft.
Background technology
Existing electronic rotor craft relies on battery power rotor rotational, so that the free flight in the range of certain space
OK.Because the electricity of the battery of load on aircraft is limited, therefore the endurance of aircraft is poor, so as to cause aircraft
Hang time is short.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of longer aircraft of hang time.
To achieve these goals, embodiment of the present invention is adopted the following technical scheme that：
A kind of aircraft, including frame and rotor assemblies, storage assembly and clamping in the frame are provided
Component, the rotor assemblies include the motor of rotor and the electrical connection rotor, and the storage assembly electrically connects the motor, institute
Stating clamp assemblies is used for gripping rods thing, so that the aircraft stops dwelling in the air, the rotor drives institute under wind-force effect
State electric power generation.
Wherein, the clamp assemblies include connecting rod, clamping jaw support and two clamping jaws, and the connecting rod is arranged on described
In frame, the clamping jaw support includes two ends being oppositely arranged and the middle part being connected between described two ends, described
Middle part is connected to one end of the connecting rod, and described two clamping jaws rotate the described two ends of connection respectively so that described two
Clamping jaw can close up to clamp the shaft or open each other to decontrol the shaft each other.
Wherein, the connecting rod is flexibly connected the frame with relatively described machine frame movement, and the rotor is flat located at first
Face, the free cheek of described two clamping jaws forms angle parallel to first plane or between first plane, described
Angle is less than or equal to 45 °.
Wherein, the aircraft also includes the moving assembly located at the frame, and the moving assembly includes gear and use
In the motor for driving the gear, the outside of the gear has the first teeth portion, and the outer wall of the connecting rod is provided with the second teeth portion,
Second teeth portion is meshed with first teeth portion.
Wherein, one end of the remote clamping jaw support of the connecting rod is provided with limited block, and the limited block is used to prevent
The connecting rod departs from the frame.
Wherein, the aircraft also includes undercarriage, and the undercarriage is fixed on the frame, and the undercarriage is V-shaped.
Wherein, each clamping jaw include the bare terminal end and movable end being oppositely arranged and be connected to the bare terminal end with
Linkage section between the movable end, the linkage section rotates the connection clamping jaw support, and the movable end is close to the clamping jaw
Support, the bare terminal end is away from the clamping jaw support；
Two movable ends away from each other when, two bare terminal ends are close to each other, and described two clamping jaws close up each other；
Two bare terminal ends away from each other when, two movable ends are close to each other, and described two clamping jaws open each other.
Wherein, the clamp assemblies also include two positioning components, and described two positioning components are connected to correspondingly
Between described two clamping jaws and described two ends；
Each positioning component includes joint, projection and elastic component, and the arthrodesis is in the corresponding end
On, the joint has spaced first groove and the second groove and is connected to first groove and described second recessed
Arcwall face between groove, the projection is set in the linkage section periphery and by being connected described in the elastic component elastic connection
Section；
When the projection is caught in first groove, described two clamping jaws close up each other, and the projection is caught in described second
During groove, described two clamping jaws open each other, and the projection shifts to the arc from first groove or second groove
During face, the deformation quantity increase of the elastic component.
Wherein, the clamp assemblies also include two adsorption pieces, and described two adsorption pieces are separately fixed at two folders
Hold on end, described two adsorption pieces are close to each other so that two bare terminal ends are adsorbed each other.
Wherein, the clamp assemblies also include the first buckle and the second buckle, and first buckle is fixed on the middle part,
Second buckle is fixed on one end of the connecting rod；
First buckle fastens to be connected the connecting rod and the clamping jaw support, or institute each other with second buckle
The first buckle is stated to separate to disconnect the connecting rod and the clamping jaw support each other with second buckle.
Compared to prior art, the invention has the advantages that：
Aircraft of the present invention can stop dwelling in the air by the clamp assemblies, then by the engine mould of the motor
Formula switches to generator mode, and the rotor is rotated under wind-force effect, so as to drive the electric power generation, the motor is produced
Raw electric energy can be used in charging to the storage assembly, therefore enhance the endurance of the aircraft so that described to fly
The hang time of row device is longer.
Brief description of the drawings
In order to illustrate more clearly of technical scheme, the required accompanying drawing used in embodiment will be made below
Simply introduce, it should be apparent that, drawings in the following description are only the schematic diagram of some embodiments of the present invention, for
For those of ordinary skill in the art, on the premise of not paying creative work, it can also obtain other such as these accompanying drawings
Accompanying drawing.
Fig. 1 is a kind of front view for aircraft that embodiment of the present invention is provided.
Fig. 2 is the top view of aircraft shown in Fig. 1.
Fig. 3 is the left view of aircraft shown in Fig. 1.
Fig. 4 is the use state schematic diagram one of aircraft shown in Fig. 1.
Fig. 5 is the use state schematic diagram two of aircraft shown in Fig. 1.
Fig. 6 is the use state schematic diagram three of aircraft shown in Fig. 1.
Fig. 7 is the use state schematic diagram four of aircraft shown in Fig. 1.
Fig. 8 is the use state schematic diagram five of aircraft shown in Fig. 1.
Fig. 9 is the use state schematic diagram six of aircraft shown in Fig. 1.
Figure 10 is the use state schematic diagram seven of aircraft shown in Fig. 1.
Figure 11 is a kind of dimensional structure diagram of embodiment of aircraft shown in Fig. 1.
Figure 12 is the schematic diagram of the part-structure of aircraft shown in Figure 11.
Figure 13 is the schematic diagram of another use state of structure shown in Figure 12.
Figure 14 is the enlarged drawing of structure at C in Figure 12.
Figure 15 is the enlarged drawing of structure at D in Figure 12.
Figure 16 is the enlarged drawing of structure at E in Figure 13.
Figure 17 is the enlarged drawing of structure at F in Figure 12.
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
In addition, the explanation of following embodiment is with reference to additional diagram, the spy implemented to illustrate the present invention can be used to
Determine embodiment.The direction term being previously mentioned in the present invention, for example, " on ", " under ", "front", "rear", "left", "right", " interior ",
" outer ", " side " etc., are only the directions with reference to annexed drawings, therefore, and the direction term used is to more preferably, more clearly say
It is bright and understand the present invention, rather than indicate or infer the device or element of meaning and must have specific orientation, with specific side
Position construction and operation, therefore be not considered as limiting the invention.
In the description of the invention, it is necessary to illustrate, unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection ", " on being arranged on ... " should be interpreted broadly, for example, it may be being fixedly connected or removably connecting
Connect, or be integrally connected；Can mechanically connect；Can be joined directly together, can also be indirectly connected to by intermediary, can
To be the connection of two element internals.For the ordinary skill in the art, above-mentioned term can be understood with concrete condition
Concrete meaning in the present invention.
In addition, in the description of the invention, unless otherwise indicated, " multiple " are meant that two or more.If this
Occur the term of " process " in specification, it refers not only to independent process, when can not clearly be distinguished with other processes, as long as
It can realize that the effect desired by the process is then also included within this term.In addition, the numerical value model represented in this specification with "~"
Enclose the scope for referring to that the numerical value recorded before and after "~" is included as minimum value and maximum.In the accompanying drawings, structure
Similar or identical unit is indicated by the same numeral.
Also referring to Fig. 1 to Figure 10, the embodiment of the present invention provides a kind of aircraft 100, including frame 1 and installed in institute
State rotor assemblies 2, storage assembly 3 and the clamp assemblies 4 in frame 1.The rotor assemblies 2 include rotor 21 and electrical connection institute
State the motor 22 of rotor 21.The storage assembly 3 electrically connects the motor 22.The clamp assemblies 4 are used for gripping rods thing 5,
So that the aircraft 100 stops dwelling in the air, the rotor 21 drives the motor 22 to generate electricity under wind-force effect.
Specifically, the motor 22 has electric motor mode and engine mode both mode of operations.The flight
When device 100 is in state of flight, the motor 22 drives the rotor 21 to rotate to produce lift in a motor mode, described
Motor 22 obtains electric energy at the storage assembly 3.The aircraft 100 be in stop dwelling state when, the clamp assemblies 4 pass through
Clamp the shaft 5 to fix the aircraft 100 in the air, the rotor 21 driving under wind-force effect is in generator
The motor 22 of pattern generates electricity, and the electric energy produced by the motor 22 is stored in the storage assembly 3.
In the present embodiment, the aircraft 100 can be stopped dwelling in the air by the clamp assemblies 4, then by the electricity
The engine mode of machine 22 switches to generator mode, and the rotor 21 is rotated under wind-force effect, so as to drive the motor
22 generate electricity, and the electric energy produced by the motor 22 can be used in charging to the storage assembly 3, therefore enhance the aircraft
100 endurance so that the hang time of the aircraft 100 is longer.
It should be understood that because the aircraft 100 can stop to dwell in the air, therefore the aircraft 100 can store described
During 3 not enough power supply of electrical component, directly select the suitable shaft 5 and be fixed, the motor 22 is then switched into hair
Motor mode, to be charged in the air to the storage assembly 3, after the electricity of the storage assembly 3 is enough, by the electricity
Machine 22 switches to electric motor mode, continues directly to fly in the air.So, the aircraft 100, which need not land, to be charged, institute
Stating aircraft 100 can be constantly in the air, further increase the hang time of the aircraft 100.The shaft 5 can be with
It is electric pole, trunk or light pole etc.." the stopping dwelling in the air " refers to there is a spacing between the aircraft 100 and ground
From so that the aircraft 100 is in the stronger environment of wind-force.
In one embodiment, the electric energy produced by the motor 22 aircraft 100 can be loaded simultaneously
Additional functional device (such as photographing module, communication module) is powered so that the aircraft 100 can be in the state of dwelling be stopped
Also can continuous firing.In a variety of environment, the beneficial effect of the continuous firing ability of the aircraft 100 is particularly evident：For example
When rescue and relief work, it is possible to use the aircraft 100 stop the state of dwelling to surrounding environment carry out real-time video transmission and
The function of mobile communication base station；In the wild when operation, it is possible to use the stopping of the aircraft 100 state of dwelling carries out meteorology and surveyed
Survey, wind-force monitoring or electric power overhaul etc.；In valley, desert etc., the remote electric power that lacks is regional, and multiple flights can be utilized simultaneously
Device 100, by clustered control technology, realizes that cluster generates electricity, so as to be built into a small-sized wind power station, realizes small range
Power supply.
Optionally, the quantity of the rotor 21 and the quantity of the motor 22 be it is multiple, multiple rotors 21 with it is many
The individual motor 22, which is corresponded, to be set so that the corresponding rotor 21 can be operated alone in each motor 22.Example
Such as, the quantity of the rotor 21 is four, and four rotors 21 are substantially arranged in decussation.Multiple motors 22 are equal
It is electrically connected to the storage assembly 3.The motor 22 can use permanent magnetic brushless, and input and output use direct current electrically.Institute
Rotor 21 is stated located at the first plane A, namely multiple rotors 21 may be contained within the first plane A, the rotor 21 goes out
Wind direction is approximately perpendicular to the first plane A.
Optionally, the frame 1 includes machine box 11 and is fixed on the support frame 12 of the top surrounding of machine box 11.The rotation
Wing component 2 is fixed on support frame as described above 12.The storage assembly 3 is in the machine box 11.The clamp assemblies 4 are arranged on institute
State on machine box 11 and positioned at the lower section of support frame as described above 12.The storage assembly 3 includes battery.
Optionally, support frame as described above 12 is provided with multiple flow channels 121, and multiple rotors 21 are located at institute correspondingly
State in multiple flow channels 121, the axis direction of the flow channel 121 is perpendicular to the first plane A, so as to more preferable
Ground utilizes wind energy, reduces the energy consumption of the aircraft 100, further extends the hang time of the aircraft 100.
As a kind of alternative embodiment, also referring to Fig. 1 to Figure 13, the clamp assemblies 4 include connecting rod 41, clamping jaw
Support 42 and two clamping jaws 43.The connecting rod 41 is arranged on the machine box 11 of the frame 1.The clamping jaw support 42
Including two ends 421 being oppositely arranged and the middle part 422 being connected between described two ends 421.The middle part 422 is connected
To one end of the connecting rod 41.Described two clamping jaws 43 rotate the described two ends 421 of connection respectively so that described two folders
Pawl 43 can close up to clamp the shaft 5 or open each other to decontrol the shaft 5 each other.
Optionally, when described two clamping jaws 43 close up each other, described two clamping jaws 43 enclose jointly with the clamping jaw support 42
It is set as loop configuration.The loop configuration and the cross-section profile shape of the shaft 5 are adapted, so that the clamping jaw branch
Frame 42 can coordinate described two clamping jaws 43 to clamp the shaft 5 jointly.For example, when the shaft 5 is electric pole, it is described
The cross section profile of shaft 5 is generally circular, then the loop configuration substantially annular.
It should be appreciated that Fig. 1 and Fig. 3 are into Figure 10, for convenience of illustrating, by the clamping jaw support 42 and described two folders
Pawl 43 is simplifiedly drawn together.
As a kind of alternative embodiment, also referring to Fig. 1 to Figure 14, the connecting rod 41 is flexibly connected the frame 1
To be moved relative to the frame 1.As shown in Fig. 2 and Figure 12, the connecting rod 41 passes through the machine box 11 and can relatively described machine
Box 11 moves back and forth.The free cheek B of described two clamping jaws 43 parallel to the first plane A or with the first plane A it
Between form angle, the angle is less than or equal to 45 °.The free cheek B of described two clamping jaws 43 refers to that described two clamping jaws 43 are received
Hold together and the movement locus that opens where plane.
In the present embodiment, because the connecting rod 41 can be moved relative to the frame 1, therefore the aircraft 100 exists
In normal flight, the collapsible connecting rod 41 (as shown in Fig. 4 and Figure 10) so that the clamping jaw support 42 and described two folders
Pawl 43 is closer to the center of the frame 1, and the center of gravity of the clamp assemblies 4 is conducive to described closer to the center of the frame 1
The smooth flight of aircraft 100 and steadily park.The aircraft 100 is when needing to clamp the shaft 5, the extending company
Extension bar 41 (as shown in Figure 5) so that the clamping jaw support 42 and described two clamping jaws 43 are relatively distant from the center of the frame 1,
Described two clamping jaws 43 are as far as possible away from the rotor 21 (for example, orthographic projection of the described two clamping jaws 43 on the first plane A
Stagger the rotor 21) so that described two clamping jaws 43 can be avoided by the rotor during the shaft 5 is clamped
21 interference, the clamp assemblies 4 can smoothly clamp the shaft 5.Because the free cheek B of described two clamping jaws 43 is parallel
Formed in the first plane A or between the first plane A less than or equal to 45 ° of the angle, therefore the aircraft
100 is low with the flare maneuver difficulty for facilitating the clamp assemblies 4 to be clamped close to the shaft 5 of general vertical, described
Aircraft 100 can be slightly tilted or be flown substantially in parallel, now the first plane A be roughly parallel to horizontal plane or with
Horizontal plane one smaller angle (being, for example, less than equal to 45 °) of formation.
Specifically, the aircraft 100 also includes the moving assembly 6 in the machine box 11 of the frame 1.Institute
Stating moving assembly 6 includes gear 61 and the motor 62 for driving the gear 61.The gear 61 can be consolidated with the motor 62
It is scheduled on the bottom of the machine box 11.The motor 62 electrically connects the storage assembly 3.The outside of the gear 61 has the first tooth
Portion 611, the outer wall of the connecting rod 41 is provided with the second teeth portion 411, and second teeth portion 411 is mutually nibbled with first teeth portion 611
Close.Powered in use, the storage assembly 3 is the motor 62, the motor 62 drives the gear 61 to rotate, described first
Teeth portion 611, which is rotated, drives second teeth portion 411 to move, so that the connecting rod 41 is moved relative to the frame 1.
Optionally, one end of the remote clamping jaw support 42 of the connecting rod 41 is provided with limited block 412, the limited block
412 are used to prevent the connecting rod 41 from departing from the frame 1.Now, the two ends of the connecting rod 41 are each provided at the machine box 11
It is outside.
Optionally, the aircraft 100 also includes undercarriage 7, and the undercarriage 7 is fixed on the frame 1.It is described to rise and fall
Frame 7 can substantially v-shaped or double V-arrangements, preferably to aid in the aircraft 100 to be fixed on the shaft 5.The undercarriage
7 can be symmetrical arranged.
When the aircraft 100 is fallen in plane (such as ground), the undercarriage 7 is used to support the aircraft 100.
Now the aircraft 100 shrinks the connecting rod 41 so that the clamping jaw support 42 and described two clamping jaws 43 are closer to institute
The center of frame 1 is stated, the center of gravity of the clamp assemblies 4 is conducive to the aircraft 100 flat closer to the center of the frame 1
Surely park.
Fig. 4 to Fig. 7 shows how the aircraft 100 switches to from state of flight and stops the state of dwelling, and Fig. 8 to Figure 10 is shown
How the aircraft 100 switches to state of flight from stopping the state of dwelling.
Specifically：As shown in figure 4, the aircraft 100 of state of flight is it is determined that be adapted to the shaft 5 for stopping dwelling
Position after, by the moving assembly 6 by the clamping jaw support 42 and described two clamping jaws 43 to the right (towards described shaft-like
The direction of thing 5) release, the flight while aircraft 100 is tilted to the right.As shown in figure 5, the aircraft 100 is close to described
Shaft 5.As shown in fig. 6, described two clamping jaws 43 of the aircraft 100 clamp the shaft 5.As shown in fig. 7, turning off
The motor 22, makes the center of frame 1 because the self gravitation of aircraft 100 is fallen down, the rotor 21 with it is described shaft-like
Form angle between thing 5, described two clamping jaws 43 and the inclination contact of shaft 5, described two clamping jaws 43 with it is described shaft-like
Frictional force between thing 5 can overcome the gravity of itself of aircraft 100, so as to prevent the aircraft 100 from continuing to fall.
Now, the aircraft 100 has larger front face area.Furthermore, the undercarriage 7 of V-shaped or double V-arrangements can block well
On the shaft 5, so as to provide certain frictional force and fixation so that the aircraft 100 will not be rocked, strengthen
Stop the stability dwelt.The aircraft 100 stops after dwelling stably, and the aircraft 100, which is switched to, stops the state of dwelling, the rotor 21
The motor 22 of the driving in generator mode generates electricity under wind-force effect, and the electric energy deposit produced by the motor 22 is described
The storage assembly 3 and additional functional device loaded by the aircraft 100 is powered.
As shown in figure 8, the aircraft 100 switches to state of flight after charge requirement is completed, the motor 22 drives
The rotor 21 is rotated to produce to upper left lift, because described two clamping jaws 43 are also clamped on the shaft 5, because
This described center of frame 1 can slowly rise.As shown in figure 9, the aircraft 100 substantially fly to it is (now described during horizontal level
First plane A is roughly parallel to horizontal plane or small angle is formed between horizontal plane), described motor 22 drives the rotor 21
Rotate so that the aircraft 100 flies to the left.As shown in Figure 10, described two clamping jaws 43 depart from the shaft 5, then
The clamping jaw support 42 and described two clamping jaws 43 are recovered to by stable home position by the moving assembly 6, it is described to fly
The smooth flight of row device 100.
It should be understood that aircraft 100 described in the present embodiment also includes controller, the controller is located at the machine box 11
It is interior.The controller electrically connects multiple motors 22, by controlling the multiple motor 22 so as to control multiple rotors
21 rotating speed.For example, the controller can control multiple rotors 21 according to different rotational speeds, so as to control described fly
The heading of row device 100 and angle of inclination etc..As shown in Fig. 4 to Figure 10, the different arrows of the top of rotor 21
Size substantially illustrates the rotating speed size of the corresponding different rotor 21, and the larger then rotating speed of arrow is higher, and arrow is smaller
Then rotating speed is relatively low.
As a kind of alternative embodiment, also referring to Figure 11 to Figure 15, each clamping jaw 43 includes being oppositely arranged
Bare terminal end 431 and movable end 432 and the linkage section 433 that is connected between the bare terminal end 431 and the movable end 432.
The linkage section 433 rotates the connection clamping jaw support 42, and the movable end 432 is close to the clamping jaw support 42, the clamping
End 431 is away from the clamping jaw support 42.Two movable ends 432 away from each other when, two bare terminal ends 431 are leaned on each other
Closely, described two clamping jaws 43 close up each other.Two bare terminal ends 431 away from each other when, two movable ends 432 are leaned on each other
Closely, described two clamping jaws 43 open each other.
Optionally, the clamp assemblies 4 also include two positioning components 44, and described two positioning components 44 are correspondingly
Be connected between described two clamping jaws 43 and described two ends 421, to position and keep described two clamping jaws 43 with it is described
Relative position between clamping jaw support 42.
For example, each positioning component 44 includes joint 441, projection 442 and elastic component 443.The joint
441 are fixed on the corresponding end 421.The joint 441 has the spaced groove of first groove 4411 and second
4412 and the arcwall face 4413 that is connected between first groove 4411 and second groove 4412.The projection 442
It is set in the periphery of linkage section 433 and by linkage section 433 described in the elastic connection of elastic component 443.The elastic component 443
Deformation quantity when changing, the projection 442 is moved relative to the linkage section 433.The elastic component 443 is in by compression shape
State, the projection 442 is pressed on the joint 441.
When the projection 442 is caught in first groove 4411, described two clamping jaws 43 close up each other.The elastic component
443 are pressed on the projection 442 in first groove 4411 so that described two clamping jaws 43 can keep what is closed up each other
State, so as to keep the state for clamping the shaft 5, the aircraft 100 can be smoothly fixed on the shaft 5
Stop the state of dwelling to realize.When the projection 442 is caught in second groove 4412, described two clamping jaws 43 open each other.It is described
The projection 442 is pressed in second groove 4412 by elastic component 443 so that described two clamping jaws 43 can be kept each other
The state opened, so that aircraft 100 can smoothly leave the shaft 5 to enter state of flight.The projection 442 is certainly
When first groove 4411 or second groove 4412 shift to the arcwall face 4413, the deformation quantity of the elastic component 443
Increase.When the projection 442 contacts the arcwall face 4413, the aircraft 100 is in state of flight and stops cutting between the state of dwelling
Change.
The projection 442 can be bumping square, triangle convex, round bump or semicircle projection etc..The elastic component 443
It can be spring.
Optionally, the clamp assemblies 4 also include two adsorption pieces, and described two adsorption pieces are separately fixed at described in two
On bare terminal end 431.Described two adsorption pieces are close to each other so that two bare terminal ends 431 are adsorbed each other, described in increasing
Aircraft 100 is fixed on the reliability on the shaft 5, reduces the wind that the aircraft 100 undesirably falls off the shaft 5
Danger.Described two adsorption pieces can be magnet.
The clamp assemblies 4 close to and during being fixed on the shaft 5, the shaft 5 is introduced into described
Between two clamping jaws 43, then the shaft 5 touches two movable ends 432 and promotes two movable ends 432, makes
Obtain two movable ends 432 away from each other, two bare terminal ends 431 are close to each other, and described two clamping jaws 43 close up each other.
During this, the projection 442 is moved to first groove 4411 from second groove 4412 by the cambered surface, described
Projection 442 is stuck in first groove 4411, so that the position of fixed described two clamping jaws 43, described two clamping jaws 43 are kept
The aircraft 100 can be fixed on the shaft 5 by the state after closing up, described two clamping jaws 43.Now, described two
Individual adsorption piece adsorbs to increase the stability that the aircraft 100 is fixed on the shaft 5 each other.
During the clamp assemblies 4 depart from the shaft 5, the clamp assemblies 4 are produced by the rotor 21
Raw power is pulled, and two bare terminal ends 431 are opened on the top of shaft 5, make two bare terminal ends 431 away from each other, and two
The individual movable end 432 is close to each other, and described two clamping jaws 43 open each other.During this, the projection 442 is from described first
Groove 4411 is stuck in second groove 4412 by the second groove 4412 described in cambered surface movement, the projection 442,
So as to the position of fixed described two clamping jaws 43, described two clamping jaws 43 keep the state after opening, and the aircraft 100 departs from
The shaft 5.
As a kind of alternative embodiment, also referring to Figure 12 and Figure 17, the clamp assemblies 4 also include the first buckle 91
With the second buckle 92.First buckle 91 is fixed on the middle part 422, and second buckle 92 is fixed on the connecting rod 41
One end.First buckle 91 fastens to be connected the connecting rod 41 and the clamping jaw support each other with second buckle 92
42.Or first buckle 91 separates to disconnect the connecting rod 41 and the clamping jaw support each other with second buckle 92
42。
In the present embodiment, the clamping jaw support 42 is detachably connected the connecting rod 41, then the aircraft 100 is just
Often in-flight, the clamping jaw support 42 and described two clamping jaws 43 can also be pulled down, so as to reduce the entirety of the aircraft 100
Weight, reduces the energy consumption of the aircraft 100, extends the hang time of the aircraft 100.Then, in the aircraft 100
When not enough power supply needs charging, then the clamping jaw support 42 and described two clamping jaws 43 are loaded onto, so that the aircraft
100 can stop to dwell is charged in the air.
Embodiment of the present invention is described in detail above, principle of the specific case used herein to the present invention
And embodiment is set forth, the explanation of embodiment of above is only intended to help the method and its core that understand the present invention to think
Think；Simultaneously for those of ordinary skill in the art, according to the thought of the present invention, in specific embodiments and applications
It will change, in summary, this specification content should not be construed as limiting the invention.
Claims (10)
1. a kind of aircraft, it is characterised in that rotor assemblies, storage assembly including frame and in the frame and
Clamp assemblies, the rotor assemblies include the motor of rotor and the electrical connection rotor, and the storage assembly electrically connects the electricity
Machine, the clamp assemblies are used for gripping rods thing, so that the aircraft stops dwelling in the air, the rotor drives under wind-force effect
Move the electric power generation.
2. aircraft as claimed in claim 1, it is characterised in that the clamp assemblies include connecting rod, clamping jaw support and
Two clamping jaws, the connecting rod is arranged in the frame, and the clamping jaw support includes two ends and the connection being oppositely arranged
Middle part between described two ends, the middle part is connected to one end of the connecting rod, and described two clamping jaws are rotated respectively
Connect described two ends so that described two clamping jaws can close up to clamp the shaft or open each other to decontrol each other
The shaft.
3. aircraft as claimed in claim 2, it is characterised in that the connecting rod is flexibly connected the frame with relatively described
Machine frame movement, the rotor is located at the first plane, the free cheeks of described two clamping jaws parallel to first plane or with institute
State and angle is formed between the first plane, the angle is less than or equal to 45 °.
4. aircraft as claimed in claim 3, it is characterised in that the aircraft also includes mobile group located at the frame
Part, the moving assembly includes gear and the motor for driving the gear, and the outside of the gear has the first teeth portion, institute
The outer wall for stating connecting rod is provided with the second teeth portion, and second teeth portion is meshed with first teeth portion.
5. aircraft as claimed in claim 4, it is characterised in that one end of the remote clamping jaw support of the connecting rod is set
Limited location block, the limited block is used to prevent the connecting rod from departing from the frame.
6. the aircraft as described in any one of claim 2~5, it is characterised in that the aircraft also includes undercarriage, described
Undercarriage is fixed on the frame, and the undercarriage is V-shaped.
7. the aircraft as described in any one of claim 2~5, it is characterised in that each clamping jaw includes being oppositely arranged
Bare terminal end and movable end and the linkage section that is connected between the bare terminal end and the movable end, the linkage section, which is rotated, to be connected
The clamping jaw support is connect, the movable end is close to the clamping jaw support, and the bare terminal end is away from the clamping jaw support；
Two movable ends away from each other when, two bare terminal ends are close to each other, and described two clamping jaws close up each other；Two
The bare terminal end away from each other when, two movable ends are close to each other, and described two clamping jaws open each other.
8. aircraft as claimed in claim 7, it is characterised in that the clamp assemblies also include two positioning components, described
Two positioning components are connected between described two clamping jaws and described two ends correspondingly；
Each positioning component includes joint, projection and elastic component, and the arthrodesis is on the corresponding end, institute
State joint there is spaced first groove and the second groove and be connected to first groove and second groove it
Between arcwall face, the projection is set in the linkage section periphery and by linkage section described in the elastic component elastic connection；
When the projection is caught in first groove, described two clamping jaws close up each other, and the projection is caught in second groove
When, described two clamping jaws open each other, the projection from first groove or second groove shift to the arcwall face when,
The deformation quantity increase of the elastic component.
9. aircraft as claimed in claim 8, it is characterised in that the clamp assemblies also include two adsorption pieces, described two
Individual adsorption piece is separately fixed on two bare terminal ends, described two adsorption pieces it is close to each other so that two bare terminal ends that
This absorption.
10. the aircraft as described in any one of claim 2~5, it is characterised in that the clamp assemblies also include the first buckle
With the second buckle, first buckle is fixed on the middle part, and second buckle is fixed on one end of the connecting rod；
First buckle fastens to be connected the connecting rod and the clamping jaw support, or described each other with second buckle
One buckle separates to disconnect the connecting rod and the clamping jaw support each other with second buckle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710375829.3A CN107176289B (en) | 2017-05-24 | 2017-05-24 | Aircraft with a flight control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710375829.3A CN107176289B (en) | 2017-05-24 | 2017-05-24 | Aircraft with a flight control device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107176289A true CN107176289A (en) | 2017-09-19 |
| CN107176289B CN107176289B (en) | 2023-04-18 |
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ID=59832789
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710375829.3A Active CN107176289B (en) | 2017-05-24 | 2017-05-24 | Aircraft with a flight control device |
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| Country | Link |
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| CN (1) | CN107176289B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112710243A (en) * | 2020-12-16 | 2021-04-27 | 贵州电网有限责任公司 | Weather-proof steel tower corrosion-resistant layer monitoring unmanned aerial vehicle locking device |
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| US20100308174A1 (en) * | 2009-06-03 | 2010-12-09 | Grant Calverley | Rotocraft power-generation, control apparatus and method |
| EP2292471A1 (en) * | 2009-09-02 | 2011-03-09 | WESTFALIA - Automotive GmbH | Attachment device with a clamp |
| CN105539829A (en) * | 2015-12-24 | 2016-05-04 | 刘海涛 | Multi-rotor craft |
| CN205524988U (en) * | 2016-02-16 | 2016-08-31 | 张博文 | Aircraft frame |
| CN105923152A (en) * | 2016-05-20 | 2016-09-07 | 苏跃进 | Captive flight system and captive flight vehicle thereof |
| CN106655400A (en) * | 2017-01-16 | 2017-05-10 | 北京交通大学 | Charging pile used for multi-rotary-wing unmanned aerial vehicle |
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2017
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100308174A1 (en) * | 2009-06-03 | 2010-12-09 | Grant Calverley | Rotocraft power-generation, control apparatus and method |
| EP2292471A1 (en) * | 2009-09-02 | 2011-03-09 | WESTFALIA - Automotive GmbH | Attachment device with a clamp |
| CN105539829A (en) * | 2015-12-24 | 2016-05-04 | 刘海涛 | Multi-rotor craft |
| CN205524988U (en) * | 2016-02-16 | 2016-08-31 | 张博文 | Aircraft frame |
| CN105923152A (en) * | 2016-05-20 | 2016-09-07 | 苏跃进 | Captive flight system and captive flight vehicle thereof |
| CN106655400A (en) * | 2017-01-16 | 2017-05-10 | 北京交通大学 | Charging pile used for multi-rotary-wing unmanned aerial vehicle |
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| CN112710243A (en) * | 2020-12-16 | 2021-04-27 | 贵州电网有限责任公司 | Weather-proof steel tower corrosion-resistant layer monitoring unmanned aerial vehicle locking device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107176289B (en) | 2023-04-18 |
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