CN107499503A - Small-sized pilotless aircraft - Google Patents
Small-sized pilotless aircraft Download PDFInfo
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- CN107499503A CN107499503A CN201710854483.5A CN201710854483A CN107499503A CN 107499503 A CN107499503 A CN 107499503A CN 201710854483 A CN201710854483 A CN 201710854483A CN 107499503 A CN107499503 A CN 107499503A
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- small
- lower house
- pilotless aircraft
- upper shell
- propeller
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- 230000037431 insertion Effects 0.000 claims abstract description 7
- 238000009434 installation Methods 0.000 claims description 20
- 238000013016 damping Methods 0.000 claims description 8
- 229910000838 Al alloy Inorganic materials 0.000 claims description 5
- 230000005611 electricity Effects 0.000 claims description 3
- 239000003292 glue Substances 0.000 claims 1
- 230000000149 penetrating effect Effects 0.000 claims 1
- 210000002683 foot Anatomy 0.000 description 8
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 5
- 239000000956 alloy Substances 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 241000276425 Xiphophorus maculatus Species 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000001914 filtration Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 229920000742 Cotton Polymers 0.000 description 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 241001465754 Metazoa Species 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 239000011358 absorbing material Substances 0.000 description 1
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- 239000012535 impurity Substances 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B64D27/40—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
Abstract
The invention discloses a kind of small-sized pilotless aircraft, including casing, including upper surface and lower surface；And multigroup Ducted propeller on casing is assemblied in, every group of Ducted propeller includes duct housing, fixed seat, force piece and the propeller of both ends insertion；Each duct housing is assemblied on casing and forms the duct chamber of insertion upper and lower surface, and fixed seat is arranged at duct intracavitary, and force piece is assemblied in fixed seat and is contained in duct intracavitary, and propeller is contained in duct intracavitary and is connected with force piece.In above-mentioned small-sized pilotless aircraft, by setting multigroup Ducted propeller to be used as the power resources of complete machine, and the propeller being arranged on every group of Ducted propeller is accommodated in duct intracavitary, it is i.e. stealthy to set rather than outside casing, so that small-sized pilotless aircraft is in flight course, avoid because propeller and external object collide, so as to effectively improve the safety and reliability of complete machine.
Description
Technical field
The present invention relates to flying machine technical field, more particularly to a kind of small-sized pilotless aircraft.
Background technology
In recent years, SUAV with the features such as its simple structure, convenient manipulation and higher security performance by more
Carry out more attention, be especially mainly used in taking photo by plane or the pocket unmanned plane of self-timer has attracted large quantities of airplane hobbyists and fan.
Pocket unmanned plane be mainly characterized by it is full-featured, compact portable and simple to operate etc., and among these, portability
It is pocket unmanned plane one of outstanding feature the most.Currently in order to carrying or convenient transportation, the propeller of part pocket unmanned plane
Foldable or detachable form is designed as, reduces the free space of fuselage.But for fuselage size natively small pocket without
For man-machine, the space availability ratio that foldable or dismountable propeller is easily caused overall pocket unmanned plane is not high, the chi of fuselage
It is very little to be increased.Meanwhile in flight course, the propeller outside fuselage is easy to touch periphery object, such as branch
Or people etc., damage is caused to propeller itself and security performance is not high.
The content of the invention
Based on this, it is necessary to the problem of and security performance big for conventional small unmanned aerial vehicle size be not high, there is provided a kind of
The small unmanned aerial vehicle that size is small and reliability is high.
A kind of small-sized pilotless aircraft, it includes：
Casing, including upper surface and the lower surface relative with the upper surface；And
The multigroup Ducted propeller being assemblied on the casing, Ducted propeller described in every group include the duct of both ends insertion
Housing, fixed seat, force piece and propeller；
Wherein, each duct housing, which is assemblied on the casing and formed, penetrates the upper surface and the lower surface
Duct chamber, the fixed seat is arranged at the duct intracavitary, and the force piece is assemblied in the fixed seat and is contained in institute
Duct intracavitary is stated, the propeller is contained in the duct intracavitary and is connected with the force piece.
In one of the embodiments, the Ducted propeller includes four groups, and four groups of Ducted propellers are several with the casing
What center symmetric setting is in the casing surrounding.
In one of the embodiments, in Ducted propeller described in every group each propeller include oar disk and one into
Type is arranged at six blades of the oar disk periphery, and each force piece be motor, each the stator of the motor with it is described
Fixed seat is fixedly connected, and each oar disk is fixed on the rotor of each motor.
In one of the embodiments, each fixed seat is integrally formed with the respective duct housing, and described
Small-sized pilotless aircraft includes damping rubber pad, and the damping rubber pad is arranged at the surface that the fixed seat installs the force piece.
In one of the embodiments, the casing is including the upper shell with the upper surface and with the lower surface
Lower house, upper shell connection relative with the lower house and enclose jointly and set the installation cavity to be formed positioned between the two；Institute
Stating small-sized pilotless aircraft includes the plug being arranged in the installation cavity and the ultrasonic sensor being set in the plug, institute
State plug to be connected between the upper shell and the lower house, sound end exposes to the lower casing in the ultrasonic sensor
Body.
In one of the embodiments, the plug includes the cock body of one end formation opening and is arranged at the cock body periphery
Support feet, the lower house and the plug correspondence position offer through hole；The cock body is provided with one end of the opening
It is contained in the through hole, the other end of the relatively described opening of the cock body is connected to the upper shell towards the lower house
Surface, the support feet are arranged at the cock body and are provided with one end of the opening and are fixedly supported to the lower house towards institute
State the surface of upper shell；Sound end described in the ultrasonic sensor by it is described opening and the through hole expose to it is described under
Housing.
In one of the embodiments, the small-sized pilotless aircraft includes the sound-absorbing part being contained in the installation cavity, institute
State sound-absorbing part and be arranged at the lower house towards the surface of the upper shell.
In one of the embodiments, the casing is including the upper shell with the upper surface and with the lower surface
Lower house, upper shell connection relative with the lower house and enclose jointly and set the installation cavity to be formed positioned between the two；Institute
The energy that stating small-sized pilotless aircraft includes being arranged in the installation cavity provides unit, circuit board, the first heat conductive pad and second
Heat conductive pad, the circuit board are arranged at the lower house and provide unit towards the surface of the upper shell, the energy and be arranged at
On the circuit board, the first heat conductive pad is arranged between the lower house and the circuit board, and second heat conductive pad is arranged at
The energy is provided between unit and the upper shell.
In one of the embodiments, the upper shell and/or the lower house offer what is connected with the installation cavity
Heat emission hole.
In one of the embodiments, the upper shell and the lower house are Al-alloy casing.
In above-mentioned small-sized pilotless aircraft, it is used as the power resources of complete machine by setting multigroup Ducted propeller, and is arranged at
Propeller on every group of Ducted propeller is accommodated in duct intracavitary, i.e., stealthy to set rather than outside casing so that small-sized
Unmanned aerial vehicle is avoided because propeller and external object collide in flight course, so as to effectively improve the security of complete machine and can
By property.
Brief description of the drawings
Fig. 1 is the part-structure schematic diagram of the small-sized pilotless aircraft in this preferred embodiment；
Fig. 2 is the structural representation of another angle of small-sized pilotless aircraft shown in Fig. 1；
Fig. 3 is the structural representation of Ducted propeller in small-sized pilotless aircraft shown in Fig. 1；
Fig. 4 is the structural representation of another angle of Ducted propeller shown in Fig. 3；
Fig. 5 is the structural representation of propeller in Ducted propeller shown in Fig. 3；
Fig. 6 is the perspective view of small-sized pilotless aircraft shown in Fig. 1；
Fig. 7 is the structural representation of damping rubber pad in small-sized pilotless aircraft shown in Fig. 6；
Fig. 8 is the structural representation of plug in small-sized pilotless aircraft shown in Fig. 6；
Fig. 9 is the structural representation of another angle of plug in small-sized pilotless aircraft shown in Fig. 6；
Figure 10 is the structural representation of sound-absorbing part in small-sized pilotless aircraft shown in Fig. 6.
Embodiment
For the ease of understanding the present invention, the present invention is described more fully below with reference to relevant drawings.In accompanying drawing
Give the preferred embodiment of the present invention.But the present invention can realize in many different forms, however it is not limited to herein
Described embodiment.On the contrary, the purpose for providing these embodiments is to make the understanding to the disclosure more saturating
It is thorough comprehensive.
It should be noted that when element is referred to as " being fixed on " another element, it can be directly on another element
Or there may also be element placed in the middle.When an element is considered as " connection " another element, it can be directly connected to
To another element or it may be simultaneously present centering elements.Term as used herein " vertical ", " horizontal ", " left side ",
" right side " and similar statement are for illustrative purposes only.
Unless otherwise defined, all of technologies and scientific terms used here by the article is with belonging to technical field of the invention
The implication that technical staff is generally understood that is identical.Term used in the description of the invention herein is intended merely to description tool
The purpose of the embodiment of body, it is not intended that in the limitation present invention.Term as used herein " and/or " include one or more phases
The arbitrary and all combination of the Listed Items of pass.
As depicted in figs. 1 and 2, a kind of small-sized pilotless aircraft 100 in this preferred embodiment, including casing 10, Duo Zuhan
Road propeller 20 (such as Fig. 3) and ultrasonic sensor 30.Multigroup Ducted propeller 20 is assemblied on casing 10, for be small-sized
Unmanned aerial vehicle 100 provides power, and ultrasonic sensor 30 is arranged on casing 10, for playing fixed high work to SUAV 100
With.In this specific embodiment, small-sized pilotless aircraft 100 is the pocket unmanned aerial vehicle that can be accommodated in pocket, and it is mainly used in
Self-timer, the defeated assistant engineer's tool of the amusement such as take photo by plane.It is to be appreciated that in some other embodiment, small-sized pilotless aircraft 100 also can be used for
Other functions, such as carry out present dispatching etc..
Casing 10 includes upper surface 110 and the lower surface 130 relative with upper surface 110.Wherein, upper surface 110 is small-sized
The surface of (towards sky) above during 100 normal use of unmanned aerial vehicle, is located at lower section when lower surface 130 is normal use
The surface of (towards ground).
Specifically, casing 10 includes upper shell 11 and the lower house 13 being oppositely arranged with upper shell 11, and upper surface 110 is set
In upper shell 11 backwards to the surface of lower house 13, lower surface 130 is arranged at lower house 13 backwards to the surface of upper shell 11.Meanwhile
Upper shell 11 is connected and enclosed jointly and sets to be formed positioned at installation cavity (not shown) between the two relatively with lower house 13, pacifies for accommodating
Fill other parts of SUAV 100.
In this specific embodiment, casing 10 is substantially square platy structure, and in order to reduce the resistance in flight course
It is typically designed with it is certain streamlined, such as square platy structure corner using fillet design etc., be construed as limiting herein.
Meanwhile upper shell 11 and lower house 13 are that aluminum alloy materials are made in casing 10, while main screw lift is mitigated, enhancing is whole
The intensity of machine.
Fig. 3 is refer to, every group of Ducted propeller 20 includes duct housing 21, fixed seat 23, force piece 25 and propeller
27.Each duct housing 21 is assemblied on casing 10 and forms the duct chamber 210 of insertion upper surface 110 and lower surface 130.It is fixed
Seat 23 is arranged in duct chamber 210, and force piece 25 is assemblied in fixed seat 23 and is contained in duct chamber 210.Propeller 27 is received
It is dissolved in duct chamber 210 and is connected with force piece 25, by the way that force piece 25 and propeller 27 is contained in into duct chamber 210
It is interior, compared to design of the tradition outside casing 10, avoid touching periphery object in flight course and causing propeller itself
Damage, effectively improve the security reliability of complete machine.
Fig. 4 is refer to, specifically, each duct housing 21 is in the hollow cylindrical of both ends insertion, and fixed seat 23 includes seat
Body 230 and some fixed arms 232 formed are radiated by the periphery of pedestal 230.Pedestal 230 is substantially in the form of annular discs, some fixed arms 232
The periphery of pedestal 230 is uniformly arranged on, and each fixed arm 232 is connected between the internal chamber wall of pedestal 230 and duct chamber 210.
In this specific embodiment, fixed arm 232 includes three, and three fixed arms 232 are with 120 degree of angles between the two
Form is uniformly arranged on the periphery of pedestal 230, to ensure the stress equalization of fixed seat 23, thinks that the force piece 25 being mounted thereon carries
For balanced support power.In addition, in order to improve the bulk strength of fixed seat 23, each fixed seat 23 and respective duct housing 21 1
It is body formed.It is to be appreciated that in some other embodiment, the quantity and structure of fixed arm 232 can as needed depending on, it is and solid
Fixed arm 232 also can use the other manners such as screw, welding to be individually fixedly connected between duct housing 21, not make herein
Limit.
Fig. 5 is refer to, propeller 27 includes oar disk 270 and is integrally formed six blades for being arranged at the periphery of oar disk 270
272.The hollow cylindrical of the generally both ends insertion of oar disk 270, axis of rotation of six blades 272 along oar disk 270 are circumferentially disposed
In the outer peripheral face of oar disk 270.Every blade 272 includes the blade root 2721 and blade tip 2723 positioned at opposite end, blade root 2721 with
Oar disk 270 connects and the central axis of relative oar disk 270 tilts at an angle.Every blade 272 from the one of blade root 2721
Hold to one end close to blade tip 2723 and gradually twist, and blade tip 2723 is reversed from lower house 13 to the direction of upper shell 11.Its
In, the torsional direction all same of six blades 272.
It is to be appreciated that in some other embodiment, the quantity and blade tip 2723 of blade 272 are reversed with respect to blade root 2721
Angle can as needed depending on, be not limited thereto.
Referring again to Fig. 3, each force piece 25 is motor, the stator of each motor and fixation in this specific embodiment
Seat 23 is fixedly connected, on rotor of each fixed cover of oar disk 270 loaded on each motor, to drive blade 272 under being driven in motor
Synchronous coaxial rotating.
In this specific embodiment, Ducted propeller 20 includes four groups, and four groups of Ducted propellers 20 are with the geometry of casing 10
The heart is symmetricly set in the surrounding of casing 10, to keep balance of the complete machine in flight course.It is to be appreciated that in some other implementation
In example, the quantity of Ducted propeller 20 can as needed depending on, be not limited thereto.
Referring again to Fig. 2, ultrasonic sensor 30 is arranged in installation cavity, and sound end is exposed to outside lower house 13,
For being detected.Wherein, ultrasonic wave is that a kind of vibration frequency height caused by vibration occurs under voltage drive as transducing chip
In the mechanical wave of sound wave, it be able to can produce significantly to reflect to form when encountering impurity or interface is reflected into echo, and encounters work
Animal physical efficiency produces Doppler effect.Therefore, it is important a member in the whole sensing system of SUAV 100.
Fig. 1 and Fig. 6 are refer to, in one of the embodiments, small-sized pilotless aircraft 100 includes ultrasonic wave anti-interference structure
40, for reducing the interference of flight course China and foreign countries bound pair ultrasonic sensor on the whole, lifting ultrasonic wave is in SUAV
100 data stability, so as to lift the flying height of complete machine and attitude stability.
Fig. 7 is refer to, specifically, ultrasonic wave anti-interference structure 40 includes damping rubber pad 41, and damping rubber pad 41 is arranged at solid
The surface of force piece 25 is installed in reservation 23, avoids directly contacting firmly between force piece 25 and fixed seat 23.Because force piece 25 exists
During high-speed rotation, caused noise (including wind is made an uproar and the mechanical noise of itself of force piece 25) and vibrations, to ultrasonic wave
The validity of the numerical value of sensor 30 produces large effect.By this damping rubber pad 41, can buffer with filtration fraction from solid
Shaken between reservation 23 and force piece 25, change the propagation medium of noise, reduce influence of the noise to ultrasonic sensor 30.
Fig. 8 and Fig. 9 are refer to, in one of the embodiments, ultrasonic wave anti-interference structure 40 includes being arranged at installation cavity
Interior plug 43, plug 43 are connected between upper shell 11 and lower house 13, and ultrasonic sensor 30 is set in plug 43, and
Sound end exposes to lower house 13 in ultrasonic sensor 30.
Specifically, plug 43 includes the cock body 430 and some support feets 432 that one end forms opening 4301.Lower house 13 with
The correspondence position of plug 43 offers through hole 132 (as shown in Figure 2), and one end that cock body 430 is provided with opening 4301 is contained in through hole
In 132, the other end of the opposed open 4301 of cock body 430 is connected to upper shell 11 towards the surface of lower house 13.Some support feets
432, which are arranged at cock body 430, is provided with the outer peripheral face of 4301 one end of opening, and is fixedly supported to lower house 13 towards upper shell 11
Surface.Ultrasonic sensor 30 is contained in cock body 430, and sound end exposes to lower house by opening 4301 and through hole 132
13.In this specific embodiment, support feet 432 includes three, and three support feets 432 are uniformly arranged on the periphery of cock body 430.Can
To understand ground, in some other embodiment, the quantity of support feet 432 can as needed depending on, and support feet 432 setting
Position also can be as needed, it is only necessary to realize that plug 43 is stably fixed between upper shell 11 and lower house 13, herein
It is not construed as limiting.
It is installed on lower house 13, and is set in cock body 430 that is, ultrasonic sensor 30 is indirect, is led to
Cross cock body 430 to be vacantly arranged between upper shell 11 and lower house 13 so that ultrasonic sensor 30 and upper shell 11 and lower casing
Body 13 is isolated, and avoids being influenceed by upper shell 11 and the vibrations of lower house 13 in flight course, while is also helped filtering and come
The influence made an uproar from the vibrations in the flight course of SUAV 100 and the wind of force piece 25.Meanwhile ultrasonic sensor 30 is set with
Damaged in cock body 430, avoiding SUAV 100 by extraneous severe impact power.
Figure 10 is refer to, in one of the embodiments, ultrasonic wave anti-interference structure 40 includes being contained in installation cavity
Sound-absorbing part 45, sound-absorbing part 45 are arranged at lower house 13 towards the surface of upper shell 11, flown for changing SUAV 100
The route of transmission of noise in journey, reduce influence of the noise to the Effective Numerical of ultrasonic sensor 30.In this specific embodiment, inhale
Sound part 45 is to be adhered to the lower house 13 of SUAV 100 towards the acoustical cotton on the surface of upper shell 11 by gum.It can manage
Solution, in some other embodiment, sound-absorbing part 45 can be also made up of other sound-absorbing materials, and the position that sound-absorbing part 45 is set also may be used
Depending on as needed, such as it is also provided on upper shell 11, is not limited thereto in addition to being arranged on lower house 13.
Please referring again to Fig. 1, in one of the embodiments, small-sized pilotless aircraft 100 includes energy and provides unit 50, electricity
Road plate 60 and radiator structure 70.Circuit board 60 is contained in installation cavity and is arranged at lower house 13 towards the table of upper shell 11
Face, energy provides unit 50 and is contained in installation cavity and is arranged on circuit board 60, for providing electricity for small-sized pilotless aircraft 100
Can, specifically, it is two pieces of lithium batteries being arranged in installation cavity that energy, which provides unit 50,.Radiator structure 70 includes the first heat conductive pad
71, the first heat conductive pad 71 is arranged between lower house 13 and circuit board 60, for providing energy to unit 50 and circuit board 60 produces
Raw heat is conducted to lower house 13, is radiated through lower house 13.Wherein, in this specific embodiment, lower house 13 is aluminium alloy
Material is made, so as to further enhance the radiating efficiency for providing energy unit 50 and circuit board 60.
Further, radiator structure 70 includes the second heat conductive pad 73, and the second heat conductive pad 73 is arranged at upper shell 11 and energy
Between unit 50 is provided, conducted for heat caused by providing energy to unit 50 and circuit board 60 to upper shell 11, through upper casing
Body 11 radiates.Wherein, in this specific embodiment, lower house 13 is made up of aluminum alloy materials, so as to further enhance to energy
Amount provides the radiating efficiency of unit 50 and circuit board 60.
Wherein, the above-mentioned heat conductive pad 73 of first heat conductive pad 71 and second is silica gel heat conductive pad.It is to be appreciated that at some other
In embodiment, the first heat conductive pad 71 and the second heat conductive pad 73 also can be other conductive structures for being beneficial to conduction heat, not make herein
Limit.
Yet further, radiator structure 70 includes the heat emission hole 75 being opened on upper shell 11 and/or lower house 13, radiating
Hole 75 connects with installation cavity, for being discharged to the heat inside complete machine.
In above-mentioned small-sized pilotless aircraft 100, by setting multigroup Ducted propeller 20 to be used as the power resources of complete machine, and set
The propeller 27 being placed on every group of Ducted propeller 20 is accommodated in duct chamber 210, i.e., stealthy to set rather than exposed to casing
Outside 10 so that small-sized pilotless aircraft 100 is avoided because propeller and external object collide, so as to effectively improve in flight course
The safety and reliability of complete machine.
The embodiment only expresses the several embodiments of the present invention above, and its description is more specific and detailed, but not
Therefore the limitation to the scope of the claims of the present invention can be interpreted as.It should be pointed out that come for one of ordinary skill in the art
Say, without departing from the inventive concept of the premise, various modifications and improvements can be made, these belong to the protection of the present invention
Scope.Therefore, the protection domain of patent of the present invention should be determined by the appended claims.
Claims (10)
- A kind of 1. small-sized pilotless aircraft, it is characterised in that including：Casing, including upper surface and the lower surface relative with the upper surface；AndThe multigroup Ducted propeller being assemblied on the casing, Ducted propeller described in every group include the duct shell of both ends insertion Body, fixed seat, force piece and propeller；Wherein, each duct housing is assemblied on the casing and forms the culvert for penetrating the upper surface and the lower surface Road chamber, the fixed seat are arranged at the duct intracavitary, and the force piece is assemblied in the fixed seat and is contained in the culvert Road intracavitary, the propeller are contained in the duct intracavitary and are connected with the force piece.
- 2. small-sized pilotless aircraft according to claim 1, it is characterised in that the Ducted propeller includes four groups, four groups Ducted propeller is symmetricly set in the casing surrounding with the casing geometric center.
- 3. small-sized pilotless aircraft according to claim 1 or 2, it is characterised in that each in Ducted propeller described in every group The propeller includes oar disk and is integrally formed six blades for being arranged at the oar disk periphery, and each force piece is electricity Machine, the stator of each motor are fixedly connected with the fixed seat, and each oar disk is fixed on turning for each motor On son.
- 4. small-sized pilotless aircraft according to claim 1, it is characterised in that each fixed seat and the respective culvert Road housing is integrally formed, and the small-sized pilotless aircraft includes damping rubber pad, and the damping rubber pad is arranged at the fixed seat peace Fill the surface of the force piece.
- 5. small-sized pilotless aircraft according to claim 1, it is characterised in that the casing is included with the upper surface Upper shell and the lower house with the lower surface, the upper shell is relative with the lower house to be connected and encloses to set jointly to form position In installation cavity between the two；The small-sized pilotless aircraft includes the plug being arranged in the installation cavity and is set in the glue Ultrasonic sensor in plug, the plug are connected between the upper shell and the lower house, the ultrasonic sensor Middle sound end exposes to the lower house.
- 6. small-sized pilotless aircraft according to claim 5, it is characterised in that the plug includes the plug that one end forms opening Body and the support feet for being arranged at the cock body periphery, the lower house offer through hole with the plug correspondence position；The plug One end that body is provided with the opening is contained in the through hole, and the other end of the relatively described opening of the cock body is connected to described For upper shell towards the surface of the lower house, the support feet is arranged at one end and the fixation that the cock body is provided with the opening The lower house is supported in towards the surface of the upper shell；Sound end passes through the opening described in the ultrasonic sensor The lower house is exposed to the through hole.
- 7. small-sized pilotless aircraft according to claim 5, it is characterised in that the small-sized pilotless aircraft includes being contained in institute The sound-absorbing part in installation cavity is stated, the sound-absorbing part is arranged at the lower house towards the surface of the upper shell.
- 8. small-sized pilotless aircraft according to claim 1, it is characterised in that the casing is included with the upper surface Upper shell and the lower house with the lower surface, the upper shell is relative with the lower house to be connected and encloses to set jointly to form position In installation cavity between the two；The energy that the small-sized pilotless aircraft includes being arranged in the installation cavity provides unit, circuit Plate, the first heat conductive pad and the second heat conductive pad, the circuit board are arranged at the lower house towards the surface of the upper shell, institute Energy offer unit to be stated to be arranged on the circuit board, the first heat conductive pad is arranged between the lower house and the circuit board, Second heat conductive pad is arranged at the energy and provided between unit and the upper shell.
- 9. small-sized pilotless aircraft according to claim 8, it is characterised in that the upper shell and/or the lower house are opened Provided with the heat emission hole connected with the installation cavity.
- 10. small-sized pilotless aircraft according to claim 8, it is characterised in that the upper shell and the lower house are Al-alloy casing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710854483.5A CN107499503A (en) | 2017-09-20 | 2017-09-20 | Small-sized pilotless aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710854483.5A CN107499503A (en) | 2017-09-20 | 2017-09-20 | Small-sized pilotless aircraft |
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| US20030062443A1 (en) * | 2001-10-02 | 2003-04-03 | Joseph Wagner | VTOL personal aircraft |
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