CN109263878A - Eight rotor manned aircraft - Google Patents
Eight rotor manned aircraft Download PDFInfo
- Publication number
- CN109263878A CN109263878A CN201811274609.2A CN201811274609A CN109263878A CN 109263878 A CN109263878 A CN 109263878A CN 201811274609 A CN201811274609 A CN 201811274609A CN 109263878 A CN109263878 A CN 109263878A
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- rotor
- aircraft
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- flight
- small
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 21
- 239000011435 rock Substances 0.000 claims abstract description 8
- ZZUFCTLCJUWOSV-UHFFFAOYSA-N furosemide Chemical compound C1=C(Cl)C(S(=O)(=O)N)=CC(C(O)=O)=C1NCC1=CC=CO1 ZZUFCTLCJUWOSV-UHFFFAOYSA-N 0.000 claims description 3
- 238000010248 power generation Methods 0.000 claims description 3
- 238000009826 distribution Methods 0.000 claims description 2
- 230000000630 rising effect Effects 0.000 claims description 2
- 239000007787 solid Substances 0.000 claims 1
- 230000005611 electricity Effects 0.000 abstract description 5
- 230000008859 change Effects 0.000 description 8
- 230000032258 transport Effects 0.000 description 8
- 238000000034 method Methods 0.000 description 4
- 230000007423 decrease Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 208000027418 Wounds and injury Diseases 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 235000005121 Sorbus torminalis Nutrition 0.000 description 1
- 244000152100 Sorbus torminalis Species 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 230000003100 immobilizing effect Effects 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000035484 reaction time Effects 0.000 description 1
- 238000009827 uniform distribution 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
- 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
-
- 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
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- 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
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
-
- 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
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The invention discloses a kind of eight rotor manned aircraft.Including aircraft body and flight control system, aircraft body includes manned storehouse, undercarriage, the support arm being fixedly connected with manned storehouse and the rotor being fixed on support arm, there are the left control-rod and right control-rod of seat and control flight in manned storehouse, it further include the display system of observation flight device location information, the ambient condition when image information observation flight of the rock type camera that can be arranged by aircraft front end shooting around aircraft；The setting for being divided into two parts control rotor of flight control system, so that aircraft has bigger power, while more flexible；Oily electricity hybrid power supply is that power source provides guarantees, and oil electricity is mixed dynamic, the aircraft down or excess energy of light load is converted to electric energy for aircraft use when declining, to achieve the purpose that fuel-efficient and quick start, extends hours underway.
Description
Technical field
The present invention relates to vehicle technology field, more particularly to a kind of eight rotor manned aircraft.
Background technique
Currently, with the development of material, electronics and Computer Control Technology, multi-rotor unmanned aerial vehicle is in the neck such as take photo by plane, monitor
Domain is widely applied.Multi-rotor aerocraft can VTOL, for a long time hover, maneuverability is stronger, while compared with helicopter etc.
With advantage small in size, therefore there is transport convenience under the specific conditions such as skyscraper, facility, steep cliff, river, mountains and rivers,
Common rotor craft has three axis list (double) rotors, four axis list (double) rotors, six axis rotors etc..
But due to the limitation of above-mentioned aircraft rotor, so that its stability and flexibility be not high, if increasing rotor
It can then consume energy and add, due to the general small volume of aircraft, available space is few, only relies on electric power and provides power, then cruise duration
Short, lifting capacity is poor, be unable to satisfy current aircraft disaster relief, mapping, inspection, in terms of demand, such as
Fruit provides power using oily power, and rotor also needs to control direction while providing lift, so that its stability, flexibility are big
It is big to reduce.
Therefore, how to improve stability, flexibility, transport capacity and the extension hours underway of aircraft is this field skill
The problem of art personnel's urgent need to resolve.
Summary of the invention
In view of this, the present invention provides a kind of eight rotor manned aircraft.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of eight rotor manned aircraft, comprising: aircraft body and flight control system；Wherein the aircraft body includes
Manned storehouse, the undercarriage for being connected to the manned orlop portion, eight support arms for being connected to the manned the top of the warehouse and with it is described
The rotor of support arm connection；The flight control system is provided in the manned storehouse；The flight control system includes left hand
Control-rod, right hand control-rod and display system；The flight control system is divided into attitude control system and spare gesture stability system
System；The flight control system is using the electric hybrid power supply of oil.
Preferably, each support arm is connected with a rotor far from one end of the Flight main body.
Preferably, the support arm is uniformly distributed in M shape, and the rotor is divided into four big rotor and four small rotors,
The big rotor is spaced apart with the small rotor.
Preferably, the flight control system is divided into attitude control system and spare attitude control system, is divided into two parts
Control system increases the flexibility of aircraft, and control easy to operate is suitable for more operative scenarios.
Preferably, the right hand control-rod controls the attitude control system, can control the revolving speed of rotor on aircraft,
To control flight attitude.
Preferably, the left hand control-rod controls the spare attitude control system, can control rotor on aircraft
Velocity of rotation rises, hovers or lands to control aircraft.
Preferably, the attitude control system controls the small rotor, and is motor driven, so that attitude of flight vehicle changes
It is changed to flexibly, the reaction time is short.
Preferably, the spare attitude control system controls the big rotor, and is oil machine driving, while hydro power generation
The motor is supplied, so that aircraft driving force enhances, load capacity increases, and the big rotor control aircraft is gone up and down so that flying
The hovering of row device is more steady.
Preferably, the identical direction of rotation of the adjacent big rotor revolving speed is on the contrary, the adjacent small rotor revolving speed is identical
Direction of rotation makes aircraft smooth flight on the contrary, the torque that the opposite rotor of the revolving speed same direction can cancel out each other to fuselage.
Preferably, be provided with the telescopic safety rope being fixedly connected on chassis in the aircraft body, it is convenient into
The transport of row disaster assistance it is injured by deliverer, it is only necessary to stretcher, which is fixed on safety rope, which can pass through aircraft, transports wound
Person.
Preferably, it is provided with rock type camera in the aircraft body, often environment when due to carrying out disaster assistance
Complexity, the camera of rotary type facilitate driver observe ambient enviroment, especially it can also be observed that transport the wounded the case where,
To handle it in time.
It can be seen via above technical scheme that compared with prior art, the present disclosure provides a kind of eight rotor manneds
Aircraft, because rotor is more, stability of aircraft is improved, while improving flying power；Separated flight control
System improves the flexibility of flying vehicles control, and big rotor provides stable lift, the small flexible change of flight posture of rotor；Together
When increased safety rope can be used to transport the safety rope by rescuer, being fixedly connected more securely；Oily electricity mixing
Power supply mode provides more structurally sound power for aircraft, and extends hours underway.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of invention for those of ordinary skill in the art without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
Fig. 1 attached drawing is eight rotor manneds Flight Vehicle Structure schematic diagram provided by the invention；
Fig. 2 attached drawing is flight control system structural schematic diagram provided by the invention；
Fig. 3 attached drawing is eight rotor manneds aircraft schematic view of the front view provided by the invention；
Fig. 4 attached drawing is rotor distributed architecture schematic diagram provided by the invention.
In Fig. 1:
11 it is aircraft body, 12 be undercarriage, 13 be support arm, 14 be big rotor, 15 be small rotor, 111 is rock type take the photograph
As head.
In Fig. 2:
21 it is right hand control-rod, 22 be left hand control-rod, 23 is display system.
In Fig. 3:
12 it is undercarriage, 13 be support arm, 14 be big rotor, 111 be rock type camera, 112 is safety rope.
In Fig. 4:
13 it is support arm, 14 be big rotor, 151 be small rotor 1,152 be small rotor 2,153 be small rotor 3,154 is small rotor
4。
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
The embodiment of the invention discloses a kind of eight rotor manned aircraft, comprising: aircraft body and flight control system；
Wherein aircraft body includes manned storehouse 11, the undercarriage 12 for being connected to by connector the manned orlop disk lower end, connection
Eight support arms 13 in 11 top of manned storehouse and the rotor that is connect with support arm 13；Flight control system is provided in manned storehouse 11
System；Flight control system includes left hand control-rod 22, right hand control-rod 21 and display system 23；Flight control system is divided into posture
Control system and spare attitude control system；Flight control system is using the electric hybrid power supply of oil.
In order to advanced optimize above scheme, floor stand 12 uses double-crossbar type, more can be suitably used for disaster relief environment, when shutdown
It is more stable.
In order to advanced optimize above scheme, each support arm 13 is connected with a rotation far from one end of aircraft body
The wing.
In order to advanced optimize above scheme, support arm 13 is uniformly distributed in M shape, and rotor is divided into four big rotor 14
With four small rotor 15, big rotor 14 is spaced apart with small rotor 15.Uniform distribution has the every part uniform force of aircraft
Conducive to having a smooth flight.
In order to advanced optimize above scheme, flight control system is divided into attitude control system and spare gesture stability system
The rotor of system, spare attitude control system control keeps revolving speed constant, and the rotor of attitude control system control is by changing revolving speed
To change of flight posture, this control mode, which still to be able to maintain when aircraft progress posture changing, has a smooth flight.
In order to advanced optimize above scheme, right hand control-rod 21 controls the attitude control system, and manipulation aircraft is bowed
It faces upward, overturn and yawing rotation, i.e., enable the motor speed of corresponding position change by certain algorithm, realize the small rotor of corresponding position
Revolving speed changes, to carry out pose adjustment.
In order to advanced optimize above scheme, left hand control-rod 22 controls spare attitude control system, for controlling flight
Device vertical lift, the revolving speed by controlling big rotor motor increase or decrease the liter of aircraft to change big rotor revolving speed
Power, change of flight height.
In order to advanced optimize above scheme, attitude control system controls four small rotor 15, by changing small rotor 15
Revolving speed achievees the purpose that change of flight posture, because 15 rotary inertia of small rotor is smaller, posture change is more flexible, simultaneously
Energy conservation continuation of the journey.
In order to advanced optimize above scheme, spare attitude control system controls four big rotor 14, and providing lift can protect
Demonstrate,prove the stationarity of aircraft flight.
In order to advanced optimize above scheme, the small rotor 15 of attitude control system control is driven by motor, motor driven
Small rotor is more flexible, is easy to carry out the adjustment of flight attitude.
In order to advanced optimize above scheme, the big rotor 14 of spare attitude control system control by oil machine through driving, together
When hydro power generation supply the motor, oil machine, which provides power big rotor can be made to stablize rotation greatly, provides lift, while when continuing a journey
Between it is longer.
In order to advanced optimize above scheme, the adjacent identical direction of rotation of 14 revolving speed of big rotor is on the contrary, adjacent small rotation
The identical direction of rotation of 15 revolving speed of the wing is on the contrary, the torque that the opposite rotor of the revolving speed same direction can cancel out each other to fuselage, when having
When one rotor breaks down, which can carry out rotation forced landing, when opposite two or two groups of rotors go out simultaneously
When existing failure, which can also carry out smooth flight landing, improve the safety of aircraft.
In order to advanced optimize above scheme, big rotor and small rotor are distributed in different planes, may when avoiding flight
The interference in air flow of generation.
In order to advanced optimize above scheme, the telescopic peace being fixedly connected on chassis is provided in aircraft body
Full rope 112, the safety rope can be used for transporting severely injured patient when relief assistance, and the stretcher of the wounded is fixedly connected with safety rope,
The safety zone for the treatment of can be provided by being passed to.
In order to advanced optimize above scheme, rock type camera 111 is provided in aircraft body, aircraft front end is set
The case where rock type camera 111 set can enable driver observe below aircraft is arranged by pressing in right hand control
Switching push button on bar 21 processed switches to the mode that rock type camera 111 rotates that controls, while the picture shot can be shown
In the display system in manned storehouse 11, the wounded's situation of transport can be paid close attention to, can accurately be carried out after arriving at the destination certain
The hovering of distance enables salvor succour the wounded, avoids it by secondary injury, while the image information shot can recorde
The substantially disaster scenarios it in disaster area, convenient for carrying out further rescue.
In order to advanced optimize above scheme, 12 bottom of undercarriage is equipped with anti-skid chequer.
Driver drives into manned storehouse, and the revolving speed of four big rotor is adjusted by left hand control-rod, so as to adjust flying
Row height, when needing to adjust flight attitude, by the revolving speed that right hand control-rod controls four small rotors complete pitching, overturning and
The movement such as yaw.The environment in disaster area can be observed by driving aircraft, to formulate further rescue method, simultaneously
If disaster site has inconvenient traffic, there is something special, and urgent the wounded needs to transport, and stretcher can be fixed on safety rope, will hurt
Person is transported to the safety area of practicable relief.Separated two parts of flight control system control the setting of eight rotors, so that flying
Row device has bigger power, while more flexible；Oily electricity hybrid power supply provides guarantee for power source, and oil electricity is mixed dynamic, flies
The excess energy of light load is converted to electric energy and uses for aircraft when row device slows down or declines, to reach fuel-efficient and quick start
Purpose, extend hours underway；The rotation camera shooting of aircraft front end setting is observed convenient for driver in flight
Ambient condition around aircraft.
Embodiment 1
Driver drives into manned storehouse, presses start button and opens aircraft, and oil electric mixed dynamic system is aircraft at this time
Flying power is provided, oil machine drives big rotor to provide lift for aircraft, and the small rotor of motor driven provides lift, when on aircraft
Eight rotors simultaneously rotate and revolving speed it is identical when, the reaction torque that every group of rotor generates fuselage is numerically identical, two on direction
Therefore two on the contrary, can cancel out each other, make aircraft stress balance in the horizontal direction, keep stablizing.When adjustment aircraft needs
When rising to eminence convenient for observation integrated environment, control left hand control-rod increases the revolving speed of big rotor, so that rotor wing rotation institute
The total life of offer increases, and aircraft rises；When needing to adjust aircraft decline, drop to away from ground closer location in order to can
When picking the wounded, control left hand control-rod reduces the revolving speed of big rotor, so that total life reduces, revolving speed is worked as in aircraft decline
When immobilizing, aircraft stable suspersion, it is suitable apart from aircraft body to be fixed to the wounded using safety rope at this time
Position.
Embodiment 2
When driver, which drives aircraft, needs to carry out course line adjustment, turning for small rotor can be adjusted by controlling right hand control-rod
Speed carries out pose adjustment.Small rotor 1 and small rotor 4 are located at the first half of aircraft.It is calculated and miniature calculating by algorithm
Machine control is finally set as, and when right hand control-rod is swung to left front, small rotor 1 and 3 revolving speed of small rotor reduce simultaneously, small rotor
2 and 4 revolving speed of small rotor increase simultaneously, since small rotor 1 and small rotor 3 rotate clockwise, small rotor 2 and small rotor 4 are counterclockwise
Rotation, the reaction torque that rotor grouping machine body counterclockwise generates at this time are greater than the reaction torque that rotor clockwise generates fuselage, therefore
Aircraft can generate deflection in the counterclockwise direction, i.e., adjust course line to the left；With should right hand control-rod to right front swing when, it is small
Rotor 1 and 3 revolving speed of small rotor increase simultaneously, and small rotor 2 and 4 revolving speed of small rotor reduce simultaneously, at this time rotor grouping machine clockwise
The reaction torque that body generates is greater than the reaction torque that rotor counterclockwise generates fuselage, therefore aircraft can generate partially along clockwise direction
Turn, i.e., adjusts course line to the right.
Embodiment 3
When driver drive aircraft need to carry out pitching movement to hide front obstacle when, by control right hand control-rod come
Change small rotor revolving speed to carry out pose adjustment.When right hand control-rod is swung forward, small rotor 1 and 4 revolving speed of small rotor are simultaneously
Increase, small rotor 2 and 3 revolving speed of small rotor reduce simultaneously, and aircraft first half lift increases at this time, and latter half lift subtracts
It is small, therefore look up sporting flying；Similarly, the revolving speed for reducing small rotor 1 and small rotor 4 increases small rotor 2 and small rotor 3
Revolving speed does vertical view sporting flying.It is moved due to pitching, aircraft and horizontal plane are at a pitch angle, therefore the liter that rotor provides
Power produces the horizontal component for moving forward and backward aircraft, makes aircraft while generation moves forward and backward.
Embodiment 4
When encountering certain danger when driver drives aircraft, or hiding two sides barrier, control right hand control can be passed through
Bar carries out roll motion.When right hand control-rod is swung to the left, small rotor 3 and 4 revolving speed of small rotor increase simultaneously, small rotor 1 and small
2 revolving speed of rotor reduces simultaneously, and aircraft left-half lift reduces at this time, and right half part lift increases, therefore does and turn on one's side to the left
Rolling movement；Similarly, the revolving speed for reducing small rotor 3 and small rotor 4 increases the revolving speed of small rotor 1 and small rotor 3, does and turn on one's side to the right
Rolling movement.Since roll motion and aircraft are at a roll angle, the lift that rotor provides is produced for aircraft side-to-side movement
Horizontal component, make aircraft while generating side-to-side movement.
Embodiment 5
Big rotor is distributed in different horizontal planes with small rotor, but overlooks and be still distributed in M shape, while small rotor 1 is towards winged
Front when row device flight, remaining rotor are ibid sequentially distributed, and oil machine drives big rotor to provide lift for aircraft, and motor drives
It moves small rotor and lift is provided.Issuable interference in air flow when can be to avoid flight of rotor distribution mode at this time, meanwhile, it carries out
When pose adjustment, the variation of small rotor revolving speed is different.
When carrying out course line adjustment, when right hand control-rod is swung to left front, small rotor 1 and 3 revolving speed of small rotor reduce simultaneously,
Small rotor 2 and 4 revolving speed of small rotor increase simultaneously, since small rotor 1 and small rotor 3 rotate clockwise, small rotor 2 and small rotor 4
Rotation counterclockwise, the reaction torque that rotor grouping machine body counterclockwise generates at this time generate fuselage greater than rotor clockwise anti-twisted
Square, therefore aircraft can generate deflection in the counterclockwise direction, i.e., adjust course line to the left；With should right hand control-rod to right front put
When dynamic, small rotor 1 and 3 revolving speed of small rotor increase simultaneously, and small rotor 2 and 4 revolving speed of small rotor reduce simultaneously, at this time rotor clockwise
The reaction torque that grouping machine body generates is greater than the reaction torque that rotor counterclockwise generates fuselage, therefore aircraft can be along clockwise direction
Deflection is generated, i.e., adjusts course line to the right.
When as pitching movement, right hand control-rod is swung forward, and small rotor 2 and 4 revolving speed of small rotor are constant, 1 turn of small rotor
Speed increases, and small 3 revolving speed of rotor reduces, and aircraft first half lift increases at this time, and latter half lift reduces, therefore looks up
Sporting flying；Similarly, the revolving speed of small rotor 1 and small rotor 4 is constant, increases the revolving speed of small rotor 3 while reducing turning for small rotor 1
Speed, then aircraft does vertical view sporting flying.
When as roll motion, right hand control-rod is swung to the left, and small rotor 1 and 3 revolving speed of small rotor are constant, 2 turns of small rotor
Speed reduces small 4 revolving speed of rotor simultaneously and increases, and aircraft left-half lift reduces at this time, and right half part lift increases, therefore does
Tumbling motion to the left；Similarly, the revolving speed of small rotor 1 and small rotor 3 is constant, increases the revolving speed of small rotor 2 while reducing small rotation
The revolving speed of the wing 4, then aircraft does tumbling motion to the right.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.For device disclosed in embodiment
For, since it is corresponded to the methods disclosed in the examples, so being described relatively simple, related place is said referring to method part
It is bright.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (10)
1. a kind of eight rotor manned aircraft characterized by comprising aircraft body and flight control system；
Wherein the aircraft body includes manned storehouse (11), by connector is connected to rising and falling for the manned orlop disk lower end
Frame (12), eight support arms (13) being connected at the top of the manned storehouse (11) and the rotation being connect with eight support arms (13)
The wing；The flight control system is provided in the manned storehouse (11)；The flight control system include left hand control-rod (22),
Right hand control-rod (21) and display system (23)；The flight control system is divided into attitude control system and spare gesture stability system
System；The eight rotor manneds aircraft is using the electric hybrid power supply of oil.
2. eight rotor manneds aircraft according to claim 1, which is characterized in that each support arm (13) is far from institute
The one end for stating aircraft body is connected with a rotor.
3. eight rotor manneds aircraft according to claim 2, which is characterized in that the support arm (13) is equal in M shape
Even distribution, the rotor are divided into four big rotor (14) and four small rotor (15), the big rotor (14) and the small rotor
(15) it is spaced apart.
4. eight rotor manneds aircraft according to claim 1, which is characterized in that the right hand control-rod (21) controls institute
State attitude control system.
5. eight rotor manneds aircraft according to claim 1, which is characterized in that the left hand control-rod (22) controls institute
State spare attitude control system.
6. eight rotor manneds aircraft according to claim 4, which is characterized in that described in the attitude control system control
Small rotor (15), and be motor driven.
7. eight rotor manneds aircraft according to claim 5 or 6, which is characterized in that the spare attitude control system
The big rotor (14) is controlled, and is oil machine driving, while hydro power generation supplies the motor.
8. eight rotor manneds aircraft according to claim 7, which is characterized in that adjacent big rotor (14) rotation
Contrary, adjacent small rotor (15) direction of rotation is opposite.
9. eight rotor manneds aircraft according to claim 1, which is characterized in that be provided in the aircraft body solid
Surely the telescopic safety rope (112) being connected on chassis.
10. eight rotor manneds aircraft according to claim 1, which is characterized in that be provided in the aircraft body
Rock type camera (111).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274609.2A CN109263878A (en) | 2018-10-30 | 2018-10-30 | Eight rotor manned aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274609.2A CN109263878A (en) | 2018-10-30 | 2018-10-30 | Eight rotor manned aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109263878A true CN109263878A (en) | 2019-01-25 |
Family
ID=65195160
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274609.2A Withdrawn CN109263878A (en) | 2018-10-30 | 2018-10-30 | Eight rotor manned aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109263878A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3128200A1 (en) * | 2021-10-20 | 2023-04-21 | Zipair | Hybrid flying device |
-
2018
- 2018-10-30 CN CN201811274609.2A patent/CN109263878A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3128200A1 (en) * | 2021-10-20 | 2023-04-21 | Zipair | Hybrid flying device |
| WO2023067253A1 (en) * | 2021-10-20 | 2023-04-27 | Zipair | Hybrid flying device |
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Application publication date: 20190125 |