CN205469819U - Manned type low latitude VTOL aircraft - Google Patents
Manned type low latitude VTOL aircraft Download PDFInfo
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- CN205469819U CN205469819U CN201620021636.9U CN201620021636U CN205469819U CN 205469819 U CN205469819 U CN 205469819U CN 201620021636 U CN201620021636 U CN 201620021636U CN 205469819 U CN205469819 U CN 205469819U
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Abstract
The utility model discloses a manned type low latitude VTOL aircraft, including a central rotor and a plurality of vice rotor of setting in the central rotor outside to set up one with the support that be used for anticollision of central rotor with the centre of a circle, central rotor all sets up in anti - collision bracket with vice rotor, the terminal surface is provided with manned passenger cabin and is used for taking under central rotor center. The utility model discloses a ground power supply system supplies power for the aircraft, has reduced aircraft electric power system's weight to utilize the cable to play the effect of supplementary direction, the security that improves the aircraft has increased one deck anticollision layer in the outside of duct, makes when this aircraft side bumps with fixed object, and the anticollision layer can be by extrusion deformation, but does not influence the duct shape, thereby makes this aircraft can intensive formation flight, have very high recreationally.
Description
Technical field
The present invention relates to aircraft field, be specifically related to a kind of riding type low latitude vertically taking off and landing flyer.
Background technology
At present, multi-rotor aerocraft has good mobility and handling, but its flight fully relies on the lift that rotor produces and carries out, and by tilting rotor plane, and the speed discrepancy between rotor obtains maneuverability, flight efficiency is poor, and crossrange maneuvering ability is the most not enough.Rotor is without guard shield and collision avoidance system, make must keep between itself and barrier enough safe distances, and between two frame gyroplanes, also must keep enough distances, cannot tight formation flight, or it is close to barrier flight, which has limited its purposes, it addition, its less loading capacity makes it cannot use as manned vehicle.The raising safety of rotor craft, mobility, stability, safety are the important directions that rotor craft is studied.Circling in the air is the dream of the mankind, has a lot of recreational facilities at present for meeting this dream of people, such as fire balloon, dirigible, helicopter, propeller-parachuting etc..The common feature of these converter tools is to need professional driver to drive, and visitor can only passive experience floating sensation.How to allow tourist experience to the sensation independently aloft circled in the air, need new recreation facility.
On JIUYUE 25th, 2013, Chinese invention patent application CN103318406A discloses a kind of composite rotor craft.Including aircraft theme, energy source device, hard disk and control device, aircraft theme includes main thruster and some auxiliary propellers, and main thruster includes main rotor one.Main rotor two and main duct, main rotor one and main rotor two are fixed in main duct by main duct support, the outer rim of main duct support is positioned at the main duct part house some vertical connecting rods of friend, and the bottom of vertical connecting rod is the most outwards horizontally disposed with cantilever, cantilever outer end house friend's auxiliary propeller.Which employs the comprehensive of multiple rotor flying mode, improve flight efficiency and the motility of aircraft, reliability and stability, but its in flight course cannot change of flight device entirety flight axis away from, mobility is poor, it is impossible to adapt to the flight requirement of specific occasion.On October 08th, 2014, Chinese invention patent application 201410252312.1 discloses a kind of coaxial multi-rotor aerocraft of duct, its integral layout is similar with application for a patent for invention CN103318406A, but the installation support arm of its auxiliary rotor can horizontally rotate, thus change wheelbase, change of flight device size, improves mobility and motility.The mobility of both aircraft, motility and safety, load-carrying, structure design still cannot meet the requirement entertaining aircraft.
Summary of the invention
The technical problem to be solved is to overcome the deficiencies in the prior art, it is provided that a kind of mobility is fabulous, and flight efficiency is higher, and loading capacity reaches more than 100 kilograms, safety and handling splendid manned amusement aircraft.
To achieve these goals, the present invention adopts the following technical scheme that
A kind of riding type low latitude vertically taking off and landing flyer, including several secondary rotors of a center rotor and centrally disposed rotor surrounding, including:
Described center rotor is that several rotors are connected with one heart and are integrated, and the direction of rotation of adjacent two rotors is contrary,
Being connected with outside the duct of center rotor and have several secondary duct supports, arrange a secondary rotor in each secondary duct support, described secondary rotor rotates around the junction point with secondary duct support, and described secondary duct support rotates around the junction point with center duct；
With the anticollision support of center rotor concentric, center rotor is arranged in the circumference of anticollision support with secondary rotor, is provided with damping spring between the inner side of described anticollision support and each secondary duct stent outer,
It is respectively disposed at the support that center rotor is upper and lower, the lower carriage of described center rotor connects a passenger cabin,
Connecting the cable of ground power supply system and passenger cabin, described passenger cabin is integrated with the electric power system of main duct and each secondary duct.
In technique scheme, described passenger cabin is connected perpendicularly to the center of the duct lower carriage of center rotor.
In technique scheme, including four arc supports being evenly distributed on passenger cabin lateral surface, described cabin interior side face is provided with passenger airbag.
In technique scheme, the bottom of described passenger cabin is provided with undercarriage, and undercarriage is connected with arc support.
In technique scheme, described undercarriage includes four support arms, passes through hinge links between each support arm and arc support.
In technique scheme, described support arm and arc support are provided with spring, and one end of spring is connected on support arm, and the other end is fixedly attached on arc support.
In technique scheme, bottom passenger cabin, it is provided with complete machine air bag.
In technique scheme, described secondary rotor carries out arbitrarily rotating clockwise or between anticlockwise 0 ° to 90 ° around the junction point of secondary duct support.
In technique scheme, described secondary duct support carries out arbitrarily rotating clockwise or between anticlockwise 0 ° to 90 ° around the junction point of center duct.
In technique scheme, described secondary rotor is equidistant, uniform, be symmetrically distributed in the surrounding of center rotor.
In sum, owing to have employed technique scheme, the invention has the beneficial effects as follows:
For the purpose of the present invention is first low latitude amusement, use center main rotor, peripheral secondary rotor, the odd number multiaxis rotor amusement aircraft of middle elliposoidal panorama passenger cabin；
Present invention employs secondary rotor inclined rotating mode, secondary rotor can rotate offer aircraft and advance, retreats, to the left, the power moved right, can be in the case of aircraft body tilt, rapid movement, comparing conventional many gyroplanes by tilting by the way of fuselage obtains onward impulse, mobility is higher, and energy efficiency is higher；
Present invention employs secondary rotor inclined rotating mode, secondary rotor can transfer acquisition turning moment by positive and negative, and the moment that the most conventional many gyroplanes of this torque ratio produce by changing rotating rotor rotating speed is much bigger, and the yaw maneuver being is greatly improved；
The main rotor of the present invention does not tilts when flight, so that aircraft flies with higher speed, thus obtains farther voyage；
The main rotor of the present invention does not tilts when flight, so that during aircraft flight, main rotor obtains additional lift so that lift efficiency is higher, and when improving voyage and boat；
The remote ground power supply system that the present invention uses, can power from ground to this aircraft in the range of hundreds of meters, so that the standby lasting stagnant empty ability more than 24 hours of this flying instrument；
Ground power supply system possesses breeze way and special fit, and electric wire can be avoided to be pulled off；
The present invention possesses complete machine air bag, can buffer impact during the improper ground connection of aircraft, it is ensured that complete machine and the safety of occupant；
The machine also has passenger airbag, can ensure passenger life safety when experience accident.
Accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is the main TV structure schematic diagram of the present invention；
Fig. 2 is the side-looking structural representation of the present invention；
Fig. 3 is the enlarged diagram of I in Fig. 1；
Wherein: 1 is center duct, 2 is secondary rotor, 3 is cable, 4 is secondary duct support system, 5 is motor, 6, 7 is the rotor of center rotor, 8 is passenger cabin, 9 is anticollision support, 10 is undercarriage, 11 is ground power supply system, 12 is airborne energy resource system, 13 is flight control system, 14 is center duct support, 15 is complete machine air bag, 16 is steering-engine, 17 is bearing block, 18 is bearing block, 19 is transit axle, 20 secondary duct supports, 21 is rowlock, 22 is secondary duct support arm, 23 is protecting against shock spring, 24 is steering-engine, 25 is bearing and horizontal rotating shaft, 26 is secondary duct.
Detailed description of the invention
Such as Fig. 1, shown in Fig. 2, the present invention includes a center rotor, several secondary rotors uniform, equidistant, that be symmetrically distributed in around the rotor of center, one is used for crashproof anticollision support, anticollision support and center rotor concentric, and between the secondary centrally disposed rotor of rotor and anticollision support, the outside of whole aircraft is a circle, and secondary duct is arranged in the circumference of anticollision support with center duct.Main rotor in the rotor of center includes propeller and lower propeller, and propeller comprises several blades as required, and upper and lower propeller is fixed in the flight support system of center duct, relies on motor to drive.Propeller coaxial up and down, rotating speed is identical, in opposite direction.The outside of center duct is equipped with the support system of secondary duct, and the quantity of support system is identical with secondary rotor quantity；The outer end of described support system is fixing and concentric rotating shafts rotary apparatus, and secondary duct is fixing on the spinning device, and rotary apparatus can rotate positive and negative an angle of 90 degrees around support system cantilever arm；Support system support arm is internal is circular or elliptic cross-section, is cased with, outside it, the lightweight drag reduction overcoat that cross section is symmetrical airfoil.In the underface of center rotor, fairshaped crew module is installed；Crew module bottom is provided with bending strip energy-absorbing undercarriage, first can improve comfortableness during landing, additionally can ensure aircraft and the safety of occupant when aircraft with relatively low speed and highly falls；It it is complete machine air bag bottom undercarriage；Crew module is inside and outside passenger airbag；Crew module bottom is battery flat, and is provided with the circumscribed energy and electric power system.Having complete machine air bag bottom passenger cabin, when aircraft exceedes certain speed and highly falls, complete machine air bag and passenger airbag and cabin safety air bag can be opened in advance, ensure aircraft and the safety of occupant.Navigation in flight control system and collision avoidance system can be at two aircraft at a distance of the nearest, or with barrier when the nearest, and new planning course line of laying equal stress on of actively slowing down, evade collision.When colliding, outermost intelligent and safe crash-proof bracket can detect dynamics and the direction of collision, and signal is passed to flight control system, to adjust flight attitude in time, reduces impact strength, it is ensured that safety.Support has the highest elasticity simultaneously, it is possible to ensure that aircraft less than specific speed collision rift, to ensure the safety of aircraft body structure by energy-absorbing.
In the present invention, several auxiliary rotors it are with outside the main rotor of center rotor, these secondary duct rotors are around the axle by secondary duct center with main duct center, also referred to as main shaft rotates the arbitrarily angled of positive and negative 0-90 degree, make the lift of secondary duct and the arbitrarily angled and parallel with the incisal plane of center duct of aircraft plane formation 0～± 90 °.
In the present invention, secondary duct rotor can also be positioned at aircraft plane, and the axle tangent with main duct around by secondary duct center, make the lift of secondary duct and the arbitrarily angled of aircraft plane formation 0～± 90 °, and be perpendicular in the plane of main duct by main shaft.
In the present invention, secondary duct rotor can also rotate around specific axle so that secondary duct rotor plane and center duct rotor plane form 0 to ± 90 ° between angle so that the lift of pair duct and aircraft plane formation 0～± 90 ° arbitrarily angled；The angle of these angles can be identical, it is also possible to different.
In the present invention, after the lift of secondary rotor forms certain angle with rotor plane, lift can promote full machine to advance at the component of aircraft in-plane, and without main frame plane of verting；The lift of the different secondary ducts component in rotor plane direction can produce moment, rotates with higher efficiency drives complete machine, change direction in main rotor plane.
In the present invention, all of duct is anticollision pneumatic shaping duct, and duct has certain thickness, hollow, after being collided, duct outer layer will occur bigger deformation, and absorbs collision energy, duct internal layer has high intensity, and deflection is the least, to ensure the safety of duct and oar.
In the present invention, the described secondary main support rotating mechanism of duct includes main shaft, the bearing block that comprises bearing, the bearing block comprising bearing, steering wheel.Secondary duct support arm is fixed on main shaft outer end, and steering wheel connects the main shaft other end.Control the steering wheel anglec of rotation, just can determine that the angle of auxiliary duct.
In the present invention, described secondary duct auxiliary support rotating mechanism includes the secondary duct support arm being fixed on outside main shaft, comprises bearing block and horizontal rotating shaft, the steering wheel of bearing.Secondary duct support arm is fixed on main shaft outer end, and secondary duct is connected on support arm by countershaft, and secondary duct can be rotated around countershaft in support arm.Steering wheel connects countershaft one end, controls the steering wheel anglec of rotation, just can determine that the angle of secondary duct.
Steering mechanism comprises two parts, and Part I is at secondary duct internal stent, and by transit axle, two bearings and bearing block, steering wheel 16 is constituted.Bearing block is nonmetallic materials, is fixed in support by bonding mode, and the center of bearing block is bearing.The longitudinal axis passes center, and one end is fixedly connected with secondary duct support arm by flange, and the other end is connected with steering-engine by gear.The steering mechanism in another one direction, steering-engine 24 is fixed in secondary duct support arm, is connected by the transverse axis of gear with secondary duct one end, the other end at secondary duct, the other side of horizontal rotating shaft is fixed on secondary duct, is simultaneously connected with at bearing, and this bearing is fixed on secondary duct support arm.
In the present invention, aircraft is had self energy and flies control and navigation system, on a support installed therein, including flight attitude panel, Navigation Control plate, electronic transmission and wireless receiver etc..
In the present invention, all propellers or fan, by rack-mount motor-driven.
In the present invention, energy resource system is made up of high-energy battery and remote ground power supply system.Wherein battery is arranged in the battery compartment bottom crew module, and battery flat also has external power interface, and the power supply connector of remote power system is just connected on the external power interface of battery flat.
In the present invention, remote power system, by one, there is bigger tensile strength, more low-resistance, length is from the cable of tens meters to hundreds of meter, and ground power supply composition, by remote power system, so that this aircraft realizes long-time uninterrupted flight within the specific limits.
In the present invention, having the elastic undercarriage of certain curvature, this undercarriage is made up of four root length linear support arm, this support arm is attached to the outside of crew module at ordinary times, it is unfolded into undercarriage during landing, aircraft and the safety of occupant can be ensured when aircraft falls with certain speed；It is connected by hinge and spring between each support arm with passenger cabin support, when aircraft landing, spring elongation, slows down impulsive force.
In the present invention, being arranged on the complete machine air bag bottom passenger cabin, this air bag can be caused danger at aircraft, the most earthward or open inflation time the water surface falls, absorbs aircraft energy and impact, ensures aircraft and the safety of occupant.
In the present invention, passenger airbag.The i.e. inside crew module has interior passenger airbag, has safety air bag outside outside crew module, can ensure crew module and occupant in certain speed, injured when colliding.
In the present invention, the support arm of main support system is the round tube of carbon fibre material, and outside puts the streamlined rent overcoat that subtracts and constitutes.Its internal pipeline can be used for laying power cable, controlling cable etc..
In the present invention, in underface or the surface of main ducted fan, being provided with fairshaped crew module, passenger rides on the seat in cabin；Having stick inside crew module, driver completes whole control actions of aircraft by stick.
In the present invention, center duct has ballistic support guard up and down, i.e. plays the effect supporting motor, has again and prevents flying bird from stepping on the effect clashing into propeller.
In the present invention, in the outermost of aircraft, having Intelligent anti-collision annular safety bar, safety pole is connected by spring with secondary duct support, inside bury foil gauge, safety pole deflection can be measured, and then draw stress size and orientation, and take corresponding safety measure, on the other hand, safety pole itself can also be by deformation energy-absorbing, it is ensured that the safety of aircraft, and aircraft pushes away barrier or an other frame aircraft.
The invention is not limited in aforesaid detailed description of the invention.The present invention expands to any new feature disclosed in this manual or any new combination, and the arbitrary new method that discloses or the step of process or any new combination.
Claims (10)
1. a riding type low latitude vertically taking off and landing flyer, including several secondary rotors of a center rotor and centrally disposed rotor surrounding, it is characterised in that including:
Described center rotor is that several rotors are connected with one heart and are integrated, and the direction of rotation of adjacent two rotors is contrary,
Being connected with outside the duct of center rotor and have several secondary duct supports, arrange a secondary rotor in each secondary duct support, described secondary rotor rotates around the junction point with secondary duct support, and described secondary duct support rotates around the junction point with center duct；
With the anticollision support of center rotor concentric, center rotor is arranged in the circumference of anticollision support with secondary rotor, is provided with damping spring between the inner side of described anticollision support and each secondary duct stent outer,
It is respectively disposed at the support that center rotor is upper and lower, the lower carriage of described center rotor connects a passenger cabin,
Connecting the cable of ground power supply system and passenger cabin, described passenger cabin is integrated with the electric power system of main duct and each secondary duct.
A kind of riding type low latitude the most according to claim 1 vertically taking off and landing flyer, it is characterised in that described passenger cabin is connected perpendicularly to the center of the duct lower carriage of center rotor.
A kind of riding type low latitude the most according to claim 2 vertically taking off and landing flyer, it is characterised in that include that four arc supports being evenly distributed on passenger cabin lateral surface, described cabin interior side face are provided with passenger airbag.
A kind of riding type low latitude the most according to claim 3 vertically taking off and landing flyer, it is characterised in that the bottom of described passenger cabin is provided with undercarriage, and undercarriage is connected with arc support.
A kind of riding type low latitude the most according to claim 4 vertically taking off and landing flyer, it is characterised in that described undercarriage includes four support arms, passes through hinge links between each support arm and arc support.
A kind of riding type low latitude the most according to claim 5 vertically taking off and landing flyer, it is characterised in that described support arm and arc support are provided with spring, and one end of spring is connected on support arm, and the other end is fixedly attached on arc support.
7. according to a kind of riding type low latitude vertically taking off and landing flyer described in claim 4 or 5 or 6, it is characterised in that be provided with complete machine air bag bottom passenger cabin.
A kind of riding type low latitude the most according to claim 1 vertically taking off and landing flyer, it is characterised in that described secondary rotor carries out arbitrarily rotating clockwise or between anticlockwise 0 ° to 90 ° around the junction point of secondary duct support.
A kind of riding type low latitude the most according to claim 1 vertically taking off and landing flyer, it is characterised in that described secondary duct support carries out arbitrarily rotating clockwise or between anticlockwise 0 ° to 90 ° around the junction point of center duct.
A kind of riding type low latitude the most according to claim 1 vertically taking off and landing flyer, it is characterised in that described secondary rotor is equidistant, uniform, be symmetrically distributed in the surrounding of center rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620021636.9U CN205469819U (en) | 2016-01-12 | 2016-01-12 | Manned type low latitude VTOL aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620021636.9U CN205469819U (en) | 2016-01-12 | 2016-01-12 | Manned type low latitude VTOL aircraft |
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| CN205469819U true CN205469819U (en) | 2016-08-17 |
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| CN201620021636.9U Active CN205469819U (en) | 2016-01-12 | 2016-01-12 | Manned type low latitude VTOL aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105480415A (en) * | 2016-01-12 | 2016-04-13 | 沈旭初 | Manned aircraft capable of realizing low-altitude vertical takeoff and landing |
| CN108725768A (en) * | 2018-05-30 | 2018-11-02 | 同济大学 | One kind being tethered at unmanned plane device |
| CN112550719A (en) * | 2020-12-17 | 2021-03-26 | 中国直升机设计研究所 | Electric vertical take-off and landing aircraft capable of separating lift force component |
-
2016
- 2016-01-12 CN CN201620021636.9U patent/CN205469819U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105480415A (en) * | 2016-01-12 | 2016-04-13 | 沈旭初 | Manned aircraft capable of realizing low-altitude vertical takeoff and landing |
| CN108725768A (en) * | 2018-05-30 | 2018-11-02 | 同济大学 | One kind being tethered at unmanned plane device |
| CN112550719A (en) * | 2020-12-17 | 2021-03-26 | 中国直升机设计研究所 | Electric vertical take-off and landing aircraft capable of separating lift force component |
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Effective date of registration: 20240410 Address after: 621052 No.6, south section of the Second Ring Road, Mianyang City, Sichuan Province Patentee after: Institute of aerospace technology, China Aerodynamics Research and Development Center Country or region after: China Address before: No. 42 Sandui Road, Fucheng District, Mianyang City, Sichuan Province, 621000 Patentee before: Shen Xuchu Country or region before: China Patentee before: OuYang Wei |