CN203439258U - Combined type rotor-wing aircraft - Google Patents
Combined type rotor-wing aircraft Download PDFInfo
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- CN203439258U CN203439258U CN201320372843.5U CN201320372843U CN203439258U CN 203439258 U CN203439258 U CN 203439258U CN 201320372843 U CN201320372843 U CN 201320372843U CN 203439258 U CN203439258 U CN 203439258U
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Abstract
The utility model relates to a combined type rotor-wing aircraft which comprises an aircraft main body, an energy device, an external connection opening and a control device, wherein the aircraft main body comprises a main propeller and a plurality of auxiliary propellers; the main propeller comprises main rotor wings I, main rotor wings II and a main duct; the main rotor wings I and the main rotor wings II are fixed in the main duct through a main duct supporting frame; a plurality of vertical connection rods are arranged on the part, which is positioned in the main duct, on the outer rim of the main duct supporting frame; the bottoms of the vertical connection rods are outwards and horizontally provided with cantilevers; the auxiliary propellers are arranged at the outer ends of the cantilevers. The combined type rotor-wing aircraft has the beneficial effects that due to the integration of flying modes of various rotor wings, the flying efficiency is greatly improved, the flexibility of the aircraft is greatly enhanced, and the flying stability and the reliability are greatly increased; by an advanced flying control mode, the multiple rotor wings can be controlled and adjusted at the same time, so that the control difficulty of the aircraft is greatly simplified, and the flying efficiency of the aircraft is improved.
Description
Technical field
The utility model relates to aircraft field, particularly relates to a kind of combined type rotor craft.
Background technology
For current rotor craft, generally be divided into single rotor, many rotors, the aircraft such as culvert type rotor, its various aircraft have the feature of self, as larger in load-carrying single rotor, efficiency is higher, many rotors are controlled flexible sensitive, culvert type rotor is safe and reliable, be subject to Turbulent Flow Effects less, but these rotor crafts have again the open defect of self, as dumb in single rotor, easy et out of order while being disturbed, many rotors efficiency is lower, environment in the time of cannot being applied to large load and long boat, duct aircraft is controlled difficulty, flight is in static indeterminacy state, easily break down.
Utility model content
The purpose of this utility model is to provide a kind of combined type rotor craft, to overcome currently available technology above shortcomings.
The purpose of this utility model is to be achieved through the following technical solutions:
A rotor craft, comprises aircraft body, energy source device, hard disk and control setup, and described aircraft body comprises main thruster and some auxiliary propellers, and described some auxiliary propellers are evenly arranged in main thruster outside; Described main thruster comprises main rotor one, main rotor two and main duct, described main rotor one and main rotor two are fixed in main duct by main duct bracing frame, the outer rim of described main duct bracing frame is positioned at main duct inside and is arranged with some vertical pipe links, the bottom of described vertical pipe link all outside level is provided with cantilever, and the outer end of described cantilever is equipped with auxiliary propeller; Described auxiliary propeller comprises auxiliary rotor, auxiliary support frame and auxiliary duct, and described auxiliary rotor is fixed in auxiliary duct by auxiliary support frame.
Further, described auxiliary rotor, auxiliary support frame and the equal horizontal distribution of auxiliary duct.
Further, described main rotor one and main rotor two are centered close on same vertical axis, and the rotation direction of described main rotor one and main rotor two is contrary, and lift all makes progress.
Further, described energy source device comprises the airborne energy and airborne energy source interface.
Further, described control setup comprises homing advice and flight control unit.
Further, described main rotor one, main rotor two and auxiliary rotor are all furnished with motor, and described motor is all connected with control setup with energy source device.
The beneficial effects of the utility model are: compared with prior art, greatly improved the full landform carrying capacity of platform, and the combined efficiency of platform, specifically have the following advantages: adopted the comprehensive of multiple rotor flying mode, compare with traditional rotor craft, flight efficiency is greatly improved, and the alerting ability of aircraft is also greatly improved, and flight stability and reliability are also greatly improved; Adopt advanced flight mode, can a plurality of rotors controlled and be adjusted simultaneously, simplified greatly the control difficulty of aircraft, improved the flight efficiency of aircraft.
Accompanying drawing explanation
With reference to the accompanying drawings the utility model is described in further detail below.
Fig. 1 is the structural representation of a kind of combined type rotor craft described in the utility model embodiment;
Fig. 2 is the birds-eye view of a kind of combined type rotor craft described in the utility model embodiment;
Fig. 3 is the lateral plan of a kind of combined type rotor craft described in the utility model embodiment.
In figure:
1, main duct; 2, main duct bracing frame; 3, main rotor one; 4, main rotor two; 5, auxiliary rotor; 6, auxiliary support frame; 7, auxiliary duct; 8, vertical pipe link; 9, cantilever.
The specific embodiment
As Figure 1-3, a kind of combined type rotor craft described in the utility model embodiment, comprise aircraft body, energy source device, hard disk and control setup, described aircraft body comprises main thruster and some auxiliary propellers, and described some auxiliary propellers are evenly arranged in main thruster outside; Described main thruster comprises main rotor 1, main rotor 24 and main duct 1, described main rotor 1 and main rotor 24 are fixed in main duct 1 by main duct bracing frame 2, the outer rim of described main duct bracing frame 2 is positioned at main duct 1 inside and is arranged with some vertical pipe links 8, the bottom of described vertical pipe link 8 all outside level is provided with cantilever 9, and the outer end of described cantilever 9 is equipped with auxiliary propeller; Described auxiliary propeller comprises auxiliary rotor 5, auxiliary support frame 6 and auxiliary duct 7, and described auxiliary rotor 5 is fixed in auxiliary duct 7 by auxiliary support frame 6.Described auxiliary rotor 5, auxiliary support frame 6 and the equal horizontal distribution of auxiliary duct 7.Described main rotor 1 and main rotor 24 are centered close on same vertical axis, and the rotation direction of described main rotor 1 and main rotor 24 is contrary, and lift all makes progress.Described energy source device comprises the airborne energy and airborne energy source interface.Described control setup comprises homing advice and flight control unit.Described main rotor 1, main rotor 24 and auxiliary rotor 5 are all furnished with motor, and described motor is all connected with control setup with energy source device.
A kind of combined type rotor craft described in the utility model is preferred for the design of aerocraft, and for current rotor craft current situation, the utility model has carried out following improvement to prior art:
1), adopt single rotor, many rotors, duct aircraft mixed layout, aircraft central authorities adopt high efficiency main thruster, adopt many rotors to assist attitude adjustment around, reduce extraneous interference in air flow by culvert device simultaneously.
2), can pass through central main thruster, comprise single rotor, coaxial anti-oar, many rotors are the mode such as supercharging step by step, realizes the propelling of high-tensile strength effect ratio, has greatly improved the flight efficiency of aircraft.
3), by aircraft many rotors device around, comprise the rotor that is no less than 2, carry out the adjustment of actv. attitude, greatly increased the alerting ability of aircraft.
4), used duct airmanship, greatly reduced the impact of surrounding environment on aircraft, also reduced the problem of phase mutual interference between a plurality of screw propellers of aircraft.
5), adopted advanced aircraft control technology, can control initiatively and auxiliary propeller simultaneously.
Main rotor 1 in main thruster and the rotation direction of main rotor 24 are contrary, lift makes progress, and main thruster provides most of lift of aircraft, improve the whole efficiency of aircraft; Auxiliary propeller consists of many rotor flight devices, and the torsional moment between a plurality of rotors can be cancelled out each other, so that adjust the flight attitude of aircraft.
The energy source device of aircraft comprises the airborne energy and airborne energy source interface, both can directly energy source device be arranged on body, also can to aircraft, carry out energy resource supply by cable, microwave equal energy source type of transmission; The control setup of aircraft comprises Navigation Control Unit and flight control unit, controls respectively flight attitude and the flight path planning of aircraft; The hard disk of aircraft can be so that aircraft lifting multiple-task load.
The utility model is not limited to above-mentioned preferred forms; anyone can draw other various forms of products under enlightenment of the present utility model; no matter but do any variation in its shape or structure; every have identical with a application or akin technical scheme, within all dropping on protection domain of the present utility model.
Claims (7)
1. a combined type rotor craft, comprises aircraft body, energy source device, hard disk and control setup, and described aircraft body comprises main thruster and some auxiliary propellers, and described some auxiliary propellers are evenly arranged in described main thruster outside; It is characterized in that: described main thruster comprises main rotor one (3), main rotor two (4) and main duct (1), described main rotor one (3) and main rotor two (4) are fixed in main duct (1) by main duct bracing frame (2), the outer rim of described main duct bracing frame (2) is positioned at main duct (1) inside and is arranged with some vertical pipe links (8), described vertical pipe link (8) bottom all outside level is provided with cantilever (9), and the outer end of described cantilever (9) is equipped with described auxiliary propeller.
2. a kind of combined type rotor craft according to claim 1, it is characterized in that: described auxiliary propeller comprises auxiliary rotor (5), auxiliary support frame (6) and auxiliary duct (7), and described auxiliary rotor (5) is fixed in auxiliary duct (7) by auxiliary support frame (6).
3. a kind of combined type rotor craft according to claim 2, is characterized in that: described auxiliary rotor (5), auxiliary support frame (6) and auxiliary duct (7) be horizontal distribution all.
4. a kind of combined type rotor craft according to claim 3, it is characterized in that: described main rotor one (3) and main rotor two (4) are centered close on same vertical axis, the contrary and lift of the rotation direction of described main rotor one (3) and main rotor two (4) all makes progress.
5. a kind of combined type rotor craft according to claim 4, is characterized in that: described energy source device comprises the airborne energy and airborne energy source interface.
6. a kind of combined type rotor craft according to claim 5, is characterized in that: described control setup comprises homing advice and flight control unit.
7. a kind of combined type rotor craft according to claim 6, is characterized in that: described main rotor one (3), main rotor two (4) and auxiliary rotor (5) are all furnished with motor, and described motor is all connected with described control setup with described energy source device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320372843.5U CN203439258U (en) | 2013-06-27 | 2013-06-27 | Combined type rotor-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320372843.5U CN203439258U (en) | 2013-06-27 | 2013-06-27 | Combined type rotor-wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203439258U true CN203439258U (en) | 2014-02-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320372843.5U Expired - Lifetime CN203439258U (en) | 2013-06-27 | 2013-06-27 | Combined type rotor-wing aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN203439258U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103318406A (en) * | 2013-06-27 | 2013-09-25 | 长源动力（北京）科技有限公司 | Composite rotor craft |
| CN104139854A (en) * | 2014-08-14 | 2014-11-12 | 西北工业大学 | Lift enhancement and stability augmentation integrated pneumatic rotor wing |
| CN104290904A (en) * | 2014-10-11 | 2015-01-21 | 江苏艾锐泰克无人飞行器科技有限公司 | Multi-rotor type aircraft |
| CN104554720A (en) * | 2014-12-31 | 2015-04-29 | 昆明天龙经纬电子科技有限公司 | Compound power helicopter |
| CN105034729A (en) * | 2015-07-21 | 2015-11-11 | 中国科学院自动化研究所 | Deformable multi-mode ground and air flying robot |
| CN105035313A (en) * | 2015-06-30 | 2015-11-11 | 北京航空航天大学 | Rotated quadrotor |
| GB2529896A (en) * | 2014-09-05 | 2016-03-09 | Richard Nathan Hadder | Multirotor |
-
2013
- 2013-06-27 CN CN201320372843.5U patent/CN203439258U/en not_active Expired - Lifetime
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103318406A (en) * | 2013-06-27 | 2013-09-25 | 长源动力（北京）科技有限公司 | Composite rotor craft |
| CN104139854A (en) * | 2014-08-14 | 2014-11-12 | 西北工业大学 | Lift enhancement and stability augmentation integrated pneumatic rotor wing |
| CN104139854B (en) * | 2014-08-14 | 2016-03-02 | 西北工业大学 | The pneumatic rotor of a kind of lift-rising, the steady integration of increasing |
| GB2529896A (en) * | 2014-09-05 | 2016-03-09 | Richard Nathan Hadder | Multirotor |
| GB2529896B (en) * | 2014-09-05 | 2016-09-14 | Nathan Hadder Richard | Multirotor |
| CN104290904A (en) * | 2014-10-11 | 2015-01-21 | 江苏艾锐泰克无人飞行器科技有限公司 | Multi-rotor type aircraft |
| CN104554720A (en) * | 2014-12-31 | 2015-04-29 | 昆明天龙经纬电子科技有限公司 | Compound power helicopter |
| CN105035313A (en) * | 2015-06-30 | 2015-11-11 | 北京航空航天大学 | Rotated quadrotor |
| CN105035313B (en) * | 2015-06-30 | 2017-03-08 | 北京航空航天大学 | One kind is verted quadrotor |
| CN105034729A (en) * | 2015-07-21 | 2015-11-11 | 中国科学院自动化研究所 | Deformable multi-mode ground and air flying robot |
| CN105034729B (en) * | 2015-07-21 | 2017-05-24 | 中国科学院自动化研究所 | Deformable multi-mode ground and air flying robot |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140219 |
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| CX01 | Expiry of patent term |