CN1876495A - Coaxial double-oared self-spinning wing aircraft with fixed wing - Google Patents
Coaxial double-oared self-spinning wing aircraft with fixed wing Download PDFInfo
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- CN1876495A CN1876495A CN 200610028280 CN200610028280A CN1876495A CN 1876495 A CN1876495 A CN 1876495A CN 200610028280 CN200610028280 CN 200610028280 CN 200610028280 A CN200610028280 A CN 200610028280A CN 1876495 A CN1876495 A CN 1876495A
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Abstract
The invention discloses a coaxial dual-screw self-spin aircraft, with fixed wings, wherein it is formed by main body, landing gear, upper and lower rotors, pushing screw, tail wing, seat, power driving and controlling device; it is characterized in that: the left and right sides of main body under the gravity center are symmetry distributed with a couple of fixed wings, to supply the lifting force more than 80% for the horizontal motion of aircraft, to reduce the dependence on the screw and the demand for rotor area and speed; therefore, the screw is allowed to rotate without power supply, to reduce the flying resistance, simplify the structure, reduce the energy consumption and improve the flying speed; and in accident, the fixed wings can supply lifting force to control the aircraft to glide.
Description
Technical field
The present invention relates to a kind of aviation aircraft, particularly a kind of coaxial pair of oar self rotor aircraft with fixed-wing.
Background technology
The helighro two big classes that need the fixed wing aircraft of equivalent length private track cooperation when popular aircraft mainly contains landing in the world today and do not need fixing special-purpose landing site to cooperate.The characteristics of fixed wing aircraft are that fuselage is huger, and flight relatively steadily, safety, peace and quiet and speed is fast, and the occupant is few as for 1 people, as many as hundreds of people.The characteristics of helighro are that fuselage is less relatively, flexible property is strong, can be in the landing of multiple place, can also carry out such as aerial vertical flight, outstanding left alone without help, multiple special flights such as side flies, inverted flight, orbit, its U.S. weak point is that structure is very complicated, operation easier is big, handling labor is heavy, operating costs is high, in addition, this aircraft is because structural relation, no emergency escape facility and gliding flight function, thereby in flight way just in case when mechanical breakdown takes place, persons on board are difficult to survive.At complex structure, the heavy problem of handling labor, in recent years, the scientific research personnel has developed from autogiro on the helighro basis, the characteristics of this aircraft are relatively simple for structure, thereby fault rate is also low, except that vertical takeoff and landing and the hovering fully, substantially the some other function that has helighro, but speed is still slower, still has when mechanical breakdown takes place contingency in the flight way problem that persons on board are difficult to survive.So also owe desirable from safety and point of view of practicability.Ground communications is more and more quick now, express network extends in all direction, and the moving velocity of automobile is very usual by 120KM/ hour to 200KM/ hour, so in the short range traffic, low-tach aircraft can not satisfy people's fast pace requirement, thereby does not have the market competitiveness.Market press for a kind of simple in structure, be easy to control, flying speed is fast, safety good, can vertical takeoff and landing, have a smooth flight and quiet novel small aircraft.
Summary of the invention
The objective of the invention is to provide a kind of simple in structure, be easy to control, flying speed is fast, safety good, have a smooth flight and coaxial pair of oar self rotor aircraft of quietly novel band fixed-wing.
The present invention is achieved in that coaxial pair of oar self rotor aircraft of band fixed-wing is mainly by fuselage, the support that rises and falls, rotor, propelling screws, empennage, passenger seat, power driven and control mechanism constitute up and down.Fuselage is the such small-sized fuselage of similar helighro, the support that rises and falls is arranged on the fuselage of bottom, aircraft center of gravity position, rotor is arranged on back up and down, propelling screws is arranged on fuselage afterbody, empennage is arranged on the afterbody of fuselage, and passenger seat, power driven and regulating control mechanism are arranged in the fuselage chamber.It is characterized in that on the left and right side of aircraft center of gravity position lower fuselage, also being symmetrically arranged with a pair of fixed-wing.
During work, coaxial pair of oar self rotor aircraft at band fixed-wing of the present invention rise to certain altitude, finish and begin to carry out translation flight after taking off, and fly when reaching certain speed when translation, can rely on fixed-wing and carry out translation flight from the common lift that produces of rotor, wherein the lift more than 80% is from fixed-wing.At this moment, driving engine can stop the power supply of rotor up and down, and rotor continues spin under action of inertia up and down.
Coaxial pair of oar self rotor aircraft of band fixed-wing can only rely on driving engine to flow to the dynamically working of propelling screws, by propelling screws aircraft pushed ahead apace.Under this mode of operation, up and down rotor be in inertia spin and by oncoming high velocity air " push away " moving, ceaselessly driven the rotary work state.The resistance that aircraft translation when flight produced reduces, and has not only helped energy savings, but also has helped improving flying speed.Resistance during method change of flight device translation flight that can be by the spin rotating speed of rotor is up and down artificially controlled, thereby change of flight speed.
Coaxial pair of oar self rotor aircraft based on the band fixed-wing of the present invention of above-mentioned design, because increase is provided with a pair of fixed-wing wing in the fuselage both sides, the lift of 80%-100% is provided for aircraft in the time of can moving in the horizontal direction, so reduced aircraft to obtain the dependence of lift by the rotor rotation, reduced rotor area and rotating speed requirement, allow rotor under the situation of unpowered supply with controlled spin rotating speed rotation, thereby help simplified structure, cut down the consumption of energy; And because fixed-wing can provide most lift, when mechanical breakdown takes place contingency in flight course, can controlling aircraft do gliding flight, help improving the safety control of aircraft; Simultaneously, owing to rotor about aircraft is in the horizontal flight process is in controlled spin mode of operation, resistance is very little, helps reducing noise and improves flying speed.Indulge the above, coaxial pair of oar self rotor aircraft of band fixed-wing of the present invention compare with coaxial pair of oar aircraft of prior art have that structure is simpler, flying speed is faster, work controllability and safety is stronger, energy consumption is lower, thereby have significant technical advance, very good economy and very strong practicality.
Description of drawings
Accompanying drawing is the structural representation of the embodiment of the invention.
Among the figure:
1. fuselage 2. support rotor 4. propelling screws about in the of 3. that rise and fall
5. empennage 6. passenger seats, 7. power drivens and control mechanism 8. fixed-wings
The specific embodiment
Below in conjunction with accompanying drawing and exemplary embodiments the present invention is further described.
In the accompanying drawings, coaxial pair of oar self rotor aircraft of band fixed-wing is mainly by fuselage 1, the support 2 that rises and falls, rotor 3, propelling screws 4, empennage 5, passenger seat 6, power driven and control mechanism 7 constitute up and down.Wherein: fuselage 1 is the such small-sized fuselage of similar helighro, the support 2 that rises and falls is arranged on the fuselage of bottom, aircraft center of gravity position, rotor 3 is arranged on back, propelling screws 4 is arranged on fuselage afterbody, empennage 5 is arranged on the afterbody of fuselage, and passenger seat 6 and power driven and control mechanism 7 are arranged in the fuselage chamber.In addition, on the left and right side of aircraft center of gravity position lower fuselage 1, be symmetrically arranged with a pair of fixed-wing 8.
Claims (1)
1. coaxial pair of oar self rotor aircraft with fixed-wing, mainly by fuselage (1), support (2) rises and falls, rotor (3) up and down, propelling screws (4), empennage (5), passenger seat (6), power driven and regulating control mechanism (7) constitute, fuselage (1) is the such small-sized fuselage of similar helighro, the support (2) that rises and falls is arranged on the fuselage of bottom, aircraft center of gravity position, rotor (3) is arranged on back, propelling screws (4) is arranged on fuselage afterbody, empennage (5) is arranged on afterbody, passenger seat (6) and power driven and control mechanism (7) are arranged in the fuselage chamber, it is characterized in that being symmetrically arranged with on the left and right side of aircraft center of gravity position lower fuselage (1) a pair of fixed-wing (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610028280 CN1876495A (en) | 2006-06-28 | 2006-06-28 | Coaxial double-oared self-spinning wing aircraft with fixed wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610028280 CN1876495A (en) | 2006-06-28 | 2006-06-28 | Coaxial double-oared self-spinning wing aircraft with fixed wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1876495A true CN1876495A (en) | 2006-12-13 |
Family
ID=37509103
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200610028280 Pending CN1876495A (en) | 2006-06-28 | 2006-06-28 | Coaxial double-oared self-spinning wing aircraft with fixed wing |
Country Status (1)
| Country | Link |
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| CN (1) | CN1876495A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101891016A (en) * | 2009-05-19 | 2010-11-24 | 孙为红 | Invisible autogyro |
| CN101417182B (en) * | 2007-09-15 | 2013-04-17 | 美泰有限公司 | Toy helicopter having a stabilizing bumper |
| CN103395492A (en) * | 2013-07-10 | 2013-11-20 | 中国航天空气动力技术研究院 | STOL (short take off and landing) unmanned aerial vehicle with unpowered-driven rotor wing |
| CN103708029A (en) * | 2014-01-06 | 2014-04-09 | 姚昊 | Light aircraft |
| CN105173070A (en) * | 2015-07-30 | 2015-12-23 | 北京航空航天大学 | Combined coaxial unmanned helicopter |
| CN109229360A (en) * | 2018-10-30 | 2019-01-18 | 南京航空航天大学 | Scissor DCB Specimen seesaw type autogyro |
| CN110294115A (en) * | 2019-08-07 | 2019-10-01 | 天津黎明时代信息技术有限公司 | Coaxial double-propeller propulsion type tail rotor unmanned helicopter for logistics transportation |
| CN113401341A (en) * | 2021-08-05 | 2021-09-17 | 北京航空航天大学 | High-speed coaxial unmanned helicopter additionally provided with double tail thrusters |
| WO2022037450A1 (en) * | 2020-08-17 | 2022-02-24 | 加拿大轻型航空有限公司 | Autogyro aircraft having combination of multiple rotors |
-
2006
- 2006-06-28 CN CN 200610028280 patent/CN1876495A/en active Pending
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101417182B (en) * | 2007-09-15 | 2013-04-17 | 美泰有限公司 | Toy helicopter having a stabilizing bumper |
| CN101891016A (en) * | 2009-05-19 | 2010-11-24 | 孙为红 | Invisible autogyro |
| CN103395492A (en) * | 2013-07-10 | 2013-11-20 | 中国航天空气动力技术研究院 | STOL (short take off and landing) unmanned aerial vehicle with unpowered-driven rotor wing |
| CN103395492B (en) * | 2013-07-10 | 2016-03-02 | 中国航天空气动力技术研究院 | A kind of unpowered short take-off and landing (STOL) unmanned plane turning rotor |
| CN103708029A (en) * | 2014-01-06 | 2014-04-09 | 姚昊 | Light aircraft |
| CN105173070A (en) * | 2015-07-30 | 2015-12-23 | 北京航空航天大学 | Combined coaxial unmanned helicopter |
| CN105173070B (en) * | 2015-07-30 | 2018-08-14 | 北京航空航天大学 | A kind of combined type unmanned helicopter |
| CN109229360A (en) * | 2018-10-30 | 2019-01-18 | 南京航空航天大学 | Scissor DCB Specimen seesaw type autogyro |
| CN110294115A (en) * | 2019-08-07 | 2019-10-01 | 天津黎明时代信息技术有限公司 | Coaxial double-propeller propulsion type tail rotor unmanned helicopter for logistics transportation |
| WO2022037450A1 (en) * | 2020-08-17 | 2022-02-24 | 加拿大轻型航空有限公司 | Autogyro aircraft having combination of multiple rotors |
| CN113401341A (en) * | 2021-08-05 | 2021-09-17 | 北京航空航天大学 | High-speed coaxial unmanned helicopter additionally provided with double tail thrusters |
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