CN105253288A - Double-seater power-driven ultra-light sport aircraft made of composite materials - Google Patents
Double-seater power-driven ultra-light sport aircraft made of composite materials Download PDFInfo
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- CN105253288A CN105253288A CN201510585677.0A CN201510585677A CN105253288A CN 105253288 A CN105253288 A CN 105253288A CN 201510585677 A CN201510585677 A CN 201510585677A CN 105253288 A CN105253288 A CN 105253288A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention provides a double-seater power-driven ultra-light sport aircraft made of composite materials to mainly overcome the problems of high cost, pollution to the environment and great noise of conventional light aircrafts. The body, wings, empennage and undercarriage of double-seater power-driven ultra-light sport aircraft employ a composite material structure with carbon fiber and glass fiber as main raw materials. A power system of the sport aircraft employs a rare earth permanent-magnet synchronous motor to provide power; the power source of the power system is a lithium battery pack which is arranged in a battery cabin; a propeller is connected with the motor; and the motor and a motor controller are both placed in an electric propulsion unit cabin. The sport aircraft provided by the invention has the advantages of a reasonable structure, a few operation and transmission parts, high reliability, a high protection grade due to the totally-enclosed structure, high efficiency, as high as 94%, strong power and easiness in operation. Since the sport aircraft employs the novel clean energy lithium batteries, operation cost of the sport aircraft is low, and the problems of noise pollution and greenhouse effect caused by emission of a great amount of exhaust gas during flying of conventional fuel light aircrafts in the sky are overcome. The integral cabin of the sport aircraft has good structural strength, is comfortable and presents a wide visual field, and the sport aircraft is extensively applicable to fields like passenger transport, agriculture, geological prospecting and emergency and disaster relief.
Description
Technical field
The present invention relates to a kind of electronic manned microlight-type sport plane, especially a kind of composite material two-seater electric airplane, belongs to field of aerospace technology.
Background technology
From the U.S. that General Aviation industry is the most flourishing, the general-purpose aircraft of 70% is middle-size and small-size personal aircraft.Now, 10,000 yuan of two-seater aviette familiarization flights carried out four hours are spent not to be strange thing at home.Therefore, the aviette of research and development 4 and following rank is first-selected.The low altitude airspace wide from America and Europe is different, and China's low altitude airspace independently exists mainly with small size.Simultaneously, by the impact of high ferro, express highway and Regional Aviation, navigation transport living space is narrow and small, personal aircraft in China mainly based on the coach of this little voyage, multi rack time, amusement flight and nearly way ferry flight, not urgent to demand when large voyage and long boat, therefore electronic aviette can meet above-mentioned requirements substantially.
In national strategy new industry is listed General Aviation industry by China.State Council's in-depth low altitude airspace administrative reform, low altitude airspace is decontroled gradually.Revision CCAR61 portion of CAAC, up-to-date proposition campaign driver's license, lists Under The Revitalization Policy of Northeast China Industrial Base plan in as the industry of giving priority to, and these opportunity intense stimulus the demand of market to general-purpose aircraft.
With the development of China's General Aviation industry, the demand of aviator will be a large amount of and urgent, flight driving school will rapid emergence, light-weight electric aircraft because of features such as its acquisition cost are low, operation cost is low and easy to maintenance, be applicable to very much driving school purchase in a large number for move according to and the training of private photograph.
Summary of the invention
The present invention is for the purpose of solving the problem, mainly solve high, the contaminated environment of manufacturing cost that prior art exists and the large problem of noise, and provide a kind of composite material two-seater rational in infrastructure, that applicability is good electronic manned microlight-type sport plane, to meet the demand of people.
For achieving the above object, the technical solution used in the present invention is: the electronic microlight-type sport plane of composite material two-seater, and aircaft configuration adopts the composite structure based on carbon fiber and glass fibre, and it comprises fuselage, wing, empennage and alighting gear.It also comprises aircraft power system, described aircraft power system take rare-earth permanent-magnet synchronous motor as power, and propulsion source is lithium cell group, and lithium cell group is located in battery flat, screw propeller is connected with electrical motor, and electrical motor and electric machine controller are all placed in electric propulsion device cabin.Described wing adopts the two section wing-like of high aspect ratio, structure by main wing, aileron and spoiler three part form.
Described fuselage comprises battery flat, electric propulsion device cabin, fireproof brickwork, windscreen, window, passenger cabin, fuselage skin, bulkhead and fixed fin etc.Above-mentioned fireproof brickwork is arranged between electric propulsion device cabin and passenger cabin, play fire prevention and heat-blocking action, thus can actv. protection aircrew safety; Above-mentioned bulkhead, by glueing joint, is arranged on aft body inside, and actv. strengthens the structural strength of aft body; Above-mentioned windscreen is arranged on the fuselage in passenger cabin dead ahead, is fixed by rivet; Above-mentioned window is arranged on the fuselage of the passenger cabin back upper place being provided with pedal and jociey stick, is fixed by rivet; Above-mentioned fuselage skin and fixed fin adopt one-body molded.
Described battery flat is arranged on the back lower place of passenger cabin.
Described wing adopts high aspect ratio high mounted wing, T-tail, front three-point fixed landing gear, preposition screw propeller, and the layout structure form opened the door in two-seater both sides.Above-mentioned main wing structure comprises wing cover, spar, Hou Qiang, root, common rib etc.; Above-mentioned root splicing is arranged on outermost; Above-mentioned spoiler is arranged between spar and rear wall, in aircraft landing process, plays a part deceleration; Above-mentioned common rib is inner at wing cover by glueing joint distributing installation, and actv. supports wing cover; Above-mentioned rear wall is connected with aileron by hinge; Above-mentioned tail structure comprises horizontal tail stabilator, elevating rudder and yaw rudder.
Described yaw rudder is connected with fixed fin by hinge.
Described elevating rudder is connected with horizontal tail stabilator by hinge.
Described horizontal tail stabilator is arranged on the upside of fixed fin by attaching parts.
Described alighting gear is made up of nose-gear and main landing gear two parts.Nose-gear adopts spring shock absorption form, has ground taxi turning function, links with yaw rudder; Main landing gear adopts leaf spring damping form, has brake function during ground taxi.Above-mentioned nose-gear is arranged on forebody, and main landing gear is arranged on the fuselage bottom of below on rear side of passenger cabin by attaching parts.
Described aircraft power system mainly comprises electrical motor, electric machine controller, lithium cell group and screw propeller.Electrical motor and electric machine controller are all placed in electric propulsion device cabin; Lithium cell group is placed in battery flat; Screw propeller is connected with electrical motor.
Beneficial effect of the present invention and feature:
1, take rare-earth permanent-magnet synchronous motor as power, electric machine structure is simple, running and drive disk assembly few, reliability is high and be full-closed structure, and degree of protection is high, and its efficiency can up to 94%, specific power greatly, powerful, simple to operate.
2, adopting its operating cost of new cleaning fuel lithium cell low, solve the green-house effect that when existing fuel oil aviette flies on high, discharge large quantity of exhaust gas produces, and the present invention there is no dusty gas to discharge when flying, little to environmental concerns; In addition, China is densely populated, and fuel oil flies the larger noise emission of Opportunity formation, and the invention solves the large problem of existing aviette noise.
3, the housing construction of the present invention 90% adopts the full composite material manufacture based on carbon fiber and glass fibre, and it is rational in infrastructure, profile streamline, smooth surface, life-span length and easy care.
4, integral type cockpit structure, structural strength is good, attractive in appearance, and seat design meets human engineering, and back of seat angle is 26 °, ride comfort, and the passenger cabin visual field is broad, can be widely used in the fields such as air transport, agricultural, geoexploration and the strong dangerous disaster relief.
Accompanying drawing explanation
Fig. 1 is aircraft front view (omitting right side wing).
Fig. 2 is the left view of Fig. 1.
Fig. 3 is airframe structure figure.
Fig. 4 is wing structure arrangement plan.
Number in the figure represents: 1, electrical motor; 2, electric machine controller; 3, pedal; 4, jociey stick; 5, battery flat; 6, aileron; 7, spoiler; 8, horizontal tail stabilator; 9, elevating rudder; 10, electric propulsion device cabin; 11, fireproof brickwork; 12, windscreen; 13, window; 14, passenger cabin and hatch door; 15, fuselage skin; 16, bulkhead; 17, vertical fin stabilator; 18, spar; 19, root; 20, common rib; 21, wing cover; 22, Hou Qiang; 23, yaw rudder; 24, nose-gear; 25, main landing gear; 26, screw propeller.
Detailed description of the invention
Embodiment
With reference to Fig. 1-Fig. 4, the electronic microlight-type sport plane of composite material two-seater, aircaft configuration adopts the composite material based on carbon fiber and glass fibre, and it mainly comprises fuselage, wing, empennage and alighting gear.It also comprises aircraft power system, and this system take rare-earth permanent-magnet synchronous motor as power, and propulsion source is lithium cell group, and lithium cell group is located in battery flat 5.
Described fuselage comprises battery flat 5, electric propulsion device cabin 10, fireproof brickwork 11, windscreen 12, window 13, passenger cabin 14, fuselage skin 15, bulkhead 16 and fixed fin 17 etc.
Above-mentioned fireproof brickwork 11 is arranged between electric propulsion device cabin 10 and passenger cabin 14, play fire prevention and heat-blocking action, thus can actv. protection aircrew safety;
Above-mentioned bulkhead 16, by glueing joint, is arranged on aft body inside, and actv. strengthens the structural strength of aft body;
Above-mentioned windscreen 12 is arranged on the fuselage in passenger cabin 14 dead ahead, is fixed by rivet; Above-mentioned window 13 is arranged on the fuselage of passenger cabin 14 back upper place being provided with pedal 3 and jociey stick 4, is fixed by rivet;
Above-mentioned fuselage skin 15 and fixed fin 17 adopt one-body molded.
Described battery flat is arranged on the back lower place of passenger cabin 14.
Described wing adopts the two section wing-like of high aspect ratio, and structure is made up of main wing, aileron 6 and spoiler 7 three part.
Above-mentioned main wing structure comprises wing cover 21, spar 18, rear wall 22, root 19, common rib 20 etc.; Above-mentioned root 19 splicing is arranged on outermost;
Above-mentioned spoiler 7 is arranged between spar 18 and rear wall 22, in aircraft landing process, plays a part deceleration;
Above-mentioned common rib 20 is inner at wing cover 21 by glueing joint distributing installation, and actv. supports wing cover 21;
Above-mentioned aileron 6 is connected with rear wall 22 by hinge.Above-mentioned tail structure comprises horizontal tail stabilator 8, elevating rudder 9 and yaw rudder 23.Described yaw rudder 23 is connected with fixed fin 17 by hinge; Described elevating rudder 9 is connected with horizontal tail stabilator 8 by hinge; Described horizontal tail stabilator 8 is arranged on the upside of fixed fin 17 by attaching parts.
Above-mentioned alighting gear is made up of nose-gear 24 and main landing gear 25 two parts.Nose-gear 24 adopts spring shock absorption form, has ground taxi turning function, links with yaw rudder; Main landing gear 25 adopts leaf spring damping form, has brake function during ground taxi.Above-mentioned nose-gear 24 is arranged on forebody, and main landing gear 25 is arranged on the fuselage bottom of below on rear side of passenger cabin 14 by attaching parts.
Described aircraft power system mainly comprises electrical motor 1, electric machine controller 2, lithium cell group 5 and screw propeller 26.Electrical motor 1 and electric machine controller 2 are all placed in electric propulsion device cabin 10; Lithium cell group is placed in battery flat 5; Screw propeller 26 is connected with electrical motor 1.
The present invention possesses efficient aerodynamic configuration, and pneumatic efficiency is high, and resistance is little, and actual measurement 1ift-drag ratio reaches 22, and gliding ability is good, and stalling speed is low, and maneuvering performance is good, flight safety, and aircraft aerodynamic arrangement and performance perameter are respectively in table 1, table 2 and table 3:
Table 1 overall aircraft parameter
Table 2 aerodynamic arrangement parameter
Table 3 aeroplane performance parameter
Maneuvering system of the present invention adopts manual operation scheme, is divided into primary control circuit and secondary control system.Primary control circuit is that two jociey stick is handled side by side, there are jociey stick and the pedal of two cover interlocks, jociey stick operate lifting rudder and aileron movement, pedal steering rudder kick and Nose Wheel Steering, all rudder faces are all handled by push-and-pull cable wire, and secondary control system is by push-and-pull cable control flaps.
Claims (5)
1. the electronic microlight-type sport plane of composite material two-seater, comprise fuselage, wing, empennage and alighting gear, also comprise aircraft power system, it is characterized in that: described aircaft configuration, that is: fuselage, wing, empennage and alighting gear adopt the composite structure based on carbon fiber and glass fibre; Described aircraft power system take rare-earth permanent-magnet synchronous motor as power, and propulsion source is lithium cell group, and lithium cell group is located in battery flat, and screw propeller is connected with electrical motor, and electrical motor and electric machine controller are all placed in electric propulsion device cabin; Described wing adopts the two section wing-like of high aspect ratio, structure by main wing, aileron and spoiler three part form.
2. the electronic microlight-type sport plane of composite material two-seater as claimed in claim 1, it is characterized in that: described fuselage comprises battery flat, electric propulsion device cabin, fireproof brickwork, windscreen, window, passenger cabin, fuselage skin, bulkhead and fixed fin, and above-mentioned fireproof brickwork is arranged between electric propulsion device cabin and passenger cabin; Above-mentioned bulkhead, by glueing joint, is arranged on aft body inside, and actv. strengthens the structural strength of aft body; Above-mentioned windscreen is arranged on the fuselage in passenger cabin dead ahead, is fixed by rivet; Above-mentioned window is arranged on the fuselage of the passenger cabin back upper place being provided with pedal and jociey stick, is fixed by rivet; Above-mentioned fuselage skin and fixed fin adopt one-body molded; Described battery flat is arranged on the back lower place of passenger cabin.
3. the electronic microlight-type sport plane of composite material two-seater as claimed in claim 1, is characterized in that: it adopts high aspect ratio high mounted wing, T-tail, front three-point fixed landing gear, preposition screw propeller, and the layout structure form opened the door in two-seater both sides.
4. the electronic microlight-type sport plane of composite material two-seater as claimed in claim 1, is characterized in that: described main wing structure comprises wing cover, spar, Hou Qiang, root, common rib etc.; Above-mentioned root splicing is arranged on outermost; Above-mentioned spoiler is arranged between spar and rear wall; Above-mentioned common rib is inner at wing cover by glueing joint distributing installation, and actv. supports wing cover; Above-mentioned aileron is connected with rear wall by hinge, and above-mentioned tail structure comprises horizontal tail stabilator, elevating rudder and yaw rudder, and described yaw rudder is connected with fixed fin by hinge; Described elevating rudder is connected with horizontal tail stabilator by hinge; Described horizontal tail stabilator is arranged on the upside of fixed fin by attaching parts.
5. the electronic microlight-type sport plane of composite material two-seater as claimed in claim 1, it is characterized in that: described alighting gear is made up of nose-gear and main landing gear two parts, nose-gear adopts spring shock absorption form, has ground taxi turning function, links with yaw rudder; Main landing gear adopts leaf spring damping form, and have brake function during ground taxi, above-mentioned nose-gear is arranged on forebody, and main landing gear is arranged on the fuselage bottom of below on rear side of passenger cabin by attaching parts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510585677.0A CN105253288A (en) | 2015-09-15 | 2015-09-15 | Double-seater power-driven ultra-light sport aircraft made of composite materials |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510585677.0A CN105253288A (en) | 2015-09-15 | 2015-09-15 | Double-seater power-driven ultra-light sport aircraft made of composite materials |
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| CN105253288A true CN105253288A (en) | 2016-01-20 |
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| CN201510585677.0A Pending CN105253288A (en) | 2015-09-15 | 2015-09-15 | Double-seater power-driven ultra-light sport aircraft made of composite materials |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106863941A (en) * | 2016-12-30 | 2017-06-20 | 易瓦特科技股份公司 | Fixed-wing unmanned plane body and its manufacture method |
| CN109573033A (en) * | 2018-12-29 | 2019-04-05 | 东莞市光点电子科技有限公司 | A kind of unmanned plane with high glide ratio fuselage |
| CN110329519A (en) * | 2019-07-05 | 2019-10-15 | 酷黑科技（北京）有限公司 | A kind of engine room structure of aircraft, aircraft and hovercar |
| CN111252256A (en) * | 2019-12-31 | 2020-06-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Electric aircraft system based on battery encapsulation |
| CN113955071A (en) * | 2021-10-09 | 2022-01-21 | 中电科芜湖通用航空产业技术研究院有限公司 | Aircraft fuselage, forming method thereof and aircraft |
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| RU122981U1 (en) * | 2012-08-07 | 2012-12-20 | Артем Владимирович Пигин | COMPACT AIRCRAFT |
| CN205059988U (en) * | 2015-09-15 | 2016-03-02 | 辽宁通用航空研究院 | Electronic microlight -type sport plane of combined material two -seater |
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- 2015-09-15 CN CN201510585677.0A patent/CN105253288A/en active Pending
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106863941A (en) * | 2016-12-30 | 2017-06-20 | 易瓦特科技股份公司 | Fixed-wing unmanned plane body and its manufacture method |
| CN106863941B (en) * | 2016-12-30 | 2019-03-12 | 易瓦特科技股份公司 | Fixed-wing unmanned plane body and its manufacturing method |
| CN109573033A (en) * | 2018-12-29 | 2019-04-05 | 东莞市光点电子科技有限公司 | A kind of unmanned plane with high glide ratio fuselage |
| CN110329519A (en) * | 2019-07-05 | 2019-10-15 | 酷黑科技（北京）有限公司 | A kind of engine room structure of aircraft, aircraft and hovercar |
| CN110329519B (en) * | 2019-07-05 | 2023-09-22 | 酷黑科技（北京）有限公司 | Cabin structure of aircraft, aircraft and aerocar |
| CN111252256A (en) * | 2019-12-31 | 2020-06-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Electric aircraft system based on battery encapsulation |
| CN113955071A (en) * | 2021-10-09 | 2022-01-21 | 中电科芜湖通用航空产业技术研究院有限公司 | Aircraft fuselage, forming method thereof and aircraft |
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