CN104494813A - Aircraft with flat rotating blade thrusting device - Google Patents
Aircraft with flat rotating blade thrusting device Download PDFInfo
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- CN104494813A CN104494813A CN201410769702.6A CN201410769702A CN104494813A CN 104494813 A CN104494813 A CN 104494813A CN 201410769702 A CN201410769702 A CN 201410769702A CN 104494813 A CN104494813 A CN 104494813A
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Abstract
The invention discloses an aircraft with a flat rotating blade thrusting device, belonging to the technical field of aviation. The aircraft mainly comprises an aircraft body, a rear wing, a left thrusting device, a right thrusting device, a left wing, a right wing and an undercarriage, wherein the aircraft body is internally matched with an operating system and an energy supply system; the left thrusting device and the right thrusting device are same in structure and working principle and are symmetrically arranged at a left gap and a right gap; the right thrusting device comprises an engine, a main shaft, a central half-tooth gear and three or four same rotating blades; each rotating blade comprises an arm shaft, a blade shaft, a center-near gear, an arm shaft sleeve, a center-far gear, a blade gear and a blade; the blade of the rotating blade and the arm shaft are located in the same vertical plane in the horizontal direction when the arm shaft of the rotating blade of the right thrusting device is located at the horizontal position at the right side of the main shaft; the transmission ratio of the central half-tooth gear to the blade gear is 1:1; and the left thrusting device and the right thrusting device can be used for accelerating air flows on the upper surfaces of the wings and are beneficial for the wings to generate lifting forces. The aircraft is relatively high in efficiency, high in maneuverability and good in safety.
Description
Technical field
Adopt an aircraft for dull and stereotyped revolving vane thrust unit, belong to technical field of aerospace, particularly relate to a kind of aircraft adopting dull and stereotyped revolving vane thrust unit.
Background technology
Traditional aircraft mainly adopts screw propeller, turbine and jet engine to make thrust unit.Screw propeller thrust unit has several shortcoming, and one is that it produces torsional flow, all has adverse effect to the safety and efficiency of aircraft; Two is that its wind area produces larger resistance to aircraft greatly, and three are its blades is curved surface, and processing and manufacturing difficulty is large.Though the high but structure of other two kinds of thrust unit efficiency is too complicated and energy consumption is larger.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming existing aircraft thrust unit, invent the aircraft of the dull and stereotyped revolving vane thrust unit of the higher employing of the simple efficiency of a kind of paddle blade structure.
Adopt an aircraft for dull and stereotyped revolving vane thrust unit, form primarily of fuselage, empennage, left thrust unit, right thrust unit, port wing, starboard wing and alighting gear.Maneuvering system, energy supplyystem, airborne equipment and various flight instrumentation instrument is furnished with in fuselage.Empennage comprises tailplane and vertical tail, and tailplane is made up of the fixed part of leading portion and horizontal stabilizer and back segment moving part and elevating rudder, and vertical tail is made up of the fixed part of leading portion and fixed fin and back segment moving part and yaw rudder.Port wing and starboard wing are arranged symmetrically with; Port wing is provided with port flap and port aileron, and starboard wing is provided with right wing flap and starboard aileron.Be positioned at the left and right sides port wing of fuselage and the root place of starboard wing and be provided with scantling of structure identical and the left breach of symmetry and right breach above port wing and starboard wing, the opening of left breach is towards a left side, and the opening of right breach is towards the right side.Left thrust unit is identical with principle of work with right thrust unit structure, and they are symmetrically arranged in the left breach of fuselage both sides and right indentation, there respectively.The left breach of the fuselage left and right sides and right breach are the sector notch that cornerite is about 180 °, the radius of their arc inner wall makes former and later two bus limits of the blade moved betwixt all touch arc inner wall to slide just, the blade on the right side of the main shaft of left thrust unit is encased by left breach substantially, and the blade in the left side of the main shaft of right thrust unit is encased by right breach substantially.The main shaft of left thrust unit is arranged in center half gear of the left thrust unit of the upper surface being fixed on port wing by bearing, the main shaft lower end of left thrust unit is connected with the engine output shaft of the left thrust unit be fixed in port wing; The main shaft of right thrust unit is arranged in center half gear of the right thrust unit of the upper surface being fixed on starboard wing by bearing, the main shaft lower end of right thrust unit is connected with the engine output shaft of the right thrust unit be fixed in starboard wing.Alighting gear adopts wheel undercarriage.
The concrete structure of right thrust unit is: right thrust unit comprises the identical rotating vane of the different structure of the setting angle of driving engine, main shaft, center half gear and three that are evenly distributed on around the gear of center half or four only blade.The tooth of center half gear is not covered with whole circumference, only arranges half circumference, and another half circumference is anodontia smooth side, this smooth side lower than tooth paddy, in order to avoid touch this smooth side when the tooth of the nearly heart gear engaged with center half gear is on the left of main shaft; Shorter than other teeth with the tooth depth of the transition tooth of the junction of anodontia half cycle with tooth half cycle, so that the nearly heart gear smooth transition engaged with center half gear.Main shaft is vertically arranged, the stage casing of main shaft is connected in the centre hole of center half gear by bearing and center half gear, and main shaft can flexible rotating in the centre hole of center half gear.Center half gear is fixedly mounted on the upper surface of starboard wing.The Dai Chiban Zhou Dynasty of center half gear is right, and anodontia half Zhou Dynasty of center half gear is left.The lower end of main shaft is connected with the output shaft of driving engine.Each rotating vane comprises arm axle, rachis, nearly heart gear, arm axle sleeve pipe, heart gear far away, leaf-teeth wheel and blade.Blade is that Rectangular Rigid is dull and stereotyped.The rachis lower end that be fixed on rachis vertical with arm axle, rachis is vertically arranged, arm axle horizontal arrangement.The upper end of rachis to be taken turns with leaf-teeth by bearing and is connected, and leaf-teeth wheel can around rachis flexible rotating.Leaf-teeth wheel and blade are fixed on the following center place of blade.Rachis and blade are in same perpendicular.Arm axle sleeve pipe is contained in around arm axle stage casing by bearing carrier ring, arm axle can in arm axle sleeve pipe flexible rotating.Nearly heart gear and heart gear far away are fixed on the two ends of arm axle sleeve pipe respectively.Heart gear far away and leaf gears meshing, its transmitting ratio is 1: 1.The upper end of main shaft is vertical with the arm axle of all rotating vanes to be connected.The nearly heart gear of all rotating vanes engages at Shi Douyu center half, the right side gear of the longitudinal vertical guide crossing main shaft, and the transmitting ratio of center half gear and nearly heart gears meshing is 1: 1.Center half gear, nearly heart gear, heart gear far away and leaf-teeth wheel all adopt finishing bevel gear cuter.When assembling right thrust unit, when guaranteeing that the arm axle of its arbitrary rotating vane is in its main shaft front-right horizontal position, the blade of this rotating vane and this arm axle are in same horizontal perpendicular.Like this, because center half gear maintains static, and the transmitting ratio that center half gear and leaf-teeth are taken turns is 1: 1, and this rotating vane goes to the blade of this rotating vane when arm axle is in any position on the right side of main shaft and is all in laterally vertically state.Because the left half cycle of center half gear is anodontia, and the restriction of right breach because of fuselage, rotating vane goes to the blade of this rotating vane when arm axle is in any position on the left of main shaft and is all in the arm axle plumbness with this rotating vane.All blades be provided with to reduce with former and later two bus limits of right breach contact internal walls the antifriction cylinder that blade is close to right breach inwall cliding friction.
The number of the rotating vane of left thrust unit is identical with the number of the rotating vane of right thrust unit.When assembling left thrust unit, when guaranteeing that the arm axle of its arbitrary rotating vane is in horizontal position, its main shaft positive left side, the blade of this rotating vane and this arm axle are in same horizontal perpendicular.
The principle of work of right thrust unit is: when the arm axle because of each rotating vane is in horizontal position, main shaft positive right side arm axle and blade coplanar, the transmitting ratio that center half gear and leaf-teeth are taken turns is 1: 1, and center half gear maintains static.When right thrust unit rotates, the blade on the right side of main shaft can keep laterally vertically state to clap wind backward, and the blade be on the left of main shaft can keep vertical with corresponding arm axle and move ahead.The efficiency of such generation thrust is higher.
See from top to bottom, namely the aircraft of the dull and stereotyped revolving vane thrust unit of this employing is overlooked, the principle of work of left thrust unit and right thrust unit is: start the driving engine of left thrust unit and the driving engine of right thrust unit, drive the rotating vane of left thrust unit to rotate counterclockwise respectively to rotate clockwise with the rotating vane of right thrust unit, produce thrust forward.Because left thrust unit and right thrust unit are installed on the upper surface of port wing and starboard wing, they can make the air-flow of port wing and starboard wing upper surface accelerate, and are conducive to port wing and starboard wing generation lift.Therefore this airplane efficiency is higher.
Elevating rudder can deflect up and down under the manipulation of maneuvering system, upward deflects and this aircraft can be made to come back, realize facing upward; The change of team of elevating rudder downward bias makes this aircraft bow, and realizes nutation.Yaw rudder is deflection under the manipulation of maneuvering system, and this aircraft can be made to go off course to the left or to the right.Manipulation port aileron and the upper and lower differential deflection of starboard aileron, horizontal rolling about this aircraft can be made; Manipulation port flap and right wing flap stretch out to the back lower place simultaneously, and this airplane ascensional force can be made to increase, favourable landing and climbing.
Because this invention aircraft adopts two cover thrust units, therefore manoevreability is high and safety good.
Accompanying drawing explanation
Fig. 1 is a kind of schematic rear view adopting the aircraft of dull and stereotyped revolving vane thrust unit of the present invention; Fig. 2 is the schematic top plan view of Fig. 1; Fig. 3 is that schematic diagram is looked on a left side of Fig. 1; Fig. 4 is the backsight simplified schematic diagram of the right thrust unit of band four rotating vanes be exaggerated; Fig. 5 is the schematic top plan view of Fig. 4; Fig. 6 is the structural representation of a rotating vane on the center that is arranged on half gear be connected with main shaft be exaggerated of right thrust unit; Fig. 7 is the schematic diagram of center half gear of the right propelling unit be exaggerated.
In figure, 1-fuselage, the left breach of 11-, the right breach of 12-; 2-empennage, 21-tailplane, 22-vertical tail; The left thrust unit of 3-; The right thrust unit of 4-, 40-driving engine, 41-main shaft, 42-center half gear, the band tooth half cycle of 421-center half gear, the anodontia half cycle of 422-center half gear, the centre hole of 423-center half gear, 43-rotating vane, 43a, 43b, 43c and 43d are the rotating vane of the diverse location be uniformly distributed in around main shaft 41; 431-arm axle, 432-rachis, the nearly heart gear of 433-, 434-arm axle sleeve pipe, 435-heart gear far away, 436-leaf-teeth are taken turns, 437-blade; 5-port wing, 51-port aileron, 52-port flap; 6-starboard wing, 61-starboard aileron, the right wing flap of 62-; The hand of rotation instruction of the left thrust unit 3 of 7-, the hand of rotation instruction of the right thrust unit 4 of 8-, 9-alighting gear.
Detailed description of the invention
Below in conjunction with accompanying drawing, 1 ~ 7 couple of the present invention is illustrated.
Adopt an aircraft for dull and stereotyped revolving vane thrust unit, form primarily of fuselage 1, empennage 2, left thrust unit 3, right thrust unit 4, port wing 5, starboard wing 6 and alighting gear 9.Maneuvering system, energy supplyystem, airborne equipment and various flight instrumentation instrument is furnished with in fuselage 1.Empennage 2 comprises tailplane 21 and vertical tail 22, tailplane 21 is made up of the fixed part of leading portion and horizontal stabilizer and back segment moving part and elevating rudder, and vertical tail 22 is made up of the fixed part of leading portion and fixed fin and back segment moving part and yaw rudder.Port wing 5 and starboard wing 6 are arranged symmetrically with; Port wing 5 is provided with port flap 52 and port aileron 51, and starboard wing 6 is provided with right wing flap 62 and starboard aileron 61.Be positioned at the left and right sides port wing 5 of fuselage 1 and the root place of starboard wing 6 and be provided with scantling of structure identical and the left breach 11 of symmetry and right breach 12 above port wing 5 and starboard wing 6, the opening of left breach 11 is towards a left side, and the opening of right breach 12 is towards the right side.Left thrust unit 3 is identical with principle of work with right thrust unit 4 structure, and they are symmetrically arranged in left breach 11 and right breach 12 place of fuselage 1 both sides respectively.The left breach 11 of fuselage 1 left and right sides and right breach 12 are about the sector notch of 180 ° for cornerite, the radius of their arc inner wall makes former and later two bus limits of the blade moved betwixt all touch arc inner wall to slide just, the blade on the right side of the main shaft of left thrust unit 3 is encased by left breach 11 substantially, and the blade in the left side of the main shaft 41 of right thrust unit 4 is encased by right breach 12 substantially.The main shaft of left thrust unit 3 is arranged in center half gear of the left thrust unit 3 of the upper surface being fixed on port wing 5 by bearing, the main shaft lower end of left thrust unit 3 is connected with the engine output shaft of the left thrust unit 3 be fixed in port wing 5; The main shaft 41 of right thrust unit 4 is arranged in center half gear 42 of the right thrust unit 4 of the upper surface being fixed on starboard wing 6 by bearing, main shaft 41 lower end of right thrust unit 4 is connected with driving engine 40 output shaft of the right thrust unit 4 be fixed in starboard wing 6.Alighting gear 9 adopts wheel undercarriage.
The concrete structure of right thrust unit 4 is: right thrust unit 4 comprises the identical rotating vane 43 of the different structure of the setting angle of driving engine 40, main shaft 41, center half gear 42 and three that are evenly distributed on around center half gear 42 or four only blade.The tooth of center half gear 42 is not covered with whole circumference, only arrange half circumference, another half circumference is anodontia smooth side, this smooth side lower than tooth paddy, in order to avoid touch this smooth side when the tooth of the nearly heart gear engaged with center half gear 42 is on the left of main shaft 41; Shorter than other teeth with the tooth depth of the transition tooth of the junction of anodontia half cycle 422 with tooth half cycle 421, so that the nearly heart gear smooth transition engaged with center half gear 42.Main shaft 41 is vertically arranged, the stage casing of main shaft 41 is connected in the centre hole 423 of center half gear 42 by bearing and center half gear 42, and main shaft 41 can flexible rotating in the centre hole 423 of center half gear.Center half gear 42 is fixedly mounted on the upper surface of starboard wing 6.The band tooth half cycle 421 of center half gear 42 is towards the right side, and the anodontia half cycle 422 of center half gear is towards a left side.The lower end of main shaft 41 is connected with the output shaft of driving engine 40.Each rotating vane 43 comprises arm axle 431, rachis 432, nearly heart gear 433, arm axle sleeve pipe 434, heart gear 435 far away, leaf-teeth wheel 436 and blade 437.Blade 437 is that Rectangular Rigid is dull and stereotyped, adopts carbon fibre material to make.Rachis 432 lower end that be fixed on rachis 432 vertical with arm axle 431, rachis 432 is vertically arranged, arm axle 431 horizontal arrangement.The upper end of rachis 432 is taken turns 436 by bearing and leaf-teeth and is connected, and leaf-teeth wheel 436 can around rachis 432 flexible rotating.Leaf-teeth wheel 436 and blade 437 are fixed on the following center place of blade 437.Rachis 432 and blade 437 are in same perpendicular.Arm axle sleeve pipe 434 is contained in around arm axle 431 stage casing by bearing carrier ring, arm axle 431 can in arm axle sleeve pipe 434 flexible rotating.Nearly heart gear 433 and heart gear 435 far away are fixed on the two ends of arm axle sleeve pipe 434 respectively.Heart gear 435 far away and leaf-teeth are taken turns 436 and are engaged, and its transmitting ratio is 1: 1.The upper end of main shaft 41 is connected with all rotating vane 43a, 43b, 43c are vertical with the arm axle of 43d.The nearly heart gear of all rotating vane 43a, 43b, 43c and 43d engages at Shi Douyu center half, the right side gear 42 of the longitudinal vertical guide crossing main shaft 41, and the transmitting ratio that center half gear 42 engages with nearly heart gear 433 is 1: 1.Center half gear 42, nearly heart gear 433, heart gear 435 far away and leaf-teeth wheel 436 all adopt finishing bevel gear cuter.When assembling right thrust unit 4, when guaranteeing that the arm axle of its arbitrary rotating vane 43 is in its main shaft 41 front-right horizontal position, the blade of this rotating vane and this arm axle are in same horizontal perpendicular.Like this, because center half gear 42 maintains static, and the transmitting ratio that center half gear 42 and leaf-teeth take turnss 436 is 1: 1, and this rotating vane goes to the blade of this rotating vane when arm axle is in any position on the right side of main shaft 41 and is all in laterally vertical state.Because the left half cycle of center half gear 42 is anodontia, and the restriction of right breach 12 because of fuselage 1, rotating vane goes to the blade of this rotating vane when arm axle is in any position on the left of main shaft and is all in the arm axle plumbness with this rotating vane.All blades be provided with to reduce with former and later two bus limits of right breach 12 contact internal walls the antifriction cylinder that blade is close to right breach 12 inwall cliding friction.
The number of the rotating vane of left thrust unit 3 is identical with the number of the rotating vane of right thrust unit 4.When assembling left thrust unit 3, when guaranteeing that the arm axle of its arbitrary rotating vane is in horizontal position, its main shaft positive left side, the blade of this rotating vane and this arm axle are in same horizontal perpendicular.
Left thrust unit 3 is identical with the driving engine of right thrust unit 4, lithium battery power supply when they all adopt motor.
The principle of work of right thrust unit 4 is: when the arm axle because of each rotating vane is in horizontal position, main shaft 41 positive right side, arm axle is coplanar with blade, and the transmitting ratio that center half gear 42 and leaf-teeth are taken turns is 1: 1, and center half gear 42 maintains static.When right thrust unit 4 rotates, the blade on the right side of main shaft 41 can keep laterally vertically state to clap wind backward, and the blade be on the left of main shaft 41 can keep vertical with corresponding arm axle and move ahead.The efficiency of such generation thrust is higher.
See from top to bottom, namely the aircraft of the dull and stereotyped revolving vane thrust unit of this employing is overlooked, the principle of work of left thrust unit 3 and right thrust unit 4 is: start the driving engine of left thrust unit 3 and the driving engine 40 of right thrust unit 4, drive the rotating vane of left thrust unit 3 to rotate counterclockwise respectively to rotate clockwise with the rotating vane of right thrust unit 4, produce thrust forward.Because left thrust unit 3 and right thrust unit 4 are installed on the upper surface of port wing 5 and starboard wing 6, they can make the air-flow of port wing 5 and starboard wing 6 upper surface accelerate, and are conducive to port wing 5 and starboard wing 6 produces lift.Therefore this airplane efficiency is higher.
Elevating rudder can deflect up and down under the manipulation of maneuvering system, upward deflects and this aircraft can be made to come back, realize facing upward; The change of team of elevating rudder downward bias makes this aircraft bow, and realizes nutation.Yaw rudder is deflection under the manipulation of maneuvering system, and this aircraft can be made to go off course to the left or to the right.Manipulation port aileron 51 and the differential deflection of starboard aileron about 61, horizontal rolling about this aircraft can be made; Manipulation port flap 52 and right wing flap 62 stretch out to the back lower place simultaneously, and this airplane ascensional force can be made to increase, favourable landing and climbing.
Because this invention aircraft adopts two cover thrust units, therefore manoevreability is high and safety good.
Claims (5)
1. one kind adopts the aircraft of dull and stereotyped revolving vane thrust unit, primarily of fuselage (1), empennage (2), left thrust unit (3), right thrust unit (4), port wing (5), starboard wing (6) and alighting gear (9) composition, it is characterized in that: fuselage is furnished with maneuvering system, energy supplyystem, airborne equipment and instrument and meter in (1); Empennage (2) comprises tailplane (21) and vertical tail (22), and tailplane (21) is made up of horizontal stabilizer and elevating rudder, and vertical tail (22) is made up of fixed fin and yaw rudder; Port wing (5) and starboard wing (6) are arranged symmetrically with; Port wing (5) is provided with port flap (52) and port aileron (51), and starboard wing (6) is provided with right wing flap (62) and starboard aileron (61); Be provided with scantling of structure identical and the left breach (11) of symmetry and right breach (12) in the left and right sides of fuselage (1), the opening of left breach (11) is towards a left side, and the opening of right breach (12) is towards the right side; Left thrust unit (3) is identical with principle of work with right thrust unit (4) structure, and they are symmetrically arranged in left breach (11) and right breach (12) place of fuselage (1) both sides respectively; The left breach (11) of fuselage (1) left and right sides and right breach (12) are about the sector notch of 180 ° for cornerite, the radius of their arc inner wall makes former and later two bus limits of the blade moved betwixt all touch arc inner wall to slide just, the blade on the right side of the main shaft of left thrust unit (3) is encased by left breach (11) substantially, and the blade in the left side of the main shaft (41) of right thrust unit (4) is encased by right breach (12) substantially; Alighting gear (9) adopts wheel undercarriage;
The concrete structure of right thrust unit (4) is: it comprises driving engine (40), main shaft (41), center half gear (42) and is evenly distributed on the identical rotating vane (43) of the different structure of the setting angle of around three, center half gear (42) or four only blade; The tooth at center half gear (42) is not covered with whole circumference, only arranges half circumference, and another half circumference is anodontia smooth side, and this smooth side is lower than tooth paddy; Main shaft (41) is vertically arranged, the stage casing of main shaft (41) is connected in the centre hole (423) at center half gear (42) by bearing and center half gear (42), and main shaft (41) is energy flexible rotating in the centre hole (423) of center half gear; Center half gear (42) is fixedly mounted on the upper surface of starboard wing (6); The band tooth half cycle (421) at center half gear (42) is towards the right side, and the anodontia half cycle (422) of center half gear is towards a left side; The lower end of main shaft (41) is connected with the output shaft of driving engine (40); Each rotating vane (43) comprises arm axle (431), rachis (432), nearly heart gear (433), arm axle sleeve pipe (434), heart gear (435) far away, leaf-teeth wheel (436) and blade (437); Blade (437) is Rectangular Rigid flat board; Rachis (432) lower end that be fixed on rachis (432) vertical with arm axle (431), rachis (432) is vertically arranged, arm axle (431) horizontal arrangement; The upper end of rachis (432) is taken turns (436) by bearing with leaf-teeth and is connected, and leaf-teeth wheel (436) can around rachis (432) flexible rotating; Leaf-teeth wheel (436) and blade (437) are fixed on the following center place of blade (437); Rachis (432) and blade (437) are in same perpendicular; Arm axle sleeve pipe (434) is contained in around arm axle (431) stage casing by bearing carrier ring, arm axle (431) can in arm axle sleeve pipe (434) flexible rotating; Nearly heart gear (433) and heart gear far away (435) are fixed on the two ends of arm axle sleeve pipe (434) respectively; Heart gear (435) far away is taken turns (436) and is engaged with leaf-teeth, its transmitting ratio is 1: 1; The upper end of main shaft (41) is vertical with the arm axle of all rotating vanes to be connected; The nearly heart gear of all rotating vanes engages at the Shi Douyu center half, right side gear (42) of the longitudinal vertical guide crossing main shaft (41), and the transmitting ratio that center half gear (42) is engaged with nearly heart gear (433) is 1: 1; Center half gear (42), nearly heart gear (433), heart gear (435) far away and leaf-teeth wheel (436) all adopt finishing bevel gear cuter; When the arm axle of rotating vane (43) is in its main shaft (41) front-right horizontal position, the blade of this rotating vane and this arm axle are in same horizontal perpendicular;
The number of the rotating vane of left thrust unit (3) is identical with the number of the rotating vane of right thrust unit (4); In left thrust unit (3), when the arm axle of arbitrary rotating vane is in horizontal position, its main shaft positive left side, the blade of this rotating vane and this arm axle are in same horizontal perpendicular.
2. a kind of aircraft adopting dull and stereotyped revolving vane thrust unit according to claim 1, is characterized in that: all blades be all provided with to reduce with former and later two bus limits of the breach contact internal walls of the fuselage left and right sides the antifriction cylinder that blade is close to breach inwall cliding friction.
3. a kind of aircraft adopting dull and stereotyped revolving vane thrust unit according to claim 1, is characterized in that: the band tooth half cycle of center half gear is shorter than other teeth with the tooth depth of the transition tooth of the junction of anodontia half cycle.
4. a kind of aircraft adopting dull and stereotyped revolving vane thrust unit according to claim 1 and 2, is characterized in that: all blades adopt carbon fibre material to make.
5. a kind of aircraft adopting dull and stereotyped revolving vane thrust unit according to claim 1, is characterized in that: lithium battery power supply during driving engine employing motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410769702.6A CN104494813B (en) | 2014-12-15 | 2014-12-15 | A kind of aircraft adopting dull and stereotyped revolving vane promotion device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410769702.6A CN104494813B (en) | 2014-12-15 | 2014-12-15 | A kind of aircraft adopting dull and stereotyped revolving vane promotion device |
Publications (2)
| Publication Number | Publication Date |
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| CN104494813A true CN104494813A (en) | 2015-04-08 |
| CN104494813B CN104494813B (en) | 2016-06-01 |
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| CN201410769702.6A Expired - Fee Related CN104494813B (en) | 2014-12-15 | 2014-12-15 | A kind of aircraft adopting dull and stereotyped revolving vane promotion device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5265827A (en) * | 1991-06-17 | 1993-11-30 | Northrop Corporation | Paddle wheel rotorcraft |
| WO2007021361A2 (en) * | 2005-08-09 | 2007-02-22 | Information Systems Laboratories, Inc. | Dual axis control for cycloidal propeller |
| CN102582830A (en) * | 2012-01-30 | 2012-07-18 | 西北工业大学 | Cycloidal paddle propeller |
| CN102582832A (en) * | 2012-03-07 | 2012-07-18 | 安徽工业大学 | Flapping-wing aircraft |
| CN103434645A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | Amphibious transportation boat with cycloidal propellers |
| CN103448908A (en) * | 2013-08-25 | 2013-12-18 | 西北工业大学 | Hybrid power airship adopting inflated wings and cycloidal propellers |
| CN204297065U (en) * | 2014-12-15 | 2015-04-29 | 佛山市神风航空科技有限公司 | A kind of aircraft adopting dull and stereotyped revolving vane thrust unit |
| CN104590547A (en) * | 2014-12-15 | 2015-05-06 | 王志成 | Aircraft with half-rotating blades |
-
2014
- 2014-12-15 CN CN201410769702.6A patent/CN104494813B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5265827A (en) * | 1991-06-17 | 1993-11-30 | Northrop Corporation | Paddle wheel rotorcraft |
| WO2007021361A2 (en) * | 2005-08-09 | 2007-02-22 | Information Systems Laboratories, Inc. | Dual axis control for cycloidal propeller |
| CN102582830A (en) * | 2012-01-30 | 2012-07-18 | 西北工业大学 | Cycloidal paddle propeller |
| CN102582832A (en) * | 2012-03-07 | 2012-07-18 | 安徽工业大学 | Flapping-wing aircraft |
| CN103434645A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | Amphibious transportation boat with cycloidal propellers |
| CN103448908A (en) * | 2013-08-25 | 2013-12-18 | 西北工业大学 | Hybrid power airship adopting inflated wings and cycloidal propellers |
| CN204297065U (en) * | 2014-12-15 | 2015-04-29 | 佛山市神风航空科技有限公司 | A kind of aircraft adopting dull and stereotyped revolving vane thrust unit |
| CN104590547A (en) * | 2014-12-15 | 2015-05-06 | 王志成 | Aircraft with half-rotating blades |
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| Publication number | Publication date |
|---|---|
| CN104494813B (en) | 2016-06-01 |
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