CN102765477B - Airplane capable of performing fixed wing flight and vertical take-off and landing based on three-axle flight control panel - Google Patents
Airplane capable of performing fixed wing flight and vertical take-off and landing based on three-axle flight control panel Download PDFInfo
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- CN102765477B CN102765477B CN201210282360.6A CN201210282360A CN102765477B CN 102765477 B CN102765477 B CN 102765477B CN 201210282360 A CN201210282360 A CN 201210282360A CN 102765477 B CN102765477 B CN 102765477B
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Abstract
An airplane capable of performing fixed wing flight and vertical take-off and landing based on a three-axle flight control panel is characterized in the airplane structure and the airplane control connection manner. In the aspect of structure, the airplane is characterized in that front inclination/rotation power capsules are symmetrically arranged on two sides of each wing of the airplane, a rear inclination/rotation power capsule is arranged at the rear part of an airplane body. In the aspect of airplane control connection manner, the airplane is characterized by adopting an innovative connection manner based on a simple three-axle flight control panel, so that the airplane can complete fixed wing flight and vertical take-off and landing under the control of the three-axle flight control panel. The airplane provided by the invention can complete double flight modes including fixed wing flight and vertical take-off and has good maneuverability and high flight efficiency, which is very important for improving the survival rate of the airplane in a war. In addition, the airplane based on the conventional three-axle control panel is convenient and reliable in the control manner and is suitable for mass production.
Description
Technical field
The present invention relates to a kind ofly based on three axles, fly to control the aircraft that plate is realized fixed-wing and vertical takeoff and landing.
Background technology
Development along with aerospace science and technology, aeronautical technology development is maked rapid progress, what especially represent advanced aeronautical technology is the aircraft that can realize fixed-wing and the double offline mode of vertical takeoff and landing, compare with existing fixed wing aircraft, the aircraft of fixed-wing and vertical takeoff and landing needs runway hardly, make like this this type of plane's serviceability and commonality better, it is high that it has also had fixed wing aircraft flight efficiency concurrently, the advantage that voyage is far away; The aerocraft of vertical takeoff and landing is because its lift and the power advancing produce by the screw propeller rotation of driving engine or motor completely, its thrust-weight ratio often requires to be greater than 1, and the aircraft of fixed-wing and vertical takeoff and landing has overcome above-mentioned shortcoming, flight efficiency is greatly improved, voyage is farther, has also had the advantage of vertically taking off and landing flyer maneuverability concurrently; What this class aircraft was especially representative is Sloped rotating wing aircraft (U.S. army " osprey " tilting rotor machine), the vertical takeoff and landing tilting rotor wing unmanned aerial vehicle " black panther " that the YY-1 of Air China Qingan County group company short distance/VUAV and Israel space flight industrial produce, " osprey " is the aircraft based on diaxon, the requirement that flight is controlled is very high, frequently the meeting accident of " osprey " make everybody seek to be easier to handle and safe design; YY-1 short distance/VUAV and tilting rotor wing unmanned aerial vehicle " black panther " are the aircraft based on three axles, are easy to handle, and safety is good, but when fixing wing flight, tail undercarriage can not provide pulling force forward; It is provided with a screw propeller at the rear portion of aircraft, for controlling heading, improves the air maneuver performance under fixed-wing offline mode; Along with the needs of socio-economic development and military technology innovation, more advanced fixed-wing and the aircraft of vertical takeoff and landing continue to bring out.
Summary of the invention
The object of the present invention is to provide a kind ofly based on three axles, to fly to control the aircraft that plate is realized fixed-wing and vertical takeoff and landing, it has simple in structure, and it is convenient to control, the advantage of maneuverability.
The present invention is achieved like this, and a kind ofly based on three axles, flies to control the aircraft that plate is realized fixed-wing and vertical takeoff and landing, and it comprises aircaft configuration and aircraft control linkage mode, and described aircaft configuration comprises top rake rotary power cabin, wing, port aileron, left tail supporting rod, left vertical fin, horizontal tail, elevating rudder, steering wheel, right vertical fin, right tail supporting rod, starboard aileron, fuselage, rear-inclined rotary power cabin, top rake rotary power cabin also comprises motor, fixing S. A., motor fixed bin, pull bar, steering wheel and rocking arm, rear-inclined rotary power cabin also comprises motor, front support side plate, steering wheel I, steering wheel II, rocking arm, pull bar, rear support side plate, rotation round bar, square fork, axle, square homalocephalus contiguous block, strut bar and pin rod, it is characterized in that fuselage is connected to wing middle part, on both sides wing about fuselage symmetry, be all connected with a top rake rotary power cabin, fuselage afterbody is provided with rear-inclined rotary power cabin, wing is also connected with port aileron and starboard aileron, left tail supporting rod is connected about fuselage is symmetrical with right tail supporting rod, and its one end is all connected on wing, and the other end of left tail supporting rod connects left vertical fin, horizontal tail and elevating rudder, the other end of right tail supporting rod connects right vertical fin, horizontal tail and elevating rudder, horizontal tail is provided with steering wheel, steering wheel in top rake rotary power cabin is by one end of rocking arm cylinder lever connecting rod, and the other end of pull bar connects motor fixed bin, and the middle part of motor fixed bin is provided with fixedly S. A., and motor fixed bin is fixedly connected with motor, in rear-inclined rotary power cabin, front support side plate connects steering wheel I and rotation round bar, steering wheel I is by one end of rocking arm cylinder lever connecting rod, the other end of pull bar connects pin rod, pin rod is connected to rotation round bar, rotation round bar connects square homalocephalus contiguous block through rear support side plate, on square homalocephalus contiguous block, be connected with steering wheel II, steering wheel II is by one end of rocking arm cylinder lever connecting rod, the other end of pull bar connects square fork, square fork is flexibly connected by axle with square homalocephalus contiguous block, square fork connects one end of strut bar, and the other end of strut bar connects motor, steering wheel I in rear-inclined rotary power cabin and steering wheel II are controlled respectively two space angles of motor in the vertical direction, and to be right angle rotatablely move, described aircraft control linkage mode is: (1) elevating rudder side connecting conductor formula: use Y wire, and a termination receiver elevating control passage, another termination three axles fly to control the elevating control passage of plate, the steering wheel in last termination horizontal tail, (2) yaw rudder side connecting conductor formula: steering wheel I and three axles are flown to control plate and control the delivery channel of tail actuator and be connected, the yaw rudder control channel that the yaw rudder control channel of receiver and three axles fly to control plate is connected, (3) motor throttle side connecting conductor formula: the Throttle Opening Control passage that the Throttle Opening Control passage of receiver and three axles is flown to control to plate is connected, three motors connect with three electric phase modulation respectively, and three throttle delivery channels that the signal wire (SW) that three electricity are adjusted flies to control plate with three axles are respectively connected, (4) aileron side connecting conductor formula: first, with Y wire A, two steering wheel lines of the control left and right sides aileron on wing are coupled together, last terminates at one end of another root Y wire B, the other end of Y wire B connects the aileron control channel that three axles fly to control plate, and last one end connects the aileron control channel of receiver, (5) two steering wheels in top rake rotary power cabin are connected with the two ends of Y wire respectively, and last one end of Y wire connects one end of another root Y wire C, and the other end of Y wire C connects steering wheel II, and last one end of Y wire C is connected with the wing flap passage of receiver, by above-mentioned connection wire, can make remote controller can control the rudder face of fixed-wing again when control three axles fly to control plate, and by the wing flap control dial on rotation aircraft remote controller, can change the direction of three motors, realize the switching of three axle patterns and fixed-wing pattern.
Technique effect of the present invention is: the present invention can realize vertical takeoff and landing and the dual offline mode of fixed-wing, take off and do not need runway, three electric propellers provide lift, tractive force and controlling party to power, especially rear portion electric propeller not only provides lift under vertical takeoff and landing pattern, also for air maneuver provides power, under fixed-wing offline mode, also can provide tractive force and motor-driven power for aircraft, manoevreability and the flying speed of aircraft have so greatly been improved, this is significant to the survival rate improving in aircraft war, the present invention is based on three conventional axle control desks simultaneously, mode is convenient and reliable, be applicable to producing in enormous quantities.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is top rake rotary power cabin structure schematic diagram of the present invention.
Fig. 3 is rear-inclined rotary power cabin structure schematic diagram of the present invention.
Top rake rotary power cabin 2, wing 3, port aileron 4, left tail supporting rod in the drawings, 1,
5, left vertical fin 6, horizontal tail 7, elevating rudder 8, steering wheel 9, right vertical fin 10, right tail supporting rod
11, starboard aileron 12, fuselage 13, rear-inclined rotary power cabin 14, motor 15, fixing S. A.
16, motor fixed bin 17, pull bar 18, rocking arm 19, front support side plate 20, steering wheel I
21, steering wheel II 22, rear support side plate 23, rotation round bar 24, square fork 25, axle
26, square homalocephalus contiguous block 27, strut bar 28, pin rod.
The specific embodiment
As Fig. 1, 2, shown in 3, the present invention is achieved like this, and it comprises aircaft configuration and aircraft control linkage mode, and described aircaft configuration comprises top rake rotary power cabin 1, wing 2, port aileron 3, left tail supporting rod 4, left vertical fin 5, horizontal tail 6, elevating rudder 7, steering wheel 8, right vertical fin 9, right tail supporting rod 10, starboard aileron 11, fuselage 12, rear-inclined rotary power cabin 13, top rake rotary power cabin 1 also comprises motor 14, fixedly S. A. 15, motor fixed bin 16, pull bar 17, steering wheel 8 and rocking arm 18, rear-inclined rotary power cabin 13 also comprises motor 14, front support side plate 19, steering wheel I 20, steering wheel II 21, rocking arm 18, pull bar 17, rear support side plate 22, rotation round bar 23, square fork 24, axle 25, square homalocephalus contiguous block 26, strut bar 27 and pin rod 28, fuselage 12 is connected to wing 2 middle parts, on both sides wing 2 about fuselage 12 symmetries, be all connected with a top rake rotary power cabin 1, fuselage 12 rear portions are provided with rear-inclined rotary power cabin 13, wing 2 is also connected with port aileron 3 and starboard aileron 11, left tail supporting rod 4 is connected about fuselage 12 is symmetrical with right tail supporting rod 10, and its one end is all connected on wing 2, and the other end of left tail supporting rod 4 connects left vertical fin 5, horizontal tail 6 and elevating rudder 7, the other end of right tail supporting rod 10 connects right vertical fin 9, horizontal tail 6 and elevating rudder 7, horizontal tail 6 is provided with steering wheel 8, steering wheel 8 in top rake rotary power cabin 1 is by one end of rocking arm 18 cylinder lever connecting rods 17, and the other end of pull bar 17 connects motor fixed bin 16, and the middle part of motor fixed bin 16 is provided with fixedly S. A. 15, and motor fixed bin 16 is fixedly connected with motor 14, in rear-inclined rotary power cabin 13, front support side plate 19 connects steering wheel I 20 and rotation round bar 23, steering wheel I 20 is by one end of rocking arm 18 cylinder lever connecting rods 17, the other end of pull bar 17 connects pin rod 28, pin rod 28 is connected to rotation round bar 23, rotation round bar 23 connects square homalocephalus contiguous block 26 through rear support side plate 22, on square homalocephalus contiguous block 26, be connected with steering wheel II21, steering wheel II 21 is by one end of rocking arm 18 cylinder lever connecting rods 17, the other end of pull bar 17 connects square fork 24, square fork 24 is flexibly connected by axle 25 with square homalocephalus contiguous block 26, square fork 24 connects one end of strut bar 27, the other end of strut bar 27 connects motor 14, described aircraft control linkage mode is: (1) elevating rudder side connecting conductor formula: use Y wire, and a termination receiver elevating control passage, another termination three axles fly to control the elevating control passage of plate, the steering wheel 8 in last termination horizontal tail 6, (2) yaw rudder side connecting conductor formula: steering wheel I 20 and three axles are flown to control plate and control the delivery channel of tail actuator and be connected, the yaw rudder control channel that the yaw rudder control channel of receiver and three axles fly to control plate is connected, (3) motor throttle side connecting conductor formula: the Throttle Opening Control passage that the Throttle Opening Control passage of receiver and three axles is flown to control to plate is connected, three motors connect with three electric phase modulation respectively, and three throttle delivery channels that the signal wire (SW) that three electricity are adjusted flies to control plate with three axles are respectively connected, (4) aileron side connecting conductor formula: first, with Y wire A, two steering wheel lines of the control port aileron 3 on wing 2, starboard aileron 11 are coupled together, last terminates at one end of another root Y wire B, the other end of Y wire B connects the aileron control channel that three axles fly to control plate, and last one end connects the aileron control channel of receiver, (5) two steering wheels 8 in top rake rotary power cabin 1 are connected with the two ends of Y wire respectively, last one end of Y wire connects one end of another root Y wire C, the other end of Y wire C connects steering wheel II 21, and last one end of Y wire C is connected with the wing flap passage of receiver, by above-mentioned connection wire, can make remote controller can control the rudder face of fixed-wing again when control three axles fly to control plate, and by the wing flap control dial on rotation aircraft remote controller, can change the direction of three motors, realize the switching of three axle patterns and fixed-wing pattern.
The present invention is based on three axles flies to control plate and realizes the aircraft of fixed-wing and vertical takeoff and landing and fly to control under the control of plate at three axles, takeoff condition can be fixed-wing or vertical takeoff and landing, when being fixed-wing pattern, motor 14 in top rake rotary power cabin 1 and rear-inclined rotary power cabin 13 is at steering wheel 8, under the regulation and control of steering wheel I 20 and steering wheel II 21 in horizontal direction, now three motors 14 all produce the tractive force of horizontal direction, aircraft is accelerated fast, shorten Take-Off Field Length, and when needs are motor-driven, can control at any time steering wheel I 20 and steering wheel II 21, and then change the forced direction that the motor 14 in rear-inclined rotary power cabin 13 produces, make under fixed-wing offline mode, the manoevreability of aircraft greatly improves, especially it is emphasized that, the outstanding feature of the present invention is, when by vertical takeoff and landing offline mode in fixed-wing offline mode transition process, three motors 14 can provide tractive force forward simultaneously, flight efficiency is greatly improved, and the motor 14 in rear-inclined rotary power cabin 13 can change force direction at any time, for aircraft provides better maneuvering performance.
Claims (1)
1. based on three axles, fly to control the aircraft that plate is realized fixed-wing and vertical takeoff and landing, it comprises aircaft configuration and aircraft control linkage mode, and described aircaft configuration comprises top rake rotary power cabin, wing, port aileron, left tail supporting rod, left vertical fin, horizontal tail, elevating rudder, steering wheel, right vertical fin, right tail supporting rod, starboard aileron, fuselage, rear-inclined rotary power cabin, top rake rotary power cabin also comprises motor, fixing S. A., motor fixed bin, pull bar, steering wheel and rocking arm, rear-inclined rotary power cabin also comprises motor, front support side plate, steering wheel I, steering wheel II, rocking arm, pull bar, rear support side plate, rotation round bar, square fork, axle, square homalocephalus contiguous block, strut bar and pin rod, it is characterized in that fuselage is connected to wing middle part, on both sides wing about fuselage symmetry, be all connected with a top rake rotary power cabin, fuselage afterbody is provided with rear-inclined rotary power cabin, wing is also connected with port aileron and starboard aileron, left tail supporting rod is connected about fuselage is symmetrical with right tail supporting rod, and its one end is all connected on wing, and the other end of left tail supporting rod connects left vertical fin, horizontal tail and elevating rudder, the other end of right tail supporting rod connects right vertical fin, horizontal tail and elevating rudder, horizontal tail is provided with steering wheel, steering wheel in top rake rotary power cabin is by one end of rocking arm cylinder lever connecting rod, and the other end of pull bar connects motor fixed bin, and the middle part of motor fixed bin is provided with fixedly S. A., and motor fixed bin is fixedly connected with motor, in rear-inclined rotary power cabin, front support side plate connects steering wheel I and rotation round bar, steering wheel I is by one end of rocking arm cylinder lever connecting rod, the other end of pull bar connects pin rod, pin rod is connected to rotation round bar, rotation round bar connects square homalocephalus contiguous block through rear support side plate, on square homalocephalus contiguous block, be connected with steering wheel II, steering wheel II is by one end of rocking arm cylinder lever connecting rod, the other end of pull bar connects square fork, square fork is flexibly connected by axle with square homalocephalus contiguous block, square fork connects one end of strut bar, and the other end of strut bar connects motor, described aircraft control linkage mode is: (1) elevating rudder side connecting conductor formula: use Y wire, and a termination receiver elevating control passage, another termination three axles fly to control the elevating control passage of plate, the steering wheel in last termination horizontal tail, (2) realize the side connecting conductor formula of yaw rudder function: steering wheel I and three axles are flown to control plate and control the delivery channel of tail actuator and be connected, the yaw rudder control channel that the yaw rudder control channel of receiver and three axles fly to control plate is connected, (3) motor throttle side connecting conductor formula: the Throttle Opening Control passage that the Throttle Opening Control passage of receiver and three axles is flown to control to plate is connected, three motors connect with three electric phase modulation respectively, and three throttle delivery channels that the signal wire (SW) that three electricity are adjusted flies to control plate with three axles are respectively connected, (4) aileron side connecting conductor formula: first, with Y wire A, two steering wheel lines of the control left and right sides aileron on wing are coupled together, last terminates at one end of another root Y wire B, the other end of Y wire B connects the aileron control channel that three axles fly to control plate, and last one end connects the aileron control channel of receiver, (5) two steering wheels in top rake rotary power cabin are connected with the two ends of Y wire respectively, and last one end of Y wire connects one end of another root Y wire C, and the other end of Y wire C connects steering wheel II, and last one end of Y wire C is connected with the wing flap passage of receiver.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210282360.6A CN102765477B (en) | 2012-08-10 | 2012-08-10 | Airplane capable of performing fixed wing flight and vertical take-off and landing based on three-axle flight control panel |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210282360.6A CN102765477B (en) | 2012-08-10 | 2012-08-10 | Airplane capable of performing fixed wing flight and vertical take-off and landing based on three-axle flight control panel |
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| Publication Number | Publication Date |
|---|---|
| CN102765477A CN102765477A (en) | 2012-11-07 |
| CN102765477B true CN102765477B (en) | 2014-09-10 |
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| CN201210282360.6A Expired - Fee Related CN102765477B (en) | 2012-08-10 | 2012-08-10 | Airplane capable of performing fixed wing flight and vertical take-off and landing based on three-axle flight control panel |
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| CN103287569B (en) * | 2013-05-15 | 2015-04-22 | 西北工业大学 | Lifting-pushing type large-scale solar-powered unmanned aerial vehicle capable of taking off and landing in non-runway field and hovering |
| CN105711832B (en) * | 2016-04-19 | 2018-04-27 | 北京航空航天大学 | One kind is verted the long endurance combined type aircraft of three rotors |
| CN106143901A (en) * | 2016-08-05 | 2016-11-23 | 北京奇正数元科技股份有限公司 | The unmanned plane wing that a kind of active force can be verted |
| CN106143898B (en) * | 2016-08-08 | 2018-07-10 | 北京奇正数元科技股份有限公司 | A kind of VTOL tilting rotor fixed wing aircraft |
| CN106275415B (en) * | 2016-08-19 | 2018-06-05 | 广东容祺智能科技有限公司 | The aircraft that a kind of fixed-wing and more rotors can automatically switch |
| CN107813928A (en) * | 2016-09-12 | 2018-03-20 | 北京航空航天大学 | One kind can vert more rotor twin fuselage canard configuration unmanned vehicles |
| CN106394867B (en) * | 2016-09-28 | 2019-09-03 | 顺丰科技有限公司 | Wing is fixed in VTOL |
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| CN106379544B (en) * | 2016-11-29 | 2018-05-25 | 北京奇正数元科技股份有限公司 | The modular removable formula nacelle of unmanned plane |
| CN106628201B (en) * | 2016-12-09 | 2023-08-08 | 北京奇正数元科技股份有限公司 | Unmanned aerial vehicle with multiple power combinations, capable of being replaced and adapted to different take-off and landing modes and different task loads |
| CN107215462B (en) * | 2017-07-01 | 2021-08-31 | 山东翔鸿电子科技有限公司 | Landing method and landing device for vertical take-off and landing fixed wing unmanned aerial vehicle |
| CN110228581A (en) * | 2019-06-06 | 2019-09-13 | 天峋创新（北京）科技有限公司 | A kind of high speed Bi-Tail-Boom Layout unmanned plane |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US3884432A (en) * | 1973-06-05 | 1975-05-20 | Nasa | High-lift aircraft |
| IT1152763B (en) * | 1982-01-25 | 1987-01-14 | Ind Aeronautiche E Meccaniche | IMPROVED AIRCRAFT |
| US7334756B2 (en) * | 2002-07-22 | 2008-02-26 | Rollan Gurgenovich Martirosov | Ground-effect craft and method for the cruising flight thereof |
| CN101353084A (en) * | 2008-09-05 | 2009-01-28 | 龙川 | Light aerobat capable of landing or taking-off vertically |
| CN201729271U (en) * | 2009-08-03 | 2011-02-02 | 北京航空航天大学 | Twin-propeller vertical duct controlled tiltrotor aircraft |
| CN101837195B (en) * | 2010-01-21 | 2012-02-08 | 罗之洪 | Model airplane with vertical takeoff and landing |
| CN102133926B (en) * | 2011-03-08 | 2013-05-08 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| CN202765290U (en) * | 2012-08-10 | 2013-03-06 | 南昌航空大学 | Airplane capable of achieving wing fixing and vertical take-off and landing based on three-shaft flight control board |
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2012
- 2012-08-10 CN CN201210282360.6A patent/CN102765477B/en not_active Expired - Fee Related
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