CN204297080U - A kind of two displacement oar aircraft - Google Patents
A kind of two displacement oar aircraft Download PDFInfo
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- CN204297080U CN204297080U CN201420789015.6U CN201420789015U CN204297080U CN 204297080 U CN204297080 U CN 204297080U CN 201420789015 U CN201420789015 U CN 201420789015U CN 204297080 U CN204297080 U CN 204297080U
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Abstract
A kind of two displacement oar aircraft, belongs to technical field of aerospace, comprises fuselage, rear-mounted installation, port wing, starboard wing, left displacement rotor, right displacement rotor and alighting gear.Control system, airborne equipment and energy device is furnished with in fuselage.Rear-mounted installation comprises left tail screw propeller, right tail screw propeller and vertical tail.Left displacement rotor and right displacement rotor structure, parameter are all identical with principle of work, and they are symmetrically arranged in the left and right sides of fuselage, for aircraft provides lift and thrust.Right displacement rotor comprise driving engine, main shaft, brush gear, wheel hub and be evenly distributed on two or four around wheel hub identical turn oar.The spindle axis counterclockwise of right displacement rotor rotates, and on the right side of main shaft, blade forward Low Angle Of Attack motion produces pulling force upwards, in the left side of main shaft, claps the thrust produced forward, this aircraft is moved ahead after blade large attack angle.The multiple-tasks such as this aircraft is used for taking photo by plane, geographical mapping, Agriculture, forestry And Animal Husbandry operation, military investigation and rescue and relief work.
Description
Technical field
A kind of two displacement oar aircraft, belongs to technical field of aerospace, particularly relates to a kind of two displacement oar aircraft.
Background technology
Two main rotor plane of rotations of traditional cross-arranging type dual-rotor helicopter can only produce lift upwards when being horizontal, can not produce pulling force forward; The pulling force that the plane of rotation of multiple rotors of existing multiaxis helicopter also can only produce lift upwards when being horizontal and can not produce forward or thrust.And the resistance be subject to during above two kinds of helicopter flight forward is all comparatively large, more difficult enforcement is cruised fast.The screw propeller wind area of twin screw fixed wing aircraft is comparatively large, and resistance is comparatively large, and can not vertical lift.With two tilting rotor machines that V-22 osprey is representative, vertical lift is realized from the angle of horizontal surface and the conversion of the different flight attitude such as to cruise fast by changing rotor wing rotation plane on a large scale, though comparatively flexibly but structure and handle very complicated and safety is not high, efficiency is also lower.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming existing vertical translation aircraft, invent two displacement oar aircraft that can cruise fast that a kind of efficiency is higher.
A kind of two displacement oar aircraft, comprises fuselage, rear-mounted installation, port wing, starboard wing, left displacement rotor, right displacement rotor and alighting gear.Be furnished with control system, airborne equipment and energy device in fuselage, this pair of displacement oar aircraft flight attitude is handled by control system, and airborne equipment comprises various flight instrumentation instrument and capture apparatus.Rear-mounted installation comprises left tail screw propeller, right tail screw propeller and vertical tail.Left tail screw propeller is identical with right tail propeller arrangement, they are all electric propellers, they are symmetrically arranged in the left and right sides of the vertical tail of afterbody, their rotational synchronization and rotating speed is identical turns to contrary, their plane of rotation is in same level, and the aerofoil profile of their blade is symmetric form, as single-rotor helicopter tail-rotor, the angle of attack of their blade can synchronization regulation, and they can produce thrust up or down, and they play equilibrium activity and elevating rudder.Vertical tail is made up of the fixed part of leading portion and fixed fin and back segment moving part and yaw rudder.Left displacement rotor and right displacement rotor structure, parameter are all identical with principle of work, the left and right sides that they are symmetrically arranged in fuselage is installed on the tip of port wing and starboard wing respectively, be placed in the top of port wing and starboard wing, their plane of rotation is in same level, and they provide lift and thrust for this pair of displacement oar aircraft.Alighting gear adopts skid landing gear.
The concrete structure of right displacement rotor is: it comprises the band driving engine of retarder, main shaft, brush gear, wheel hub and be evenly distributed on and around wheel hub and identical with the two or four structure that wheel hub is connected turns oar.Main shaft is vertically arranged, the hypomere of main shaft is connected in the centre hole of brush gear by bearing and brush gear, and main shaft can flexible rotating in the centre hole of brush gear.The lower end of main shaft is connected with driving engine.The center that be fixed on wheel hub vertical with wheel hub, upper end of main shaft.Wheel hub horizontal arrangement.Each oar that turns comprises motor and blade.The aspect of blade is rectangular, and blade is rigidity, and the aerofoil profile of blade is flat pattern under the recessed or epirelief of epirelief.All motors are evenly connected in around wheel hub, and the output shaft of all motors is in same level.The output shaft of each motor and corresponding blade are fixed on the root of blade, and the connection location of the output shaft of motor and this blade is between 1/1 to three/4th of the chord length of this blade.Brush gear comprises support and several to brush, and the logarithm of brush is according to turning oar number and motor determines, be two as turned oar, each motor has two power leads, and firm brush is four right.Often pair of brush comprises the brush head be arranged on brush gear and the conducting ring be arranged on the moving contact of brush head on main shaft, is insulation between each conducting ring, and conducting ring adopts silver or copper material to make.All motors are connected with brush with adopting electric wire between controller.With equal live wire passage in main shaft in wheel hub, the connection wire between all motors and the conducting ring of brush gear passes through from cable channel.Motor adopts servomotor, is controlled its running and has a rest to stop, thus control the angle of attack of blade by controller.The adapter plate with holes that the support of brush gear and starboard wing tip upper surface stretch out to the right is connected, and the driving engine of brush gear and band retarder is placed in the below of this adapter plate.Driving engine is arranged on the fixed support that is connected with starboard wing tip lower surface.
The principle of work of right displacement rotor is: see from top to bottom, namely overlooks this invention aircraft, and engine drive spindle axis counterclockwise rotates, and the phase relation setting controller and main shaft makes each oar that turns run in the following manner:
When vertical and landing takeoff and hovering: the angle of attack of blade be fixed on α ° constant.
When cruising: set the reference position turning oar to be in the rear of main shaft as turning oar, the output shaft horizontal arrangement of motor is in the dead aft of main shaft, namely the output shaft of motor is in 6 o ' clock positions, for convenience of description, hour position residing for the output shaft of motor is also defined as the hour position residing for blade, namely now blade is in 6 o ' clock positions, control the position of output shaft of motor well by controller to make: the angle of attack of blade is α °, along with the rotation of main shaft, blade runs to 12 o ' clock positions by 6 o ' clock positions, the operational process of this half cycle, motor does not rotate, blade angle of attack under the locking of motor is constant, keep α °.Blade runs to the process at 11 o'clock from 12 o'clock, and controller controls electric machine rotation, makes the angle of attack of blade gradually become β ° by α °.Blade runs to the process at 5 o'clock from 11 o'clock, motor stalling and pin blade keep the angle of attack of blade be β ° constant.Finally, blade runs to the process of 6 from 5 o'clock, and controller controls motor reversal, makes the angle of attack of blade change back to α ° gradually by β °.Blade completes a swing circle, has got back to reference position and has entered next identical cycle of operations.The angle of attack of blade does periodically change, and on the right side of longitudinal vertical guide crossing main shaft, blade is to the predetermination angle of attack and Low Angle Of Attack motion produces pulling force upwards, and make the protection of this aircraft have certain height aloft, effect is with the main rotor of helicopter; In the left side of longitudinal vertical guide of mistake main shaft, clap the thrust produced forward after blade large attack angle, this aircraft is moved ahead, and the air-flow of starboard wing upper surface can be accelerated, make starboard wing produce larger lift.
Above-mentioned α ° is a fixed angle between 4 ° ~ 12 °; β ° is a fixed angle between 80 ° ~ 90 °.
The principle of work of left displacement rotor is identical with the principle of work of right displacement rotor, but their hand of rotation is contrary, and the change of the blade angle of attack is symmetrical.See from top to bottom, namely overlook this invention aircraft, main shaft clickwise under the driving of the driving engine of left displacement rotor of left displacement rotor.
Left displacement rotor and right displacement rotor independently control or coordinated signals, and independent control mobility strong is a little, and coordinated signals stability is quite a lot of.
Accompanying drawing explanation
Fig. 1 is the schematic rear view of the present invention's a kind of pair of displacement oar aircraft, in this figure, left displacement rotor and right displacement rotor all adopt two to turn oar, the output shaft of four motors is on a transverse horizontal straight line, the angle of attack near two blades of fuselage is 88 °, and the angle of attack away from two blades of fuselage is 6 °; Fig. 2 is the schematic diagram be exaggerated of right displacement rotor in Fig. 1; Fig. 3 is that schematic diagram is looked on the right side being in the blade in left side in Fig. 2; Fig. 4 is that schematic diagram is looked on the left side being in the blade on right side in Fig. 2; Fig. 5 is schematic top plan view when flying before being in of the present invention's a kind of pair of displacement oar aircraft, in this figure, left displacement rotor and right displacement rotor all adopt two to turn oar, the output shaft of four motors is on same transverse horizontal straight line, the angle of attack near two blades of fuselage is 88 °, the angle of attack away from two blades of fuselage is 6 °, and in figure, dotted portion is the signal that blade forwards diverse location to; Fig. 6 is the schematic diagram be exaggerated of right displacement rotor in Fig. 5; Fig. 7 is that schematic diagram is looked on the right side being in the blade in left side in Fig. 6; Fig. 8 is that schematic diagram is looked on the left side being in the blade on right side in Fig. 6.
In figure, 1-fuselage; 2-rear-mounted installation, the left tail screw propeller of 21-, the right tail screw propeller of 22-, 23-vertical tail; 3-port wing, the adapter plate with holes that 31-port wing tip upper surface stretches out left, 32-port wing tip fixed support; 4-starboard wing, the adapter plate with holes that 41-starboard wing tip upper surface stretches out to the right, 42-starboard wing tip fixed support; The left displacement rotor of 5-; The right displacement rotor of 6-; 7-alighting gear.The hand of rotation instruction of the right displacement rotor of 8-; The hand of rotation instruction of the left displacement rotor of 9-.Belong to the parts in right displacement rotor 6: 60-driving engine, 61-main shaft, 62-brush gear, the support of 621-brush gear, 63-wheel hub, 64-motor, 641-motor output shaft, 65-blade.
Detailed description of the invention
Now 1 ~ 8 couple of the present invention is illustrated by reference to the accompanying drawings: a kind of two displacement oar aircraft, comprises fuselage 1, rear-mounted installation 2, port wing 3, starboard wing 4, left displacement rotor 5, right displacement rotor 6 and alighting gear 7.Be furnished with control system, airborne equipment and energy device in fuselage 1, this pair of displacement oar aircraft flight attitude is handled by control system, and airborne equipment comprises various flight instrumentation instrument and capture apparatus.Rear-mounted installation 2 comprises left tail screw propeller 21, right tail screw propeller 22 and vertical tail 23.Left tail screw propeller 21 is identical with right tail screw propeller 22 structure, they are all electric propellers, they are symmetrically arranged in the left and right sides of the vertical tail 23 of fuselage 1 afterbody, their rotational synchronization and rotating speed is identical turns to contrary, their plane of rotation is in same level, and the aerofoil profile of their blade is symmetric form, as single-rotor helicopter tail-rotor, the angle of attack of their blade can synchronization regulation, and they can produce thrust up or down, and they play equilibrium activity and elevating rudder.Vertical tail 23 is made up of the fixed part of leading portion and fixed fin and back segment moving part and yaw rudder.Left displacement rotor 5 and right displacement rotor 6 structure, parameter are all identical with principle of work, the left and right sides that they are symmetrically arranged in fuselage 1 is installed on the tip of port wing 3 and starboard wing 4 respectively, be placed in the top of port wing 3 and starboard wing 4, their plane of rotation is in same level, and they provide lift and thrust for this pair of displacement oar aircraft.Alighting gear 7 adopts skid landing gear.
The concrete structure of right displacement rotor 6 is: it comprises the band driving engine 60 of retarder, main shaft 61, brush gear 62, wheel hub 63 and be evenly distributed on and around wheel hub 63 and identical with the two or four structure that wheel hub 63 is connected turns oar.Main shaft 61 is vertically arranged, the hypomere of main shaft 61 is connected in the centre hole of brush gear 62 by bearing and brush gear 62, and main shaft 61 can flexible rotating in the centre hole of brush gear 62.The lower end of main shaft 61 is connected with driving engine 60.The center that be fixed on wheel hub 63 vertical with wheel hub 63, upper end of main shaft 61.Wheel hub 63 horizontal arrangement.Each oar that turns comprises motor 64 and blade 65.The aspect of blade 65 is rectangular, and blade 65 is rigidity, and the aerofoil profile of blade 65 is flat pattern under the recessed or epirelief of epirelief.All motors 64 are evenly connected in wheel hub 63 around, and the output shaft 641 of all motors 64 is in same level.Output shaft 641 and the corresponding blade 65 of each motor 64 are fixed on the root of blade 65, and the output shaft 641 of motor and the connection location of this blade 65 are between 1/1 to three/4th of the chord length of this blade 65.Brush gear 62 comprises support 621 and several to brush, and the logarithm of brush is according to turning oar number and motor determines, be two as turned oar, each motor has two power leads, and firm brush is four right.Often pair of brush comprises the brush head be arranged on brush gear 62 and the conducting ring be arranged on the moving contact of brush head on main shaft 61, is insulation between each conducting ring, and conducting ring adopts silver or copper material to make.All motors are connected with brush with adopting electric wire between controller.With equal live wire passage in main shaft 61 in wheel hub 63, the connection wire between the conducting ring of all motors and brush gear 62 passes through from cable channel.Motor adopts servomotor, is controlled its running and has a rest to stop, thus control the angle of attack of blade by controller.The adapter plate with holes 41 that support 621 and the starboard wing tip upper surface of brush gear 62 stretch out to the right is connected, and the driving engine 60 of brush gear 62 and band retarder is placed in the below of this adapter plate 41.Driving engine 60 is arranged on the fixed support 42 that is connected with starboard wing 4 tip lower surface.
The principle of work of right displacement rotor 4 is: see from top to bottom, namely overlooks this invention aircraft, driving engine 60 drive shaft 61 left-hand revolution, and the phase relation setting controller and main shaft 61 makes each oar that turns run in the following manner:
When vertical and landing takeoff and hovering: the angle of attack of blade be fixed on α ° constant.
When cruising: set the reference position turning oar to be in the rear of main shaft 61 as turning oar, the output shaft horizontal arrangement of motor is in the dead aft of main shaft, namely the output shaft of motor is in 6 o ' clock positions, for convenience of description, hour position residing for the output shaft of motor is also defined as the hour position residing for blade, namely now blade is in 6 o ' clock positions, control the position of output shaft of motor well by controller to make: the angle of attack of blade is α °, along with the rotation of main shaft 61, blade runs to 12 o ' clock positions by 6 o ' clock positions, the operational process of this half cycle, motor does not rotate, blade angle of attack under the locking of motor is constant, keep α °.Blade runs to the process at 11 o'clock from 12 o'clock, and controller controls electric machine rotation, makes the angle of attack of blade gradually become β ° by α °.Blade runs to the process at 5 o'clock from 11 o'clock, motor stalling and pin blade keep the angle of attack of blade be β ° constant.Finally, blade runs to the process of 6 from 5 o'clock, and controller controls motor reversal, makes the angle of attack of blade change back to α ° gradually by β °.Blade completes a swing circle, has got back to reference position and has entered next identical cycle of operations.The angle of attack of blade does periodically change, and on the right side of longitudinal vertical guide crossing main shaft 61, blade is to the predetermination angle of attack and Low Angle Of Attack motion produces pulling force upwards, and make the protection of this aircraft have certain height aloft, effect is with the main rotor of helicopter; In the left side of longitudinal vertical guide of mistake main shaft 61, clap the thrust produced forward after blade large attack angle, this aircraft is moved ahead, and the air-flow of starboard wing 4 upper surface can be accelerated, make starboard wing 4 produce larger lift.
Above-mentioned α ° is a fixed angle between 4 ° ~ 12 °; β ° is a fixed angle between 80 ° ~ 90 °.
The principle of work of left displacement rotor 5 is identical with the principle of work of right displacement rotor 6, but their hand of rotation is contrary, and the change of the blade angle of attack is symmetrical.See from top to bottom, namely overlook this invention aircraft, main shaft clickwise under the driving of the driving engine of left displacement rotor 3 of left displacement rotor 3.
Left displacement rotor 5 and right displacement rotor 6 independently control or coordinated signals, and independent control mobility strong is a little, and coordinated signals stability is quite a lot of.
The light material that the fuselage 1 of this pair of displacement oar aircraft adopts the hardness such as this material, glass-felt plastic, aluminum alloy or titanium alloy high makes.All blades adopt carbon fibre material to make.Be furnished with pick up camera and information handling system in fuselage 1, can take photo by plane, the image information of shooting can be sent to wayside equipment.
Four blades are locked in α ° by engine fire, and allowing this aircraft keep, left displacement rotor 5 is vertical with the rotation of right displacement rotor 6 steadily declines, and control rear-mounted installation well simultaneously, this aircraft successfully can be force-landed.
The multiple-tasks such as a kind of two displacement oar aircraft of the present invention can be used for taking photo by plane, geographical mapping, Agriculture, forestry And Animal Husbandry operation, military investigation and rescue and relief work.
Claims (10)
1. a two displacement oar aircraft, comprise fuselage (1), rear-mounted installation (2), port wing (3), starboard wing (4), left displacement rotor (5), right displacement rotor (6) and alighting gear (7), it is characterized in that: fuselage is furnished with control system, airborne equipment and energy device in (1); Rear-mounted installation (2) comprises left tail screw propeller (21), right tail screw propeller (22) and vertical tail (23); Left tail screw propeller (21) is identical with right tail screw propeller (22) structure, they are symmetrically arranged in the left and right sides of the vertical tail (23) of fuselage (1) afterbody, their rotational synchronization and rotating speed identical turn to contrary, their plane of rotation is in same level, the aerofoil profile of their blade is symmetric form, and the angle of attack of their blade can synchronization regulation; Vertical tail (23) is made up of the fixed fin of leading portion and the yaw rudder of back segment; Left displacement rotor (5) and right displacement rotor (6) structure, parameter are all identical with principle of work, the left and right sides that they are symmetrically arranged in fuselage (1) is installed on the tip of port wing (3) and starboard wing (4) respectively, be placed in the top of port wing (3) and starboard wing (4), their plane of rotation is in same level;
The concrete structure of right displacement rotor (6) is: it comprises the band driving engine (60) of retarder, main shaft (61), brush gear (62), wheel hub (63) and and be evenly distributed on wheel hub (63) surrounding and identical with the two or four structure that wheel hub (63) is connected turns oar; Main shaft (61) is vertically arranged, the hypomere of main shaft (61) is connected in the centre hole of brush gear (62) by bearing and brush gear (62), and main shaft (61) is energy flexible rotating in the centre hole of brush gear (62); The lower end of main shaft (61) is connected with driving engine (60); The center that be fixed on wheel hub (63) vertical with wheel hub (63), upper end of main shaft (61); Wheel hub (63) horizontal arrangement; Each oar that turns comprises motor (64) and blade (65); The aspect of blade (65) is rectangular, and blade (65) is rigidity; All motors are evenly connected in wheel hub (63) around, and the output shaft of all motors is in same level; The output shaft of each motor and corresponding blade are fixed on the root of blade; Brush gear (62) comprises support (621) and several to brush, and the often pair of brush comprises the brush head that is arranged on brush gear (62) and is arranged on the upper conducting ring with the moving contact of brush head of main shaft (61), is insulate between each conducting ring; All motors are connected with brush with adopting electric wire between controller; The adapter plate with holes (41) that support (621) and the starboard wing tip upper surface of brush gear (62) stretch out to the right is connected, and the driving engine (60) of brush gear (62) and band retarder is placed in the below of this adapter plate (41); Driving engine (60) is arranged on the fixed support (42) that is connected with starboard wing (4) tip lower surface;
The range of angles of attack of the blade of right displacement rotor (4) transfer oar is:
When vertical and landing takeoff and hovering: the fixed angle of the angle of attack between 4 ° ~ 12 ° of blade is constant;
When cruising: the right side of main shaft (61) and blade are by 6 o ' clock positions to 12 o ' clock positions, the fixed angle of the angle of attack between 4 ° ~ 12 ° of blade is constant; Blade runs to the process at 11 o'clock from 12 o'clock, and the angle of attack of blade gradually becomes a fixed angle between 80 ° ~ 90 ° by a fixed angle between 4 ° ~ 12 °; From 11 o'clock to 5 o'clock, the angle of attack of blade is that a fixed angle between 80 ° ~ 90 ° is constant; Blade runs to the process of 6 from 5 o'clock, and the angle of attack of blade changes back to a fixed angle between 4 ° ~ 12 ° gradually by a fixed angle between 80 ° ~ 90 °.
2. the two displacement oar aircraft of one according to claim 1, is characterized in that: left tail screw propeller (21) and right tail screw propeller (22) are all electric propellers.
3. the two displacement oar aircraft of one according to claim 1, is characterized in that: alighting gear (7) adopts skid landing gear.
4. the two displacement oar aircraft of one according to claim 1, is characterized in that: the output shaft of motor and the connection location of corresponding blade are between 1/1 to three/4th of the chord length of this blade.
5. the two displacement oar aircraft of one according to claim 1, is characterized in that: fuselage (1) adopts this material, glass-felt plastic, aluminum alloy or titanium alloy material to make; All blades adopt carbon fibre material to make.
6. the two displacement oar aircraft of one according to claim 1, is characterized in that: the aerofoil profile of all blades is flat pattern under the recessed or epirelief of epirelief.
7. the two displacement oar aircraft of one according to claim 1, is characterized in that: with equal live wire passage in main shaft (61) in wheel hub (63), the connection wire between the conducting ring of all motors and brush gear (62) passes through from cable channel.
8. the two displacement oar aircraft of one according to claim 1, is characterized in that: motor adopts servomotor.
9. the two displacement oar aircraft of one according to claim 1, is characterized in that: fuselage is furnished with pick up camera and information handling system in (1), the image information of shooting can be sent to wayside equipment.
10. the two displacement oar aircraft of one according to claim 1, is characterized in that: conducting ring adopts silver or copper material to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789015.6U CN204297080U (en) | 2014-12-15 | 2014-12-15 | A kind of two displacement oar aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789015.6U CN204297080U (en) | 2014-12-15 | 2014-12-15 | A kind of two displacement oar aircraft |
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| Publication Number | Publication Date |
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| CN204297080U true CN204297080U (en) | 2015-04-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420789015.6U Withdrawn - After Issue CN204297080U (en) | 2014-12-15 | 2014-12-15 | A kind of two displacement oar aircraft |
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| Country | Link |
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| CN (1) | CN204297080U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104477381A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Double-variable-pitch-propeller aircraft |
| CN105197223A (en) * | 2015-10-30 | 2015-12-30 | 王志成 | Convenient-to-glide aircraft provided with moving vane |
-
2014
- 2014-12-15 CN CN201420789015.6U patent/CN204297080U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104477381A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Double-variable-pitch-propeller aircraft |
| CN105197223A (en) * | 2015-10-30 | 2015-12-30 | 王志成 | Convenient-to-glide aircraft provided with moving vane |
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Granted publication date: 20150429 Effective date of abandoning: 20160803 |
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| C25 | Abandonment of patent right or utility model to avoid double patenting |