CN104229124B - Coaxial anti-paddle spherical aircraft control system - Google Patents

Coaxial anti-paddle spherical aircraft control system Download PDF

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Publication number
CN104229124B
CN104229124B CN201310231936.0A CN201310231936A CN104229124B CN 104229124 B CN104229124 B CN 104229124B CN 201310231936 A CN201310231936 A CN 201310231936A CN 104229124 B CN104229124 B CN 104229124B
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rod
control
spring
engine
paddle
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CN104229124A (en
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杨立发
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Anhui an Fei Intelligent Technology Co., Ltd.
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Anhui An Fei Intelligent Technology Co Ltd
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Abstract

Coaxial anti-paddle spherical aircraft control system, installs seat in the cabin, spring 24 is installed below in seat 23, driver controls aircraft come rake of blade by seat movement;27 one end of connecting rod and 28 one end of connecting rod are separately fixed at control 26 the same sides, 35 one end of connecting rod and 36 one end of connecting rod are separately fixed at control 37 both sides, 27 one end of connecting rod and 35 one end of connecting rod are separately connected 29 both ends of spring, valve 31 is fixed on 29 intermediate point of spring, 28 one end of connecting rod and 36 one end of connecting rod are separately connected on 30 both ends of spring, and valve 32 is fixed on 30 intermediate point of spring;Size of the control 26 synchronous control engine I throttles valves 31 and engine II throttles valve 32;Size of the control 37 Differential Control engine I throttles valves 31 and engine II throttles valve 32;The present invention can efficiently control coaxial anti-paddle spherical aircraft state of flight, control aircraft nacelle relative equilibrium.

Description

Coaxial anti-paddle spherical aircraft control system
Technical field
The invention belongs to aircraft classes, and in particular to a kind of coaxial anti-paddle spherical aircraft control system.
Background technology
The rotor system of single-rotor helicopter is made of main rotor, tail rotor and stabilizing gyroscope.Single-rotor helicopter tail Rotor is to generate opposing torque when main rotor rotation to offset.Therefore a part of work(is additionally consumed when tail rotor rotation is dynamic Rate;The tail rotor diamcter of single-rotor helicopter is the 16%-22% of main rotor, in this way, it is assumed that tail rotor paddle disk is close to main rotor paddle Disk, then single-rotor helicopter main rotor paddle disk front end is 1.16-1.22 times of main paddle disk diameter to tail rotor paddle disk rearmost end, The drive mechanism of long tail boom is complicated, and tail boom vibration and deformation are the potential faults for causing transmission mechanism in flight course.For The defect of single-blade helicopter, current people design coaxial anti-paddle helicopter, it is the two slave wing structure up and down by a positive and a negative At this helicopter is not necessarily to empennage.Since upper and lower rotor turns on the contrary, the torque of two secondary rotors generations is in steady flight shape It is mutually balanced under state, change of flight course is typically always to be manipulated away from the uneven torque of differential generation to realize by upper lower wing 's.Its features described above determines the characteristics of it has itself compared with traditional single-wing tail-rotor helicopter.40 years 20th century In generation, just this structure caused the mutually big interest of aerophile, and attempt will to become can practicality aircraft.However due to working as When people's difficulty that coaxial anti-paddle aerodynamic characteristic understanding is lacked and encountered in terms of structure design, many designers finally put Effort has been abandoned, and in a very long time has been rested on to the research of coaxial anti-paddle helicopter the experimental stage.Since coaxial anti-paddle is straight It rises the confidential feathering for solving the problems, such as two propeller blades, become always away from structure is extremely complex, is also extremely difficult to implement, so far Until the present, also only Russia has exclusively grasped manned helicopter close coupled type Propeller technology.Such as Russia sieve to come into operation at present This card -28.Coaxial anti-paddle helicopter has prodigious advantage:The single-rotor helicopter phase of coaxial anti-paddle helicopter and same weight Than due to there is no tail-rotor, can not only save the drive mechanism of a part of complexity, but also course behaviour need not be used for excess power It is vertical;The fuselage sections ordinary circumstance of coaxial anti-paddle helicopter is within rotor disk area, and longitudinal size is exactly paddle disk to body in total Size.In this way, under the gross weight of disk loading, engine and identical load-carrying, the size generally longitudinally of coaxial anti-paddle helicopter Only 60% or so of single-rotor helicopter;Coaxial anti-paddle helicopter is manipulated mainly by its inclinator and pitch-changing mechanism to carry out , when most of state of flight, the angle of attack of rotor is ceaselessly to change weekly, by being constantly changing rotor different angle The angle of attack, so that helicopter is hovered, all around fly freely;Since double blades provide lift, in identical pulling force and rotation Under wing diameter, the induced drag of rigid coaxial rotor is lower 20%-30% than monoplane;Coaxial anti-paddle helicopter can provide larger Lift, and the main paddle that available diameter is smaller, so the space of the grounding occupied is small very much, by barrier when low-latitude flying Influence it is also small very much, no matter to fight or carrier-borne all beneficial.However, there is also many for coaxial anti-paddle helicopter at present Defect:The propeller hub up and down and other component of the steerable system part non-streamline shape of coaxial anti-paddle helicopter expose in the gas flow, Thus useless face resistance increases;The fuselage sections ordinary circumstance of coaxial anti-paddle helicopter within rotor disk area, blade drive Fluid impact fuselage will lose a part of power;Coaxial anti-paddle helicopter rotor pitch-changing mechanism and inclines in flight course Always under very high-frequency action, failure rate is relatively fixed for wing aircraft at oblique angle, much more.Therefore, in forefathers couple On the basis of coaxial anti-paddle helicopter achievement in research, coaxial anti-paddle spherical aircraft is designed, core technology is divided into four parts: 1, coaxial anti-paddle spherical aircraft transmission system;2, coaxial anti-paddle spherical aircraft control system;3, coaxial anti-paddle spherical shape flight Device turns to display;4, coaxial anti-paddle spherical aircraft twin shaft clutch;Present invention relates particularly to a kind of coaxial anti-paddle spherical shapes to fly Row device control system.
Invention content
The purpose of the present invention is:Solve the problems, such as coaxial anti-paddle spherical aircraft control system.
The technical scheme is that:Coaxial anti-paddle spherical aircraft control system, as shown in Figure 1, including mainly seat, bullet Spring, connecting rod, engine oil gate valve, control handle;It is characterized in that:Seat is installed below spring, driver by seat movement come Control aircraft center of gravity position;Spring 25 is mounted on control on 26, and spring 38 is mounted on control on 37;27 one end of connecting rod and 28 one end of connecting rod is separately fixed at control and 26 the same sides, 35 one end of connecting rod and 36 one end of connecting rod is separately fixed at control 37 liang Side;One end of connecting rod 27 and one end of connecting rod 35 are separately connected 29 both ends of spring, and engine I throttles valve 31 is fixed in spring 29 Between point on, 33 one end of spring is fixed on engine I throttles valve 31;28 one end of connecting rod and 36 one end of connecting rod are separately connected spring 30 Both ends, engine II throttles valve 32 are fixed on 30 intermediate point of spring, and 34 one end of spring is fixed on engine II throttles valve 32; Control is 26 synchronous control engine I throttles valves 31 and engine II throttles valve 32, oil of the control 37 Differential Control engine I Gate valve 31 and engine II throttles valve 32;
The beneficial effects of the invention are as follows:Coaxial anti-paddle spherical aircraft control system, is changed by seat gravity motion Wing capstan gradient controls aircraft flight state by synchronous control engine oil gate valve, is started by Differential Control Machine oil gate valve changes the rotating torque of upper and lower rotor, ensures cabin relative equilibrium.
Description of the drawings:
Fig. 1 is schematic front view of the present invention.
In figure:25, spring;26, handle is controlled;27 connecting rods;28, connecting rod;29, spring;30, spring;31, engine I throttles Valve;32, engine II throttles valve;33, spring;34, spring;35, connecting rod;36, connecting rod;37, handle is controlled;38, spring.
Specific implementation mode
1, it is illustrated below in conjunction with drawings and examples.
As shown in Figure 1, coaxial anti-paddle spherical aircraft control system, includes mainly seat, spring, connecting rod, engine valve Door, control handle;It is characterized in that:Compressed spring is installed below in seat, and driver is by seat movement come the weight of change of flight device Heart position, to change the gradient of upper and lower rotor, the advance of control aircraft, retrogressing, up and down, hovering flight state; Torsionspring 25 is mounted on control on 26, and torsionspring 25 is for balancing control 26;Torsionspring 38 is mounted on control handle On 37, torsionspring 38 is for balancing control 37;It is same 26 that 27 one end of connecting rod and 28 one end of connecting rod are separately fixed at control Side can pull connecting rod 27 and connecting rod 28 in the same direction simultaneously when control is rotated 26;35 one end of connecting rod and 36 one end of connecting rod are fixed respectively In control 37 both sides, it can while be pushed away respectively when control is 37 rotation, draw connecting rod 27 and connecting rod 28;27 other end of connecting rod and connecting rod 35 other end is separately connected 29 both ends of spring, and engine I throttles valve 31 is fixed on 29 intermediate point of spring, and 33 one end of spring is solid It is scheduled on engine I throttles valve 31, spring 33 is used for balanced engine I throttles valve 31;28 other end of connecting rod and connecting rod 36 are another End is separately connected 30 both ends of spring, and 30 intermediate point of spring is fixed on engine II throttles valve 32, and 34 one end of spring is fixed on hair On motivation II throttles valve 32, spring 34 is used for balanced engine II throttles valve 32;Control passes through connecting rod 27 and connecting rod 28 26 Pulling force, the size of synchronous control engine I throttles valve 31 and engine II throttles valve 32;Control passes through 35 He of connecting rod respectively 37 The thrust and pulling force of connecting rod 36, the size of Differential Control engine I throttles valve 31 and engine II throttles valve 32;
2, coaxial anti-paddle spherical aircraft control system operation principle:In design based on upper propeller drive mechanism and The rotary inertia of the next propeller drive mechanism is equal, and using symmetrical transmission mechanism come passing power, and coaxial anti-paddle spherical shape flies Row device is controlled 26 synchronous control engine I throttles valves 31 and engine II throttles valve 32 so that upper spiral shell in flight course The rotating torque of rotation paddle transmission mechanism and the next propeller drive mechanism has the tendency that equal, is matched with seat displacement, to grasp The various state of flights such as vertical aircraft climb, decline, hovering, advance, retrogressing, while also having and cabin is maintained to be in relative equilibrium people Function.Control is same 26 37 Differential Control engine I throttles valves 31 and 32 size of engine II throttles valve, that is, in control On the basis of step two engine outputs of control, the output power size of two hair engine of fine tuning promotes upper propeller to pass Motivation structure is equal with the next propeller drive mechanism rotating torque.Reason is:Since coaxial anti-paddle spherical aircraft is flying Various states under there is interference in air flow, show as influence and lower rotor of the rotor to the purling of lower rotor to upper rotor The influence of fluidised form.Under hovering or low speed forward flight state, rotor influences each other so that downwash velocity compares single rotor aircraft It is much bigger, and the downwash velocity of upper rotor is almost the same or somewhat larger with single rotor;The slip-stream flow tube of upper rotor is in backspin Shunk at the wing, i.e., paddle disk descend to be influenced by upper rotor down-wash flow with inner region in paddle disk radius, and the upper complete place of paddle disk by Lower paddle disk is washed in the slip-stream of stream effect;In vertical climb, due to the interference in air flow of upper and lower rotor, the axial velocity of every group of rotor Disturbance velocity is induced including aircraft climb speed, self-induced velocity and from another rotor.Due to the induction speed of upper and lower rotor Degree is different, and pneumatic the holding property of upper and lower rotor is different, shows that the torque of upper and lower rotor is not when upper and lower rotor lift is identical Together;When the torque of upper and lower rotor is identical, the lift of upper and lower rotor is different.And the tension coefficient and resistance coefficient of upper and lower rotor And the torque of upper and lower rotor changes with state of flight and flying speed.Become with course variation and aircraft lifting Change, the coupling response in this course and elevating movement, it is necessary to by controlling 37 differential controls, change two engines previously defeated Go out watt level, so that a secondary rotor rotating speed is increased, another secondary rotor rotating speed reduction, the case where not influencing aircraft flight state Under, to correct the torque variation of upper and lower propeller drive mechanism, promote upper propeller drive mechanism and the next spiral The rotating torque of paddle transmission mechanism is equal, reaches control cabin and is in equilibrium state purpose, is convenient for pilot control aircraft.

Claims (2)

1. a kind of coaxial anti-paddle spherical aircraft control system, including seat, spring, connecting rod, engine valve, control handle;Its It is characterized in that, the first spring is installed below in seat;Second spring(25)It is installed on the first control handle(26)On, third spring(38) It is installed on the second control handle(37)On;First connecting rod(27)One end and second connecting rod(28)One end be fixed on the first control handle (26)On, third connecting rod(35)One end and fourth link(36)One end be fixed on the second control handle(37)On;First connecting rod (27)One end and third connecting rod(35)One end be separately connected the 4th spring(29)Both ends, engine I throttle valves(31)It is fixed In the 4th spring(29)On intermediate point, the 5th spring(33)One end is fixed on engine I throttle valves(31)On;Second connecting rod(28) One end and fourth link(36)One end is separately connected the 6th spring(30)Both ends, engine II throttle valves(32)It is fixed on the 6th bullet Spring(30)On intermediate point;7th spring(34)One end is fixed on engine II throttle valves(32)On;The first connecting rod(27) One end and second connecting rod(28)One end is individually fixed in the first control handle(26)The same side, the first control handle(26)Synchronous control is sent out The throttle valve of motivation I(31)With engine II throttle valves(32);Third connecting rod(35)One end and fourth link(36)Distinguish one end It is fixed on the second control handle(37)Both sides, the second control handle(37)Differential Control engine I throttle valves(31)With engine II oil Gate valve(32).
2. coaxial anti-paddle spherical aircraft control system according to claim 1, which is characterized in that the seat is used for Driver takes, and driver is by seat movement come the position of centre of gravity of change of flight device.
CN201310231936.0A 2013-06-05 2013-06-05 Coaxial anti-paddle spherical aircraft control system Active CN104229124B (en)

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Application Number Priority Date Filing Date Title
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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101204992A (en) * 2006-12-22 2008-06-25 郭正 Helicopter co-axis double rotator rotate speed differential device
CN102658865A (en) * 2012-05-17 2012-09-12 李游 Coaxial drive and control structure for coaxial contrarotation rotor helicopter
CN103072689A (en) * 2013-01-28 2013-05-01 黄春水 Low-rotating-speed double-layer propcopter

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101204992A (en) * 2006-12-22 2008-06-25 郭正 Helicopter co-axis double rotator rotate speed differential device
CN102658865A (en) * 2012-05-17 2012-09-12 李游 Coaxial drive and control structure for coaxial contrarotation rotor helicopter
CN103072689A (en) * 2013-01-28 2013-05-01 黄春水 Low-rotating-speed double-layer propcopter

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