CN106218863A - A kind of aircraft control system - Google Patents
A kind of aircraft control system Download PDFInfo
- Publication number
- CN106218863A CN106218863A CN201610909203.1A CN201610909203A CN106218863A CN 106218863 A CN106218863 A CN 106218863A CN 201610909203 A CN201610909203 A CN 201610909203A CN 106218863 A CN106218863 A CN 106218863A
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- Prior art keywords
- rollover
- regulator
- aircraft
- driftage
- elevon
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 230000007246 mechanism Effects 0.000 claims description 3
- 230000009471 action Effects 0.000 abstract description 7
- 238000013016 damping Methods 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 3
- 230000008901 benefit Effects 0.000 abstract description 2
- 150000001875 compounds Chemical class 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 5
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 4
- 238000009826 distribution Methods 0.000 description 4
- 230000001965 increasing effect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000002153 concerted effect Effects 0.000 description 3
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 230000006698 induction Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000009194 climbing Effects 0.000 description 2
- 229910052742 iron Inorganic materials 0.000 description 2
- 238000009987 spinning Methods 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 238000012935 Averaging Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 229940056582 human hair preparation Drugs 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000005654 stationary process Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/12—Adjustable control surfaces or members, e.g. rudders surfaces of different type or function being simultaneously adjusted
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/06—Adjustable control surfaces or members, e.g. rudders with two or more independent movements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/32—Air braking surfaces
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Toys (AREA)
Abstract
A kind of aircraft control system, it is characterized in that, be provided with two elevons (1) being symmetrical arranged along the aircraft plane of symmetry, can deflecting up and down at tail (3), and on two aircraft planes of symmetry being positioned at tail (3) place, upwards downwardly extend from mass centre, driftage rollover regulator (2) that can rotate.The invention have the advantage that utilize two to be positioned on the aircraft plane of symmetry along the symmetrical elevon of the aircraft plane of symmetry and two, near tail, upwards extend downwards from mass centre simultaneously, difference symmetrical, can the compound action of driftage rollover regulator of all-direction rotation, integrate pitching, turn on one's side, go off course, and can have the effect that air damping controls.
Description
Technical field
The present invention relates to a kind of integrate pitching, turn on one's side, go off course and can as air damping control aircraft control
System, be mainly used in fixed-wing, rotary wings, hybrid power and flapping-wing aircraft etc. have wing type it can also be used to helicopter, four rotors,
All gyroplanes such as balloon and dirigible and the aircraft of buoyancy-driven.
Background technology
From Lai Te brother's epoch, just have started to the control system utilizing rotating chain of command as aircraft.Flying the earliest
The elevator used on machine and rudder control pitching and the driftage/rollover of aircraft respectively.The rollover of these aircrafts and turning to all
The slowest.Warpage wing is invented by Lai Te brother, achieves independent aircraft three axle first and controls, and adds rollover speed
Rate, decreases radius of turn.Later, Glenn Ke Disi invented aircraft aileron aileron control rollover, with warpage wing
Comparing, being one has the great invention significantly simplifying and improveing.
Hereafter, have again Crinis Carbonisatus to understand lifting regulator (stabilator), it be the stabilization function of horizontal stabilizer and
The control system that the pitch control function of elevator combines.Having invented the most again elevon (elevon), it combines
Elevator and the function of aileron, be generally used in wingflying aircraft and mixing wing body design.This elevon utilizes symmetric deflection difference
Realize independent pitching and rolling controls.Being similar to, vertical slab tail is also invented, it is achieved that drag iron and side
Combination to the function of rudder.
Some fixed-wing VTOL (VTOL) aircrafts are described as X-wing machine, and it has four moveable control tables
Face, is substantially two adjacent V-tails.These types may have four to be hinged on built-in stabilizer, can rotate respectively
Independent chain of command, is similar to conventional direction rudder and the elevator of original fixed-wing aircraft.
Rudder controls, because vertical tail compares wing traditionally not as a rollover having notable contribution traditionally
Much shorter, too short moment arm causes cannot be carried out control of effectively turning on one's side.For newer fuselage design, including low aspect ratio
Fixed-wing VTOL aircraft, the aerodynamic drag of rollover inertia and suppression rollover is low-down, so makes vertical tail table
Face is possibly realized as main rollover control, but this technology was not the most put into practice.
The existing multiple invention of pneumatic aerial braking technology, has been utilized respectively following multiple technologies, including: thrust vectoring method,
Power splitter, spoiler, parachute etc..With regard to known to the author, always do not have any Pneumatic brake systems be to rely on two different
The control surface that the induction of separate sets rotates, toward each other deflection braking method for the purpose of dramatically increasing air drag.
Summary of the invention
The invention provides a brand-new aircraft control system, i.e. gather the merit of drag iron, rudder and aileron
The new parts being referred to as driftage rollover regulator (stabiruderon) can be combined into, in order to increase yaw stability and to carry
Control for independent yaw and rollover.
The technical scheme is that a kind of aircraft control system, it is characterised in that be provided with two edges at tail (3) and fly
The elevon (1) that the machine plane of symmetry is symmetrical arranged, can deflect up and down, and two aircraft planes of symmetry being positioned at tail (3) place
Above, driftage rollover regulator (2) that upwards downwardly extend from mass centre, that can rotate.
The upper and lower part of described driftage rollover regulator (2) can be respectively to identical with the left and right portion of elevon (1)
Or different direction deflection, to produce the rollover moment or contrary rollover moment mutually supplied.
Described driftage rollover regulator (2) is symmetrical airfoil.
Upper and lower two parts of described rollover regulator (2) use identical airfoil.
The mass centre of upper and lower two parts distance aircraft of described rollover regulator (2) is equidistant or approximation is equidistant.
The upper and lower of described driftage rollover regulator (2) is connected to machine by the axis of rotation of above-below direction respectively
Above and below, this rotating shaft is respectively by a drive mechanism with the electric-motor drive being located in tail (3) or fuselage even for tail (3)
Connect.
The invention have the advantage that and utilize two to be positioned at aircraft pair along the symmetrical elevon of the aircraft plane of symmetry and two
On title face, near tail, upwards extend downwards from mass centre simultaneously, difference symmetrical, can the driftage rollover of all-direction rotation
The compound action of regulator, integrates pitching, turns on one's side, goes off course, and can have the effect that air damping controls.
The elevon of the present invention and being arranged symmetrically with of driftage rollover regulator (stabiruderon) subtract to greatest extent
Few spinning movement coupling, the most smooth to ensure the control of aircraft.The slip-stream center that propeller produces is concentrated on controlling surface
Near line, it is ensured that the eternal effectiveness that air force controls, though the most perfectly safe when low-speed operations and hovering.Bowing of aircraft
Face upward action to be controlled by the symmetric deflection of elevon, the symmetric deflection by driftage rollover regulator (stabiruderon) of going off course
Control, turn on one's side and controlled by the differential deflection of elevon and/or driftage rollover regulator (stabiruderon).Aerial gas
The method of dynamic braking is a stationary process, when elevon and driftage rollover regulator (stabiruderon) are with wider numerical value
The differential deflection of scope, produces the resistance increased continuously and is braked aircraft.Because elevon and driftage rollover are stable
Device (stabiruderon) produces the rotating torque of counteracting relatively simultaneously, will not induce net torque while producing aerodynamic drag
Generation.Once controlling the inflection point before surface recovery stall, himself slip-stream may result in Quick air reset laminating, so
Control surface and have only to deflect into momently stall angle, speed and the action of aircraft can be controlled rapidly.This elevon and
The combination of driftage rollover regulator (stabiruderon) can also realize being imbued with the acrobatic maneuver of aggressivity and novelty.
Driftage rollover regulator (stabiruderon) can also be combined complete along three axis of control aircraft with elevator
Portion's spinning movement.By combining driftage rollover regulator (stabiruderon) and aileron or elevon, a brand-new sky
The concept of gas braking is achieved, and is referred to as " toss about and turn over air damping method ".By inducing driftage rollover regulator simultaneously
And aileron (stabiruderon) difference deflection that/elevon produces and the moment of turning on one's side on the contrary that produces, do not increasing clean side
A large amount of aerodynamic drag is produced in the case of turning over moment.This brand-new pneumatic aerial brakes is to can low-speed operations VTOL
The fixed-wing type of low aspect ratio particularly useful.
Accompanying drawing explanation
Fig. 1 describes elevon and the driftage rollover regulator of VTOL fixed wing airplane；
Fig. 2 illustrates the luffing angle being controlled aircraft by elevon symmetric deflection；
Fig. 3 describes the yaw angle being controlled aircraft by the symmetric deflection of driftage rollover regulator；
Fig. 4 is illustrated and is deflected the rollover action controlling aircraft by the difference of elevon；
Fig. 5 illustrates the rollover angle being controlled aircraft by the difference deflection of driftage rollover regulator；
Fig. 6 illustrates the difference deflection by driftage rollover regulator and elevon and controls the rollover angle of aircraft；
The difference deflection that Fig. 7 illustrates by driftage rollover regulator and elevon carries out air damping；
Fig. 8 illustrates and causes advanced stall formula air damping by the difference deflection of driftage rollover regulator；
Fig. 9 illustrates the aerobatics obtained by the advanced stall of driftage rollover regulator.
Detailed description of the invention
See Fig. 1, an embodiment of a kind of aircraft control system of the present invention, it is provided with two along aircraft symmetry at tail 3
On the elevon 1 that face is symmetrical arranged, can deflect up and down, and two aircraft planes of symmetry being positioned at tail 3, from quality
Driftage that the heart upwards downwardly extends, that can rotate rollover regulator 2.
The upper and lower part of described driftage rollover regulator 2 and the left and right portion of elevon 1 can be respectively to identical or not
Same direction deflection, to produce the rollover moment or contrary rollover moment mutually supplied.
Described driftage rollover regulator 2 is symmetrical airfoil, and its upper and lower two parts use identical airfoil.
The mass centre of upper and lower two parts distance aircraft of described rollover regulator 2 is equidistant or approximation equidistantly (differs little
In 20%).
The upper and lower of described driftage rollover regulator 2 is connected to tail by the axis of rotation of above-below direction respectively
3 above and below, and this rotating shaft is connected with the electric-motor drive being located in tail 3 or fuselage by a drive mechanism respectively.
The operation principle of the present invention is described below:
1, the deflection of elevon 1:
Elevon 1 deflects and effectively changes the angle of attack of its aerofoil profile and affected by deflection and the mean camber line shape that changes, causes this
The pressure distribution change in the surrounding flow field of a little aerofoil profiles.One difference empty aerodynamic force of the integrated generation of the pressure distribution of airfoil surface,
These power have a size, point of application, and this aerofoil plane aerofoil profile direction point.Because these power are in the plane of aerofoil profile
(ignoring viscous effect), there is no cross stream component, therefore can not induce yawing.But, these power are in longitudinal direction and vertical direction
Important, so having the potentiality producing rollover and pitching moment.From the point of view of Jian Huaing, each aerofoil profile difference power can be at each wing
Integrated making a concerted effort with acquisition equivalence in half-span, these power have dividing of size, direction and the point of application on each half wing.
2, elevon 1 symmetric deflection:
If equivalence is made a concerted effort identical on each half wing of elevon 1, and have identical point of application, then induction is turned on one's side
Upright projection power will be identical, and measures from by the line of symmetry of mass cg, and horizontal orientation force moment arm is identical by having
Length and contrary direction.Its result is that the rollover moment of the every side of wing occurred when symmetrical elevon deflection is mutually supported
Disappear, cause zero net rollover moment, as shown in Figure 2.When symmetrical elevon deflection, the point of application that equivalence is made a concerted effort would generally be from
Through the main body fixed lateral axis runout at Aircraft Quality center, aircraft longitudinally on produce a non-zero forces moment arm and one non-
Zero upright projection air force, thus produce the pneumatic pitching moment of a non-zero.Therefore, symmetrical elevon deflection can be used
In the pitching motion controlling aircraft.
3, the differential deflection of elevon 1:
In the case of the differential deflection of elevon 1 (accompanying drawing 4), the deflection amplitude of the both sides (two parts) of elevon 1 is phase
With, but in opposite direction, the pressure distribution on elevon 1 surface makes the induction pitching moment major part of either side cancel, and produces
Life is approximately the pitching moment of zero.Perpendicular projection power will increase in elevon 1 side and reduce at opposite side, causes rollover
Moment is no longer cancelled, it is achieved use the deflection of difference elevon to control rollover action.
4, the deflection of driftage rollover regulator 2:
Driftage rollover regulator 2 deflection can effectively change himself angle of attack, be increased or decreased act on self air move
The size and Orientation of power.Produced aerodynamic force will act predominantly on vertical and horizontal direction, almost without vertical component.Because
The equivalent synthesis gas power that driftage rollover regulator 2 produces can produce vertically between himself and the mass centre of aircraft
Moment arm on direction and longitudinal direction, so driftage, rollover and the moment of pitching can be produced.
The medium symmetric deflection (accompanying drawing 3) of driftage rollover regulator 2 mainly will produce approximately equalised sky at horizontal direction
Aerodynamic force.The moment arm of longitudinal direction is longer, forms powerful yawing, it is ensured that control of effectively going off course.Due to driftage rollover
The regulator 2 near symmetrical distribution in upper and lower both sides, Aircraft Quality center, size, shape and the deflection angle similar with it, this control
System processed design is to causing may there's almost no of driftage-rollover coupling.Pitching-driftage coupling can also be ignored, because of
For the time averaging induced drag as rollover regulator 2 generation of going off course up and down by roughly equal.
The difference deflection of the driftage rollover regulator in Fig. 5, produces the torsional moment with fuselage center as axle, controls to fly
The rollover angle of machine.
Degree of depth driftage rollover regulator 2 deflection will cause himself advanced stall, produce a bigger longitudinal time flat
All air forces.When two driftage rollover regulator 2 stall simultaneously, will result in a Quick air braking function, the most effectively
Driftage controls and stability (accompanying drawing 8) is by transitory loss.When driftage rollover regulator 2 advanced stall (accompanying drawing 9), will draw
Playing a non-zero pitching moment, it can be strengthened by symmetrical elevon deflection or weaken, to cause a quick pitching power
Aerobraking in square, or Quick air.In this case, yaw stability and control will not be lost, and only can be weakened.
5, elevon and the difference deflection of driftage rollover regulator 2:
Differential deflection while elevon 1 and driftage rollover regulator 2, mutually strengthens (Fig. 6) by producing or mutually restricts (figure
7) rollover moment.In the case of mutually strengthening, can quickly dispose action, improve the mobility of aircraft, be allowed to
To pilot more " joyful ".In the case of mutually restriction, the smooth and aerial aerobraking of continuous print can be realized.Rapid flight
Fixed-wing VTOL aircraft from traditional fixing wing horizontal flight pattern, spiral towards flight mould to a near vertical
The transition period of formula, the problem having " quickly climbing ".This problem is owing to the whirlpool of a make-up machine nose of wing causes
, this leading edge whirlpool can postpone wing stall and increase maximum airfoil lift.The aerial aerobraking technology of the present invention,
The verified problem that can alleviate existing " quickly climbing ".
Claims (6)
1. an aircraft control system, it is characterised in that tail (3) be provided with two be symmetrical arranged along the aircraft plane of symmetry, can
On the elevon (1) deflected up and down, and two aircraft planes of symmetry being positioned at tail (3) place, the most downward from mass centre
Driftage rollover regulator (2) that extend, that can rotate.
Aircraft control system the most according to claim 1, it is characterised in that described driftage rollover regulator (2) upper,
The left and right portion of bottom and elevon (1) can be respectively to identical or different direction deflection, the rollover mutually supplied with generation
Moment or contrary rollover moment.
Aircraft control system the most according to claim 1, it is characterised in that described driftage rollover regulator (2) is right
Claim aerofoil profile.
Aircraft control system the most according to claim 1, it is characterised in that upper and lower the two of described rollover regulator (2)
Part uses identical airfoil.
Aircraft control system the most according to claim 1, it is characterised in that upper and lower the two of described rollover regulator (2)
The mass centre of partial distance aircraft is equidistant or approximation is equidistant.
Aircraft control system the most according to claim 1, it is characterised in that described driftage rollover regulator (2) upper
Portion and bottom are connected to tail (3) above and below by the axis of rotation of above-below direction respectively, and this rotating shaft is respectively by one
Drive mechanism is connected with the electric-motor drive being located in tail (3) or fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610909203.1A CN106218863A (en) | 2016-10-19 | 2016-10-19 | A kind of aircraft control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610909203.1A CN106218863A (en) | 2016-10-19 | 2016-10-19 | A kind of aircraft control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106218863A true CN106218863A (en) | 2016-12-14 |
Family
ID=58077080
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610909203.1A Pending CN106218863A (en) | 2016-10-19 | 2016-10-19 | A kind of aircraft control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106218863A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173073A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Single steering engine control double-vertical-tail control structure |
| CN114572381A (en) * | 2022-04-19 | 2022-06-03 | 中国商用飞机有限责任公司 | Tail cone with speed reducing assembly and airplane provided with tail cone |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2303695A (en) * | 1940-07-22 | 1942-12-01 | Lockheed Aircraft Corp | Differential rudder for airplanes |
| US5340057A (en) * | 1991-11-20 | 1994-08-23 | Freewing Aerial Robotics Corporation | Thrust vectoring free wing aircraft |
| US20020047069A1 (en) * | 1998-10-13 | 2002-04-25 | Ladd Paul Vincent | Directional control and aerofoil system for aircraft |
| US20070102575A1 (en) * | 2005-11-09 | 2007-05-10 | Morgan Aircraft, Llc | Aircraft attitude control configuration |
| CN101080345A (en) * | 2004-12-16 | 2007-11-28 | 法国空中巴士公司 | Method for improving roll steering of an aircraft and aircraft using same |
| CN102133926A (en) * | 2011-03-08 | 2011-07-27 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| CN201923320U (en) * | 2011-01-13 | 2011-08-10 | 杨苡 | Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle |
| CN206265290U (en) * | 2016-10-19 | 2017-06-20 | 青岛兰道尔空气动力工程有限公司 | A kind of aircraft control system |
-
2016
- 2016-10-19 CN CN201610909203.1A patent/CN106218863A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2303695A (en) * | 1940-07-22 | 1942-12-01 | Lockheed Aircraft Corp | Differential rudder for airplanes |
| US5340057A (en) * | 1991-11-20 | 1994-08-23 | Freewing Aerial Robotics Corporation | Thrust vectoring free wing aircraft |
| US20020047069A1 (en) * | 1998-10-13 | 2002-04-25 | Ladd Paul Vincent | Directional control and aerofoil system for aircraft |
| CN101080345A (en) * | 2004-12-16 | 2007-11-28 | 法国空中巴士公司 | Method for improving roll steering of an aircraft and aircraft using same |
| US20070102575A1 (en) * | 2005-11-09 | 2007-05-10 | Morgan Aircraft, Llc | Aircraft attitude control configuration |
| CN201923320U (en) * | 2011-01-13 | 2011-08-10 | 杨苡 | Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle |
| CN102133926A (en) * | 2011-03-08 | 2011-07-27 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| CN206265290U (en) * | 2016-10-19 | 2017-06-20 | 青岛兰道尔空气动力工程有限公司 | A kind of aircraft control system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173073A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Single steering engine control double-vertical-tail control structure |
| CN114572381A (en) * | 2022-04-19 | 2022-06-03 | 中国商用飞机有限责任公司 | Tail cone with speed reducing assembly and airplane provided with tail cone |
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| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161214 |