CN106275389A - A kind of control aircraft pitch, the system turned on one's side, go off course - Google Patents
A kind of control aircraft pitch, the system turned on one's side, go off course Download PDFInfo
- Publication number
- CN106275389A CN106275389A CN201610908744.2A CN201610908744A CN106275389A CN 106275389 A CN106275389 A CN 106275389A CN 201610908744 A CN201610908744 A CN 201610908744A CN 106275389 A CN106275389 A CN 106275389A
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- CN
- China
- Prior art keywords
- elevator
- aircraft
- course
- wing
- system turned
- Prior art date
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/08—Stabilising surfaces mounted on, or supported by, wings
-
- 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
- B64C2009/005—Ailerons
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A kind of control aircraft pitch, the system turned on one's side, go off course, the front of its elevator (1) is hinged in the recess in the middle part of trailing edge, in the front portion of this elevator (1) or all and trailing edge is provided with the elongated breach (2) along centre-line of aircraft, it is provided with to fix with wing in this breach (2) and is connected, is positioned at the aircraft plane of symmetry the drag iron (3) extended above and below to aircraft；It is respectively articulated with a direction aileron (4) in the upper and lower of this drag iron (3) back, between both direction aileron (4), leaves the recess that elevator (1) swings up and down.The invention have the advantage that whole three axles only using three actuators just can realize airborne vehicle control.For the airborne vehicle of the mixing wing body of the all-wing aircraft taking off vertically and landing and low aspect ratio, the present invention especially has value.
Description
Technical field
The present invention relates to a kind of control aircraft pitch, the system turned on one's side, go off course, can be applicable to fixed-wing, flying wing, wing body
Fusion type aircraft, has the aircraft of low aspect ratio wing, and the aircraft with coaxial reverse spiral propeller.
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, having again Crinis Carbonisatus to understand lifting regulator stabilator, it is the stabilization function horizontal stabilizer and liter
The control system that the pitch control function of fall rudder combines.Having invented the most again elevon elevon, it combines lifting
Rudder and the function of aileron, be generally used in wingflying aircraft and mixing wing body design.It is real that this elevon utilizes symmetric deflection difference
The most independent pitching and rolling control.Being similar to, vertical slab tail is also invented, it is achieved that drag iron and rudder
The combination of function.
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 and vertical full motivation tail control, because traditionally not as a rollover having notable contribution traditionally
Vertical tail is than wing much shorter, and too short moment arm causes cannot be carried out control of effectively turning on one's side.Newer fuselage is set
Meter, including low aspect ratio fixed-wing VTOL aircraft, the aerodynamic drag of rollover inertia and suppression rollover is low-down, so
Vertical tail surfaces is possibly realized as main rollover control, but this technology was not the most put into practice.
Summary of the invention
It is an object of the invention to provide and a kind of can control aircraft pitch, the control system turned on one's side, go off course.
The technical scheme is that and a kind of control aircraft pitch, the system turned on one's side, go off course, it is characterised in that include rising
Fall rudder (1), drag iron (3) and direction aileron (4), the front of elevator (1) is hinged in the recess in the middle part of trailing edge,
In the front portion of this elevator (1) or all and trailing edge is provided with the elongated breach (2) along centre-line of aircraft, at this breach
(2) it is provided with in fix with wing and is connected, is positioned at the aircraft plane of symmetry the drag iron extended above and below to aircraft
(3)；A direction aileron (4) it is respectively articulated with, at both direction aileron in the upper and lower of this drag iron (3) back
(4) recess that elevator (1) swings up and down is left between.
Described drag iron (3) uses symmetrical airfoil part, direction aileron (4) adjacent with elevator (1)
For inclined-plane or chamfering (5), it is to avoid direction aileron (4) and elevator (1) interfere when rotating simultaneously.
Described direction aileron (4) is that the smooth and continuous of the aerofoil profile of drag iron (3) extends when not doing deflection action.
Described elevator (1) is that the smooth and continuous of the aerofoil profile of aircraft wing extends when not doing deflection action.
Described drag iron (3) uses thick Airfoil Design.
Described drag iron (3) is included in the electrical equipment of outside installation.
Described drag iron (3) is included in the electrical equipment being internally embedded installation.
The invention have the advantage that whole three axles only using three actuators just can realize airborne vehicle control.For hanging down
The all-wing aircraft of straight take-off and landing and the airborne vehicle of the mixing wing body of low aspect ratio, the present invention especially has value.Vertical steady
Determine being arranged symmetrically with of device, elevator and direction aileron and rotatable communication is reduced to minimum, thus realize the simple peace of airborne vehicle
Steady action control.The present invention is positioned at the design on the centrage of airborne vehicle, can ensure that it makes full use of aero propulsion device and produces
Slip-stream, even low-speed operations and hovering time, can produce effective air force control, reduce simultaneously with control relevant
The sensitivity of wind, solve and be that VTOL Fixed-Wing is in low-speed operations before the sensitivity controlling relevant wind
There are serious problems during with hovering.In the present invention, the deflection of elevator controls the pitching motion of airborne vehicle, direction aileron
Symmetric deflection control airborne vehicle yaw maneuver, its difference deflection control airborne vehicle rollover action.
Accompanying drawing explanation
Fig. 1 is the perspective view that the present invention does not has deflection state on the fixed wing airplane of low aspect ratio；
Fig. 2 is the structural representation that the present invention realizes the pitch control of aircraft by the deflection of elevator；
Fig. 3 is that the present invention realizes, by the symmetric deflection of direction aileron, the structural representation that the driftage of aircraft controls；
Fig. 4 is the structural representation that the present invention deflects the rollover control realizing aircraft by the difference of direction aileron；
Fig. 5 is the present invention combined by the deflection of these control surfaces and realize aircraft action jointly control schematic diagram.
Detailed description of the invention
See Fig. 1-Fig. 5, a kind of aircraft control system for pitching-rollover-driftage of the present invention, it is characterised in that bag
Including elevator 1, drag iron 3 and direction aileron 4, the front of elevator 1 is hinged in the recess in the middle part of trailing edge, at this
Anterior more than half portion of elevator 1 and wing 6 trailing edge are provided with the breach 2 of elongated breach this embodiment of 2(along centre-line of aircraft
Run through the major part of elevator 1 front portion；Breach 2 may also extend through whole elevator 1, is split into two halves by elevator 1；Breach 2
Front end extends to the trailing edge of wing 6).It is provided with in this breach 2 and fixing with wing 6 is connected, is positioned at the aircraft plane of symmetry and to flying
The drag iron 3 that machine extends above and below；It is respectively articulated with a direction in the upper and lower of this drag iron 3 back
Aileron 4, between both direction aileron 4, leave the trapezoidal recess that elevator 1 swings up and down, i.e. direction aileron 4 with elevator 1
Adjacent while being inclined-plane (or chamfering) 5, it is to avoid direction aileron 4 and elevator 1 interfere when rotating simultaneously.
Described elevator 1 and direction aileron 4 are equipped with driving means and (include drive mechanism etc., be routine techniques, not
Diagram)
Described drag iron 3 uses symmetrical airfoil part.
Described direction aileron 4 is that the smooth and continuous of the aerofoil profile of drag iron 3 extends when not doing deflection action.
Described elevator 1 is that the smooth and continuous of the aerofoil profile of aircraft wing extends when not doing deflection action.
Described drag iron 3 uses thick Airfoil Design.
Driving means of the present invention, controller etc. control parts etc. and may be mounted at wing 6 or drag iron 3 outside, also
Wing 6 or the inside of drag iron 3 can be embedded.
The present invention has following several typicalness when flight:
See Fig. 2, realized the pitch control of aircraft by the deflection of elevator 1
See Fig. 3, realized the driftage of aircraft by the symmetric deflection (upper and lower direction aileron 4 deflects in the same direction) of direction aileron 4
Control.
See Fig. 4, deflect (upper and lower direction aileron 4 reversely deflects) by the difference of direction aileron 4 and realize aircraft
Rollover controls.
See Fig. 5, realized aircraft by elevator 1 and the combination of the deflection of above each control surface of direction aileron 4 and move
That makees jointly controls.
Claims (7)
1. one kind controls aircraft pitch, the system turned on one's side, go off course, it is characterised in that include elevator (1), drag iron (3)
With direction aileron (4), the front of elevator (1) is hinged in the recess in the middle part of trailing edge, in the front portion of this elevator (1) or
Whole and trailing edge is provided with the elongated breach (2) along centre-line of aircraft, is provided with connect fixing with wing in this breach (2)
Connect, be positioned at the aircraft plane of symmetry the drag iron (3) extended above and below to aircraft；After this drag iron (3)
The upper and lower on limit is respectively articulated with a direction aileron (4), leaves elevator (1) upper and lower between both direction aileron (4)
The recess swung.
Control aircraft pitch the most according to claim 1, the system turned on one's side, go off course, it is characterised in that described is vertical steady
Determining device (3) and use symmetrical airfoil part, the adjacent with elevator (1) of direction aileron (4) is inclined-plane or chamfering (5), it is to avoid
Direction aileron (4) and elevator (1) interfere when rotating simultaneously.
Control aircraft pitch the most according to claim 1, the system turned on one's side, go off course, it is characterised in that described direction is secondary
The wing (4) is that the smooth and continuous of the aerofoil profile of drag iron (3) extends when not doing deflection action.
Control aircraft pitch the most according to claim 1, the system turned on one's side, go off course, it is characterised in that described elevator
(1) when not doing deflection action be aircraft wing aerofoil profile smooth and continuous extend.
Control aircraft pitch the most according to claim 1, the system turned on one's side, go off course, it is characterised in that described is vertical steady
Determine device (3) and use thick Airfoil Design.
Control aircraft pitch the most according to claim 1, the system turned on one's side, go off course, it is characterised in that described is vertical steady
Determine device (3) and be included in the electrical equipment of outside installation.
Control aircraft pitch the most according to claim 1, the system turned on one's side, go off course, it is characterised in that described is vertical steady
Determine device (3) and be included in the electrical equipment being internally embedded installation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610908744.2A CN106275389A (en) | 2016-10-19 | 2016-10-19 | A kind of control aircraft pitch, the system turned on one's side, go off course |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610908744.2A CN106275389A (en) | 2016-10-19 | 2016-10-19 | A kind of control aircraft pitch, the system turned on one's side, go off course |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106275389A true CN106275389A (en) | 2017-01-04 |
Family
ID=57720725
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610908744.2A Pending CN106275389A (en) | 2016-10-19 | 2016-10-19 | A kind of control aircraft pitch, the system turned on one's side, go off course |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106275389A (en) |
Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190911501A (en) * | 1909-05-15 | 1910-05-12 | Claud Crompton | Improvements relating to the Steering and Balancing of Aerial Machines. |
| US2303695A (en) * | 1940-07-22 | 1942-12-01 | Lockheed Aircraft Corp | Differential rudder for airplanes |
| US2402118A (en) * | 1941-12-22 | 1946-06-18 | Northrop Aircraft Inc | Roll control for airplanes |
| WO1993017908A1 (en) * | 1992-03-13 | 1993-09-16 | Hugh Schmittle | Thrust vectoring free wing aircraft |
| WO1998023482A1 (en) * | 1996-11-26 | 1998-06-04 | Freewing Aerial Robotics Corp. | Stol/vtol aircraft with improved control during transition |
| KR200334568Y1 (en) * | 2003-09-06 | 2003-12-18 | 학교법인 건국대학교 | Air vehicle with horizontal tailing of back of the body |
| 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 |
| CN101293141A (en) * | 2006-01-24 | 2008-10-29 | 株式会社多美 | Propeller plane toy |
| US20110095136A1 (en) * | 2009-10-27 | 2011-04-28 | Airbus Operations Gmbh | Aircraft with vertical stabilizers arranged on a central fuselage body and method, as well as control unit, for compensating a negative pitching moment |
| 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 |
| CN102501971A (en) * | 2011-11-20 | 2012-06-20 | 西北工业大学 | Micro flapping wing aerobat with horizontal front wing and vertical front wing |
| WO2013070296A2 (en) * | 2011-08-19 | 2013-05-16 | Aerovironment, Inc. | Aircraft system for reduced observer visibility |
| CN104015925A (en) * | 2014-05-27 | 2014-09-03 | 南京航空航天大学 | Multi-purpose vertical take-off and landing unmanned aerial vehicle |
| CN104477389A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Minitype fluttering-wing aircraft |
| CN204473119U (en) * | 2014-12-16 | 2015-07-15 | 常州市华奥泡塑新材料有限公司 | Lightweight unmanned plane |
| CN205076028U (en) * | 2015-10-16 | 2016-03-09 | 河南翱翔航空科技有限公司 | Assembled unmanned aerial vehicle fin |
| CN105438444A (en) * | 2015-12-08 | 2016-03-30 | 山西大学 | Deformable wings and vertical take-off and landing aircraft using wings |
| CN206278259U (en) * | 2016-10-19 | 2017-06-27 | 青岛兰道尔空气动力工程有限公司 | It is a kind of to control aircraft pitch, rollover, the system of driftage |
-
2016
- 2016-10-19 CN CN201610908744.2A patent/CN106275389A/en active Pending
Patent Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190911501A (en) * | 1909-05-15 | 1910-05-12 | Claud Crompton | Improvements relating to the Steering and Balancing of Aerial Machines. |
| US2303695A (en) * | 1940-07-22 | 1942-12-01 | Lockheed Aircraft Corp | Differential rudder for airplanes |
| US2402118A (en) * | 1941-12-22 | 1946-06-18 | Northrop Aircraft Inc | Roll control for airplanes |
| US5340057A (en) * | 1991-11-20 | 1994-08-23 | Freewing Aerial Robotics Corporation | Thrust vectoring free wing aircraft |
| WO1993017908A1 (en) * | 1992-03-13 | 1993-09-16 | Hugh Schmittle | Thrust vectoring free wing aircraft |
| WO1998023482A1 (en) * | 1996-11-26 | 1998-06-04 | Freewing Aerial Robotics Corp. | Stol/vtol aircraft with improved control during transition |
| KR200334568Y1 (en) * | 2003-09-06 | 2003-12-18 | 학교법인 건국대학교 | Air vehicle with horizontal tailing of back of the body |
| 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 |
| CN101293141A (en) * | 2006-01-24 | 2008-10-29 | 株式会社多美 | Propeller plane toy |
| US20110095136A1 (en) * | 2009-10-27 | 2011-04-28 | Airbus Operations Gmbh | Aircraft with vertical stabilizers arranged on a central fuselage body and method, as well as control unit, for compensating a negative pitching moment |
| 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 |
| WO2013070296A2 (en) * | 2011-08-19 | 2013-05-16 | Aerovironment, Inc. | Aircraft system for reduced observer visibility |
| CN102501971A (en) * | 2011-11-20 | 2012-06-20 | 西北工业大学 | Micro flapping wing aerobat with horizontal front wing and vertical front wing |
| CN104015925A (en) * | 2014-05-27 | 2014-09-03 | 南京航空航天大学 | Multi-purpose vertical take-off and landing unmanned aerial vehicle |
| CN104477389A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Minitype fluttering-wing aircraft |
| CN204473119U (en) * | 2014-12-16 | 2015-07-15 | 常州市华奥泡塑新材料有限公司 | Lightweight unmanned plane |
| CN205076028U (en) * | 2015-10-16 | 2016-03-09 | 河南翱翔航空科技有限公司 | Assembled unmanned aerial vehicle fin |
| CN105438444A (en) * | 2015-12-08 | 2016-03-30 | 山西大学 | Deformable wings and vertical take-off and landing aircraft using wings |
| CN206278259U (en) * | 2016-10-19 | 2017-06-27 | 青岛兰道尔空气动力工程有限公司 | It is a kind of to control aircraft pitch, rollover, the system of driftage |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170104 |