CN109334950A - A kind of fixed wing aircraft - Google Patents
A kind of fixed wing aircraft Download PDFInfo
- Publication number
- CN109334950A CN109334950A CN201811212557.6A CN201811212557A CN109334950A CN 109334950 A CN109334950 A CN 109334950A CN 201811212557 A CN201811212557 A CN 201811212557A CN 109334950 A CN109334950 A CN 109334950A
- Authority
- CN
- China
- Prior art keywords
- rudder
- aileron
- elevator
- wing
- pair
- 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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- 239000003381 stabilizer Substances 0.000 claims abstract description 17
- 230000005540 biological transmission Effects 0.000 claims description 19
- 230000000694 effects Effects 0.000 abstract description 11
- 238000000034 method Methods 0.000 abstract description 6
- 238000010586 diagram Methods 0.000 description 5
- 230000000386 athletic effect Effects 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
Abstract
The invention discloses a kind of fixed wing aircraft, the rear of every side wing is mounted on the aileron that a pair is distributed up and down；The rear of fixed fin is equipped with the rudder of a pair of of left and right distribution；The rear of every side horizontal stabilizer is mounted on the elevator that a pair is distributed up and down.This fixed wing aircraft uses completely new aerodynamic arrangement's structure, one piece of rotating opening in a pair of aileron/rudder/elevator may be selected, retain traditional working method and function, each pair of aileron/rudder/elevator can also be opened simultaneously, shape is at a certain angle, so that within the same time, every side wing/horizontal stabilizer all has inclined and downward bias aileron/elevator upwards, fixed fin has to left avertence and to the rudder of right avertence, increase the flight resistance of aircraft, achieve the effect that quick deceleration, shorten landing time and distance, improve maneuverability, more flight experiences and movement can also be expanded, increase more enjoyment and challenge for numerous fans.
Description
Technical field
The present invention relates to vehicle technology field more particularly to a kind of fixed wing aircrafts.
Background technique
Currently, fixed wing aircraft either large-sized civil passenger plane, military aircraft, unmanned plane or the model of an airplane, main to wrap
Include fuselage, wing, tailplane, vertical tail, Landing Gear System, electronic servo and dynamical system etc..
Wherein, wing includes main body wing and aileron system, and there are also the system of flaps for certain special types, traditional
Aileron refers to one piece of movable aerofoil being mounted on the outside of trailing edge, and the working method of aileron is that rudder face stroke in the left and right sides is past
Opposite direction is synchronous, and the right is also the left side is also upward upwards or while the right is downward while the left side is downward, and row
Journey distance is the same, is the main steering face of aircraft, and pilot/operator manipulates the differential lift for making wing both ends of left and right aileron and occurs
Variation produces pressure difference, deflect caused by rolling moment aircraft can be made to do roll movement or adjustment course.
Tailplane includes horizontal stabilizer and one piece of elevator for being mounted on horizontal stabilizer rear, traditional
The effect of elevator is that control aircraft pitch posture, working method upwards or are both simultaneously for left and right sides lifting rudder face stroke
Downwards, when elevator is upward, for airflow function when on elevator, power suffered by elevator is downward at this time, produces to aircraft
The torque of a raw new line, aircraft is in posture is risen at this time, and when elevator is downward, airflow function is when on elevator, at this time
Power suffered by elevator is upward, generates the torque bowed to aircraft, and aircraft is in touch down attitude at this time.
Vertical tail includes fixed fin and the Block direction rudder for being mounted on fixed fin rear, traditional
The effect of rudder is that aircraft generation yaw when crosswind takeoff, crosswind land or carry out sports movement is modified course, work
Making mode is that rudder face is swung to the left or to the right to realize.
The aerodynamic arrangement of all kinds of aircrafts is not quite similar, but all more or less encounters various bottlenecks, after carrying out high-speed flight
Short distance is needed to slow down, it is necessary to increase resistance, the size of resistance directly determines slowing effect, currently, aircraft is promoting resistance
There are also very big development spaces for aspect, and most apparent example is exactly that landing runway is still too long；The maneuvering performance of fixed wing aircraft
It is manipulated by pilot/operator and changes its state of flight under elevator, rudder and aileron and determine, aileron, rudder and liter
Dropping rudder, Each performs its own functions, plays different effects, and all kinds of aircrafts are higher and higher to the maneuvering performance requirement of aircraft, and especially stunt flies
Row performance and model are raced aircraft, it is desirable to pursue and expand it is more it is unprecedented cross flight experience and movement, in existing liter
It drops under rudder, rudder and aileron structure, it is difficult to be formed compared with quantum jump.
Summary of the invention
In order to overcome the above-mentioned deficiencies of the prior art, the present invention provides a kind of fixed wing aircrafts, use completely new gas
Dynamic layout structure, can increase resistance, achieve the purpose that quick deceleration, additionally it is possible to expand more flight experiences and movement.
The technical solution adopted by the present invention to solve the technical problems are as follows:
The rear of a kind of fixed wing aircraft, including fuselage, wing, tailplane and vertical tail, every side wing is respectively mounted
The aileron for thering is a pair to be distributed up and down；The vertical tail includes fixed fin, and the rear of the fixed fin is equipped with one
To the rudder of left and right distribution；The tailplane includes horizontal stabilizer, and the rear of every side horizontal stabilizer is mounted on one
To the elevator being distributed up and down.
As an improvement of the above technical solution, the aileron is articulated with the rear of wing, and the wing is equipped with the first steering engine,
First steering engine connects aileron by the first transmission mechanism.
As an improvement of the above technical solution, first transmission mechanism includes the first rocker arm, the first drive rod and first
The both ends of rudder angle, first drive rod are respectively hinged on the first rocker arm and the first rudder angle, and first rocker arm is mounted on
On one steering engine, first rudder angle is mounted on aileron.
As an improvement of the above technical solution, the inside of the aileron is close to the wing root position of wing, and outside is close to wing
Tip location.
As an improvement of the above technical solution, the rudder is articulated with the rear of fixed fin, the fuselage or vertical
Straight stabilization is equipped with the second steering engine, and second steering engine connects rudder by the second transmission mechanism.
As an improvement of the above technical solution, second transmission mechanism includes the second rocker arm, the second drive rod and second
The both ends of rudder angle, second drive rod are respectively hinged on the second rocker arm and the second rudder angle, and second rocker arm is mounted on
On two steering engines, second rudder angle is mounted on rudder.
As an improvement of the above technical solution, the elevator is articulated with the rear of horizontal stabilizer, described horizontal stable
Face is equipped with third steering engine, and the third steering engine connects elevator by third transmission mechanism.
As an improvement of the above technical solution, the third transmission mechanism includes third rocker arm, third drive rod and third
The both ends of rudder angle, the third drive rod are respectively hinged on third rocker arm and third rudder angle, and the third rocker arm is mounted on
On three steering engines, the third rudder angle is mounted on elevator.
The beneficial effects of the present invention are as follows:
This fixed wing aircraft uses completely new aerodynamic arrangement's structure, stable in every side wing, fixed fin and every side level
The rear in face is separately installed with aileron, the rudder of a pair of left and right distribution and the lifting of a pair of distribution up and down that a pair is distributed up and down
Rudder may be selected one piece of rotating opening in a pair of aileron/rudder/elevator, retain traditional working method and function, may be used also
To open simultaneously each pair of aileron/rudder/elevator, shape is at a certain angle, so that within the same time, every side wing/water
Flat stabilization all has upwards partially and aileron/elevator of downward bias, and fixed fin is with to left avertence and to the direction of right avertence
Rudder increases the flight resistance of aircraft, can achieve the effect that quick deceleration, shortens landing time and distance, improves maneuverability；Needle
To part type, it is contemplated that vertical tail, two sides wing and tailplane add up at least ten separately controllable rudder faces, also
More flight experiences and movement can be expanded, increases more enjoyment and challenge for numerous fans, to the following athletic competition
Content and judgment criteria play more far-reaching positive influences.
Detailed description of the invention
With reference to the accompanying drawing and specific embodiment the invention will be further described, in which:
Fig. 1 is structural schematic diagram of the embodiment of the present invention when each rudder face is closed；
Fig. 2 is structural schematic diagram of the embodiment of the present invention when each rudder face is opened；
Fig. 3 is the partial structure diagram of wing in the embodiment of the present invention；
Fig. 4 is the structural schematic diagram of vertical tail in the embodiment of the present invention；
Fig. 5 is the structural schematic diagram of tailplane in the embodiment of the present invention.
Specific embodiment
In the description of the present invention, it is to be understood that, in the art, term " opening " refers to opening/rotation
To certain angle；"ON" in " folding " is same " opening ", refers to and opens/turn to certain angle, and " conjunction " refers to that closure is received
Hold together/be combined together, " rudder face " refers to aileron/rudder/elevator, and fixed wing aircraft includes but are not limited to carry in the present invention
People's aircraft, military aircraft, unmanned plane and the model of an airplane are merely for convenience of simplifying description.
Referring to Fig. 1 and Fig. 2, a kind of fixed wing aircraft of the invention, including fuselage 1, wing 2, tailplane 3 and vertical end
The wing 4, the inside of the aileron 21 is close to the wing root position of wing, tip location of the outside close to wing 2.
Referring to figs. 2 and 3, the rear of every side wing 2 is mounted on the aileron 21 that a pair is distributed up and down, and a pair of of aileron 21 can
It opens and closes simultaneously, i.e. the aileron 21 of upside rotates upward, and downside aileron 21 turns downward, or a pair of of aileron 21 is one of individually
It is rotated towards up/down.
Specifically, aileron 21 is articulated with the rear of wing 2, and the wing 2 is equipped with the first steering engine, and first steering engine passes through
First transmission mechanism connects aileron 21, and the first transmission mechanism includes that the first drive rod 25, first be mounted on the first steering engine shake
Arm 23 and the first rudder angle 24 being mounted on aileron 21, first rocker arm 23 connect the first rudder angle by the first drive rod 25
24, the both ends of first drive rod 25 are respectively hinged on the first rocker arm 23 and the first rudder angle 24, and pilot/operator passes through
The first steering engine is controlled, corresponding aileron 21 has both been can control and has rotated, to realize the open or close of aileron 21, the present embodiment is total
Four the first steering engines can be correspondingly respectively set in four pieces of ailerons 21, achieve the effect that individually to control, are also provided with confession on wing 2
The first open slot 22 that first rocker arm 23 stretches out, 21 rotational angle of aileron is excessive in order to prevent, wherein a pair of of aileron 21 is respectively
Maximum angle under upper and lower opening state is 120 °.
Referring to fig. 2 and Fig. 4, the vertical tail 4 include fixed fin 41, and the rear of the fixed fin 41 is installed
There is the rudder 42 of a pair of of left and right distribution, a pair of of rudder 42 can open and close simultaneously, i.e. the rudder 42 in left side bears left dynamic, right side
Rudder 42 bears right dynamic, or a pair of of rudder 42 is one of individually rotates towards left/right.
Specifically, the rudder 42 is articulated with the rear of fixed fin 41, and the fuselage 1 or fixed fin 41 are set
There is the second steering engine, the second steering engine in the present embodiment is mounted on 1 rear portion of fuselage, and second steering engine is connected by the second transmission mechanism
Rudder 42 is connect, the second transmission mechanism includes the second drive rod 43, the second Rocker arm 44 being mounted on the second steering engine and is mounted on
The second rudder angle 45 on rudder 42, second Rocker arm 44 by the second drive rod 43 connect the second rudder angle 45, described second
The both ends of drive rod 43 are respectively hinged on the second Rocker arm 44 and the second rudder angle 45, and pilot/operator passes through the second rudder of control
Machine both can control corresponding rudder 42 and rotate, to realize the open or close of rudder 42, the present embodiment totally two pieces of sides
To rudder 42, two the second steering engines can correspondingly be respectively set, achieve the effect that individually to control, a pair of of rudder 42 is in left and right respectively
Maximum angle under opening state is 60 °.
Referring to fig. 2 and Fig. 5, the tailplane 3 include horizontal stabilizer 31, and the rear of every side horizontal stabilizer 31 is pacified
Equipped with the elevator 32 that a pair is distributed up and down, a pair of of elevator 32 can open and close simultaneously, i.e. the elevator 32 of upside rotates upward, under
Side elevator 32 turns downward, or a pair of of elevator 32 is one of individually towards up/down rotation.
The elevator 32 is articulated with the rear of horizontal stabilizer 31, and the horizontal stabilizer 31 is equipped with third steering engine, institute
It states third steering engine and elevator 32 is connected by third transmission mechanism, third transmission mechanism includes third drive rod 36, is mounted on the
Third rocker arm 34 on three steering engines and the third rudder angle 35 being mounted on elevator 32, the third rocker arm 34 pass through third transmission
Bar 36 connects third rudder angle 35, and the both ends of third drive rod 36 are respectively hinged on third rocker arm 34 and third rudder angle 35, flies
Member/operator both can control corresponding elevator 32 and rotated, to realize the opening of elevator 32 by control third steering engine
Or closure, the present embodiment totally four pieces of elevators 32 can correspondingly be respectively set four third steering engines, also open on horizontal stabilizer 31
Equipped with the third open slot 33 stretched out for third rocker arm 34, achieve the effect that individually to control, in order to prevent 32 angle of rotation of elevator
It spends big, wherein maximum angle of a pair of of elevator 32 under difference up and down opening state is 60 °.
This fixed wing aircraft can be applicable in traditional working method and operating function, and optional a pair of aileron/rudder/liter
One piece of rotating opening in rudder drops, for example, in order to make aircraft do roll movement or adjustment course, the upside aileron 21 in left side is kept
Motionless, the downside aileron 21 in left side turns downward, while the downside aileron 21 on right side remains stationary, 21 court of upside aileron on right side
Upper rotation, and stroke distances are the same, the differential lift for making 2 both ends of wing of the aileron of the left and right sides is changed, and pressure is produced
Power is poor, and deflecting generated rolling moment can make aircraft do roll movement or adjustment course.Similarly, rudder 42 and elevator
32 can also equally operate.
The feature of this fixed wing aircraft maximum is can to open simultaneously each pair of 21/ rudder of aileron, 42/ elevator 32, is formed
Certain angle, so that every 2/ horizontal stabilizer 31 of side wing all has inclined and downward bias aileron upwards within the same time
21/ elevator 32, fixed fin 41 have the flight resistance for effectively increasing aircraft to left avertence and to the rudder 42 of right avertence
Power can achieve the effect that quick deceleration, shorten landing time and distance.
In addition, the aerodynamic arrangement of this fixed wing aircraft use brand new ideas, have the function of it is positive, for part machine
Type, such as acrobatic performer, model race aircraft, it is contemplated that vertical tail 4, two sides wing 2 and tailplane 3 add up to
Rare ten separately controllable rudder faces arbitrarily manipulate wherein one or more cooperation manipulations, improve maneuverability, additionally it is possible to extend
More flight experiences and movement out increase more enjoyment and challenge for numerous fans, content to the following athletic competition and
Judgment criteria plays more far-reaching positive influences, for example, aircraft, when being dived, due to acceleration of gravity, inertia integrally increases
Add, many difficulty of the manipulation increase to subsequent action, and the design that left and right directions rudder 42 is opened, it exactly can solve this
A problem.
The above, only better embodiment of the invention, but the present invention is not limited to above-described embodiments, as long as
The technical effect of the present invention is achieved by any identical or similar means for it, all should belong to protection scope of the present invention.
Claims (8)
1. a kind of fixed wing aircraft, including fuselage, wing, tailplane and vertical tail, it is characterised in that: after every side wing
Edge is mounted on the aileron that a pair is distributed up and down；The vertical tail includes fixed fin, the rear of the fixed fin
The rudder of a pair of of left and right distribution is installed；The tailplane includes horizontal stabilizer, and the rear of every side horizontal stabilizer is equal
The elevator that a pair is distributed up and down is installed.
2. a kind of fixed wing aircraft according to claim 1, it is characterised in that: the aileron is articulated with the rear of wing,
The wing is equipped with the first steering engine, and first steering engine connects aileron by the first transmission mechanism.
3. a kind of fixed wing aircraft according to claim 2, it is characterised in that: first transmission mechanism shakes including first
The both ends of arm, the first drive rod and the first rudder angle, first drive rod are respectively hinged on the first rocker arm and the first rudder angle, institute
It states the first rocker arm to be mounted on the first steering engine, first rudder angle is mounted on aileron.
4. a kind of fixed wing aircraft according to claim 1, it is characterised in that: the wing of the inside of the aileron close to wing
Root position, tip location of the outside close to wing.
5. a kind of fixed wing aircraft according to claim 1, it is characterised in that: the rudder is articulated with fixed fin
Rear, the fuselage or fixed fin be equipped with the second steering engine, and second steering engine connects direction by the second transmission mechanism
Rudder.
6. a kind of fixed wing aircraft according to claim 5, it is characterised in that: second transmission mechanism shakes including second
The both ends of arm, the second drive rod and the second rudder angle, second drive rod are respectively hinged on the second rocker arm and the second rudder angle, institute
It states the second rocker arm to be mounted on the second steering engine, second rudder angle is mounted on rudder.
7. a kind of fixed wing aircraft according to claim 1, it is characterised in that: the elevator is articulated with horizontal stabilizer
Rear, the horizontal stabilizer be equipped with third steering engine, the third steering engine by third transmission mechanism connect elevator.
8. a kind of fixed wing aircraft according to claim 7, it is characterised in that: the third transmission mechanism includes that third is shaken
The both ends of arm, third drive rod and third rudder angle, the third drive rod are respectively hinged on third rocker arm and third rudder angle, institute
It states third rocker arm to be mounted on third steering engine, the third rudder angle is mounted on elevator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811212557.6A CN109334950A (en) | 2018-10-18 | 2018-10-18 | A kind of fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811212557.6A CN109334950A (en) | 2018-10-18 | 2018-10-18 | A kind of fixed wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109334950A true CN109334950A (en) | 2019-02-15 |
Family
ID=65309996
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811212557.6A Pending CN109334950A (en) | 2018-10-18 | 2018-10-18 | A kind of fixed wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109334950A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111674542A (en) * | 2020-06-19 | 2020-09-18 | 四川省天域航通科技有限公司 | Unmanned aerial vehicle's landing gear and unmanned aerial vehicle thereof |
| CN112173068A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Adjustable helicopter side end plate structure |
| CN112498661A (en) * | 2020-12-04 | 2021-03-16 | 中国航空工业集团公司沈阳飞机设计研究所 | Multifunctional control surface structure |
| CN114476093A (en) * | 2022-03-17 | 2022-05-13 | 北京航空航天大学 | Distributed electric propulsion aircraft and control method thereof |
| CN114558329A (en) * | 2022-02-11 | 2022-05-31 | 东莞市飞翼电子科技有限公司 | Steering control structure of model airplane |
| US11352123B2 (en) * | 2018-06-28 | 2022-06-07 | Lucas Kai-Luen Hung | Wing assembly for a high endurance aircraft |
| CN114750931A (en) * | 2022-04-14 | 2022-07-15 | 中国空气动力研究与发展中心空天技术研究所 | Front flap rudder surface structure of unmanned aerial vehicle |
| US11548616B1 (en) | 2020-03-02 | 2023-01-10 | Lucas Kai-Luen Hung | Split-flap wing assembly for a high endurance aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US11548616B1 (en) | 2020-03-02 | 2023-01-10 | Lucas Kai-Luen Hung | Split-flap wing assembly for a high endurance aircraft |
| CN111674542A (en) * | 2020-06-19 | 2020-09-18 | 四川省天域航通科技有限公司 | Unmanned aerial vehicle's landing gear and unmanned aerial vehicle thereof |
| CN112173068A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Adjustable helicopter side end plate structure |
| CN112498661A (en) * | 2020-12-04 | 2021-03-16 | 中国航空工业集团公司沈阳飞机设计研究所 | Multifunctional control surface structure |
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| CN114476093A (en) * | 2022-03-17 | 2022-05-13 | 北京航空航天大学 | Distributed electric propulsion aircraft and control method thereof |
| CN114750931A (en) * | 2022-04-14 | 2022-07-15 | 中国空气动力研究与发展中心空天技术研究所 | Front flap rudder surface structure of unmanned aerial vehicle |
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