CN107972848A - Aircraft redundance force vector controls tail vane - Google Patents
Aircraft redundance force vector controls tail vane Download PDFInfo
- Publication number
- CN107972848A CN107972848A CN201711273755.9A CN201711273755A CN107972848A CN 107972848 A CN107972848 A CN 107972848A CN 201711273755 A CN201711273755 A CN 201711273755A CN 107972848 A CN107972848 A CN 107972848A
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- aircraft
- redundance
- force vector
- tail vane
- propeller
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- 230000000694 effects Effects 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 4
- 238000010586 diagram Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 230000001141 propulsive effect Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The invention belongs to aviation aircraft field.The present invention provides a kind of aircraft redundance force vector to control tail vane, including moves horizontal rudder face, motor and propeller entirely；The motor is connected with the propeller, the motor and propeller can need to be installed on the front portion or rear portion for moving horizontal rudder face entirely according to different, the propeller rotation axis should be located on the longitudinal centre line for moving horizontal rudder face entirely, above-mentioned redundance force vector control tail vane both horizontally and vertically can produce steerage, it can be achieved that effectively controlling the posture of aircraft under zero velocity.Redundance aircraft redundance force vector control tail vane of the present invention can effectively improve the security and mobility of various fixed-wings, the control ability of rotor craft, raising aircraft under low speed or stall conditions.
Description
Technical field
The invention belongs to aviation aircraft field, and in particular to a kind of aircraft redundance force vector controls tail vane.
Background technology
Description of the present invention for background technology belongs to correlation technique related to the present invention, be only used for explanation with just
In the content of the invention for understanding the present invention, it should not be construed as applicant and be specifically identified to or estimate applicant being considered of the invention first
The prior art for the applying date filed an application.
Unmanned plane, that is, UAV (UAS, Unmanned Aircraft Systems), it is using more and more extensive.
Conventional fixed-wing unmanned plane realizes the control of flight attitude using air force rudder face mostly, and speed is before determining control ability
Carry, when aircraft has substantially weakened in the air force control ability close to its afterbody rudder face during stalling speed flight, if at this time
Meet prominent air-dried disturb and easily enter stall conditions, since horizontal velocity is less than stalling speed at this time, air force rudder face, which enters, to be lost
Control state, aircraft, which often has to sacrifice height, enters undulating flight, may be follow-up wavy in the case of limited height
In-flight crash.The control ability of fixed-wing unmanned plane, mobility and the safety under low speed or stall conditions at present
Property has much room for improvement.
The content of the invention
An embodiment of the present invention provides a kind of aircraft redundance force vector to control tail vane, can effectively improve various fixations
The security and mobility of the wing, the control ability of rotor craft, raising aircraft under low speed or stall conditions.
An embodiment of the present invention provides a kind of aircraft redundance force vector control tail vane, including entirely move horizontal rudder face,
Motor and propeller；The motor and its propeller driven adapt to different situations, coordinate the adjustment of rotating speed, in level
And effective control is imposed in vertical direction to attitude of flight vehicle；In the horizontal direction can tuning the motor and its driven
Propeller is installed on the front portion or rear portion for moving horizontal rudder face entirely, and effective control effect can be achieved；The propeller rotates axle position
In on the longitudinal centre line for moving horizontal rudder face entirely；Aircraft redundance force vector control tail vane is suitable for various at present
Fixed-wing and rotor craft are, it can be achieved that control the effective of attitude of flight vehicle under low speed even zero velocity.
Present invention also offers a kind of aircraft, including above-mentioned aircraft redundance force vector control tail vane.
Aircraft redundance of embodiment of the present invention force vector control tail vane has the advantages that：
Aircraft redundance of the embodiment of the present invention force vector control tail vane propeller can in the horizontal direction, vertical direction
Tuning, variable thrust, so can not only realize effective control to stall aircraft under the low speed, or even still have foot under zero velocity
Enough control abilities.As a result of electric-powered vector controlled tail vane, the mobility of aircraft is not only increased, can also be completed
The advanced flight maneuver that other fixed wing aircrafts can not be completed.Since it is with extensive adaptability, other can be also installed on
Control ability and horizontal flight speed are improved on various rotor crafts, this has important meaning for the various practical applications of the army and the people
Justice.
Tail vane can effectively improve various fixed-wings, rotor flies for the aircraft redundance force vector control of the embodiment of the present invention
The control ability of row device, improve security and mobility of the aircraft under low speed or stall conditions.
Brief description of the drawings
, below will be to attached drawing needed in embodiment description in order to illustrate more clearly of technical scheme
It is briefly described：
Fig. 1 is the structure diagram that aircraft redundance force vector of the present invention controls tail vane embodiment one；
Fig. 2 is the structure diagram that aircraft redundance force vector of the present invention controls tail vane embodiment two；
Fig. 3 is that the aircraft redundance force vector of the embodiment of the present invention one controls the installation of tail vane and aircraft fuselage to show
It is intended to.
Description of reference numerals：
1 propeller
2 motor
3 motor horizontal steering axis
4 motor radome fairings
5 move horizontal rudder face entirely
6 horizontal rudder face shafts
7 two-beam type fuselages
8 vertical tail vanes
Embodiment
The present invention is further discussed in detail with reference to the accompanying drawings and examples.
An embodiment of the present invention provides a kind of aircraft redundance force vector control tail vane, including entirely move horizontal rudder face,
Motor and propeller；Motor and its propeller driven adapt to different situations, coordinate the adjustment of rotating speed, horizontal and vertical
Nogata upwards imposes attitude of flight vehicle effective control；In the horizontal direction can tuning motor and its driven propeller peace
Mounted in the front portion or rear portion for moving horizontal rudder face entirely, effective control effect can be achieved；Propeller rotation axis is positioned at dynamic hydroplane entirely
On the longitudinal centre line in face；Aircraft redundance force vector control tail vane is suitable for current various fixed-wings and rotor flying
Device is, it can be achieved that control the effective of attitude of flight vehicle under low speed even zero velocity.
Traditional fixed-wing rudder face is only having high-speed flow just to produce lift when flowing through rudder face generation pressure differential, by changing
Become lift size to adjust flight attitude, the embodiment of the present invention then controls what propeller produced by active all-electric force vector
Propulsive force draws in power to complete pose adjustment.The aircraft redundance force vector control tail vane of the embodiment of the present invention can be effective
Improve the security and machine of various fixed-wings, the control ability of rotor craft, raising aircraft under low speed or stall conditions
Dynamic performance.
An embodiment of the present invention provides a kind of aircraft redundance force vector control tail vane, including entirely move horizontal rudder face,
Motor and propeller；Motor is connected with propeller, and motor and propeller can be installed on complete dynamic level according to different needs
The front portion or rear portion of rudder face, propeller rotation axis should be located on the longitudinal centre line for moving horizontal rudder face entirely, above-mentioned redundance power
Vector controlled tail vane both horizontally and vertically can produce steerage, it can be achieved that effectively controlling the posture of aircraft under zero velocity.
Embodiment one
As shown in Figure 1, the aircraft redundance force vector control tail vane of the present embodiment includes moving horizontal rudder face 5, electricity entirely
Motivation 2 and propeller 1；Motor 2 and its propeller 1 that is driven adapt to different situations, coordinate the adjustment of rotating speed, horizontal and
Effective control is imposed in vertical direction to attitude of flight vehicle.In the horizontal direction can tuning motor 2 and its driven spiral
Paddle 1 is installed on moves the rear portion of horizontal rudder face 5, it can be achieved that effective control effect entirely；1 rotation axis of propeller is positioned at dynamic horizontal rudder face entirely
On 5 longitudinal centre line, the longitudinal centre line i.e. fuselage longitudinal centre line of horizontal rudder face 5 are moved entirely, is longitudinally referred to from fuselage
The direction of fuselage afterbody is arrived in front portion.The aircraft redundance force vector control tail vane of the present embodiment is suitable for current various fixations
The wing and rotor craft are, it can be achieved that control the effective of attitude of flight vehicle under low speed even zero velocity.In the reality of the present invention
Apply in example, motor 2 can be around the tuning in the horizontal direction of motor horizontal steering axis 3, so that propeller 1 is in the horizontal direction
Tuning, there is provided active controlling force.In one embodiment of the invention, propeller 1 in the horizontal direction tuning angle for ±
25°.In another embodiment of the present invention, aircraft redundance force vector control tail vane further includes horizontal rudder face shaft 6,
Horizontal rudder face shaft 6 is installed between the two-beam type fuselage 7 of aircraft, is moved horizontal rudder face 5 entirely and is installed on horizontal rudder face shaft 6
On, so that moving horizontal rudder face 5 entirely can rotate in vertical direction, that is to say, that moving horizontal rudder face 5 entirely can be around horizontal rudder face
Shaft 6 rotates in vertical direction, and vertical direction here can be understood as the direction of vertical level.At one of the present invention
In embodiment, full propeller 1 with move horizontal rudder face 5 in vertical direction tuning angle be ± 15 °.
The present embodiment aircraft redundance force vector control tail vane form in the horizontal direction, the active of vertical direction
Vector controlled power.In flight, propeller 1 through this embodiment coordinates aircraft with moving horizontal rudder face 5 entirely, can effectively improve
The control ability of overall tail vane.
In the present embodiment, motor 2 is installed on the rear portion for moving horizontal rudder face 5 entirely, and rear portion here refers to move hydroplane entirely
Face 5 is close to the part of aircraft aft.Motor 2 drives propeller 1 to rotate, and propeller 1 produces aircraft thrust, that is,
Say, the aircraft redundance force vector of the present embodiment controls tail vane as pusher control mode.In the reality of the present invention
Apply in example, propeller 1 is directly driven by high power density, the high KV values motor 2 of microlight-type, and propeller 1 uses larger pitch.
The aircraft redundance force vector control tail vane of the present embodiment has the effect that：(1) as a result of direct
Installed in entirely move horizontal rudder face on can in the horizontal direction, the high power density of vertical direction tuning, high KV values directly drive motor 2
And lightweight carbon fibre propeller 1, tail vane is quick on the draw, rapidly, this security pole to fly at low speed to fixed wing aircraft has
Meaning.(2) for aircraft in horizontal flight at a relatively high speed, active power vector controlled tail vane can significantly increase complete machine tail vane
Gesture stability ability.Simultaneously because propeller 1 employs larger pitch, it is set not only to have the effect of higher in horizontal flight
Rate, can also be effectively increased the level speed of aircraft.(3) since the control ability of redundance force vector control tail vane is able to greatly
Width is lifted, then aircraft control requirements can be met by having reduced air force rudder face, This reduces both main screw lift and is flown
Row resistance, also effectively reduces energy consumption.(4) when aircraft lands, motor high speed reverse rotation is produced deboost and (be similar to
The propulsive thrust of aircraft and anti-paddle), effectively realize power brake.
As shown in Figure 1, in one embodiment of the invention, aircraft redundance force vector control tail vane further includes electricity
Motivation radome fairing 4, motor 2 are installed on by motor radome fairing 4 and moved entirely on horizontal rudder face 5.In the implementation of the present invention
In example, 7 top of two-beam type fuselage is provided with vertical tail vane 8.
Embodiment two
The aircraft redundance force vector control tail vane of the present embodiment is installed on from motor 2 unlike embodiment one
The front portion of horizontal rudder face 5 is moved entirely, and front portion here refers to move horizontal rudder face 5 entirely close to the part of aircraft front portion, the present embodiment
Aircraft redundance force vector control tail vane be drawing-in type control mode, propeller 1 rotate to aircraft produce pulling force.
The aircraft redundance force vector control tail vane of the present embodiment is roughly the same with the working method and effect of embodiment one, simply
Selected according to the needs of different aircraft, related content refer to embodiment one, and details are not described herein.
Fig. 3 is that the aircraft redundance force vector of the embodiment of the present invention one controls the installation of tail vane and aircraft fuselage to show
It is intended to, is divided into the aircraft redundance force vector control tail vane of the embodiment of the present invention one in figure inside dotted line frame.
Present invention also offers a kind of aircraft, including above-mentioned aircraft redundance force vector control tail vane, at this
In one embodiment of invention, aircraft is fixed-wing or rotor craft.
In the present invention, term " first ", " second " are only used for the purpose described, and it is not intended that instruction or hint phase
To importance；Term " multiple " then refers to two or more, unless otherwise restricted clearly.Term " installation ", " connected ",
The terms such as " connection ", " fixation " should all be interpreted broadly, for example, " connection " can be fixedly connected or detachably connect
Connect, or be integrally connected；" connected " can be directly connected, and can also be indirectly connected by intermediary.For this area
For those of ordinary skill, the concrete meaning of above-mentioned term in the present invention can be understood as the case may be.
In description of the invention, it is to be understood that the orientation or position relationship of the instruction such as term " on ", " under " be based on
Orientation shown in the drawings or position relationship, are for only for ease of description description of the invention and simplified, rather than instruction or hint institute
The device or unit of finger must have specific direction, with specific azimuth configuration and operation, it is thus impossible to be interpreted as to this hair
Bright limitation.
In the description of this specification, the description of term " one embodiment ", " some embodiments ", " specific embodiment " etc.
Mean to combine at least one reality that the particular features, structures, materials, or characteristics that the embodiment or example describe are contained in the present invention
Apply in example or example.In the present specification, schematic expression of the above terms is not necessarily referring to identical embodiment or reality
Example.Moreover, description particular features, structures, materials, or characteristics can in any one or more embodiments or example with
Suitable mode combines.
The above is only the embodiment of the present invention, is made skilled artisans appreciate that or realizing this hair
It is bright.A variety of modifications to these embodiments will be apparent to one skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore the present invention
The embodiments shown herein is not intended to be limited to, and is to fit to and the principles and novel features disclosed herein phase one
The most wide scope caused.
Embodiment of the present invention above, is not intended to limit the scope of the present invention..
Claims (2)
1. a kind of aircraft redundance force vector controls tail vane, it is characterised in that including moving horizontal rudder face, motor and spiral shell entirely
Revolve paddle；The motor and its propeller driven adapt to different situations, coordinate the adjustment of rotating speed, both horizontally and vertically
On effective control is imposed to attitude of flight vehicle；In the horizontal direction can tuning the motor and its driven propeller installation
The front portion or rear portion of horizontal rudder face are being moved entirely, and effective control effect can be achieved；The propeller rotation axis is positioned at described complete dynamic
On the longitudinal centre line of horizontal rudder face；Aircraft redundance force vector control tail vane is suitable for current various fixed-wings and rotation
Rotor aircraft is, it can be achieved that control the effective of attitude of flight vehicle under low speed even zero velocity.
2. a kind of aircraft, it is characterised in that control tail vane including the aircraft redundance force vector described in claim 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711273755.9A CN107972848B (en) | 2017-12-06 | 2017-12-06 | Redundant power vector control tail rudder of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711273755.9A CN107972848B (en) | 2017-12-06 | 2017-12-06 | Redundant power vector control tail rudder of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107972848A true CN107972848A (en) | 2018-05-01 |
| CN107972848B CN107972848B (en) | 2024-03-15 |
Family
ID=62009172
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711273755.9A Active CN107972848B (en) | 2017-12-06 | 2017-12-06 | Redundant power vector control tail rudder of aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN107972848B (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103786881A (en) * | 2014-02-28 | 2014-05-14 | 武汉蓝天翔航空科技有限公司 | Tilting rotor wing helicopter |
| RU2534676C1 (en) * | 2013-05-27 | 2014-12-10 | Дмитрий Сергеевич Дуров | Cryogenic turbo-electric stol aircraft |
| CN106005371A (en) * | 2016-05-27 | 2016-10-12 | 东北师范大学 | Differential and transfer direct-drive unmanned aerial vehicle with three full-flying control surfaces |
| CN106428527A (en) * | 2016-11-30 | 2017-02-22 | 深圳市优鹰科技有限公司 | Dual-axis vector servo turning device with propeller and vertical take-off and landing unmanned aerial vehicle with fixed wings |
| CN106672232A (en) * | 2017-03-02 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Efficient vertical takeoff and landing aircraft |
| CN206552260U (en) * | 2017-03-02 | 2017-10-13 | 北京天宇新超航空科技有限公司 | A kind of efficient vertically taking off and landing flyer |
-
2017
- 2017-12-06 CN CN201711273755.9A patent/CN107972848B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2534676C1 (en) * | 2013-05-27 | 2014-12-10 | Дмитрий Сергеевич Дуров | Cryogenic turbo-electric stol aircraft |
| CN103786881A (en) * | 2014-02-28 | 2014-05-14 | 武汉蓝天翔航空科技有限公司 | Tilting rotor wing helicopter |
| CN106005371A (en) * | 2016-05-27 | 2016-10-12 | 东北师范大学 | Differential and transfer direct-drive unmanned aerial vehicle with three full-flying control surfaces |
| CN106428527A (en) * | 2016-11-30 | 2017-02-22 | 深圳市优鹰科技有限公司 | Dual-axis vector servo turning device with propeller and vertical take-off and landing unmanned aerial vehicle with fixed wings |
| CN106672232A (en) * | 2017-03-02 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Efficient vertical takeoff and landing aircraft |
| CN206552260U (en) * | 2017-03-02 | 2017-10-13 | 北京天宇新超航空科技有限公司 | A kind of efficient vertically taking off and landing flyer |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107972848B (en) | 2024-03-15 |
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| TA01 | Transfer of patent application right |
Effective date of registration: 20210428 Address after: 101300 Cultural Ying Village North, Gaoliying Town, Shunyi District, Beijing (No. 1 Science and Technology Innovation Functional Zone, Linkong Second Road) Applicant after: Beijing Liou Aviation Technology Co.,Ltd. Address before: 100083, No. 14, No. 35, Nanjing Ning building, Xueyuan Road, Beijing, Haidian District, China. 1406-009 Applicant before: BEIJING DIOU AVIATION TECHNOLOGY Co.,Ltd. |
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