CN109353506A - A kind of tailstock formula unmanned plane of double redundancy actuation - Google Patents
A kind of tailstock formula unmanned plane of double redundancy actuation Download PDFInfo
- Publication number
- CN109353506A CN109353506A CN201811160531.1A CN201811160531A CN109353506A CN 109353506 A CN109353506 A CN 109353506A CN 201811160531 A CN201811160531 A CN 201811160531A CN 109353506 A CN109353506 A CN 109353506A
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- China
- Prior art keywords
- rudder
- vector
- degrees
- pedestal
- elevator
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of tailstock formula unmanned planes of double redundancy actuation, it is characterised in that contains: fuselage, wing, rotor engine, two degrees of freedom vector pedestal, vector steering engine, aileron, elevator, rudder, rudder face steering engine.The rotor engine is mounted on the two degrees of freedom vector pedestal, the two degrees of freedom vector pedestal is fixed on the fore-body, the deflection of rotor engine omnidirectional described in the vector servo driving, the aileron is mounted below the wing, the elevator and the rudder are mounted on afterbody, aileron described in the rudder face servo driving, the elevator and the rudder kick.Unmanned plane of the invention is using two degrees of freedom thrust vectoring and controls the double redundancy that combines of rudder face and makees flowing mode, ensure that entire flight envelope gesture stability it is reliable with it is efficient, be suitable for popularization and application.
Description
Technical field
The invention belongs to field of flight vehicle design, are related to vehicle reliability design, control efficiency analysis.
Background technique
Tailstock formula unmanned plane has the ability of rotor wing unmanned aerial vehicle VTOL and hovering, has both fixed-wing unmanned plane and flies
The advantages that scanning frequency degree is fast, the cruise time is long, receives significant attention in recent years and studies.The unmanned mechanism type of domestic and international tailstock formula at present
Can probably it be divided into: single rotor (rudder face control), more rotors (thrust Differential Control), ducted fan (thruster vector control), double/more
Rotor (thrust is differential and rudder face controls).Existing tailstock formula unmanned plane is usually filled when configuration designs with required power and actuation
Simple and minimum number is set as main target, not can guarantee the reliability of unmanned plane manipulation.In addition, since power and actuation fill
The limitation set, the existing unmanned mechanism type of tailstock formula often only have higher manipulation efficiency under particular flight state, do not have complete
The efficient gesture stability ability of flight envelope.
Summary of the invention
In order to overcome the problems such as above-mentioned tailstock formula unmanned plane reliability is insufficient, full flight envelope control efficiency is low, the present invention
There is provided a kind of full flight envelope control reliable, efficient double redundancy actuation tailstock formula unmanned plane.
A kind of tailstock formula unmanned plane of double redundancy actuation belongs to technical field of aircraft design, which is characterized in that including (such as
Shown in Fig. 1) fuselage (1), wing (2), rotor engine (3), two degrees of freedom vector pedestal (4), vector steering engine (5), aileron
(6), elevator (7), rudder (8), rudder face steering engine (9).
Rotor engine (3) is mounted on two degrees of freedom vector pedestal (4), and two degrees of freedom vector pedestal (4) is fixed on machine
Body (1) front, vector steering engine (5) drive the deflection of rotor engine (3) omnidirectional, and aileron (6) is mounted below wing (2), lifting
Rudder (7) and rudder (8) are mounted on afterbody, and rudder face steering engine (9) drives aileron (6), elevator (7) and rudder (8) inclined
Turn.
As shown in Fig. 2, unmanned plane of the invention is bowed by deflection two degrees of freedom vector pedestal (4) and elevator (7) realization
Face upward channel gesture stability.
As shown in figure 3, unmanned plane of the invention is realized partially by deflection two degrees of freedom vector pedestal (4) and rudder (8)
Navigate channel gesture stability.
As shown in figure 4, unmanned plane of the invention realizes roll channel gesture stability by rudderon (6).
The present invention has the advantages that unmanned plane of the invention uses the control mode of double redundancy actuation, control is improved
Reliability.Unmanned plane of the invention can mainly pass through deflection two degrees of freedom vector pedestal (4) and aileron under low-speed condition
(4) gesture stability is realized；Under the flat winged state of high speed, it is real can mainly to pass through rudderon (6), elevator (7) and rudder (8)
Existing gesture stability, has the efficient gesture stability ability of full flight envelope.
Detailed description of the invention
A kind of Fig. 1: unmanned mechanism type schematic diagram of the tailstock formula of double redundancy actuation.
A kind of Fig. 2: tailstock formula unmanned plane pitch control schematic diagram of double redundancy actuation.
A kind of Fig. 3: tailstock formula unmanned plane yaw control schematic diagram of double redundancy actuation.
A kind of Fig. 4: tailstock formula unmanned machine rolling control schematic diagram of double redundancy actuation.
Specific embodiment
Using drawings and examples, the present invention will be further described below, and attached drawing described herein is used to provide to this
Further understanding for invention, constitutes part of this application, and do not constitute a limitation of the invention.
A kind of unmanned mechanism type schematic diagram of tailstock formula of double redundancy actuation as shown in Figure 1, fuselage (1) and wing (2) are adopted
Mitigate unmanned plane overall weight with kt plate matter, rotor engine (3) is mounted on two degrees of freedom vector pedestal (4), and two freely
Spending vector pedestal (4) maximum deflection angle is 20 degree, and two degrees of freedom vector pedestal (4) is fixed on fuselage (1) front, vector steering engine
(5) deflection of driving rotor engine (3) omnidirectional, aileron (6) are mounted below wing (2), elevator (7) and rudder (8) peace
Mounted in afterbody, rudder face steering engine (9) drives aileron (6), elevator (7) and rudder (8) deflection.
As shown in Fig. 2, unmanned plane of the invention is real by deflection two degrees of freedom vector pedestal (4) and the elevator (7)
Existing pitch channel gesture stability.
As shown in figure 3, unmanned plane of the invention is real by deflection two degrees of freedom vector pedestal (4) and the rudder (8)
Existing jaw channel gesture stability.
As shown in figure 4, unmanned plane of the invention realizes roll channel gesture stability by rudderon (6).
Unmanned plane of the invention is main to pass through deflection two degrees of freedom vector pedestal (4) and aileron under low-speed condition
(4) gesture stability is realized；Under the flat winged state of high speed, mainly realized by rudderon (6), elevator (7) and rudder (8)
Gesture stability, to realize reliable, the efficient control of full flight envelope.
Above-described specific embodiment has carried out further the purpose of the present invention, technical scheme and beneficial effects
It is described in detail, it should be understood that being not intended to limit the present invention the foregoing is merely a specific embodiment of the invention
Protection scope, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should all include
Within protection scope of the present invention.
Claims (1)
1. a kind of tailstock formula unmanned plane of double redundancy actuation, which is characterized in that including fuselage (1), wing (2), rotor engine
(3), two degrees of freedom vector pedestal (4), vector steering engine (5), aileron (6), elevator (7), rudder (8), rudder face steering engine (9)；
The rotor engine (3) is mounted on the two degrees of freedom vector pedestal (4), and the two degrees of freedom vector pedestal (4) is fixed
In the fuselage (1) front, the vector steering engine (5) drives rotor engine (3) the omnidirectional deflection, aileron (6) peace
Below the wing (2), the elevator (7) and the rudder (8) are mounted on the fuselage (1) tail portion, the rudder
Face steering engine (9) drives the aileron (6), the elevator (7) and the rudder (8) deflection；A kind of double redundancy actuation
Tailstock formula unmanned plane by deflect the two degrees of freedom vector pedestal (4) and the elevator (7) realization pitch channel posture
Control is realized jaw channel gesture stability by deflecting the two degrees of freedom vector pedestal (4) and the rudder (8), is passed through
It deflects the aileron (6) and realizes roll channel gesture stability.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811160531.1A CN109353506A (en) | 2018-09-30 | 2018-09-30 | A kind of tailstock formula unmanned plane of double redundancy actuation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811160531.1A CN109353506A (en) | 2018-09-30 | 2018-09-30 | A kind of tailstock formula unmanned plane of double redundancy actuation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109353506A true CN109353506A (en) | 2019-02-19 |
Family
ID=65348714
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811160531.1A Pending CN109353506A (en) | 2018-09-30 | 2018-09-30 | A kind of tailstock formula unmanned plane of double redundancy actuation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109353506A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111532428A (en) * | 2020-04-28 | 2020-08-14 | 北京航空航天大学 | Tilting power micro fixed wing unmanned aerial vehicle capable of freely taking off and landing |
| CN112937916A (en) * | 2021-01-27 | 2021-06-11 | 西北工业大学深圳研究院 | Space robot capable of reducing wake effect of attitude engine and working method of space robot |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| US8505846B1 (en) * | 2010-05-11 | 2013-08-13 | II Stanley Gordon Sanders | Vertical takeoff and landing aircraft |
| EP3121117A1 (en) * | 2015-07-23 | 2017-01-25 | Sikorsky Aircraft Corporation | Control system and strategy for tail sitter |
| CN207773470U (en) * | 2017-12-15 | 2018-08-28 | 江西希德防务***技术有限公司 | A kind of vector power tailstock formula double side wings unmanned plane |
-
2018
- 2018-09-30 CN CN201811160531.1A patent/CN109353506A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| US8505846B1 (en) * | 2010-05-11 | 2013-08-13 | II Stanley Gordon Sanders | Vertical takeoff and landing aircraft |
| EP3121117A1 (en) * | 2015-07-23 | 2017-01-25 | Sikorsky Aircraft Corporation | Control system and strategy for tail sitter |
| CN207773470U (en) * | 2017-12-15 | 2018-08-28 | 江西希德防务***技术有限公司 | A kind of vector power tailstock formula double side wings unmanned plane |
Non-Patent Citations (1)
| Title |
|---|
| 刘东辉等: "矢量拉力垂直起降无人机姿态纵向控制研究", 《计算机工程与应用》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111532428A (en) * | 2020-04-28 | 2020-08-14 | 北京航空航天大学 | Tilting power micro fixed wing unmanned aerial vehicle capable of freely taking off and landing |
| CN112937916A (en) * | 2021-01-27 | 2021-06-11 | 西北工业大学深圳研究院 | Space robot capable of reducing wake effect of attitude engine and working method of space robot |
| CN112937916B (en) * | 2021-01-27 | 2022-12-06 | 西北工业大学深圳研究院 | Space robot for reducing influence of tail flow of attitude engine and working method thereof |
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| PB01 | 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 |
Application publication date: 20190219 |
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| RJ01 | Rejection of invention patent application after publication |