CN102874400B - A kind of dirigible afterbody vectored thrust device - Google Patents
A kind of dirigible afterbody vectored thrust device Download PDFInfo
- Publication number
- CN102874400B CN102874400B CN201210403674.7A CN201210403674A CN102874400B CN 102874400 B CN102874400 B CN 102874400B CN 201210403674 A CN201210403674 A CN 201210403674A CN 102874400 B CN102874400 B CN 102874400B
- Authority
- CN
- China
- Prior art keywords
- dirigible
- axis swivel
- thruster
- afterbody
- vectored thrust
- 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.)
- Active
Links
Landscapes
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The invention discloses a kind of dirigible afterbody vectored thrust device.It forms primarily of tail cone, two-freedom turret base, Z axis swivel, Y-axis swivel and thruster, during afterbody vectored thrust device work of the present invention, the deflection of Z axis swivel and Y-axis swivel drives thruster, make it can carry out verting within the scope of ± 90 ° in hull horizontal surface and vertical guide, produce certain vectored thrust, thus realize dirigible pitching, yaw attitude adjustment and the auxiliary effect accelerated.Significantly improve the speed of response that airship's posture (pitching, driftage) regulates, increase control torque, auxiliary increase flying speed, improves the adaptive capacity to environment of dirigible.
Description
Technical field
This technology relates to a kind of dirigible afterbody vectored thrust device, and this device is used for pitching in airship flight process, yaw attitude regulates, and can the flying speed of assisted Extraction height dirigible, belongs to aerostatics control field.
Background technology
Existing dirigible mainly relies on empennage rudder face (covering skeleton type or inflation membrane type) deflection, realizes the pitching of dirigible, driftage controls, thus realize dirigible turning, climb, lower degradation action.The deflection effect of empennage rudder face (covering skeleton type or inflation membrane type) is subject to the restriction that wind carries size, and range of deflection is generally within the scope of ± 30 °.Rely on empennage control surface deflection to realize airship's posture adjustment and mainly there is two problems: one is the increase gradually along with dirigible volume, dirigible utricule length increases, the installation site of empennage on dirigible (general empennage root leading edge is the position of ship body length 75% at distance utricule head) distance dirigible barycenter is far away, the control arm of force of empennage is longer, be subject under wind carries effect, empennage rudder face is difficult to the new line/nose-down pitching moment overcoming dirigible at short notice, thus realizes the adjustment of attitude; Two is along with airship flight is increased (current various countries Airship flying height target is about 20km) highly gradually, the Wind field variety of dirigible working environment is violent, when passing through torrent layer, maximum wind speed reaches the magnitude of 120m/s, and fly period 20km is highly flat, wind speed is generally at below 10m/s, and wind field difference large like this, realizes attitude regulation to tail structure design and dependence Wind and bring difficulty.
Summary of the invention
The present invention is intended to overcome the deficiencies in the prior art, provides that a kind of speed of response is faster, range of control is wider, regulates and use airship's posture control apparatus flexibly, realize the object not relying on extraneous wind field quick adjustment dirigible pitching and yaw attitude.
For achieving the above object, technical scheme provided by the invention is:
Described dirigible afterbody vectored thrust device comprises the tail cone that two-freedom turret base is equipped with in rear end; Described two-freedom turret base is connected with turntable controller; Z axis swivel is installed in two-freedom turret base by the A screw shaft at two ends, and Z axis swivel can to carry out in vertical guide ± 90 ° of deflections around A screw shaft; Y-axis swivel is installed on Z axis swivel by the B screw shaft at two ends, and Y-axis swivel can to carry out in horizontal surface ± 90 ° of deflections around B screw shaft; Described Y-axis swivel is equipped with thruster; Described thruster is connected with thruster controller, and thruster realizes vectored thrust by the deflection of Z axis swivel and Y-axis swivel.
Wherein, described tail cone adopts circular table structure, and its front end is connected with dirigible utricule afterbody with bracing cable by hasp, and rear end is connected with two-freedom turret base by screw; Described thruster is motor or the combination unit for oil machine and screw propeller; Described turntable controller is installed in dirigible End-Management cabinet; Described thruster controller is installed on Z axis swivel or Y-axis swivel.
Compared with prior art, beneficial effect of the present invention is:
In the present invention, the deflection of Z axis swivel and Y-axis swivel drives thruster, make it can carry out verting within the scope of ± 90 ° in hull horizontal surface and vertical guide, produce certain vectored thrust, thus realize dirigible pitching, yaw attitude adjustment and the auxiliary effect accelerated.Significantly improve the speed of response that airship's posture (pitching, driftage) regulates, increase control torque, auxiliary increase flying speed, improves the adaptive capacity to environment of dirigible.
Accompanying drawing explanation
Fig. 1 is dirigible afterbody vectored thrust apparatus structure schematic diagram of the present invention.
In figure: 1-tail cone, 2-two-freedom turret base, 3-Z axle swivel, 4-Y axle swivel, 5-thruster, 6-A screw shaft; 7-B screw shaft; Note: system of axes is with dirigible cephalad apex for initial point, and ox axle forward sensing ship parallel with main gasbag center shaft tail, oy axle forward and main gasbag central axis point to.
Detailed description of the invention
Embodiment 1
See Fig. 1, described dirigible afterbody vectored thrust device comprises the tail cone 1 that two-freedom turret base 2 is equipped with in rear end; Described two-freedom turret base 2 is connected with turntable controller; Z axis swivel 3 is installed in two-freedom turret base 2 by the A screw shaft 6 at two ends, and Z axis swivel 3 can to carry out in vertical guide ± 90 ° of deflections around A screw shaft 6; Y-axis swivel 4 is installed on Z axis swivel 3 by the B screw shaft 7 at two ends, and Y-axis swivel 4 can to carry out in horizontal surface ± 90 ° of deflections around B screw shaft 7; Described Y-axis swivel 4 is equipped with thruster 5; Described thruster 5 is connected with thruster controller.
Wherein, described tail cone 1 is circular table structure, and tail cone 1 front end is connected with dirigible utricule afterbody with bracing cable by hasp, and tail cone 1 rear end is connected with two-freedom turret base 2 by screw; Described thruster 5 is motor.
Claims (3)
1. a dirigible afterbody vectored thrust device, is characterized in that, described dirigible afterbody vectored thrust device comprises the tail cone (1) that two-freedom turret base (2) are equipped with in rear end; Described two-freedom turret base (2) is connected with turntable controller; Z axis swivel (3) is installed in two-freedom turret base (2) by the A screw shaft (6) at two ends, and Z axis swivel (3) can to carry out in vertical guide ± 90 ° of deflections around A screw shaft (6); Y-axis swivel (4) is installed on Z axis swivel (3) by the B screw shaft (7) at two ends, and Y-axis swivel (4) can to carry out in horizontal surface ± 90 ° of deflections around B screw shaft (7); Described Y-axis swivel (4) is equipped with thruster (5); Described thruster (5) is connected with thruster controller; Described tail cone (1) front end is connected with dirigible utricule afterbody with bracing cable by hasp, and tail cone (1) rear end is connected with two-freedom turret base (2) by screw; Described turntable controller is installed in dirigible End-Management cabinet; Described thruster controller is installed on Z axis swivel (3) or Y-axis swivel (4).
2. dirigible afterbody vectored thrust device as claimed in claim 1, it is characterized in that, described thruster (5) is motor.
3. dirigible afterbody vectored thrust device as claimed in claim 1, is characterized in that, the combination unit that described thruster (5) is oil machine and screw propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210403674.7A CN102874400B (en) | 2012-10-22 | 2012-10-22 | A kind of dirigible afterbody vectored thrust device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210403674.7A CN102874400B (en) | 2012-10-22 | 2012-10-22 | A kind of dirigible afterbody vectored thrust device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102874400A CN102874400A (en) | 2013-01-16 |
| CN102874400B true CN102874400B (en) | 2015-08-12 |
Family
ID=47475979
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210403674.7A Active CN102874400B (en) | 2012-10-22 | 2012-10-22 | A kind of dirigible afterbody vectored thrust device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102874400B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104950908B (en) * | 2015-07-02 | 2017-08-15 | 上海交通大学 | Stratospheric airship horizontal level control system and implementation method |
| CN106741918B (en) * | 2017-01-14 | 2022-01-18 | 陕西捷恒航空技术有限责任公司 | Oblique product vector diaxon aircraft control structure |
| CN110091974A (en) * | 2019-06-05 | 2019-08-06 | 南京信息工程大学 | A kind of single driving underwater robot of annular |
| CN111746773B (en) * | 2020-07-10 | 2022-07-01 | 上海交通大学 | Rigid-flexible integrated airship tail cone |
| CN113753214B (en) * | 2021-09-24 | 2023-08-04 | 复旦大学 | Half-lift airship |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB191326897A (en) * | 1913-11-22 | 1915-01-28 | Joseph Macinante | Improvements in the Propulsion of Aerial or Water Vehicles. |
| US4591112A (en) * | 1975-09-09 | 1986-05-27 | Piasecki Aircraft Corporation | Vectored thrust airship |
| CN1128522A (en) * | 1993-08-19 | 1996-08-07 | 洛克希德马丁公司 | Propulsion system for a lighter-than-air vehicle |
| CN1135740A (en) * | 1994-02-18 | 1996-11-13 | 洛克希德·马丁公司 | Propulsion system for a lighter-than-air vehicle |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04169398A (en) * | 1990-10-31 | 1992-06-17 | Sosuke Omiya | Airship |
| JPH058796A (en) * | 1991-07-03 | 1993-01-19 | Canon Inc | Flying body |
| DE19753548A1 (en) * | 1997-12-03 | 1999-08-26 | Daimler Chrysler Ag | Electrically powered air ship, especially zeppelin |
| ATE275065T1 (en) * | 1998-12-11 | 2004-09-15 | Southwest Res Inst | AUTONOMOUS STRATOSPHERE AIRSHIP |
| CN2752175Y (en) * | 2004-12-08 | 2006-01-18 | 李鱼飞 | Man power dynamic light-gas airship |
-
2012
- 2012-10-22 CN CN201210403674.7A patent/CN102874400B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB191326897A (en) * | 1913-11-22 | 1915-01-28 | Joseph Macinante | Improvements in the Propulsion of Aerial or Water Vehicles. |
| US4591112A (en) * | 1975-09-09 | 1986-05-27 | Piasecki Aircraft Corporation | Vectored thrust airship |
| CN1128522A (en) * | 1993-08-19 | 1996-08-07 | 洛克希德马丁公司 | Propulsion system for a lighter-than-air vehicle |
| CN1135740A (en) * | 1994-02-18 | 1996-11-13 | 洛克希德·马丁公司 | Propulsion system for a lighter-than-air vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102874400A (en) | 2013-01-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102874400B (en) | A kind of dirigible afterbody vectored thrust device | |
| CN107176286A (en) | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems | |
| CN204355275U (en) | There is the aircraft of safe propulsion system | |
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| CN205022861U (en) | VTOL fixed wing aircraft | |
| CN101879945A (en) | Electric tilting rotor wing unmanned aerial vehicle | |
| CN201712787U (en) | Electric tilt rotor unmanned aircraft | |
| CN104477376A (en) | Combined pneumatic control method for aerodynamic rudder/reaction control system of hypersonic flight vehicle | |
| CN104590535A (en) | Propelling device for airship power device | |
| CN204310028U (en) | A kind of dirigible two-axle interlocking screw propeller vector propulsion device | |
| CN105223577A (en) | The collapsible sonar unit of a kind of underwater vehicle | |
| CN205022854U (en) | Deformable compound aircraft | |
| CN107953987B (en) | Series hybrid power vector propulsion sea-air detection carrying platform | |
| CN204473123U (en) | Unmanned plane | |
| CN203996872U (en) | A kind of unmanned airplane empennage balance adjusting structure | |
| CN201484655U (en) | Power flying and floating aircraft | |
| CN109808871A (en) | A kind of all-wing aircraft combination rudder face with high maneuvering characteristics | |
| CN102632991A (en) | Wing full-motion airplane without rudder surface | |
| CN206900657U (en) | Gyroplane auto-leveling mechanism | |
| CN203032936U (en) | Passenger helicopter | |
| CN104787305B (en) | A kind of aircraft of the leading edge of a wing with wind ball driving wind wheel | |
| CN103863556A (en) | Device for preventing out-of-control aircraft in air from mountain collision and ocean crash | |
| CN203512023U (en) | Pitching control rudder surface on tail of airframe of airplane | |
| CN202593851U (en) | All-moving wing aircraft without control plane | |
| CN105197230A (en) | Aircraft provided with double rotor wings |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160527 Address after: Three Hunan province Changsha Fenglin Road 410205 No. 217 Patentee after: HUNAN AEROSPACE YUANWANG TECHNOLOGY CO., LTD. Address before: 585 box 3, box 410205, Changsha City, Hunan Province Patentee before: Hunan Aerospace Electromechanical Equipment and Special Material Institute |