CN102874400A - Airship tail vectored thrust device - Google Patents
Airship tail vectored thrust device Download PDFInfo
- Publication number
- CN102874400A CN102874400A CN2012104036747A CN201210403674A CN102874400A CN 102874400 A CN102874400 A CN 102874400A CN 2012104036747 A CN2012104036747 A CN 2012104036747A CN 201210403674 A CN201210403674 A CN 201210403674A CN 102874400 A CN102874400 A CN 102874400A
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- Prior art keywords
- airship
- dirigible
- vectored thrust
- thrust device
- axis swivel
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Abstract
The invention discloses an airship tail vectored thrust device which mainly comprises a tail cone, a two-degree-of-freedom rotary table base, a Z-axis rotating body, a Y-axis rotating body and thrust devices. When the airship tail vectored thrust device is operated, deflection of the Z-axis rotating body and the Y-axis rotating body drives the thrust devices to enable the same to rotate tipsily in an airship body plane and a vertical plane within the range of +/-90 degrees, and a certain vectored thrust is generated, so that pitching and yaw attitude adjustment and auxiliary acceleration of an airship are achieved. By the aid of the airship tail vectored thrust device, response speed of airship attitude (pitching and yaw) adjustment is remarkably increased, control torque is increased, flying speed is increased in an assisted manner, and environmental adaptability of the airship is enhanced.
Description
Technical field
Present technique relates to a kind of dirigible afterbody vectored thrust device, and this device is used for pitching, yaw attitude of airship flight process to be regulated, but and the flying speed of the high dirigible of assisted Extraction, belong to the aerostatics control field.
Background technology
Existing dirigible mainly relies on empennage rudder face (covering skeleton type or inflation membrane type) deflection, realizes pitching, the driftage control of dirigible, thus realize dirigible turning, climb, the action of lower degradation.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 in ± 30 ° of scopes.Rely on the empennage control surface deflection to realize two problems of the main existence of airship's posture adjusting: the one, along with the gradually increase of dirigible volume, dirigible utricule length increases, the installation site (general empennage root leading edge at distance utricule head be the position of ship height degree 75%) of empennage on dirigible is far away apart from the dirigible barycenter, the control arm of force of empennage is longer, carry under the effect being subject to wind, the empennage rudder face is difficult to overcome at short notice the new line/nose-down pitching moment of dirigible, thereby realizes the adjustment of attitude; The 2nd, along with (various countries' Airship flying height target is about 20km at present) increased in airship flight highly gradually, the wind field of dirigible working environment changes violent, when passing through the torrent layer, maximum wind speed reaches the magnitude of 120m/s, and during the 20km height flat flies, generally below 10m/s, large like this wind field difference realizes that to tail structure design and dependence Wind attitude regulation brings difficulty to wind speed.
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 flexibly airship's posture control apparatus, realizes not relying on the purpose of 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 that the rear end is equipped with the tail cone of two-freedom turret base; Described two-freedom turret base is connected with turntable controller; The Z axis swivel is installed on the two-freedom turret base by the A screw shaft at two ends, and the Z axis swivel can be in the A screw shaft carries out vertical guide ± 90 ° of deflections; The Y-axis swivel is installed on the Z axis swivel by the B screw shaft at two ends, and the Y-axis swivel can be in the B screw shaft carries out horizontal surface ± 90 ° of deflections; On the described Y-axis swivel thruster is housed; Described thruster is connected with the thruster controller, and thruster is realized vectored thrust by the deflection of Z axis swivel and Y-axis swivel.
Wherein, described tail cone adopts the circular table structure, and its front end is connected with dirigible utricule afterbody with bracing cable by hasp, and the rear end is connected with the two-freedom turret base by screw; Described thruster is motor or is the composite set of oil machine and screw propeller; Described turntable controller is installed in the dirigible End-Management cabinet; Described thruster controller is installed on Z axis swivel or the Y-axis swivel.
Compared with prior art, beneficial effect of the present invention is:
Among the present invention, the deflection of Z axis swivel and Y-axis swivel drives thruster, make it can in hull horizontal surface and vertical guide, carry out verting in ± 90 ° of scopes, produce certain vectored thrust, thereby realize dirigible pitching, yaw attitude adjustment and the auxiliary effect of accelerating.Significantly improved the speed of response that airship's posture (pitching, driftage) is regulated, increased control torque, assisting increases flying speed, has improved the adaptive capacity to environment of dirigible.
Description of drawings
Fig. 1 is dirigible afterbody vectored thrust apparatus structure schematic diagram of the present invention.
Among the figure: 1-tail cone, 2-two-freedom turret base, 3-Z axle swivel, 4-Y axle swivel, 5-thruster, 6-A screw shaft; The 7-B screw shaft; Annotate: system of axes is take dirigible head summit as initial point, and ox axle forward and main gasbag central axes are pointed to the ship tail, in the sensing vertical with the main gasbag center shaft of oy axle forward.
The specific embodiment
Embodiment 1
Referring to Fig. 1, described dirigible afterbody vectored thrust device comprises that the rear end is equipped with the tail cone 1 of two-freedom turret base 2; Described two-freedom turret base 2 is connected with turntable controller; Z axis swivel 3 is installed on the two-freedom turret base 2 by the A screw shaft 6 at two ends, and Z axis swivel 3 can carry out in the vertical guide around A screw shaft 6 ± 90 ° of deflections; Y-axis swivel 4 is installed on the Z axis swivel 3 by the B screw shaft 7 at two ends, and Y-axis swivel 4 can carry out in the horizontal surface around B screw shaft 7 ± 90 ° of deflections; On the described Y-axis swivel 4 thruster 5 is housed; Described thruster 5 is connected with the thruster controller.
Wherein, described tail cone 1 is the 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 (5)
1. a dirigible afterbody vectored thrust device is characterized in that, described dirigible afterbody vectored thrust device comprises that the rear end is equipped with the tail cone of two-freedom turret base (2) (1); Described two-freedom turret base (2) is connected with turntable controller; Z axis swivel (3) is installed on the two-freedom turret base (2) by the A screw shaft (6) at two ends, and Z axis swivel (3) can carry out in the vertical guide around A screw shaft (6) ± 90 ° of deflections; Y-axis swivel (4) is installed on the Z axis swivel (3) by the B screw shaft (7) at two ends, and Y-axis swivel (4) can carry out in the horizontal surface around B screw shaft (7) ± 90 ° of deflections; Thruster (5) is housed on the described Y-axis swivel (4); Described thruster (5) is connected with the thruster controller.
2. dirigible afterbody vectored thrust device as claimed in claim 1 is characterized in that, 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.
3. dirigible afterbody vectored thrust device as claimed in claim 1 is characterized in that, described thruster (5) is motor.
4. dirigible afterbody vectored thrust device as claimed in claim 1 is characterized in that, described thruster (5) is the composite set of oil machine and screw propeller.
5. such as each described dirigible afterbody vectored thrust device of claim 1 to 5, it is characterized in that, described turntable controller is installed in the dirigible End-Management cabinet; Described thruster controller is installed on Z axis swivel (3) or the Y-axis swivel (4).
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 true CN102874400A (en) | 2013-01-16 |
| CN102874400B CN102874400B (en) | 2015-08-12 |
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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 |
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| CN (1) | CN102874400B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104950908A (en) * | 2015-07-02 | 2015-09-30 | 上海交通大学 | Horizontal position control system for stratospheric airship as well as implementing method |
| CN106741918A (en) * | 2017-01-14 | 2017-05-31 | 陕西捷恒新材料有限责任公司 | The axle flying vehicles control structure of skew product vector two |
| 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 |
| CN111746773A (en) * | 2020-07-10 | 2020-10-09 | 上海交通大学 | Rigid-flexible integrated airship tail cone |
| CN113753214A (en) * | 2021-09-24 | 2021-12-07 | 复旦大学 | Half-lift airship |
Citations (9)
| 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 |
| JPH04169398A (en) * | 1990-10-31 | 1992-06-17 | Sosuke Omiya | Airship |
| JPH058796A (en) * | 1991-07-03 | 1993-01-19 | Canon Inc | Flying body |
| 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 |
| DE19753548A1 (en) * | 1997-12-03 | 1999-08-26 | Daimler Chrysler Ag | Electrically powered air ship, especially zeppelin |
| US20020134884A1 (en) * | 1998-12-11 | 2002-09-26 | Southwest Research Institute | Autonomous stratospheric airship |
| CN2752175Y (en) * | 2004-12-08 | 2006-01-18 | 李鱼飞 | Man power dynamic light-gas airship |
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2012
- 2012-10-22 CN CN201210403674.7A patent/CN102874400B/en active Active
Patent Citations (9)
| 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 |
| JPH04169398A (en) * | 1990-10-31 | 1992-06-17 | Sosuke Omiya | Airship |
| JPH058796A (en) * | 1991-07-03 | 1993-01-19 | Canon Inc | Flying body |
| 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 |
| DE19753548A1 (en) * | 1997-12-03 | 1999-08-26 | Daimler Chrysler Ag | Electrically powered air ship, especially zeppelin |
| US20020134884A1 (en) * | 1998-12-11 | 2002-09-26 | Southwest Research Institute | Autonomous stratospheric airship |
| CN2752175Y (en) * | 2004-12-08 | 2006-01-18 | 李鱼飞 | Man power dynamic light-gas airship |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104950908A (en) * | 2015-07-02 | 2015-09-30 | 上海交通大学 | Horizontal position control system for stratospheric airship as well as implementing method |
| CN104950908B (en) * | 2015-07-02 | 2017-08-15 | 上海交通大学 | Stratospheric airship horizontal level control system and implementation method |
| CN106741918A (en) * | 2017-01-14 | 2017-05-31 | 陕西捷恒新材料有限责任公司 | The axle flying vehicles control structure of skew product vector two |
| 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 |
| CN111746773A (en) * | 2020-07-10 | 2020-10-09 | 上海交通大学 | Rigid-flexible integrated airship tail cone |
| CN111746773B (en) * | 2020-07-10 | 2022-07-01 | 上海交通大学 | Rigid-flexible integrated airship tail cone |
| CN113753214A (en) * | 2021-09-24 | 2021-12-07 | 复旦大学 | Half-lift airship |
| CN113753214B (en) * | 2021-09-24 | 2023-08-04 | 复旦大学 | Half-lift airship |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102874400B (en) | 2015-08-12 |
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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 |