CN203698643U - Airship vector thrust device and airship - Google Patents
Airship vector thrust device and airship Download PDFInfo
- Publication number
- CN203698643U CN203698643U CN201420080464.3U CN201420080464U CN203698643U CN 203698643 U CN203698643 U CN 203698643U CN 201420080464 U CN201420080464 U CN 201420080464U CN 203698643 U CN203698643 U CN 203698643U
- Authority
- CN
- China
- Prior art keywords
- dirigible
- airship
- utricule
- clamping rings
- thrust device
- 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.)
- Expired - Lifetime
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 37
- 239000000725 suspension Substances 0.000 claims description 9
- 238000005728 strengthening Methods 0.000 claims description 7
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 239000002775 capsule Substances 0.000 abstract 4
- 238000009434 installation Methods 0.000 description 7
- 101100433229 Caenorhabditis elegans zip-4 gene Proteins 0.000 description 1
- 206010057071 Rectal tenesmus Diseases 0.000 description 1
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 208000012271 tenesmus Diseases 0.000 description 1
Landscapes
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The utility model relates to an airship and particularly relates to a vector thrust device on an airship and an airship with the vector thrust devices. The vector thrust device comprises a fixation ring, and a rotation mechanism, a motor and a controller are mounted on the fixation ring. One or a plurality of parallel cambered rods is or are arranged on the outer side of the fixation ring which is connected with the cambered rods through supporting frames. A capsule is arranged in the airship, the airship vector thrust devices are mounted symmetrically on the left and right sides and/or the front and rear ends of the capsule symmetrically. The cambered rods are connected with the capsule through connection mechanisms, and the radian of the cambered rods is accordant with the radian of the outer wall of the capsule at the corresponding connection position. According to the airship vector thrust device and the airship, perpendicular/runway landing and vector control of aerial maneuvering flight of the airship are achieved through the side arrangement of the thrust devices, the spliced cambered rod mounting structure and the independent control mechanism, the device is adapted to vector thrust of airships of novel and unique shapes (double- ellipsoidal, spherical and butterfly shapes), and differential control of the airship can be achieved.
Description
Technical field
The utility model relates to a kind of dirigible, is specially the vectored thrust device on dirigible and the dirigible of this vectored thrust device is installed.
Background technology
Dirigible be a kind of main rely on air lift force (or claiming static lift) overcome self gravitation, with thruster, can maneuvering flight aerocraft.Tradition dirigible is arranged on driving engine the both sides of utricule belly gondola, adopts a set of inclining rotary mechanism to drive turn of engine to produce thrust.This layout type is because thrust is arranged in the below of dirigible center of gravity, the phenomenon that while existing thrust to accelerate, dirigible pitch angle increases; Owing to adopting a set of inclining rotary mechanism to drive two cover simultaneous firings, high to inclining rotary mechanism requirement, in the time that inclining rotary mechanism breaks down, two driving engines all can not be realized vectored thrust, are unfavorable for the safe landing of dirigible.Dirigible is as aerial platform, the capacity weight carrying is varied, along with load volume increases, the raising of installation requirement, the utricule size of the single ellipsoid dirigible of tradition has been difficult to meet load installation requirement, produce accordingly the dirigible of a lot of new external forms, as two ellipsoid dirigibles, flat dirigible, spherical dirigible etc.
Summary of the invention
The purpose of this utility model is, for the deficiencies in the prior art, provides a kind of dirigible vectored thrust device and dirigible, makes dirigible possess vectored thrust, guarantees the stability that thruster is installed, and can realize the differentiating control of dirigible.
The technical solution of the utility model is, a kind of dirigible vectored thrust device, comprises inclining rotary mechanism, driving engine and controller, and this thruster is also provided with clamping rings, and described inclining rotary mechanism, driving engine and controller are installed on clamping rings; The outside of described clamping rings is provided with one or many parallel circular arc bars, and described clamping rings is connected with circular arc bar by bracing frame.
Left and right driving engine and controller are the independent control mechanisms of two covers, can synchro control or differentiating control.Inclining rotary mechanism, driving engine and controller are arranged in clamping rings, can make full use of space, and can guarantee the installation stability of inclining rotary mechanism, driving engine and controller, and the circular arc bar arranging can be used for being connected with the utricule of dirigible, realize being rigidly connected of utricule and thruster, guarantee thruster installation firmly.
The outer end of clamping rings is arranged with two groups of bracing frames, is symmetrical arranged the stability that two groups of bracing frames can guarantee that clamping rings is connected with circular arc bar.
Support frame as described above is made up of many strut bars, and the top of many strut bars links into an integrated entity and passes through the first fastener and is connected with clamping rings, and the bottom of strut bar is connected with circular arc bar by the second fastener.
Preferably, the first fastener is screw and nut, and the second fastener is special fit and bearing pin.
Bracing frame is made up of many strut bars, and whole bracing frame has multiple spot to be connected with circular arc bar, and the stability of bracing frame is better.
The technical solution of the utility model also relates to a kind of dirigible, there is utricule, the above-mentioned dirigible vectored thrust device of the symmetrical installation in the left and right sides of described utricule and/or front and back end, described circular arc bar is connected with utricule by bindiny mechanism, and the radian of described circular arc bar is consistent with the utricule outer wall radian of corresponding connection location.
Dirigible vectored thrust device can be set respectively or simultaneously in the utricule left and right sides, rear and front end as required.
Engine controller is realized igniting, speed governing, flame-out control of driving engine, and the rotation of driven by engine screw propeller, produces thrust.Inclining rotary mechanism, under controller action, drives tiliting axis to carry out verting of 270 ° of scopes by steering wheel, and driving engine and screw propeller carry out verting of 270 ° of scopes, realize the change of thrust direction, make dirigible possess vectored thrust upwards, forward and backward.The driving engine of overlap/quadruplet of dirigible two thruster and controller, inclining rotary mechanism are all independent controls, have both had good synchronism, again can differentiating control, and realizing turns controls flexibly; In the time of a set of driving engine and controller or inclining rotary mechanism fault, another set of or other many covers still can be worked, and guarantee dirigible safe landing.
Adopt circular arc bar mounting structure to realize being rigidly connected of utricule and thruster, guarantee in-flight thruster installation firmly, the phenomenons such as nothing is rocked, tenesmus; Inclining rotary mechanism control setup and engine control unit adopt respectively independently mechanism of two covers or quadruplet, realize individual operation and the control of many cover thrust devices; By dirigible vectored thrust device being arranged on to the left and right sides and/or the rear and front end of utricule, can make dirigible possess vectored thrust.
Described dirigible is also provided with the strengthening mechanism being connected between utricule and dirigible vectored thrust device for reinforcing.Described strengthening mechanism comprise be located at bracing frame and the suspension ring of clamping rings connecting portion, symmetrically centered by suspension ring be located at multiple load sticking patch on utricule, for being connected the steel zip of suspension ring and load sticking patch.
Strengthening mechanism can prevent that thrust devices is rocked or dropped in-flight, the stability that keeps dirigible vectored thrust device to be connected with utricule.
Preferably, bindiny mechanism is the combination connecting mode of velcro and tied rope.
The utility model adopts thruster side layout, spliced circular arc bar mounting structure, independent control mechanism to realize vertical/sliding vector controlled of running landing, air maneuver of dirigible, more be adapted to the vectored thrust of novel unique profile (two elliposoidal, spherical, butterfly) dirigible, can realize the differentiating control of dirigible, more be conducive to the turning control of dirigible, and in the time of a set of inclining rotary mechanism fault, can rely on another set of inclining rotary mechanism to realize safe flight and the Landing Control of dirigible.
Accompanying drawing explanation
Fig. 1 is the structural representation of dirigible vectored thrust device described in the utility model;
Fig. 2 is the back view of dirigible described in the utility model;
Fig. 3 is the lateral plan of dirigible described in the utility model.
The specific embodiment
As shown in Figure 1, a kind of dirigible vectored thrust device, the screw propeller 8 that comprises inclining rotary mechanism 6, driving engine and controller 7, is connected with driving engine and controller, this thruster is also provided with clamping rings 5, and inclining rotary mechanism 6, screw propeller 8, driving engine and controller 7 are installed on clamping rings 5; The outside of clamping rings 5 is provided with two parallel circular arc bars 10, and described clamping rings 5 is connected with circular arc bar 10 by bracing frame 9.
The outer end of clamping rings 5 is arranged with upper and lower two groups of bracing frames 9.
Bracing frame 9 forms cone by 4 strut bars, and the top of many strut bars links into an integrated entity and is connected with clamping rings 5 by the first fastener, and the bottom of strut bar is connected with circular arc bar 10 by the second fastener; The first fastener is screw and nut, and the second fastener is special fit and bearing pin.
As shown in Figure 2 and Figure 3, a kind of dirigible, has utricule 2, and utricule comprises left side ellipsoid and right side ellipsoid, and left side ellipsoid and right side ellipsoid from back to front portion close up gradually, are connected in one at head; The above-mentioned dirigible vectored thrust device 1 of the symmetrical installation in the left and right sides of utricule 2 and/or front and back end, circular arc bar 10 is connected with utricule 2 by bindiny mechanism, and the radian of described circular arc bar 10 is consistent with the utricule of corresponding connection location 2 outer wall radians; Bindiny mechanism is velcro and tied rope.
Dirigible is also provided with the strengthening mechanism being connected between utricule 2 and dirigible vectored thrust device 1 for reinforcing, strengthening mechanism comprise be located at bracing frame 9 and the suspension ring of clamping rings 5 connecting portions, symmetrically centered by suspension ring be located at multiple load sticking patch 3 on utricule 2, for being connected the steel zip 4 of suspension ring and load sticking patch 3.
Claims (7)
1. a dirigible vectored thrust device, comprise inclining rotary mechanism (6), driving engine and controller (7), it is characterized in that, this thruster is also provided with clamping rings (5), and described inclining rotary mechanism (6), driving engine and controller (7) are installed on clamping rings (5); The outside of described clamping rings (5) is provided with one or parallel many circular arc bars (10), and described clamping rings (5) is connected with circular arc bar (10) by bracing frame (9).
2. dirigible vectored thrust device according to claim 1, is characterized in that, the outer end of clamping rings (5) is arranged with two groups of bracing frames (9).
3. according to dirigible vectored thrust device described in claim 1 or 2, it is characterized in that, support frame as described above (9) is made up of many strut bars, the top of many strut bars links into an integrated entity and passes through the first fastener and is connected with clamping rings (5), and the bottom of strut bar is connected with circular arc bar (10) by the second fastener.
4. a dirigible, there is utricule (2), it is characterized in that, symmetrical one of the claim 1-3 described dirigible vectored thrust device (1) of installing in the left and right sides of described utricule (2) and/or front and back end, described circular arc bar (10) is connected with utricule (2) by bindiny mechanism, and the radian of described circular arc bar (10) is consistent with utricule (2) the outer wall radian of corresponding connection location.
5. dirigible according to claim 4, is characterized in that, described dirigible is also provided with the strengthening mechanism being connected between utricule (2) and dirigible vectored thrust device (1) for reinforcing.
6. dirigible according to claim 5, it is characterized in that, described strengthening mechanism comprise be located at bracing frame (9) and the suspension ring of clamping rings (5) connecting portion, centered by suspension ring symmetry be located at multiple load sticking patch (3) on utricule (2), for being connected the steel zip (4) of suspension ring and load sticking patch (3).
7. dirigible according to claim 4, is characterized in that, described bindiny mechanism is velcro and tied rope.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420080464.3U CN203698643U (en) | 2014-02-25 | 2014-02-25 | Airship vector thrust device and airship |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420080464.3U CN203698643U (en) | 2014-02-25 | 2014-02-25 | Airship vector thrust device and airship |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203698643U true CN203698643U (en) | 2014-07-09 |
Family
ID=51049118
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420080464.3U Expired - Lifetime CN203698643U (en) | 2014-02-25 | 2014-02-25 | Airship vector thrust device and airship |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203698643U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104210640A (en) * | 2014-09-18 | 2014-12-17 | 北京航空航天大学 | Stratosphere aerostat vector propelling device |
| CN104443343A (en) * | 2014-11-13 | 2015-03-25 | 上海交通大学 | Vectored thruster suspension type flight device |
| CN105620709A (en) * | 2014-10-27 | 2016-06-01 | 中国科学院光电研究院 | Vector propelling device for two-shaft linkage propeller for airship |
| CN108263592A (en) * | 2018-02-26 | 2018-07-10 | 中国科学院光电研究院 | Triaxial ellipsoid dirigible |
| CN109808859A (en) * | 2019-03-20 | 2019-05-28 | 上海彩虹鱼深海装备科技有限公司 | A kind of manned underwater vehicle of centrosymmetric structure |
-
2014
- 2014-02-25 CN CN201420080464.3U patent/CN203698643U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104210640A (en) * | 2014-09-18 | 2014-12-17 | 北京航空航天大学 | Stratosphere aerostat vector propelling device |
| CN105620709A (en) * | 2014-10-27 | 2016-06-01 | 中国科学院光电研究院 | Vector propelling device for two-shaft linkage propeller for airship |
| CN105620709B (en) * | 2014-10-27 | 2018-03-06 | 中国科学院光电研究院 | A kind of dirigible two-axle interlocking propeller vector propulsion device |
| CN104443343A (en) * | 2014-11-13 | 2015-03-25 | 上海交通大学 | Vectored thruster suspension type flight device |
| CN108263592A (en) * | 2018-02-26 | 2018-07-10 | 中国科学院光电研究院 | Triaxial ellipsoid dirigible |
| CN108263592B (en) * | 2018-02-26 | 2024-05-07 | 中国科学院光电研究院 | Triaxial ellipsoid airship |
| CN109808859A (en) * | 2019-03-20 | 2019-05-28 | 上海彩虹鱼深海装备科技有限公司 | A kind of manned underwater vehicle of centrosymmetric structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203698643U (en) | Airship vector thrust device and airship | |
| CN104085530B (en) | The coaxial multi-rotor aerocraft of duct | |
| WO2017107720A1 (en) | Multirotor manned aerial vehicle | |
| CN103935517B (en) | Aircraft | |
| CN105564664B (en) | Short distance takes off method | |
| CN103552686A (en) | Combined type ducted aerial reconnaissance robot | |
| CN105109677A (en) | Composite aircraft composed of fixed wings and multi-rotary wings and control method of composite aircraft | |
| CN104276281A (en) | One-man flight vehicle | |
| CN102490897A (en) | Multi-driving embedded rotor manned helicopter | |
| CN103057702A (en) | Jet-propelled rotor helicopter | |
| CN205469803U (en) | Manned aircraft | |
| US1838248A (en) | Airship | |
| CN104417750A (en) | Tandem tilt rotor aircraft | |
| CN104875875B (en) | A kind of gas wing-type air-flow orients load transportation aircraft | |
| US1825363A (en) | Water plane | |
| CA2914287A1 (en) | Aircraft with rotating outer shells | |
| US3469804A (en) | Rotary and circular saucer-shaped airfoil aircraft | |
| CN101525049B (en) | High-speed rotator type helicopter | |
| CN204134213U (en) | Aeromodelling airplane VTOL power rack | |
| CN202481307U (en) | Four-propeller aircraft taking off and landing vertically | |
| CN102910287A (en) | Rotor aircraft | |
| CN105329441A (en) | Combined four-shaft flying-wing aircraft | |
| CN101920787A (en) | Aircraft fuselage orientation adjustment steering wheel stand | |
| CN105691614B (en) | A kind of double drive class flapping wing aircrafts | |
| CN102862680A (en) | Spherically dished aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20160526 Address after: Three Hunan province Changsha Fenglin Road 410205 No. 217 Patentee after: HUNAN AEROSPACE YUANWANG SCIENCE & TECHNOLOGY Co.,Ltd. Address before: Three Hunan province Changsha Fenglin Road 410205 No. 217 Patentee before: Hunan Aerospace Electromechanical Equipment and Special Material Institute |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140709 |