CN102030106A - Omnidirectional traction type rotor reconnaissance aircraft and system thereof - Google Patents
Omnidirectional traction type rotor reconnaissance aircraft and system thereof Download PDFInfo
- Publication number
- CN102030106A CN102030106A CN2010105654761A CN201010565476A CN102030106A CN 102030106 A CN102030106 A CN 102030106A CN 2010105654761 A CN2010105654761 A CN 2010105654761A CN 201010565476 A CN201010565476 A CN 201010565476A CN 102030106 A CN102030106 A CN 102030106A
- Authority
- CN
- China
- Prior art keywords
- scout
- omnidirectional
- aircraft
- traction
- center
- 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.)
- Pending
Links
Images
Landscapes
- Alarm Systems (AREA)
Abstract
The invention relates to a military, police and civil omnidirectional traction type rotor reconnaissance aircraft and a system thereof, which can perform air observation, tacking and the and other tasks for a target for a long time and provide permanent real-time conditions for a ground command system with extreme low cost and infinite endurance. The overall arrangement of the aircraft utilizes the good stabilization principle of single-side diabolo; coaxial reversal fans are arranged in the center of an unroofed frisbee-shaped aircraft protection cover; a motor with the highest weight is arranged below the center of the protection cover; a horizontal large hollow omnidirectional traction axle is arranged above the center of the aircraft; a omnidirectional traction rack is axially connected to the omnidirectional traction axle so that no unbalance can be caused by traction lines in any direction; in addition, the aircraft is continuously powered by a ground power so that the purpose of executing tasks in the air for a long time can be achieved.
Description
Affiliated technical field
The present invention relates to a kind of military, alert usefulness, civilian rotor scout and system thereof, with extremely low system cost, arrive mission area fast, target is carried out carried out tasks such as long air observation, tracking, for ground command system provides lasting real-time condition.
Background technology
In the present reconnaissance flight equipment, Air Surveillance Platform is subjected to airborne period to limit generally tracking target for a long time, the dirigibles that can leave a blank for a long time etc. are scouted equipment, again can not quick travel, and own volume is big, can not hiddenly scout, be subjected to weather effect big, the fast speed that is not suitable for little target reconnaissance in the city is disposed, and simultaneously owing to reconnaissance flight equipment technology complexity, costing an arm and a leg causes the large tracts of land equipment restricted.
Summary of the invention
At the Air Surveillance Platform that does not have suitable a large amount of equipments now, the invention provides the towed rotor scout of omnidirectional under a kind of suitable multiple-task situation, actv. solves the long-time low-to-medium altitude observation problem of mission area, and convenient moving, with low cost, simple structure, widely applicable.
The technical solution adopted for the present invention to solve the technical problems is: the monolateral diabolo good stable of playing when utilizing people to take exercise; the aircraft integral layout is also taked similar principles; center dress contrarotation fan in the flying disc shape aircraft protecting sheathing of no top; the motor mounting of weight maximum is in the central lower of protecting sheathing; and be connected with the contrarotation fan shaft; electrical motor below dress task is scouted the storehouse; most weight all is positioned at provides the contrarotation of lift fan below; guarantee flight stability, adorn the ducted fan that is used for parallel motion and direction control on flying disc shape aircraft protecting sheathing both sides, no top respectively.For stable flying platform provides suitable parallel motion ability, make scout can be in draught line oblique angle length range horizontal maneuver.For guaranteeing lack of equilibrium not under the situation of traction, above the center of gravity of airplane, establish level, the universal axis of traction of imperial palace sky, square drawbar frame axle is connected on the universal axis of traction, make draught line which direction can not cause lack of equilibrium in, draught line also is a power lead, data line, the lower end by the ground capstan winch respectively with power supply, control convenience links to each other, when providing power supply, ground-surface control signal is passed to scout for scout, the ground capstan winch is positioned at matrix and reclaims the air cushion center, by capstan winch scout is retracted during recovery, matrix reclaims air cushion and guarantees the motor that scout protrudes and hang the storehouse not to be damaged, power supply is positioned at matrix and reclaims the air cushion below, and entirely plane system is vehicle-mounted, utilizes moving of vehicle, in conjunction with ducted fan, the traction scout is done at mission area and is continued the air mobile investigation.
The invention has the beneficial effects as follows:
Simple structure: this aircraft is with draught line control flight, and ground power supply provides continuous driving force, and integral structure is simple, does not also worry electro countermeasure.
Cheap: because big heavy equipment need not too much be considered flying weight on ground, simple structure, average price are very cheap, do not worry the war loss, are fit to a large amount of equipments.
Convenient moving: total system all is stated from the Mobility Enhancement Vehicle, also can be used as strategic point monitoring fixed part and is deployed on ground or other carriers, as naval vessels.
Widely applicable: this system can not only penetrate with supervision, military scouting, school as alert, also can be used for vast fields such as strategic point monitoring, communication relaying, forest fire protection.
Dispose fast: this equipment can vertical fast at any time lift-off, and can be aloft by the land vehicle quick traction to the task zone, it is motor-driven among a small circle to the mission area also can be drawn oneself up by ducted fan on the machine.
Task is flexible: this this aircraft can monitor for a long time in fixed area that also can move all the time threatens at troop's Force Reconnaissance Company in patrol mission.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Among the figure 1, shell 2, horizontal ducted fan 3, contrarotation fan 4, universal axis of traction 5, square drawbar frame 6, electrical motor 7, task hang storehouse 8, data, power supply, traction one line 9, matrix and reclaim air cushion 10, towing capstan 11, ground power supply 12, control storehouse 13, carrier.
Fig. 1 is towed rotor scout of this omnidirectional and system side surface construction figure thereof.
Fig. 2 is this omnidirectional towed rotor scout forward sight constructional drawing.
Fig. 3 is that the towed rotor scout of this omnidirectional is overlooked constructional drawing.
Fig. 4 is towed rotor scout of this omnidirectional and system recoveries trailing flank constructional drawing thereof.
The specific embodiment
In the embodiment shown in fig. 1,
Ground power supply (11) is given electrical motor (6) power supply by towing capstan (10), data power supply traction one line (8), drive contrarotation fan (3) rotation, task is hung storehouse (7) rises in the air, and by horizontal ducted fan (2) controlled motion to appropriate area execution monitoring task.
In embodiment illustrated in fig. 2
For guaranteeing lack of equilibrium not under the situation of traction, above the center of gravity of airplane, establish the universal axis of traction (4) of level, imperial palace sky, square drawbar frame (5) axle is connected on the universal axis of traction (4), makes data power supply traction one line (8) which direction can not cause the center of gravity unstability in.
In the embodiment shown in fig. 3
Adorn the horizontal ducted fan (2) that is used for parallel motion and direction control respectively on no top flying disc shape aircraft protecting sheathing (1) both sides, for stable flying platform provides suitable parallel motion ability.
In the embodiment shown in fig. 4
Ground capstan winch (10) is positioned at matrix and reclaims air cushion (9) center, by towing capstan (10) scout is retracted during recovery, and electrical motor (6) that matrix recovery air cushion (9) assurance scout protrudes and task are hung storehouse (7) and be not damaged.
Claims (8)
1. towed rotor scout of omnidirectional and system thereof; hanging storehouse, data, power supply, traction one line, matrix by shell, horizontal ducted fan, contrarotation fan, universal axis of traction, square drawbar frame, electrical motor, task reclaims air cushion, towing capstan, ground power supply, control storehouse, carrier and constitutes; it is characterized in that: the similar monolateral diabolo of aircraft integral layout, center dress contrarotation fan in the flying disc shape aircraft protecting sheathing of no top.
2. towed rotor scout of omnidirectional according to claim 1 and system thereof is characterized in that: motor mounting is in the central lower of protecting sheathing, and is connected with the contrarotation fan shaft.
3. towed rotor scout of omnidirectional according to claim 1 and system thereof is characterized in that: electrical motor below dress task is scouted the storehouse.
4. towed rotor scout of omnidirectional according to claim 1 and system thereof is characterized in that: adorn the ducted fan that is used for parallel motion and direction control respectively on flying disc shape aircraft protecting sheathing both sides, no top.
5. towed rotor scout of omnidirectional according to claim 1 and system thereof is characterized in that: establish the universal axis of traction of level, imperial palace sky above the center of gravity of airplane, square drawbar frame axle is connected on the universal axis of traction.
6. towed rotor scout of omnidirectional according to claim 1 and system thereof is characterized in that: draught line is the line of power lead, data line unification.
7. towed rotor scout of omnidirectional according to claim 1 and system thereof is characterized in that: the ground capstan winch is positioned at matrix and reclaims the air cushion center, and power supply is positioned at matrix and reclaims the air cushion below.
8. towed rotor scout of omnidirectional according to claim 1 and system thereof, it is characterized in that: total system is stated from the Mobility Enhancement Vehicle of ground.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105654761A CN102030106A (en) | 2010-11-30 | 2010-11-30 | Omnidirectional traction type rotor reconnaissance aircraft and system thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105654761A CN102030106A (en) | 2010-11-30 | 2010-11-30 | Omnidirectional traction type rotor reconnaissance aircraft and system thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102030106A true CN102030106A (en) | 2011-04-27 |
Family
ID=43883673
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010105654761A Pending CN102030106A (en) | 2010-11-30 | 2010-11-30 | Omnidirectional traction type rotor reconnaissance aircraft and system thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102030106A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013079034A (en) * | 2011-10-05 | 2013-05-02 | Zero:Kk | Rotorcraft for aerial photographing |
| CN105739523A (en) * | 2015-12-07 | 2016-07-06 | 北京航空航天大学 | Police vehicle-mounted unmanned aerial vehicle monitoring system and control method |
| JP2017165363A (en) * | 2016-03-18 | 2017-09-21 | 株式会社Ｉｈｉエアロスペース | Landing assist device and method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1080609A (en) * | 1992-06-29 | 1994-01-12 | 蔡渤啸 | Electric power helicopter |
| FR2793467A1 (en) * | 1999-05-12 | 2000-11-17 | Didier Costes | Ground mooring for airship comprises grapnel, fixed to adjustable cable passing through sleeve mounted on ball joint at airship front, introduced into funnel fixed to ground |
| DE10023269A1 (en) * | 2000-05-12 | 2001-11-29 | Josef Sykora | Aircraft with circular basic contour has lift component constructed as tubular tire with gondola located in middle symmetrical to tire and connected to it by retaining arms, and helicopter engine on upper side of cabin |
| CN2767323Y (en) * | 2004-12-28 | 2006-03-29 | 王忠信 | Float bowl type loop umbrella one-seater aerobat |
| CN201494622U (en) * | 2009-12-18 | 2010-06-02 | 杨礼诚 | Wired electric flying and floating aircraft |
-
2010
- 2010-11-30 CN CN2010105654761A patent/CN102030106A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1080609A (en) * | 1992-06-29 | 1994-01-12 | 蔡渤啸 | Electric power helicopter |
| FR2793467A1 (en) * | 1999-05-12 | 2000-11-17 | Didier Costes | Ground mooring for airship comprises grapnel, fixed to adjustable cable passing through sleeve mounted on ball joint at airship front, introduced into funnel fixed to ground |
| DE10023269A1 (en) * | 2000-05-12 | 2001-11-29 | Josef Sykora | Aircraft with circular basic contour has lift component constructed as tubular tire with gondola located in middle symmetrical to tire and connected to it by retaining arms, and helicopter engine on upper side of cabin |
| CN2767323Y (en) * | 2004-12-28 | 2006-03-29 | 王忠信 | Float bowl type loop umbrella one-seater aerobat |
| CN201494622U (en) * | 2009-12-18 | 2010-06-02 | 杨礼诚 | Wired electric flying and floating aircraft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013079034A (en) * | 2011-10-05 | 2013-05-02 | Zero:Kk | Rotorcraft for aerial photographing |
| CN105739523A (en) * | 2015-12-07 | 2016-07-06 | 北京航空航天大学 | Police vehicle-mounted unmanned aerial vehicle monitoring system and control method |
| CN105739523B (en) * | 2015-12-07 | 2018-09-14 | 北京航空航天大学 | A kind of police vehicle-mounted unmanned aerial vehicle monitoring system and control method |
| JP2017165363A (en) * | 2016-03-18 | 2017-09-21 | 株式会社Ｉｈｉエアロスペース | Landing assist device and method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10384777B1 (en) | Tethering system for unmanned aerial vehicles | |
| US8167234B1 (en) | Insect-like micro air vehicle having perching, energy scavenging, crawling, and offensive payload capabilities | |
| US20150136897A1 (en) | Aircraft, preferably unmanned | |
| US20170253325A1 (en) | Unmanned aerial vehicle (uav) and a method of improving the performance thereof | |
| CN106809402B (en) | Automatic auxiliary landing system of rotor unmanned aerial vehicle and control method thereof | |
| CN107856840B (en) | Aircraft with high takeoff and landing stability | |
| CN103025609A (en) | Reconfigurable battery-operated vehicle system | |
| KR101933003B1 (en) | A Vertical Take off and Landing Quadrotor Drone having A Fixed Wing | |
| CN104843178A (en) | Flying motorcycle or automobile and flight attitude adjustment method thereof | |
| CN112357078B (en) | Method for carrying out patrol operation in abnormal seepage area of earth-rock dam by unmanned aerial vehicle | |
| KR20160116736A (en) | Convertible Wing Type Hybrid UAV | |
| CN105539037A (en) | Land-air four-rotor-wing unmanned aerial vehicle capable of rolling on ground | |
| CN103895860A (en) | Novel coaxial double-rotary double-degree-of-freedom eight-rotor-wing amphibious aircraft | |
| CN104443380A (en) | Splay-track flapping wing mechanism and miniature flapping wing air vehicle | |
| CN112902759A (en) | Anti-unmanned aerial vehicle system | |
| CN102030106A (en) | Omnidirectional traction type rotor reconnaissance aircraft and system thereof | |
| CN106005371B (en) | Difference directly drives dynamic three rudder face unmanned planes entirely | |
| CN204642151U (en) | Rotorcycle car or automobile | |
| CN213168519U (en) | Air-ground dual-purpose unmanned aerial vehicle | |
| KR101621210B1 (en) | Tilt-Cube-In-Wing Unmanned Aerial Vehicle | |
| CN206437212U (en) | Unmanned vehicle | |
| CN205554578U (en) | High time of endurance's unmanned aerial vehicle device | |
| CN204323688U (en) | A kind of Eight characters track flapping wing mechanism and micro flapping wing air vehicle | |
| CN104229130B (en) | Pneumatic structure four rotor unmanned aircraft | |
| Skitmore | Launch and Recovery System for Improved Fixed-Wing UAV Deployment in Complex Environments |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20110427 |