CN201678040U - Unmanned helicopter applicable to engineering - Google Patents
Unmanned helicopter applicable to engineering Download PDFInfo
- Publication number
- CN201678040U CN201678040U CN2010201982796U CN201020198279U CN201678040U CN 201678040 U CN201678040 U CN 201678040U CN 2010201982796 U CN2010201982796 U CN 2010201982796U CN 201020198279 U CN201020198279 U CN 201020198279U CN 201678040 U CN201678040 U CN 201678040U
- Authority
- CN
- China
- Prior art keywords
- helicopter
- unmanned helicopter
- unmanned
- engine
- frame
- 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
Images
Landscapes
- Toys (AREA)
Abstract
The utility model discloses an unmanned helicopter applicable to engineering. The unmanned helicopter comprises a landing gear, a helicopter frame fixed on the landing gear, a main rotor wing and a tail wing at the top end of the manless helicopter, and a power device fixed at the front end of the helicopter frame; the power device comprises an engine; an exhaust device on the engine is placed at the front end of the engine; the power device drives the main rotor wing and the tail wing at the top end of the manless helicopter to rotate; and the unmanned helicopter further comprises a central controller capable of controlling the power device. An exhaust pipe and other electric appliances of the engine of the unmanned driving helicopter are mounted at the front end of the helicopter, so that the weight of the helicopter body shifts forwards to achieve the forward and backward weight balance of a main rotor wing shaft. Therefore, the forward and backward balance of the helicopter is achieved without depending on any task load; and the airplane made by utilizing the characteristic can achieve the purpose of changing the task load at any moment during the transportation, engineering or detection.
Description
Technical field
The utility model relates to a kind of unmanned helicopter, the unmanned helicopter of self main rotor shaft anterior-posterior balance that particularly a kind of suitable engineering is used.
Background technology
At present, self balance that can arbitrarily change mission payload and not destroy its unmanned helicopter becomes the key property of engineering with machine, but the unmanned helicopter variation of load carrying ability awing at present can make aircraft self unbalance, can not normal flight, lack the unmanned machine self structure balance that a kind of suitable engineering is used, awing loads can change, and therefore, a kind of new unmanned helicopter airframe structure of utility model becomes the needs of present unmanned plane development.
The utility model content
For solving the problems referred to above that prior art exists, the unmanned helicopter that the utility model provides a kind of suitable engineering to use, also improved fuselage intensity and reliability, this aircraft is played a role in the engineering use of needs change load by making the exhaust pipe of engine make aircraft self obtain balance with the technology such as electrical equipment upset installation and fuselage narrow down of flying.
The utility model can be solved by the following technical programs:
A kind of unmanned helicopter of the utility model, it comprises alighting gear, and be fixed on frame on the alighting gear, and the main rotor on unmanned plane empennage and top, also comprise the engine installation that is fixed on front end on the frame, this engine installation comprises a driving engine, and the exhaust gear on the described driving engine places the front end of driving engine, the freeing pipe of described exhaust gear places this exhaust gear front end, and described engine installation drives the main rotor and the empennage rotation on unmanned plane top; Also comprise a central controller, it controls described engine installation.
Frame described in the utility model is two platy structures that a spaced and parallel vertically is provided with.
Unmanned helicopter waste pipe described in the utility model and other electric equipmenies are installed in the aircraft front end.
Alighting gear described in the utility model comprises an arch pipe support, a sled formula base, and described frame is fixed on the arch pipe support by positioning seat, and the lower end of arch pipe support connection sled formula base, and described sled formula base one end is a U type pipe fitting, and the other end is a straight tube.
Unmanned plane empennage described in the utility model comprises respectively by straight-bar and is connected blade-rotating and trammel beam on the frame, trammel beam comprises bonded assembly longitudinal rod, U type connecting rod, curved rod successively, connect longitudinal rod near on the straight-bar of described blade-rotating, connect curved rod on the straight-bar away from blade-rotating.
Owing to adopt above technical scheme, the unmanned helicopter that a kind of suitable engineering of the present utility model is used, fuselage intensity and reliability have also been improved by making technology such as the exhaust pipe of engine and the upset installation of flight electrical equipment and fuselage narrow down make aircraft self obtain balance, can change the bearing load or the oil plant that are placed near the aircraft central principal axis awing still can make aircraft keep the balance normal flight, the aircraft that utilizes this characteristic to make, can be used as transportation, engineering or investigation is main purposes.
Description of drawings
Fig. 1 is unmanned helicopter integral structure figure of the present utility model
Fig. 2 is a unmanned helicopter front elevation of the present utility model
Fig. 3 is the concrete structure figure of pilotless helicopter frame of the present utility model and engine section
Among the figure, 1, alighting gear; 2, driving engine; 3, freeing pipe; 4, frame; 5, empennage 11, positioning seat; 12, the arch pipe support; 13, sled formula base; 51, blade-rotating; 52, longitudinal rod; 53, U type connecting rod; 54, curved rod.
The specific embodiment
Below in conjunction with the specific embodiment, further set forth the utility model:
A kind of unmanned helicopter of the utility model shown in Figure 1, it comprises alighting gear 1, and be fixed on frame 4 on the alighting gear 1, and unmanned plane empennage 5, also comprise the engine installation that is fixed on front end on the frame, this engine installation comprises a driving engine 2, exhaust gear on this driving engine places the front end of driving engine, be that driving engine 2 upsets are installed, make the freeing pipe 3 of exhaust gear place this exhaust gear front end, driving engine upset back is installed and is made whole unmanned helicopter in main shaft rear and front end balance.This engine installation drives the rotation of unmanned plane empennage; Also comprise a central controller, it controls engine installation.Unmanned helicopter waste pipe and other electric equipmenies are installed in the aircraft front end, make the fuselage weight reach reach main rotor shaft front and back weight balancing, therefore need not rely on mission payload to obtain the aircraft anterior-posterior balance awing, the aircraft that utilizes this characteristic to make can play the effect that changes mission payload at any time in transportation, engineering or investigation.This alighting gear 1 comprises an arch pipe support 12, a sled formula base 13, frame 4 is fixed on the arch pipe support 12 by positioning seat 11, and the lower end of arch pipe support 12 connects sled formula base 13, sled formula base 13 1 ends are U type pipe fitting, the other end is a straight tube, for strengthening this tubing, Y shape muscle has been strengthened in inside during pipe drawing.Unmanned plane empennage 5 comprises respectively by straight-bar and is connected blade-rotating 51 and trammel beam on the frame, trammel beam comprises bonded assembly longitudinal rod 52, U type connecting rod 53, curved rod 54 successively, near connecting longitudinal rod 52 on the straight-bar of blade-rotating 51, away from connecting curved rod 54 on the straight-bar of blade-rotating 51.
A specific embodiment of the present utility model as shown in Figures 2 and 3, above-mentioned frame 4 is two and parallelly sets up and be vertically fixed on the platy structure on the alighting gear and place picking-up plate between two plates, the two parallel plates of this structure abut against the gear case both sides, therefore structural strength and the stability of can actv. having strengthened overall aircraft, and establish a zone that driving engine 2 is snapped at the plate middle section.The freeing pipe 3 of this exhaust gear places the place ahead to dwindle with regard to making the distance between frame two plates, makes the frame narrowed width.For guaranteeing the gravitational equilibrium of fuselage, other parts in that the fore-end of above-mentioned picking-up plate is installed engine installation comprise fuel tank and power supply, and driving engine 2 is fixed as one with above-mentioned exhaust gear.
Because unmanned helicopter waste pipe of the present utility model and other electric equipmenies are installed in the aircraft front end, make the fuselage weight reach reach main shaft front and back weight balancing, therefore need not rely on mission payload to obtain the aircraft anterior-posterior balance awing.Because this characteristic, can change the bearing load or the oil plant that are placed near the aircraft central principal axis awing and still can make aircraft keep the balance normal flight, the aircraft that utilizes this characteristic to make, can be used as transportation, engineering or investigation is main purposes.As: transmit fortune in clearance line, the rescue in the air in power industry and pass the scoutplane (is basic load with the power oil plant that is changing) of medicine and rope, overlength airborne period, pesticide spraying aircraft etc.
But the above-mentioned specific embodiment is exemplary, is to be the restriction that this patent is comprised scope in order better to make those skilled in the art can understand this patent, can not to be interpreted as; So long as according to spirit that this patent discloses done anyly be equal to change or modify, all fall into the scope that this patent comprises.
Claims (5)
1. unmanned helicopter that suitable engineering is used, it comprises alighting gear, and be fixed on frame on the alighting gear, and the main rotor on unmanned plane top and empennage, it is characterized in that: also comprise the engine installation that is fixed on the frame front end, this engine installation comprises a driving engine, and the exhaust gear on the described driving engine places the front end of driving engine, the freeing pipe of described exhaust gear places this exhaust gear front end, and described engine installation drives the main rotor and the empennage rotation on unmanned plane top; Also comprise a central controller, it controls described engine installation.
2. unmanned helicopter according to claim 1 is characterized in that: described frame is two platy structures that a spaced and parallel is provided with.
3. unmanned helicopter according to claim 2 is characterized in that: described unmanned helicopter waste pipe and other electric equipmenies are installed in the aircraft front end.
4. unmanned helicopter according to claim 3, it is characterized in that: described alighting gear comprises an arch pipe support, a sled formula base, described frame is fixed on the arch pipe support by positioning seat, and the lower end of arch pipe support connects sled formula base, described sled formula base one end is a U type pipe fitting, and the other end is a straight tube.
5. unmanned helicopter according to claim 4, it is characterized in that, described unmanned plane empennage comprises respectively by straight-bar and is connected blade-rotating and trammel beam on the frame, trammel beam comprises bonded assembly longitudinal rod, U type connecting rod, curved rod successively, connect longitudinal rod near on the straight-bar of described blade-rotating, connect curved rod on the straight-bar away from blade-rotating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201982796U CN201678040U (en) | 2010-05-18 | 2010-05-18 | Unmanned helicopter applicable to engineering |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201982796U CN201678040U (en) | 2010-05-18 | 2010-05-18 | Unmanned helicopter applicable to engineering |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201678040U true CN201678040U (en) | 2010-12-22 |
Family
ID=43343095
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201982796U Expired - Lifetime CN201678040U (en) | 2010-05-18 | 2010-05-18 | Unmanned helicopter applicable to engineering |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201678040U (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101830281A (en) * | 2010-05-18 | 2010-09-15 | 无锡汉和航空技术有限公司 | Unmanned helicopter for project |
| GB2483881A (en) * | 2010-09-22 | 2012-03-28 | Thomas Irps | A dual-function landing gear and rotor protector for a UAV |
| CN102774492A (en) * | 2012-06-08 | 2012-11-14 | 无锡汉和航空技术有限公司 | Small unmanned helicopter fuselage |
| CN103029834A (en) * | 2012-11-26 | 2013-04-10 | 北京兰亭华谊文化传媒有限责任公司 | Small electric unmanned helicopter aerial photography system based on front-end triaxial-type pan-tilt |
| CN103523199A (en) * | 2013-09-29 | 2014-01-22 | 郭献民 | Novel tubular-structure electric unmanned helicopter |
| CN103803071A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN103803081A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Vertical take-off and landing rotary wing type unmanned aerial vehicle |
| CN103803070A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN103803072A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN104743103A (en) * | 2015-03-31 | 2015-07-01 | 东莞市汇天玩具模型有限公司 | Super-miniature fuel oil unmanned helicopter |
-
2010
- 2010-05-18 CN CN2010201982796U patent/CN201678040U/en not_active Expired - Lifetime
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101830281A (en) * | 2010-05-18 | 2010-09-15 | 无锡汉和航空技术有限公司 | Unmanned helicopter for project |
| GB2483881A (en) * | 2010-09-22 | 2012-03-28 | Thomas Irps | A dual-function landing gear and rotor protector for a UAV |
| GB2483881B (en) * | 2010-09-22 | 2017-04-26 | Irps Thomas | A dual-function landing gear and rotor protector for a UAV |
| CN102774492A (en) * | 2012-06-08 | 2012-11-14 | 无锡汉和航空技术有限公司 | Small unmanned helicopter fuselage |
| CN102774492B (en) * | 2012-06-08 | 2016-03-30 | 无锡汉和航空技术有限公司 | A kind of small-sized depopulated helicopter fuselage |
| CN103029834A (en) * | 2012-11-26 | 2013-04-10 | 北京兰亭华谊文化传媒有限责任公司 | Small electric unmanned helicopter aerial photography system based on front-end triaxial-type pan-tilt |
| CN103029834B (en) * | 2012-11-26 | 2015-07-01 | 天峋创新（北京）科技有限公司 | Small electric unmanned helicopter aerial photography system based on front-end triaxial-type pan-tilt |
| CN103523199A (en) * | 2013-09-29 | 2014-01-22 | 郭献民 | Novel tubular-structure electric unmanned helicopter |
| CN103803072A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN103803070A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN103803081A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Vertical take-off and landing rotary wing type unmanned aerial vehicle |
| CN103803081B (en) * | 2014-01-24 | 2016-03-30 | 兰州神龙航空科技有限公司 | Vertical takeoff and landing rotary wind type unmanned vehicle |
| CN103803072B (en) * | 2014-01-24 | 2016-04-06 | 兰州神龙航空科技有限公司 | Engineering-type rotary wind type unmanned vehicle |
| CN103803070B (en) * | 2014-01-24 | 2016-04-06 | 兰州神龙航空科技有限公司 | Engineering-type rotary wind type unmanned vehicle |
| CN103803071B (en) * | 2014-01-24 | 2016-08-17 | 兰州神龙航空科技有限公司 | Engineering-type rotary wind type unmanned vehicle |
| CN103803071A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN104743103A (en) * | 2015-03-31 | 2015-07-01 | 东莞市汇天玩具模型有限公司 | Super-miniature fuel oil unmanned helicopter |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201678040U (en) | Unmanned helicopter applicable to engineering | |
| CN101830281A (en) | Unmanned helicopter for project | |
| CN104176248B (en) | Twin-engined four axle four rotor wing unmanned aerial vehicles | |
| WO2020259570A1 (en) | Modular intermeshing and tandem unmanned helicopter and working method thereof | |
| US9399982B2 (en) | Auto-gyro rotor flying electric generator (FEG) with wing lift augmentation | |
| CN101314409B (en) | Swallow type inclined rotation rotorcraft | |
| CN101384481A (en) | Modular articulated-wing aircraft | |
| CN108473191A (en) | Aircraft | |
| CN101758922B (en) | Retractable captive flight support for external hanging equipment | |
| CN103523199A (en) | Novel tubular-structure electric unmanned helicopter | |
| CN205971844U (en) | Fixed wing aircraft vertical take -off auxiliary system | |
| CN101602403A (en) | Vertical take-off and landing aircraft (VTOL aircraft) | |
| CN110844065A (en) | Unmanned aerial vehicle with strong loading capacity and capable of vertically taking off and landing | |
| WO2018233570A1 (en) | Gasoline-electric hybrid multiaxis rotor type unmanned aerial vehicle | |
| CN203698657U (en) | Engineering rotor unmanned aerial vehicle | |
| CN201321159Y (en) | Unmanned aircraft with vertical ducts | |
| CN102963521A (en) | Central wing of horizontal tail of civil airplane | |
| CN103803070B (en) | Engineering-type rotary wind type unmanned vehicle | |
| CN109733599A (en) | A kind of combined dual-purpose unmanned plane | |
| CN205150233U (en) | Aircraft | |
| CN206528616U (en) | A kind of lightweight low-cost unmanned target drone | |
| CN210555568U (en) | Modularized crossed type tandem unmanned helicopter | |
| CN204323683U (en) | Engineering-type rotary wind type unmanned vehicle | |
| CN114013642A (en) | Vertical take-off and landing fixed wing unmanned aerial vehicle | |
| CN203698662U (en) | Vertical take-off and landing rotary wing type unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Unmanned helicopter for project Effective date of registration: 20150601 Granted publication date: 20101222 Pledgee: Wuxi New District Chuang friends financing Company limited by guarantee Pledgor: Wuxi Hanhe Aviation Technology Co., Ltd. Registration number: 2015320000005 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20160711 Granted publication date: 20101222 Pledgee: Wuxi New District Chuang friends financing Company limited by guarantee Pledgor: Wuxi Hanhe Aviation Technology Co., Ltd. Registration number: 2015320000005 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20101222 |