CN101830281A - Unmanned helicopter for project - Google Patents
Unmanned helicopter for project Download PDFInfo
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- CN101830281A CN101830281A CN201010178342A CN201010178342A CN101830281A CN 101830281 A CN101830281 A CN 101830281A CN 201010178342 A CN201010178342 A CN 201010178342A CN 201010178342 A CN201010178342 A CN 201010178342A CN 101830281 A CN101830281 A CN 101830281A
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- unmanned helicopter
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Abstract
The invention discloses an unmanned helicopter for a project, which comprises an undercarriage, a helicopter frame which is fixed on the undercarriage, main rotor wings and a tail wing which are arranged at the top end of the unmanned helicopter, and a power device which is arranged at the front end of the helicopter frame. The power device comprises an engine and a central controller, wherein an exhaust device is arranged at the front end of the engine; the power device drives the main rotor wings and the tail wing at the top end of the unmanned helicopter to rotate; and the central controller controls the power device. Exhaust pipes and other electrical equipment of the engine of the unmanned helicopter are arranged at the front end of the helicopter so that the weight of the helicopter is transferred to the front part and the weight of the front and rear parts of the main rotor wings is balanced. In a flying process, the front and rear parts of the helicopter are balanced without depending on any load. The helicopter made by taking advantage of the characteristic plays a role in changing the load at any time during transportation, engineering or detection.
Description
Technical field
The present invention 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, invents the needs that a kind of new unmanned helicopter airframe structure becomes present unmanned plane development.
Summary of the invention
For solving the problems referred to above that prior art exists, the invention provides the unmanned helicopter that a kind of suitable engineering is used, 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 present invention can be solved by the following technical programs:
A kind of unmanned helicopter of the present invention, 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 of the present invention is two platy structures that a spaced and parallel vertically is provided with.
Unmanned helicopter waste pipe of the present invention and other electric equipmenies are installed in the aircraft front end.
Alighting gear of the present invention 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 that the U type pipe fitting other end is a straight tube.
Unmanned plane empennage of the present invention 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 invention 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 invention
Fig. 2 is a unmanned helicopter front elevation of the present invention
Fig. 3 is the concrete structure figure of pilotless helicopter frame of the present invention 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 present invention:
A kind of unmanned helicopter of the present invention 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 comprising 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 that the U type pipe fitting 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 invention 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 invention 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, and described sled formula base one end is that the U type pipe fitting 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 |
|---|---|---|---|
| CN201010178342A CN101830281A (en) | 2010-05-18 | 2010-05-18 | Unmanned helicopter for project |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010178342A CN101830281A (en) | 2010-05-18 | 2010-05-18 | Unmanned helicopter for project |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101830281A true CN101830281A (en) | 2010-09-15 |
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ID=42714534
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201010178342A Pending CN101830281A (en) | 2010-05-18 | 2010-05-18 | Unmanned helicopter for project |
Country Status (1)
| Country | Link |
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| CN (1) | CN101830281A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101973393A (en) * | 2010-09-30 | 2011-02-16 | 清华大学 | High-strength cage-type undercarriage of unmanned helicopter |
| CN102806989A (en) * | 2011-06-02 | 2012-12-05 | 贝尔直升机德事隆公司 | Integrally stiffened panel |
| CN103818551A (en) * | 2014-01-24 | 2014-05-28 | 兰州神龙航空科技有限公司 | Vertical take-off and landing rotary wing type unmanned aerial vehicle |
| CN103921936A (en) * | 2014-02-12 | 2014-07-16 | 无锡汉和航空技术有限公司 | Oil and power mixed small unmanned helicopter and its power principle |
| CN104002961A (en) * | 2014-06-13 | 2014-08-27 | 韩世宇 | Miniature helicopter undercarriage |
| CN108945486A (en) * | 2018-08-04 | 2018-12-07 | 江苏东翼通用航空科技有限公司 | A kind of unmanned helicopter and its working method |
| WO2019006697A1 (en) * | 2017-07-05 | 2019-01-10 | SZ DJI Technology Co., Ltd. | Portable integrated uav |
| CN112607006A (en) * | 2020-12-30 | 2021-04-06 | 中国人民解放军总参谋部第六十研究所 | Touchdown feedback type undercarriage system of unmanned helicopter |
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| CN2392582Y (en) * | 1999-11-05 | 2000-08-23 | 罗军 | Sport-composition type 3D space freedom model helicopter |
| CN1556007A (en) * | 2003-12-30 | 2004-12-22 | 何主能 | Coaxial unmanned crane vertical lifting machine |
| CN1631733A (en) * | 2003-12-22 | 2005-06-29 | 上海雏鹰科技有限公司 | Beyond visual range autonomously flying unmanned helicopter system |
| CN101238033A (en) * | 2005-08-04 | 2008-08-06 | 雅马哈发动机株式会社 | Unmanned helicopter |
| CN201240500Y (en) * | 2008-07-25 | 2009-05-20 | 朱家乐 | Small-sized unmanned helicopter body structure system |
| CN201364497Y (en) * | 2009-01-12 | 2009-12-16 | 甘灿新 | Remote-control far-distance monitoring and loading unmanned helicopter system |
| CN101604830A (en) * | 2009-07-14 | 2009-12-16 | 山东电力研究院 | Patrolling trolly wire route and shaft tower unmanned helicopter system and method thereof |
| CN201678040U (en) * | 2010-05-18 | 2010-12-22 | 无锡汉和航空技术有限公司 | Unmanned helicopter applicable to engineering |
-
2010
- 2010-05-18 CN CN201010178342A patent/CN101830281A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2392582Y (en) * | 1999-11-05 | 2000-08-23 | 罗军 | Sport-composition type 3D space freedom model helicopter |
| CN1631733A (en) * | 2003-12-22 | 2005-06-29 | 上海雏鹰科技有限公司 | Beyond visual range autonomously flying unmanned helicopter system |
| CN1556007A (en) * | 2003-12-30 | 2004-12-22 | 何主能 | Coaxial unmanned crane vertical lifting machine |
| CN101238033A (en) * | 2005-08-04 | 2008-08-06 | 雅马哈发动机株式会社 | Unmanned helicopter |
| CN201240500Y (en) * | 2008-07-25 | 2009-05-20 | 朱家乐 | Small-sized unmanned helicopter body structure system |
| CN201364497Y (en) * | 2009-01-12 | 2009-12-16 | 甘灿新 | Remote-control far-distance monitoring and loading unmanned helicopter system |
| CN101604830A (en) * | 2009-07-14 | 2009-12-16 | 山东电力研究院 | Patrolling trolly wire route and shaft tower unmanned helicopter system and method thereof |
| CN201678040U (en) * | 2010-05-18 | 2010-12-22 | 无锡汉和航空技术有限公司 | Unmanned helicopter applicable to engineering |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101973393A (en) * | 2010-09-30 | 2011-02-16 | 清华大学 | High-strength cage-type undercarriage of unmanned helicopter |
| CN102806989A (en) * | 2011-06-02 | 2012-12-05 | 贝尔直升机德事隆公司 | Integrally stiffened panel |
| CN102806989B (en) * | 2011-06-02 | 2015-04-01 | 贝尔直升机德事隆公司 | Integrally stiffened panel |
| CN103818551A (en) * | 2014-01-24 | 2014-05-28 | 兰州神龙航空科技有限公司 | Vertical take-off and landing rotary wing type unmanned aerial vehicle |
| CN103818551B (en) * | 2014-01-24 | 2016-04-13 | 兰州神龙航空科技有限公司 | Vertical takeoff and landing rotary wind type unmanned vehicle |
| CN103921936A (en) * | 2014-02-12 | 2014-07-16 | 无锡汉和航空技术有限公司 | Oil and power mixed small unmanned helicopter and its power principle |
| CN104002961A (en) * | 2014-06-13 | 2014-08-27 | 韩世宇 | Miniature helicopter undercarriage |
| WO2019006697A1 (en) * | 2017-07-05 | 2019-01-10 | SZ DJI Technology Co., Ltd. | Portable integrated uav |
| CN110770123A (en) * | 2017-07-05 | 2020-02-07 | 深圳市大疆创新科技有限公司 | Portable integrated UAV |
| CN108945486A (en) * | 2018-08-04 | 2018-12-07 | 江苏东翼通用航空科技有限公司 | A kind of unmanned helicopter and its working method |
| CN112607006A (en) * | 2020-12-30 | 2021-04-06 | 中国人民解放军总参谋部第六十研究所 | Touchdown feedback type undercarriage system of unmanned helicopter |
| CN112607006B (en) * | 2020-12-30 | 2022-04-08 | 中国人民解放军总参谋部第六十研究所 | Touchdown feedback type undercarriage system of unmanned helicopter |
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Application publication date: 20100915 |