CN203428026U - Small duct-type aircraft - Google Patents

Small duct-type aircraft Download PDF

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Publication number
CN203428026U
CN203428026U CN201320351056.2U CN201320351056U CN203428026U CN 203428026 U CN203428026 U CN 203428026U CN 201320351056 U CN201320351056 U CN 201320351056U CN 203428026 U CN203428026 U CN 203428026U
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CN
China
Prior art keywords
duct
fuselage
fixedly connected
type aircraft
small
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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.)
Active
Application number
CN201320351056.2U
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Chinese (zh)
Inventor
庞振岳
王鹤
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shenyang Aircraft Design Institute Yangzhou Collaborative Innovation Research Institute Co., Ltd
Original Assignee
Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority date (The priority date 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 date listed.)
Filing date
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Application filed by Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC filed Critical Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority to CN201320351056.2U priority Critical patent/CN203428026U/en
Application granted granted Critical
Publication of CN203428026U publication Critical patent/CN203428026U/en
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Abstract

The utility model discloses a small duct-type aircraft. The small duct-type aircraft comprises a duct fuselage (1), a landing frame (2), flight control cabinets (3), a task device cabinet (4), an engine (5), a propeller system (6), an oil tank (7) and control planes (8); the flight control cabinets (3) are fixedly connected to one side of the engine (5); the task device cabinet (4) is fixedly connectd to the other side of the engine (5); the lower part of the engine (5) is fixedly connected with the upper part of the duct fuselage (1); the lower part of the duct fuselage (1) is fixedly connected with the upper part of the duct fuselage (1); the lower part of the duct fuselage (1) is fixedly connected with the landing frame (2); the propeller system (6), the oil tank (7) and the control planes (8) are positioned in the duct fuselage (1). The duct fuselage is utilized for wrapping propellers inside so as to improve the pneumatic efficiency of the aircraft, so that the lifting power is increased; the small duct-type aircraft can effectively reduce noise generated by propeller tips, and has greater economical value and social value.

Description

A kind of small-sized culvert type aircraft
Technical field
The utility model relates to Aircraft structural design and applied technical field, and a kind of small-sized culvert type aircraft is provided especially.
Background technology
At present, Fixed Wing AirVehicle needs runway to carry out landing, can not be parked in and stare region of war environment in the air when battlefield surveillance.Relatively and Fixed Wing AirVehicle, the advantage that helicopter has vertical takeoff and landing and can hover, but helicopter pneumatic efficiency is low, during flight, noise is very large, when battlefield surveillance, be easy to be found by enemy, and in forest is searched, wing tip easily knocks branch and causes body damage, and the screw propeller of High Rotation Speed can damage to personnel simultaneously.Along with aircraft is in security, the disaster relief and the effect of anti-terrorism aspect are increasing, and traditional Fixed Wing AirVehicle and helicopter cannot meet the demands.
People urgently wish to obtain the good small-sized culvert type aircraft of a kind of technique effect.
Utility model content
The purpose of this utility model is to provide a kind of small-sized culvert type aircraft.
Small-sized culvert type aircraft described in the utility model, is constructed as follows: duct fuselage 1, alighting gear 2, flight control cabinet 3, task device cabin 4, driving engine 5, propeller system 6, fuel tank 7, rudder face 8; Described flight control cabinet 3 is fixedly connected on driving engine 5 one sides, and task device cabin 4 is fixedly connected on driving engine 5 opposite sides; The bottom of driving engine 5 is fixedly connected with duct fuselage 1 top, and the bottom of duct fuselage 1 and alighting gear 2 are fixedly linked; Described propeller system 6, fuel tank 7 and rudder face are positioned at the inside of duct fuselage 1, and described propeller system 6 is positioned at the upside of duct fuselage 1 inside, and rudder face 8 is positioned at propeller system 6 downsides, and fuel tank 7 is arranged on duct fuselage 1 inwall place.
The interior installation autopilot of described flight control cabinet 3, control cabinet flies by controlling rudder face automatic vehicle, and the interior installation picture pick-up device in task device cabin 4, can aloft monitor ground; Task device cabin 4 does not need to be used in conjunction with other parts.
The groundwork of described small-sized culvert type aircraft flight is by the work of driving engine 5, to drive the rotation of duct internal propeller system 6, give by downward power of air of duct body, produced induction velocity, the propulsive force while flying before lift when its antagonistic force just becomes vehicle rudder 8 vertical takeoff and landing and level.
The feature that small-sized culvert type aircraft described in the utility model has vertical takeoff and landing and can hover, utilize culvert type fuselage that screw propeller is wrapped in to the interior pneumatic efficiency that can improve aircraft, lift is increased, and can effectively reduce the flight noise that screw propeller blade tip produces, can avoid screw propeller collision branch to cause damaging simultaneously, strengthen aircraft and passed through the ability that forest is searched target, last operation personnel can directly not face the screw propeller of High Rotation Speed in use, the safety in utilization of aircraft is also significantly improved, there is comparatively huge economic value and social value.
Accompanying drawing explanation
Fig. 1 is small-sized culvert type aircraft front elevation;
Fig. 2 is small-sized culvert type aircraft upward view;
Fig. 3 is small-sized culvert type aircraft lateral plan;
The specific embodiment
Embodiment 1
Small-sized culvert type aircraft described in the present embodiment, is constructed as follows: duct fuselage 1, alighting gear 2, flight control cabinet 3, task device cabin 4, driving engine 5, propeller system 6, fuel tank 7, rudder face 8; Described flight control cabinet 3 is fixedly connected on driving engine 5 one sides, and task device cabin 4 is fixedly connected on driving engine 5 opposite sides; The bottom of driving engine 5 is fixedly connected with duct fuselage 1 top, and the bottom of duct fuselage 1 and alighting gear 2 are fixedly linked; Described propeller system 6, fuel tank 7 and rudder face are positioned at the inside of duct fuselage 1, and described propeller system 6 is positioned at the upside of duct fuselage 1 inside, and rudder face 8 is positioned at propeller system 6 downsides, and fuel tank 7 is arranged on duct fuselage 1 inwall place.
The interior installation autopilot of described flight control cabinet 3, control cabinet flies by controlling rudder face automatic vehicle, and the interior installation picture pick-up device in task device cabin 4, can aloft monitor ground; Task device cabin 4 does not need to be used in conjunction with other parts.
The groundwork of described small-sized culvert type aircraft flight is by the work of driving engine 5, to drive the rotation of duct internal propeller system 6, give by downward power of air of duct body, produced induction velocity, the propulsive force while flying before lift when its antagonistic force just becomes vehicle rudder 8 vertical takeoff and landing and level.
The feature that described in the present embodiment, small-sized culvert type aircraft has vertical takeoff and landing and can hover, utilize culvert type fuselage that screw propeller is wrapped in to the interior pneumatic efficiency that can improve aircraft, lift is increased, and can effectively reduce the flight noise that screw propeller blade tip produces, can avoid screw propeller collision branch to cause damaging simultaneously, strengthen aircraft and passed through the ability that forest is searched target, last operation personnel can directly not face the screw propeller of High Rotation Speed in use, the safety in utilization of aircraft is also significantly improved, there is comparatively huge economic value and social value.

Claims (1)

1. a small-sized culvert type aircraft, is characterized in that: it is constructed as follows: duct fuselage (1), alighting gear (2), flight control cabinet (3), task device cabin (4), driving engine (5), propeller system (6), fuel tank (7), rudder face (8); Described flight control cabinet (3) is fixedly connected on driving engine (5) one sides, and task device cabin (4) are fixedly connected on driving engine (5) opposite side; The bottom of driving engine (5) is fixedly connected with duct fuselage (1) top, and the bottom of duct fuselage (1) and alighting gear (2) are fixedly linked; Described propeller system (6), fuel tank (7) and rudder face are positioned at the inside of duct fuselage (1), described propeller system (6) is positioned at the inner upside of duct fuselage (1), rudder face (8) is positioned at propeller system (6) downside, and fuel tank (7) is arranged on duct fuselage (1) inwall place.
CN201320351056.2U 2013-06-18 2013-06-18 Small duct-type aircraft Active CN203428026U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201320351056.2U CN203428026U (en) 2013-06-18 2013-06-18 Small duct-type aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201320351056.2U CN203428026U (en) 2013-06-18 2013-06-18 Small duct-type aircraft

Publications (1)

Publication Number Publication Date
CN203428026U true CN203428026U (en) 2014-02-12

Family

ID=50057081

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201320351056.2U Active CN203428026U (en) 2013-06-18 2013-06-18 Small duct-type aircraft

Country Status (1)

Country Link
CN (1) CN203428026U (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106927023A (en) * 2017-03-27 2017-07-07 上海珞鹏航空科技有限公司成都研发分公司 A kind of agricultural plant protection controls culvert type unmanned plane with rudder face
CN108945483A (en) * 2017-05-19 2018-12-07 林瑤章 propulsion device
CN112706932A (en) * 2021-01-12 2021-04-27 涵涡智航科技(玉溪)有限公司 Fuel storage device of oil-driven ducted aircraft and control method

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106927023A (en) * 2017-03-27 2017-07-07 上海珞鹏航空科技有限公司成都研发分公司 A kind of agricultural plant protection controls culvert type unmanned plane with rudder face
CN108945483A (en) * 2017-05-19 2018-12-07 林瑤章 propulsion device
CN112706932A (en) * 2021-01-12 2021-04-27 涵涡智航科技(玉溪)有限公司 Fuel storage device of oil-driven ducted aircraft and control method

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Legal Events

Date Code Title Description
C14 Grant of patent or utility model
GR01 Patent grant
TR01 Transfer of patent right
TR01 Transfer of patent right

Effective date of registration: 20201021

Address after: Building B, building 28, Jiangsu information service industry base, Guangling New Town, Yangzhou City, Jiangsu Province, 225002

Patentee after: Shenyang Aircraft Design Institute Yangzhou Collaborative Innovation Research Institute Co., Ltd

Address before: Thavorn street in Huanggu District of Shenyang city of Liaoning Province, No. 40 110000

Patentee before: SHENYANG AIRCRAFT DESIGN INSTITUTE, AVIATION INDUSTRY CORPORATION OF CHINA