CN110065639A - One kind being used for unmanned plane quick-release opposite opened power hatch cover - Google Patents
One kind being used for unmanned plane quick-release opposite opened power hatch cover Download PDFInfo
- Publication number
- CN110065639A CN110065639A CN201910385113.0A CN201910385113A CN110065639A CN 110065639 A CN110065639 A CN 110065639A CN 201910385113 A CN201910385113 A CN 201910385113A CN 110065639 A CN110065639 A CN 110065639A
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- CN
- China
- Prior art keywords
- hatch cover
- power
- quick
- power hatch
- detachable lock
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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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/06—Attaching of nacelles, fairings or cowlings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses one kind to be used for unmanned plane quick-release opposite opened power hatch cover, is made of fagging, quick-detachable lock, load frame and mooring line under power hatch cover, hatch cover.Wherein, power hatch cover is the identical component of two structures, and using whole Design of Aerodynamic Configuration, streamlined finishes up structure power hatch cover, is respectively equipped with fast plug-in card hole in power hatch cover；Reinforce side with power hatch cover and piggyback pod firewall respectively and connect in mooring line both ends；Fagging and load frame are connected under hatch cover, and fagging two sides are connect with power hatch cover by connects hinge respectively under hatch cover, and power hatch cover is connected to body and fixation by quick-detachable lock along fuselage cross-section and load frame, and two power hatch covers fasten docking and fastened by quick-detachable lock；When needing to check power chamber device and engine condition, quick-detachable lock is pressed, two split power hatch covers is separated from top and gravity fall is pulled by mooring line, maintenance test rapidly is carried out to power plant system, ensures that unmanned plane is reliably let fly away.
Description
Technical field
The present invention relates to air vehicle technique fields, specifically, being related to a kind of for unmanned plane quick-release opposite opened piggyback pod
Cover.
Background technique
Unmanned Aerial Vehicle Powerplants system is installed concentratedly mostly in its piggyback pod, and on unmanned plane power plant system ground
Face inspection is the important component of unmanned aerial vehicle engineering safeguard work, is to guarantee that engine reliable work, unmanned plane are reliable
The important means let fly away.
As the capital equipment cabin of power plant system, be disposed in piggyback pod engine and its observing and controlling, power supply, lubrication,
The correlation subsystem such as ventilating and cooling, fuel feeding.Before unmanned vehicle engine ground is driven and is let fly away, it is necessary to ensure that in power plant system
Engine and the installation of other equipment are fixed reliably, and pipeline is connected firmly, without aging crackle, working solution No leakage, pollution-free, electricity
Cable connection is effective, insulation is reliable, far from high temperature surface etc..It is general at present using by piggyback pod maintenance lid visually with tool phase
In conjunction with test mode ensure that above-mentioned state is met the requirements, engine and aircraft work safety.As unmanned plane scale is smaller or knot
Structure is limited, safeguards that lid is small or it is not in place to open up, is difficult comprehensive visual inspection of carry out system, using tool inspection and repairs more
Add difficulty, generally require directly to dismantle the fixed power hatch cover of more screws, intricate operation, amount are big, in, large-scale unmanned plane can
Can also be by ancillary equipment and specific purpose tool, engineering prepares that time-consuming, needs manpower more.
Patent of invention 201711073960.6 proposes a kind of " the modular removable formula nacelle of unmanned plane ", this is dynamic
Power nacelle only proposes modularized design to wing hanging nacelle, and mainly for the integral replacing and remodeling of dynamical system,
Structure is complicated, components are more.And inspection and dimension for the power plant system especially power plant system of fuselage installation
Shield is not directed to.
With constantly widening for unmanned plane application field, cumbersome for current Unmanned Aerial Vehicle Powerplants system ground maintenance,
Engineering the problem of time-consuming, user meet an urgent need out dynamic response to unmanned plane, and quick engineering inspection lets fly away etc. and to propose higher want
It asks, to the convenience of power plant system maintenance, more stringent requirements are proposed for the reliability that unmanned plane is let fly away.
Summary of the invention
In order to avoid the shortcomings of the prior art, overcome that Unmanned Aerial Vehicle Powerplants system ground maintenance is cumbersome, engineering consumption
The problem of duration, the present invention propose that one kind for unmanned plane quick-release opposite opened power hatch cover, by shirtsleeve operation, convenient can be beaten
Power hatch cover is started, realization quickly comprehensively checks Unmanned Aerial Vehicle Powerplants system on ground, so that it is fast to meet unmanned aerial vehicle
The demand of fast comprehensive coverage.
The technical solution adopted by the present invention to solve the technical problems is: including fagging, quick-release under power hatch cover, hatch cover
Lock, hatch cover are closed fixed quick-detachable lock, connects hinge, load frame and mooring line, it is characterised in that the power hatch cover is two knots
The identical component of structure, power hatch cover are finished up using whole Design of Aerodynamic Configuration, streamlined, opposite opened structure, are divided in power hatch cover
It She You not fast plug-in card hole；Piggyback pod firewall be equipped with reinforce side, mooring line both ends respectively with power hatch cover and piggyback pod firewall
Reinforce side connection；
Fagging and load frame are connected under hatch cover, and fagging two sides are connect with power hatch cover by connects hinge respectively under hatch cover,
Power hatch cover is connected to body and fixation by quick-detachable lock along fuselage cross-section and load frame, and two power hatch covers fasten docking and pass through
Quick-detachable lock fastening；When needing to check power chamber device and engine condition, quick-detachable lock, the fixed quick-detachable lock of hatch cover closure are pressed,
It separates two split power hatch covers from top, and gravity fall is pulled by mooring line, power hatch cover open angle is 180 °
Folding.
The mooring line is light metal material, 8 > of minimum point road clearance after mooring line length is opened by power hatch cover
150mm setting.
Beneficial effect
Proposed by the present invention a kind of for unmanned plane quick-release opposite opened power hatch cover, power hatch cover is designed for opposite opened, is beaten
Cabin intrinsic motivation, mounting rack, equipment, pipeline and cable etc. is set to cover all at one glance after opening, the use of attachment tools and detection device is empty
Between it is without any restrictions, disassembly checks quickly, efficiently solve usual unmanned plane piggyback pod maintenance lid it is narrow or open up less than
Position, the problem that the inspections such as engine and its relevant device, structure, pipeline are limited；The maintainability for improving unmanned plane, reduces
Locomotive work difficulty and intensity, improve detection efficiency.Maintenance lid that no setting is required in hatch cover, in use, only needing one directly
Hatch cover is opened, open type inspection and maintenance can be carried out to system in unmanned plane piggyback pod, ensure that unmanned plane is reliably let fly away.
The present invention is used for unmanned plane quick-release opposite opened power hatch cover, when needing to check power chamber device and engine condition
When, quick-detachable lock is pressed, separates two split power hatch covers from top, because power hatch cover lower part is fixed by rotary type hinge, is moved
Power hatch cover is not fallen out, and does not influence its folding, at this point, all devices all appear in piggyback pod.According to power below deck equipment
Profile, Z-direction height and unmanned aerial vehicle shutdown support road clearance are installed, choose appropriate hatch cover open angle, not to prevent aperture
Properly, it influences flight crew and is damaged with wiping close to aircraft or hatch cover.Fast plug-in card hole, piggyback pod are respectively kept in split power hatch cover
Cover is inserted fastly using mooring line and is fixed, and guarantees that its open angle and height meet requirement.
Detailed description of the invention
One kind of the invention is made for unmanned plane quick-release opposite opened power hatch cover into one with embodiment with reference to the accompanying drawing
Step is described in detail.
Fig. 1 is that the present invention is used for unmanned plane quick-release opposite opened power hatch cover schematic diagram.
Fig. 2 is that the present invention is used for unmanned plane quick-release opposite opened power hatch cover open position schematic diagram.
In figure:
101. 103. quick-detachable lock of fagging, 04. hatch cover is closed fixed quick-detachable lock 105. and connects under 102. hatch cover of power hatch cover
106. load frame of hinge, 201. mooring line, 202. power hatch cover firewall reinforces 203. quick-release lock position of side, 204. engine
Fast 207. power hatch cover open position of plug-in card hole, the 208. power hatch cover open angle of 205. piggyback pod firewall of profile 206.
209. the road clearance
Specific embodiment
The present embodiment is a kind of for unmanned plane quick-release opposite opened power hatch cover.
Refering to fig. 1, Fig. 2, the present embodiment is used for unmanned plane quick-release opposite opened power hatch cover, by under power hatch cover 101, hatch cover
Fagging 102, quick-detachable lock 103, hatch cover are closed fixed quick-detachable lock 104, connects hinge 105, load frame 106 and mooring line 201 and form；
Wherein, power hatch cover 101 is the identical component of two structures, and power hatch cover 101 is received using whole Design of Aerodynamic Configuration, streamlined
Tail, opposite opened structure are respectively equipped with fast plug-in card hole 206 in power hatch cover 101；Piggyback pod firewall, which is equipped with, reinforces side, mooring line
Reinforce side with power hatch cover 101 and piggyback pod firewall respectively and connect in 201 both ends.Fagging 102 and load frame 106 are solid under hatch cover
Even, 102 two sides of fagging are connect with power hatch cover by connects hinge 105 respectively under hatch cover, power hatch cover along fuselage cross-section with
Load frame is connected to body and fixation by quick-detachable lock, and two power hatch covers 101 fasten docking and fastened by quick-detachable lock；When needing to examine
When looking into power chamber device and engine condition, quick-detachable lock 103 is pressed, hatch cover is closed fixed quick-detachable lock 104, makes two split power
Hatch cover 101 is separated from top, and pulls gravity fall by mooring line 201, and power hatch cover open angle 208 is 180 ° of foldings.
In the present embodiment, mooring line 201 is light metal material, minimum point after 201 length of mooring line is opened by power hatch cover
The setting of 8 > 150mm of road clearance.
In the present embodiment, piggyback pod cover structure is fixed and link position:
It is designed in unmanned plane structure-bearing frame 106 and reinforces side, conducive to the fixation of opposite opened hatch cover 101 and the peace of quick-detachable lock 103
Dress；According to the dimension and weight of power hatch cover, 1~2 hatch cover is set on split 101 top of hatch cover and is closed fixed quick-detachable lock 104,
Lower part design strength is high, fagging 102 and is fastenedly connected with structure-bearing frame 106, split power hatch cover under on-deformable hatch cover
101 lower parts are connect with 102 two sides of fagging under hatch cover by 1~2 connects hinge 105 respectively, can 180 ° of rotating foldings.
Power hatch cover is opened and is fixed:
When needing to carry out the inspection of quick engineering, quick-detachable lock 103 is pressed, power hatch cover is separated with body, presses hatch cover
It is closed fixed quick-detachable lock 104, two split power hatch covers 101 is opened, the gold at 106 edge of structure-bearing frame is fixed on using one end
Belong to soft mooring line 201, other end buckle directly buckles into the fast plug-in card hole 206 of two power hatch covers, 101 edge.Mooring line
210 designs consider tensile strength and static conductive ability.Consideration unmanned plane lifting gear is with aircraft bracket height and dust and outside
The factors such as object pollution are tethered at minimum point road clearance > 150mm design after 201 length of line is opened by split power hatch cover 101, keep away
Exempt to scrape, trample and foreign matter abrasion or pollution hatch cover.
The unfolding mode and open angle of power hatch cover:
When needing to check power chamber device and engine condition, quick-detachable lock 103 is pressed, hatch cover is closed fixed quick-detachable lock
104, separate the split hatch cover 101 of two halves from top, and by gravity fall, because hatch cover lower part is fixed by rotary type hinge 105,
Hatch cover is not fallen out, and nor affects on its folding, and all devices all appear in piggyback pod at this time.
According to the installation profile 205 of power below deck equipment, Z-direction height and unmanned aerial vehicle shutdown support road clearance 208,
Hatch cover open angle 207 is chosen, it is improper to prevent aperture, it influences flight crew and is damaged with wiping close to aircraft or hatch cover.
Claims (2)
1. one kind is used for unmanned plane quick-release opposite opened power hatch cover, including fagging, quick-detachable lock, hatch cover are closed under power hatch cover, hatch cover
Close fixed quick-detachable lock, connects hinge, load frame and mooring line, it is characterised in that: the power hatch cover is that two structures are identical
Component, power hatch cover are finished up using whole Design of Aerodynamic Configuration, streamlined, opposite opened structure, are respectively equipped in power hatch cover fast
Plug-in card hole；Piggyback pod firewall, which is equipped with, reinforces side, and mooring line both ends are reinforced side with power hatch cover and piggyback pod firewall respectively and connected
It connects；
Fagging and load frame are connected under hatch cover, and fagging two sides are connect with power hatch cover by connects hinge respectively under hatch cover, power
Hatch cover is connected to body and fixation by quick-detachable lock along fuselage cross-section and load frame, and two power hatch covers fasten docking and pass through quick-release
Locking is solid；When needing to check power chamber device and engine condition, quick-detachable lock, the fixed quick-detachable lock of hatch cover closure are pressed, makes two
Split power hatch cover is separated from top, and pulls gravity fall by mooring line, and power hatch cover open angle is 180 ° of foldings.
2. according to claim 1 be used for unmanned plane quick-release opposite opened power hatch cover, it is characterised in that: the mooring line is
Light metal material, 8 > 150mm of the minimum point road clearance is arranged after mooring line length is opened by power hatch cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910385113.0A CN110065639A (en) | 2019-05-09 | 2019-05-09 | One kind being used for unmanned plane quick-release opposite opened power hatch cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910385113.0A CN110065639A (en) | 2019-05-09 | 2019-05-09 | One kind being used for unmanned plane quick-release opposite opened power hatch cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110065639A true CN110065639A (en) | 2019-07-30 |
Family
ID=67370521
Family Applications (1)
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|---|---|---|---|
| CN201910385113.0A Pending CN110065639A (en) | 2019-05-09 | 2019-05-09 | One kind being used for unmanned plane quick-release opposite opened power hatch cover |
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Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101384485A (en) * | 2006-02-16 | 2009-03-11 | 埃尔塞乐公司 | Turbojet engine nacelle with lateral opening of covers |
| CN101528543A (en) * | 2006-10-31 | 2009-09-09 | 埃尔塞乐公司 | Side-opening jet engine nacelle |
| CN101778765A (en) * | 2007-08-20 | 2010-07-14 | 埃尔塞乐公司 | Coupling system connecting an internal structure and an external structure of a jet engine nacelle |
| US20110091317A1 (en) * | 2008-06-25 | 2011-04-21 | Snecma | Fairing device for nacelle of an aircraft propulsion power unit |
| CN104097781A (en) * | 2013-04-03 | 2014-10-15 | 波音公司 | Aircraft nacelle assembly |
| CN203928305U (en) * | 2014-07-16 | 2014-11-05 | 烟台金海创新空调设备有限公司 | A kind of aircondition |
| CN104401478A (en) * | 2014-11-27 | 2015-03-11 | 江西洪都航空工业集团有限责任公司 | Belly large-opening engine load-bearing quick-release compartment door structure |
| CN204661129U (en) * | 2015-03-06 | 2015-09-23 | 徐州重型机械有限公司 | The device of engine for engineering machinery cover lifting |
| CN105460224A (en) * | 2014-09-29 | 2016-04-06 | 空中客车防务及航天股份有限公司 | Alignment and safety device for cowls of aircraft engine nacelles |
| US20160376015A1 (en) * | 2015-06-23 | 2016-12-29 | Rohr, Inc. | Installing or removing aircraft engines |
| CN207436789U (en) * | 2017-11-23 | 2018-06-01 | 株洲九方装备股份有限公司 | A kind of switching mechanism of motor-car hatch door |
| CN108454868A (en) * | 2018-03-23 | 2018-08-28 | 中科灵动航空科技成都有限公司 | A kind of rotor wing unmanned aerial vehicle protective cover |
-
2019
- 2019-05-09 CN CN201910385113.0A patent/CN110065639A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101384485A (en) * | 2006-02-16 | 2009-03-11 | 埃尔塞乐公司 | Turbojet engine nacelle with lateral opening of covers |
| CN101528543A (en) * | 2006-10-31 | 2009-09-09 | 埃尔塞乐公司 | Side-opening jet engine nacelle |
| CN101778765A (en) * | 2007-08-20 | 2010-07-14 | 埃尔塞乐公司 | Coupling system connecting an internal structure and an external structure of a jet engine nacelle |
| US20110091317A1 (en) * | 2008-06-25 | 2011-04-21 | Snecma | Fairing device for nacelle of an aircraft propulsion power unit |
| CN104097781A (en) * | 2013-04-03 | 2014-10-15 | 波音公司 | Aircraft nacelle assembly |
| CN203928305U (en) * | 2014-07-16 | 2014-11-05 | 烟台金海创新空调设备有限公司 | A kind of aircondition |
| CN105460224A (en) * | 2014-09-29 | 2016-04-06 | 空中客车防务及航天股份有限公司 | Alignment and safety device for cowls of aircraft engine nacelles |
| CN104401478A (en) * | 2014-11-27 | 2015-03-11 | 江西洪都航空工业集团有限责任公司 | Belly large-opening engine load-bearing quick-release compartment door structure |
| CN204661129U (en) * | 2015-03-06 | 2015-09-23 | 徐州重型机械有限公司 | The device of engine for engineering machinery cover lifting |
| US20160376015A1 (en) * | 2015-06-23 | 2016-12-29 | Rohr, Inc. | Installing or removing aircraft engines |
| CN207436789U (en) * | 2017-11-23 | 2018-06-01 | 株洲九方装备股份有限公司 | A kind of switching mechanism of motor-car hatch door |
| CN108454868A (en) * | 2018-03-23 | 2018-08-28 | 中科灵动航空科技成都有限公司 | A kind of rotor wing unmanned aerial vehicle protective cover |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20221031 Address after: No.34, Fenghui South Road, Xi'an, Shaanxi 710065 Applicant after: Xi'an Aisheng Technology Group Co.,Ltd. Address before: 710072 No. 127 Youyi West Road, Shaanxi, Xi'an Applicant before: Northwestern Polytechnical University Applicant before: XI'AN AISHENG TECHNOLOGY GROUP Co.,Ltd. |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190730 |
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| RJ01 | Rejection of invention patent application after publication |