CN103523239A - Installation structure of helicopter earth observation device - Google Patents
Installation structure of helicopter earth observation device Download PDFInfo
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- CN103523239A CN103523239A CN201210232985.1A CN201210232985A CN103523239A CN 103523239 A CN103523239 A CN 103523239A CN 201210232985 A CN201210232985 A CN 201210232985A CN 103523239 A CN103523239 A CN 103523239A
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- helicopter
- camber beam
- earth observation
- transition
- box type
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Abstract
The invention relates to the field of aircraft manufacturing and provides an installation structure of a helicopter earth observation device. The installation structure comprises a transition platform, a camber beam, a structure transferring device and an onboard connecting part. The course width and section shape of the camber beam used for the earth observation device, the size and orientation of a connector opening of the structure transferring device and the size of a connector opening of the transition platform are changed, so that requirements for installing the earth observation device on helicopters with different tonnages and aerodynamic shapes and helicopters with different connector opening sizes and types are met. The installation structure has the advantages of being good in generality, high in adaptability and the like.
Description
Technical field
The present invention relates to aircraft manufacturing field, relate in particular to a kind of helicopter earth observation equipment mounting structure.
Background technology
Helicopter earth observation equipment is the indispensable instrument that obtains ground observation data on helicopter, have observation method various, the feature such as be widely used.Existing helicopter earth observation equipment mounting means comprises head rotary type tower, forward fuselage structure formula and rotor shaft rotary type.Head rotary type tower is installed on helicopter head place, but is generally used for installation airborne radar herein; Forward fuselage structure formula is installed on forebody one side, but forebody both sides are generally provided with emergent floating drum; Rotor shaft rotary type is large owing to having rotor inertia, helicopter is grasped to steady properties influence outstanding and limited its use.Because helicopter earth observation equipment is numerous, not only there is TV/infrared/laser gondola, take the photograph photographic camera, radar, also comprise optical spectrometer, boat magnetic machine etc., existing earth observation equipment mounting means is because itself feature is difficult to fully meet the complete requirement of helicopter earth observation means, and then limited the application of helicopter earth observation equipment.
Summary of the invention
The technical problem to be solved in the present invention: design a kind of helicopter earth observation equipment mounting structure, be not subject to the restriction of existing helicopter earth observation equipment installation site.
Technical scheme of the present invention: a kind of helicopter earth observation equipment mounting structure, comprising:
A transition platform, transition platform comprises a box type part, the screw hole that has the opening consistent with earth observation equipment capstan head top bore on box type part and connect use; An earth observation equipment is installed and maintenance lid; Transition platform also comprises upper and lower covering and front and back and sidepiece fairing, covering before and after respectively supporting by an angle section before and after box type part.Box type part is bolted on the strengthening rib of camber beam by two rows.
A camber beam, three strengthening ribs arranging between longeron, front and back longeron before and after camber beam comprises, upper and lower covering, front and back side fairing.The front end of camber beam passes through three angle sections and supports front side skins, and rear side skins are supported by two angle sections in rear end.Front-axle beam is with the ears sheet being connected with top connection before helicopter.
A structure transition apparatus, structure transition apparatus comprises a monaural angle section being connected with camber beam floor side member; Two ends are with the transition structure part of ears sheet; An ears sheet being connected with top connection after helicopter; A monaural angle section being connected with camber beam strengthening rib, two ends are respectively with the connection pipe of monaural sheet and ears sheet, and two auricles are connected with thread forms with connection pipe, so that the adjusting in when assembling; An ears joint, is connected with lower adaptor after helicopter.
Connecting bridge on a machine, on machine, connecting bridge comprises four permanent joints, rivets or is bolted on helicopter structure, fixes by self-locking screw with structure transition apparatus and camber beam.
Beneficial effect of the present invention: thus by changing the connector interface size of camber beam course width and section shape, structure transition apparatus for earth observation equipment and meeting the installation requirement of the helicopter of different tonnages, different aerodynamic configurations and distinct interface size, dissimilar helicopter earth observation equipment towards the interface size of, transition platform, there is the features such as commonality is good, applicability is strong.
Accompanying drawing explanation
Fig. 1 is a kind of helicopter earth observation of the present invention equipment mounting structure general illustration.
Fig. 2 is connecting bridge structural representation on machine of the present invention.
Fig. 3 is structure transition apparatus structural representation of the present invention.
Fig. 4 is camber beam structural representation of the present invention.
Fig. 5 is transition platform structural representation of the present invention.
The specific embodiment
Shown in accompanying drawing 1～5, this kind of helicopter earth observation equipment mounting structure comprises 4 parts, connecting bridge 5, structure transition apparatus 4, camber beam 3 and transition platform 2 on machine.
On machine, connecting bridge comprises two top connections 7, two lower adaptors 8, and wherein top connection is monaural structure.Four joints and body can be fixed by bolt and self lock nut, also can adopt rivet to fix.Joint and Helicopter body structure 6 be fixedly by bolt and self lock nut.On machine, connecting bridge architectural feature is to be determined by the version of selected helicopter.
Structure transition apparatus comprises a monaural angle section 9 being connected with camber beam floor side member, two ends are with the transition structure part 12 of ears sheet, an ears sheet 13 being connected with top connection after helicopter, a monaural angle section 10 being connected with camber beam strengthening rib, two ends are respectively with 14, one of the connection pipes of monaural sheet 15 and the ears sheet 11 ears joint 16 that is connected with lower adaptor after helicopter.Two auricles are connected with thread forms with connection pipe, so that the adjusting in when assembling.Two monaural angle sections can adopt riveted joint with being connected of camber beam longeron and strengthening rib, also can fix by bolt and self lock nut.Structure transition apparatus be characterised in that can by change auricle towards, thereby the helicopter of having guaranteed different structure form all can be well and camber beam couple together.
Camber beam comprises front side member 25, on it with the top connection 24 being connected with helicopter top connection, lower adaptor 26; Floor side member 22; Strengthen 23 for three that are arranged between two beams; In order to ensure camber beam, have good aerodynamic characteristic, not only camber beam is designed to streamline contour, and its outside is also by upper covering 19, lower covering 18, front fairing 17,20 rectifications in addition of rear fairing; By being arranged in three angle struts 27 between front-axle beam and two angle struts, the 21 fixation side fairings between the back rest.Covering adopts riveted joint form with being connected of camber beam, and fairing is connected with removable fasteners with angle strut and longeron.The architectural feature of camber beam is determined according to the earth observation equipment size and the weight that install additional.
Transition platform comprises a box type part 31, the screw hole that has the opening consistent with earth observation equipment 1 top bore on box type part and connect use; An earth observation equipment is installed and safeguards by lid 28; Transition platform also comprises upper and lower covering 29 and sidepiece fairing 30, covering before and after respectively supporting by an angle section 32,33 before and after box type part.Box type part is bolted on the strengthening rib of camber beam by two rows.The architectural feature of transition platform is to determine the opening of box type part and selected fastener size according to the earth observation equipment size and the weight that install additional.
Claims (1)
1. a helicopter earth observation equipment mounting structure, is characterized in that, comprising:
A transition platform, transition platform comprises a box type part, the screw hole that has the opening consistent with earth observation equipment capstan head top bore on box type part and connect use; An earth observation equipment is installed and maintenance lid; Transition platform also comprises upper and lower covering and front and back and sidepiece fairing, covering before and after respectively supporting by an angle section before and after box type part; Box type part is bolted on the strengthening rib of camber beam by two rows;
A camber beam, three strengthening ribs arranging between longeron, front and back longeron before and after camber beam comprises, upper and lower covering, front and back side fairing; The front end of camber beam passes through three angle sections and supports front side skins, and rear side skins are supported by two angle sections in rear end; Front-axle beam is with the ears sheet being connected with top connection before helicopter;
A structure transition apparatus, structure transition apparatus comprises a monaural angle section being connected with camber beam floor side member; Two ends are with the transition structure part of ears sheet; An ears sheet being connected with top connection after helicopter; A monaural angle section being connected with camber beam strengthening rib, two ends are respectively with the connection pipe of monaural sheet and ears sheet, and two auricles are connected with thread forms with connection pipe, so that the adjusting in when assembling; An ears joint, is connected with lower adaptor after helicopter;
Connecting bridge on a machine, on machine, connecting bridge comprises four permanent joints, rivets or is bolted on helicopter structure, fixes by self-locking screw with structure transition apparatus and camber beam.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210232985.1A CN103523239B (en) | 2012-07-06 | 2012-07-06 | Installation structure of helicopter earth observation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210232985.1A CN103523239B (en) | 2012-07-06 | 2012-07-06 | Installation structure of helicopter earth observation device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103523239A true CN103523239A (en) | 2014-01-22 |
| CN103523239B CN103523239B (en) | 2015-12-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210232985.1A Expired - Fee Related CN103523239B (en) | 2012-07-06 | 2012-07-06 | Installation structure of helicopter earth observation device |
Country Status (1)
| Country | Link |
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| CN (1) | CN103523239B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105564661A (en) * | 2014-10-15 | 2016-05-11 | 哈尔滨飞机工业集团有限责任公司 | Transport helicopter task load hanging point |
| CN106483528A (en) * | 2015-09-02 | 2017-03-08 | 中国航空工业第六八研究所 | A kind of airborne laser radar fixing device |
| CN108357694A (en) * | 2018-04-24 | 2018-08-03 | 中电科芜湖钻石飞机制造有限公司 | General-purpose aircraft vent pipe fittings mounting tool |
| CN109080850A (en) * | 2018-07-25 | 2018-12-25 | 陕西飞机工业（集团）有限公司 | A kind of installation adjusting method of Large aircraft landing gear nacelle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101298283A (en) * | 2008-04-15 | 2008-11-05 | 孙卓 | Airborne tripod head apparatus for collecting aerial information and use thereof |
| CN201235938Y (en) * | 2008-07-04 | 2009-05-13 | 中国船舶重工集团公司第七一七研究所 | Machine-carried visible light image apparatus |
| US20100208130A1 (en) * | 2009-02-19 | 2010-08-19 | Desorbo Alexander P | Pan and tilt control system with inductive power supply |
| CN101905746A (en) * | 2009-06-02 | 2010-12-08 | 上海中瑞通用航空有限公司 | Mounting method for externally hanging onboard electro-optical pod on helicopter |
-
2012
- 2012-07-06 CN CN201210232985.1A patent/CN103523239B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101298283A (en) * | 2008-04-15 | 2008-11-05 | 孙卓 | Airborne tripod head apparatus for collecting aerial information and use thereof |
| CN201235938Y (en) * | 2008-07-04 | 2009-05-13 | 中国船舶重工集团公司第七一七研究所 | Machine-carried visible light image apparatus |
| US20100208130A1 (en) * | 2009-02-19 | 2010-08-19 | Desorbo Alexander P | Pan and tilt control system with inductive power supply |
| CN101905746A (en) * | 2009-06-02 | 2010-12-08 | 上海中瑞通用航空有限公司 | Mounting method for externally hanging onboard electro-optical pod on helicopter |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105564661A (en) * | 2014-10-15 | 2016-05-11 | 哈尔滨飞机工业集团有限责任公司 | Transport helicopter task load hanging point |
| CN106483528A (en) * | 2015-09-02 | 2017-03-08 | 中国航空工业第六八研究所 | A kind of airborne laser radar fixing device |
| CN108357694A (en) * | 2018-04-24 | 2018-08-03 | 中电科芜湖钻石飞机制造有限公司 | General-purpose aircraft vent pipe fittings mounting tool |
| CN108357694B (en) * | 2018-04-24 | 2024-02-20 | 中电科芜湖钻石飞机制造有限公司 | General aircraft ventilation pipe joint installation frock |
| CN109080850A (en) * | 2018-07-25 | 2018-12-25 | 陕西飞机工业（集团）有限公司 | A kind of installation adjusting method of Large aircraft landing gear nacelle |
| CN109080850B (en) * | 2018-07-25 | 2022-02-11 | 陕西飞机工业（集团）有限公司 | Installation and adjustment method for large aircraft landing gear nacelle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103523239B (en) | 2015-12-02 |
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Granted publication date: 20151202 Termination date: 20170706 |
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