CN103523239B - Installation structure of helicopter earth observation device - Google Patents
Installation structure of helicopter earth observation device Download PDFInfo
- Publication number
- CN103523239B CN103523239B CN201210232985.1A CN201210232985A CN103523239B CN 103523239 B CN103523239 B CN 103523239B CN 201210232985 A CN201210232985 A CN 201210232985A CN 103523239 B CN103523239 B CN 103523239B
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- China
- Prior art keywords
- helicopter
- camber beam
- earth observation
- transition
- cell type
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- 238000009434 installation Methods 0.000 title claims abstract description 13
- 230000007704 transition Effects 0.000 claims abstract description 30
- 210000005069 ears Anatomy 0.000 claims description 14
- 238000005728 strengthening Methods 0.000 claims description 9
- 238000012423 maintenance Methods 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
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Abstract
The present invention relates to aircraft manufacturing field, a kind of installation structure of helicopter earth observation device is provided, comprises: connecting bridge on a transition platform, a camber beam, a structure transition apparatus, a machine.The present invention by change earth observation equipment camber beam course width and section shape, structure transition apparatus connector interface size and towards, transition platform interface size thus meet the installation requirement of different tonnage, the helicopter of different aerodynamic configuration and distinct interface size, dissimilar helicopter earth observation equipment, there is the features such as commonality is good, applicability is strong.
Description
Technical field
The present invention relates to aircraft manufacturing field, particularly relate to a kind of installation structure of helicopter earth observation device.
Background technology
Helicopter earth observation equipment is indispensable instrument helicopter obtaining ground observation data, have observation method various, the feature such as to 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 side, but forebody both sides are generally provided with emergent floating drum; Rotor shaft rotary type is large owing to having rotor inertia, gives prominence to and limit its use to the impact of helicopter control and stability.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 difficult to fully meet the complete requirement of helicopter earth observation means due to itself feature, and then limits 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 installation structure of helicopter earth observation device, not by the restriction of existing helicopter earth observation equipment installation site.
Technical scheme of the present invention: a kind of installation structure of helicopter earth observation device, comprising:
A transition platform, transition platform comprises a cell type part, screw hole cell type part having the opening consistent with earth observation equipment capstan head top bore and connect; An earth observation equipment is installed and maintenance lid; Transition platform also comprises upper and lower covering and front and back and sidepiece fairing, respectively supports front and back covering by an angle section before and after cell type part.Cell type part is bolted on the strengthening rib of camber beam by two rows.
A camber beam, camber beam comprises three strengthening ribs arranged between front and back longeron, front and back longeron, upper and lower covering, side, front and back fairing.The front end of camber beam supports front side fairing by three angle sections, and rear end supports rear side fairing by two angle sections.Front side member is with the ears sheet be connected with top connection before helicopter.
A structure transition apparatus, structure transition apparatus comprises a monaural angle section be connected with camber beam floor side member; Two ends are with the transition structure part of ears sheet; An ears sheet be connected with top connection after helicopter; A monaural angle section be 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 adjustment during 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, is fixed by self-locking screw with structure transition apparatus and camber beam.
Beneficial effect of the present invention: by change earth observation equipment camber beam course width and section shape, structure transition apparatus connector interface size and towards, transition platform interface size thus meet the installation requirement of different tonnage, the helicopter of different aerodynamic configuration and distinct interface size, dissimilar helicopter earth observation equipment, there is the features such as commonality is good, applicability is strong.
Accompanying drawing explanation
Fig. 1 is a kind of installation structure of helicopter earth observation device general illustration of the present invention.
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.
Detailed description of the invention
Shown in accompanying drawing 1 ~ 5, this kind of installation structure of helicopter earth observation device 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, and rivet also can be adopted to fix.Joint and helicopter body structure 6 be fixedly by bolt and self lock nut.On machine, connecting bridge architectural feature is determined by the version of selected helicopter.
Structure transition apparatus comprises a monaural angle section 9 be connected with camber beam floor side member, two ends are with the transition structure part 12 of ears sheet, an ears sheet 13 be connected with top connection after helicopter, a monaural angle section 10 be connected with camber beam strengthening rib, two ends to be connected with lower adaptor after helicopter ears joint 16 with the connection pipe 14, of monaural sheet 15 and ears sheet 11 respectively.Two auricles are connected with thread forms with connection pipe, so that adjustment during assembling.The connection of two monaural angle sections and camber beam longeron and strengthening rib can adopt riveted joint, also can be fixed by bolt and self lock nut.The feature of structure transition apparatus be can by change auricle towards, thus the helicopter that ensure that different structure form all can well and camber beam couple together.
Camber beam comprises front side member 25, with the top connection 24 be connected with helicopter top connection, lower adaptor 26 on it; Floor side member 22; Three of being arranged between two beams strengthen 23; Have good aerodynamic characteristic in order to ensure camber beam, not only camber beam is designed to streamline contour, and its outside is also by upper covering 19, lower covering 18, front fairing 17, rear fairing 20 rectification in addition; By being arranged in three angle struts 27 between front-axle beam and two angle strut 21 fixation side fairings between the back rest.The connection of covering and camber beam adopts riveted joint form, 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 installed additional and weight.
Transition platform comprises a cell type part 31, screw hole cell type part having the opening consistent with earth observation equipment 1 top bore and connect; An earth observation equipment is installed and safeguards by lid 28; Transition platform also comprises upper and lower covering 29 and sidepiece fairing 30, respectively supports front and back covering by an angle section 32,33 before and after cell type part.Cell type part is bolted on the strengthening rib of camber beam by two rows.The architectural feature of transition platform is opening according to the earth observation equipment size installed additional and weight determination cell type part and selected fastener sizes.
Claims (1)
1. an installation structure of helicopter earth observation device, is characterized in that, comprising:
A transition platform, transition platform comprises a cell type part, screw hole cell type part having the opening consistent with earth observation equipment capstan head top bore and connect; An earth observation equipment is installed and maintenance lid; Transition platform also comprises upper and lower covering and front and back and sidepiece fairing, respectively supports front and back covering by an angle section before and after cell type part; Cell type part is bolted on the strengthening rib of camber beam by two rows;
A camber beam, camber beam comprises three strengthening ribs, up and down covering, side, the front and back fairing arranged between front and back longeron, front and back longeron; The front end of camber beam supports front side fairing by three angle sections, and rear end supports rear side fairing by two angle sections; Front side member is with the ears sheet be connected with top connection before helicopter;
A structure transition apparatus, structure transition apparatus comprises a monaural angle section be connected with camber beam floor side member; Two ends are with the transition structure part of ears sheet; An ears sheet be connected with top connection after helicopter; A monaural angle section be 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 adjustment during 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, is fixed 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 CN103523239A (en) | 2014-01-22 |
| CN103523239B true CN103523239B (en) | 2015-12-02 |
Family
ID=49925686
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) |
Families Citing this family (5)
| 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 |
| 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 |
| 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 |
| CN115447763A (en) * | 2022-10-12 | 2022-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Main fairing structure of airplane |
Citations (3)
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100208130A1 (en) * | 2009-02-19 | 2010-08-19 | Desorbo Alexander P | Pan and tilt control system with inductive power supply |
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2012
- 2012-07-06 CN CN201210232985.1A patent/CN103523239B/en not_active Expired - Fee Related
Patent Citations (3)
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103523239A (en) | 2014-01-22 |
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| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151202 Termination date: 20170706 |