CN102717894A - Fixing structure of external onboard photoelectric pod on fixed-wing aircraft - Google Patents
Fixing structure of external onboard photoelectric pod on fixed-wing aircraft Download PDFInfo
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- CN102717894A CN102717894A CN2012101954893A CN201210195489A CN102717894A CN 102717894 A CN102717894 A CN 102717894A CN 2012101954893 A CN2012101954893 A CN 2012101954893A CN 201210195489 A CN201210195489 A CN 201210195489A CN 102717894 A CN102717894 A CN 102717894A
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- wing aircraft
- door closure
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- photoelectric nacelle
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- 230000007704 transition Effects 0.000 claims abstract description 10
- 238000005516 engineering process Methods 0.000 description 3
- 238000012857 repacking Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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Abstract
The invention discloses a fixing structure of an external onboard photoelectric pod on a fixed-wing aircraft. The fixing structure comprises a door cover, a damper and an embedded part, wherein the door cover is coincident with an opening of an aircraft body pod in shape and structure, and a transition support plate is arranged on the door cover; the damper is arranged on the pod; the embedded part is pre-arranged on the aircraft; the damper is matched with the transition support plate on the door cover and supports the pod; and the door cover is fixedly connected with the embedded part and is fastened with an aircraft body. By adopting the fixing structure of the external onboard photoelectric pod on the fixed-wing aircraft, the photoelectric pod can be smoothly suspended on the fixed-wing aircraft according to a top-to-bottom and inside-to-outside installing sequence, and the pod is ensured to be firmly and reliably connected with the aircraft.
Description
Technical field
The present invention relates on a kind of fixed wing aircraft, is the fixed sturcture of plug-in airborne photoelectric nacelle specifically.
Background technology
At present, along with becoming stronger day by day of various onboard electro-optical pod functions, make aircraft bring into play more wide effect in every field, it is also more and more that all kinds of aircrafts add the demand of reequiping onboard electro-optical pod.It is many that existing helicopter adds the repacking onboard electro-optical pod, because existing gondola comparison of sizes is little, the distance of search target is also short, so adopt helicopter to install the application that electro-optical pod goes to accomplish fields such as take photo by plane in some low latitudes, aerial survey additional mostly.
Existing nowadays along with science and technology development; After the airborne photoelectric gondola that power is big, size is big, search is far away and function is more complete occurs; The mounting structure of gondola is also ensued change; On the higher fixed wing aircraft of flying height, add the repacking onboard electro-optical pod, be the technical barrier that the industry needs to be resolved hurrily.
Summary of the invention
In view of this, the technical matters that the present invention will solve is to provide the installation of the plug-in onboard electro-optical pod of a kind of fixed wing aircraft, particularly the mounting structure of the plug-in onboard electro-optical pod of fixed wing aircraft.
For solving the problems of the technologies described above; Technical scheme of the present invention is achieved in that a kind of fixed sturcture that is used for fixing plug-in airborne photoelectric nacelle on the wing aircraft; Include: door closure matches with airframe gondola opening shape, structure, and has the transition stay bearing plate on it; Bumper is arranged on the said gondola; And built-in fitting, be arranged on the aircraft in advance; Said bumper matches with transition stay bearing plate on the said door closure, supports this gondola; Said door closure is captiveed joint with said built-in fitting, and said door closure and fuselage are tightened up.
Further, said built-in fitting comprises total stressed crossbeam and the retractor device on the stressed framework that is fixed on said aircraft, and this total stressed crossbeam is connected with an end of retractor device, and the other end of retractor device is connected with door closure.
Further, said retractor device comprises pull bar and upper and lower lug, is threaded about adopting respectively between pull bar and the upper and lower lug, can stretch out simultaneously or withdraw each other during pull bar in the middle of rotating.
Further, said door closure is provided with and regulates the flap that said pull bar stretches.
Further, said built-in fitting also comprises the pre-buried hanger of fuselage.
The technique effect that the present invention reaches is following: adopt the present invention to be used for fixing the fixed sturcture of plug-in airborne photoelectric nacelle on the wing aircraft; According to from top to bottom, sequence of erection from inside to outside; Can successfully photoelectric nacelle be lifted on the fixed wing aircraft, and guarantee that gondola and aircraft bonded assembly are solid and reliable.
Description of drawings
Fig. 1 is the structural representation after the fixed sturcture that is used for fixing plug-in airborne photoelectric nacelle on the wing aircraft of the present invention is installed.
Fig. 2 is the connection structure scheme drawing of overall stressed hanger of the present invention and pull bar.
Fig. 3 is the connection structure scheme drawing of gondola bumper of the present invention and transition stay bearing plate.
The specific embodiment
As shown in Figure 1, be used for fixing the fixed sturcture of plug-in airborne photoelectric nacelle on the wing aircraft for the present invention is a kind of, include: door closure 2 matches with airframe photoelectric nacelle 1 opening shape, structure, and has transition stay bearing plate 10 on it; Bumper 9 is arranged on the photoelectric nacelle 1; And built-in fitting, be arranged on the aircraft in advance; Bumper 9 matches with transition stay bearing plate 10 on the door closure, supports this photoelectric nacelle 1; At first, photoelectric nacelle 1 and door closure 2 are assembled together, with reference to figure 3; 3 bumpers 9 are arranged on the photoelectric nacelle 1, photoelectric nacelle 1 is sling put into door closure 2, let bumper 9 be seated on the transition stay bearing plate 10 of door closure; Fastening with screw 14, so just photoelectric nacelle 1 and door closure 2 have been installed.
After these work are accomplished, just etc. to be assembled the door closure 2 of photoelectric nacelle 1 has been installed.For door closure 2 firm the fixing that photoelectric nacelle 1 will be installed with airframe; Interior of aircraft will add the built-in fitting of repacking earlier; Built-in fitting comprises total stressed crossbeam 5 and the retractor device on the stressed framework that is fixed on aircraft; This total stressed crossbeam 5 is connected with an end of retractor device, and the other end of retractor device is connected with door closure 2.In the present embodiment, retractor device comprises lug 12 under pull bar 7 and last lug 11, the pull bar, is threaded about employing; Pull bar 2 in the middle of rotating can lug 12 stretches out or withdrawal simultaneously simultaneously under lug 11, the pull bar with going up; When 12 withdrawals of lug under last lug 11, the pull bar, just can door closure 2 upwards be carried,, be fixed on the stressed framework of aircraft at total stressed crossbeam 5 until being adjacent to fuselage; Be fixed with overall stressed hanger 6 on total stressed crossbeam 5; Again with reference to figure 2, the last lug 11 of pull bar 7 is connected with overall stressed hanger 6 usefulness screws 13, door closure 2 is provided with hanger 8; The screw and the hanger 8 on the door closure 2 of following lug 12 usefulness same sizes are fastening, have so just guaranteed door closure 2 is connected tightly with fuselage.On door closure 2, be provided with the mounting process flap 3 that adjusting yoke 7 stretches.Certainly, this constriction device also can adopt worm and gear.Spring or other any devices that can adjust length needn't be given unnecessary details at this.
Built-in fitting also comprises the pre-buried hanger 4 of fuselage, and the door closure 2 that gondola 1 will be housed at last links to each other with the pre-buried hanger 4 of fuselage, and so far fastening, fitting work has just been accomplished.
The above is merely preferred embodiment of the present invention, is not to be used to limit protection scope of the present invention.
Claims (5)
1. a fixed sturcture that is used for fixing plug-in airborne photoelectric nacelle on the wing aircraft is characterized in that, includes:
Door closure matches with airframe gondola opening shape, structure, and has the transition stay bearing plate on it;
Bumper is arranged on the said gondola; And
Built-in fitting is arranged on the aircraft in advance;
Said bumper matches with transition stay bearing plate on the said door closure, supports this gondola; Said door closure is captiveed joint with said built-in fitting, and said door closure and fuselage are tightened up.
2. the fixed sturcture that is used for fixing plug-in airborne photoelectric nacelle on the wing aircraft as claimed in claim 1; It is characterized in that; Said built-in fitting comprises total stressed crossbeam and the retractor device on the stressed framework that is fixed on said aircraft; This total stressed crossbeam is connected with an end of retractor device, and the other end of retractor device is connected with door closure.
3. the fixed sturcture that is used for fixing plug-in airborne photoelectric nacelle on the wing aircraft as claimed in claim 1; It is characterized in that; Said retractor device comprises pull bar and upper and lower lug; Be threaded about adopting respectively between pull bar and the upper and lower lug, can stretch out simultaneously or withdraw each other during pull bar in the middle of rotating.
4. the fixed sturcture that is used for fixing plug-in airborne photoelectric nacelle on the wing aircraft as claimed in claim 3 is characterized in that, said door closure is provided with regulates the flap that said pull bar stretches.
5. the fixed sturcture that is used for fixing plug-in airborne photoelectric nacelle on the wing aircraft as claimed in claim 1 is characterized in that, said built-in fitting also comprises the pre-buried hanger of fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210195489.3A CN102717894B (en) | 2012-06-14 | 2012-06-14 | Fixing structure of external onboard photoelectric pod on fixed-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210195489.3A CN102717894B (en) | 2012-06-14 | 2012-06-14 | Fixing structure of external onboard photoelectric pod on fixed-wing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102717894A true CN102717894A (en) | 2012-10-10 |
| CN102717894B CN102717894B (en) | 2015-01-21 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210195489.3A Expired - Fee Related CN102717894B (en) | 2012-06-14 | 2012-06-14 | Fixing structure of external onboard photoelectric pod on fixed-wing aircraft |
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| CN (1) | CN102717894B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106742005A (en) * | 2016-11-21 | 2017-05-31 | 国网山东省电力公司电力科学研究院 | A kind of power-line patrolling photoelectric nacelle and depopulated helicopter |
| CN108216660A (en) * | 2017-12-08 | 2018-06-29 | 西安飞机工业（集团）有限责任公司 | A kind of flame drilling for aircraft of increasing rain artificially dissipates equipment mounting structure |
| CN112208770A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业集团有限责任公司 | Linkage retraction device for cabin door of exposed equipment of airplane |
Citations (6)
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|---|---|---|---|---|
| US5383645A (en) * | 1992-01-12 | 1995-01-24 | State Of Israel-Ministry Of Defence Armament Development Authority, Rafael | Stabilized payload |
| US20030071170A1 (en) * | 2001-10-15 | 2003-04-17 | Hilbert Andrea A. | Reconfigurable reconnaissance pod system |
| 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 |
| CN201432799Y (en) * | 2009-06-02 | 2010-03-31 | 上海中瑞通用航空有限公司 | Mounting structure for external airborne photoelectric nacelle equipment of helicopter |
| CN101758922A (en) * | 2008-12-23 | 2010-06-30 | 江西洪都航空工业集团有限责任公司 | Retractable captive flight support for external hanging equipment |
| CN202686768U (en) * | 2012-06-14 | 2013-01-23 | 北京中陆航星科技有限公司 | Fixing structure for plug-in airborne photoelectric pod on fixed wing aircraft |
-
2012
- 2012-06-14 CN CN201210195489.3A patent/CN102717894B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5383645A (en) * | 1992-01-12 | 1995-01-24 | State Of Israel-Ministry Of Defence Armament Development Authority, Rafael | Stabilized payload |
| US20030071170A1 (en) * | 2001-10-15 | 2003-04-17 | Hilbert Andrea A. | Reconfigurable reconnaissance pod system |
| 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 |
| CN101758922A (en) * | 2008-12-23 | 2010-06-30 | 江西洪都航空工业集团有限责任公司 | Retractable captive flight support for external hanging equipment |
| CN201432799Y (en) * | 2009-06-02 | 2010-03-31 | 上海中瑞通用航空有限公司 | Mounting structure for external airborne photoelectric nacelle equipment of helicopter |
| CN202686768U (en) * | 2012-06-14 | 2013-01-23 | 北京中陆航星科技有限公司 | Fixing structure for plug-in airborne photoelectric pod on fixed wing aircraft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106742005A (en) * | 2016-11-21 | 2017-05-31 | 国网山东省电力公司电力科学研究院 | A kind of power-line patrolling photoelectric nacelle and depopulated helicopter |
| CN108216660A (en) * | 2017-12-08 | 2018-06-29 | 西安飞机工业（集团）有限责任公司 | A kind of flame drilling for aircraft of increasing rain artificially dissipates equipment mounting structure |
| CN112208770A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业集团有限责任公司 | Linkage retraction device for cabin door of exposed equipment of airplane |
| CN112208770B (en) * | 2020-10-10 | 2022-08-26 | 江西洪都航空工业集团有限责任公司 | Cabin door linkage retracting and releasing device for exposed equipment of airplane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102717894B (en) | 2015-01-21 |
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Owner name: JIANGSU A-STAR AVIATION INDUSTRY CO., LTD. Free format text: FORMER OWNER: BEIJING ZHONGLU HANGXING TECHNOLOGY CO., LTD. Effective date: 20150427 |
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Effective date of registration: 20150427 Address after: Zhenjiang City, Jiangsu province 212132 Ruicheng District Road No. 88 Patentee after: Jiangsu Zhong Luhang star Israel Aircraft Industries Ltd. Address before: 102200, Beijing, Changping District, Ma Chi Town, Cross Bridge Village West courtyard Patentee before: Beijing Zhonglu Hangxing Technology Co.,Ltd. |
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| 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: 20150121 Termination date: 20170614 |