CN103640705B - One plug-in device anchor fitting on Small General Aircraft - Google Patents
One plug-in device anchor fitting on Small General Aircraft Download PDFInfo
- Publication number
- CN103640705B CN103640705B CN201310614285.3A CN201310614285A CN103640705B CN 103640705 B CN103640705 B CN 103640705B CN 201310614285 A CN201310614285 A CN 201310614285A CN 103640705 B CN103640705 B CN 103640705B
- Authority
- CN
- China
- Prior art keywords
- aircraft
- via hole
- fairing
- equipment via
- plug
- Prior art date
- 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
Links
Landscapes
- Connection Of Plates (AREA)
Abstract
The present invention relates to the fixed sturcture on a kind of Small General Aircraft, relate to one plug-in device anchor fitting on Small General Aircraft specifically, comprise the transition adapter plate be fixedly mounted on by anchor fitting on aircraft floor, described transition adapter plate is arranged on above the fairing of aircraft bottom, described fairing offers equipment via hole, described equipment via hole is positioned at immediately below transition adapter plate, corresponding with transition adapter plate.The present invention is based on Small General Aircraft body, in conjunction with the locus of aircraft airborne equipment installation site and aircraft abdomen and the plug-in device fixed sturcture designed, aircraft is enable to load infrared acquisition gondola, meet the purposes requirements such as aircraft aerial survey is taken photo by plane, the air patrol of each industry of farming, forestry, husbandary and fishing, expand the versatility of Small General Aircraft.
Description
Technical field
The present invention relates to the fixed sturcture on a kind of Small General Aircraft, relate to one plug-in device anchor fitting on Small General Aircraft specifically.
Background technology
Small General Aircraft has good manoevreability and cruise performance, and current Small General Aircraft is used for the basic purposes such as aviator's teaching and training, private business flying, also takes photo by plane for aerial survey, the professional purpose such as the air patrol of each industry of farming, forestry, husbandary and fishing.Along with various onboard electro-optical pod more can be become stronger day by day, make aircraft play more wide effect in every field, the demand that all kinds of aircraft adds repacking onboard electro-optical pod also gets more and more.
But Small General Aircraft is because aircraft volume is little, and airborne equipment is many, does not load plug-in failing according to the limitation such as detecting devices space and expand, can not play the multifunctionality of Small General Aircraft, constrain its expansion in market.
Summary of the invention
The invention provides one plug-in device anchor fitting on Small General Aircraft, solve Small General Aircraft because aircraft volume is little, airborne equipment is many and can not load the plug-in technical matters according to detecting devices, promotes the potentiality of Small General Aircraft high-mobility, multipurpose, wheeled vehicle function.
The present invention adopts following technical scheme:
The present invention includes the transition adapter plate be fixedly mounted on by retaining element on aircraft floor, described transition adapter plate is arranged on above the fairing of aircraft bottom, described fairing offers equipment via hole, described equipment via hole is positioned at immediately below transition adapter plate.
Further, described retaining element is pipe link, and described pipe link upper end is fixedly connected with aircraft floor, and lower end is fixedly connected with transition adapter plate.
Further, described pipe link quantity is 4.
Further, described pipe link comprises pull bar, upper hanger and lower hanger, the two ends of described pull bar are fixedly connected with lower hanger with upper hanger respectively, and described lower hanger is fixed on the upside of transition adapter plate, and described upper hanger is fixedly installed on aircraft floor.
Further, on the upside of described aircraft floor, the position of fixing upper hanger is provided with airframe reinforcement.
Further, inside described fairing, be provided with fairing in the position of equipment via hole and strengthen structure.
Further, described fairing is strengthened structure and is comprised equipment via hole reinforcement, and described equipment via hole reinforcement is arranged on inside the edge of equipment via hole, and described equipment via hole reinforcement is the metal parts of annular.
Further, described fairing is strengthened structure and is also comprised fairing covering reinforcement, and described fairing covering reinforcement is the bullion parts of middle part protuberance in inverted V-shaped, is fixedly installed on equipment via hole both sides.
Further, described equipment via hole is also provided with supporting equipment and crosses scuttle hatch.
Good effect of the present invention is as follows:
The present invention by arranging transition adapter plate above the fairing of fuselage bottom, form the mounting bracket of plug-in pod, and by offering equipment via hole on fairing, can plug-in pod be fixedly mounted on transition adapter plate, plug-in pod is suspended on outside fuselage bottom by the equipment via hole on fairing, achieves the professional purpose such as aerial survey is taken photo by plane, the air patrol of each industry of farming, forestry, husbandary and fishing.
Transition adapter plate is fixedly installed on the downside of aircraft floor by pipe link, and structure is simple, easy for installation, reduces the weight of whole mounting bracket to greatest extent, prevents from impacting other performances of aircraft.
In addition, the place of installing hanger on the upside of aircraft floor is provided with airframe reinforcement, strengthens the mechanical strength on aircraft floor, makes whole mounting bracket firm stable more; The equipment via hole reinforcement of annular is provided with inside the edge of equipment via hole, and the fairing covering reinforcement of bar shaped is also provided with in equipment via hole both sides, solve the problem reducing its mechanical strength after fairing offers equipment via hole, avoid fairing deformation in compression.
Equipment crosses scuttle hatch can not needed to be sealed by equipment via hole when loading outward appearance pod at aircraft, and the outer shape that reduction fairing is original, does not affect the aerodynamic force of overall aircraft, enable aircraft normal flight and landing.
Accompanying drawing explanation
Accompanying drawing 1 is the main TV structure schematic diagram of the present invention;
Accompanying drawing 2 is the left TV structure schematic diagram of the present invention;
Accompanying drawing 3 is plan structure schematic diagram fairing of the present invention offering equipment via hole;
Accompanying drawing 4 is fairing covering reinforcement cross-sectional structure schematic diagram of the present invention.
In the accompanying drawings: 1. aircraft floor, 2. pull bar, 3. transition adapter plate, 4. airframe reinforcement, the upper hanger of 5-1., hanger under 5-2., 6. plug-in pod, 7. fairing, 7-1. equipment via hole, 8. equipment via hole reinforcement, 9. fairing covering reinforcement, 10. equipment crosses scuttle hatch.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, further detailed description is done to the present invention.
As shown in accompanying drawing 1-4, one plug-in device anchor fitting on Small General Aircraft, comprise transition adapter plate 3, for fixedly mounting plug-in pod 6, described transition adapter plate 3 is arranged on above aircraft bottom fairing 7, is fixedly mounted on aircraft floor 1 by retaining element, and fairing 7 offers equipment via hole 7-1, described equipment via hole 7-1 is positioned at immediately below transition adapter plate 3, corresponding with transition adapter plate 3.
The installation site of transition adapter plate 3 is determined according to the actual installation position of plug-in pod 6.For not affecting the stability of aircraft, make aircraft be all longitudinal static-stabilities at takeoff and anding and the flat stage that flies, the installation site of plug-in pod 6 is limit away from after the center of gravity of airplane, makes the maximum use gravity's center control of aircraft at 28%b
awithin.
As shown in Figure 2, described retaining element is 4 pipe links, and described pipe link upper end is fixedly connected with aircraft floor, and lower end is fixedly connected with transition adapter plate.Described pipe link comprises pull bar 2, upper hanger 5-1 and lower hanger 5-2, the two ends of described pull bar 2 are fixedly connected with lower hanger 5-1 with upper hanger 5-1 respectively, described lower hanger 5-2 is fixed on the upside of transition adapter plate 3, and described upper hanger 5-1 is fixedly installed on aircraft floor 1.This fixed form structure is simple, easy for installation, reduces the weight of whole mounting bracket to greatest extent, prevents from impacting other performances of aircraft.
As shown in accompanying drawing 1,2, on the upside of aircraft floor 1, the position of fixing upper hanger 5-1 is provided with airframe reinforcement 4, and for increasing the mechanical strength of airframe, described airframe reinforcement 4 is fixedly linked by rivet and aircraft floor 1.
As shown in Figure 3, be provided with equipment via hole reinforcement 8 inside the edge of equipment via hole 7-1, described equipment via hole reinforcement 8 is the metal parts of annular.
As shown in accompanying drawing 3,4, fairing 7 is also provided with fairing covering reinforcement 9, described fairing covering reinforcement 9 is the bullion parts of middle part protuberance in inverted V-shaped, is fixedly installed on equipment via hole 7-1 both sides.
Equipment via hole reinforcement 8 and fairing covering reinforcement 9 strengthen structure as fairing, solve the problem reducing its mechanical strength after fairing 7 offers equipment via hole 7-1, avoid fairing 7 deformation in compression.
Described equipment via hole 7-1 is also provided with supporting equipment and crosses scuttle hatch 10, when not needing to install plug-in pod 6 additional, crossing scuttle hatch 10 with equipment and the equipment via hole 7-1 on fairing 7 is sealed, avoiding airflow influence aircraft normal flight and landing.
When plug-in pod 6 operation installed aboard by needs, dismounting fairing 7 and equipment cross scuttle hatch 10, are fixed on transition adapter plate 3 by plug-in pod 6 by bolt, then recover to install aircraft radome 7.
The present invention by arranging transition adapter plate above the fairing of fuselage bottom, form the mounting bracket of plug-in pod, and by offering equipment via hole on fairing, can plug-in pod be fixedly mounted on transition adapter plate, plug-in pod is suspended on outside fuselage bottom by the equipment via hole on fairing, realizes the professional purpose such as aerial survey is taken photo by plane, the air patrol of each industry of farming, forestry, husbandary and fishing.
Claims (6)
1. a plug-in device anchor fitting on Small General Aircraft, it is characterized in that: it comprises the transition adapter plate (3) be fixedly mounted on by retaining element on aircraft floor (1), described transition adapter plate (3) is arranged on top, aircraft bottom fairing (7), described fairing (7) offers equipment via hole (7-1), described equipment via hole (7-1) is positioned at immediately below transition adapter plate (3), described fairing (7) inner side, be provided with fairing in the position of equipment via hole (7-1) and strengthen structure, described fairing is strengthened structure and is comprised equipment via hole reinforcement (8), described equipment via hole reinforcement (8) is arranged on inside the edge of equipment via hole (7-1), described equipment via hole reinforcement (8) is the metal parts of annular, described fairing is strengthened structure and is also comprised fairing covering reinforcement (9), described fairing covering reinforcement (9) is the bullion parts of middle part protuberance in inverted V-shaped, be fixedly installed on equipment via hole (7-1) both sides.
2. according to claim 1 on Small General Aircraft plug-in device anchor fitting, it is characterized in that: described retaining element is pipe link, described pipe link upper end is fixedly connected with aircraft floor (1), and lower end is fixedly connected with transition adapter plate (3).
3. according to claim 2 on Small General Aircraft plug-in device anchor fitting, it is characterized in that: described pipe link quantity is 4.
4. according to claim 2 on Small General Aircraft plug-in device anchor fitting, it is characterized in that: described pipe link comprises pull bar (2), upper hanger (5-1) and lower hanger (5-2), the two ends of described pull bar (2) are fixedly connected with lower hanger (5-1) with upper hanger (5-1) respectively, described lower hanger (5-2) is fixed on the upside of transition adapter plate (3), and described upper hanger (5-1) is fixed on described aircraft floor (1).
5. according to claim 4 on Small General Aircraft plug-in device anchor fitting, it is characterized in that: upside, described aircraft floor (1), the position of fixing upper hanger (5-1) is provided with airframe reinforcement (4).
6. according to claim 1 on Small General Aircraft plug-in device anchor fitting, it is characterized in that: described equipment via hole (7-1) is also provided with supporting equipment and crosses scuttle hatch (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310614285.3A CN103640705B (en) | 2013-11-28 | 2013-11-28 | One plug-in device anchor fitting on Small General Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310614285.3A CN103640705B (en) | 2013-11-28 | 2013-11-28 | One plug-in device anchor fitting on Small General Aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103640705A CN103640705A (en) | 2014-03-19 |
| CN103640705B true CN103640705B (en) | 2016-03-02 |
Family
ID=50246045
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310614285.3A Active CN103640705B (en) | 2013-11-28 | 2013-11-28 | One plug-in device anchor fitting on Small General Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103640705B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691626B (en) * | 2014-11-28 | 2018-07-20 | 中国飞行试验研究院 | A kind of airframe bottom gondola |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1713851A1 (en) * | 1989-09-11 | 1992-02-23 | Предприятие П/Я В-2141 | Device for fastening searchlight to rescue hydroplane |
| JPH1129098A (en) * | 1997-07-14 | 1999-02-02 | Kawada Kogyo Kk | Accessory equipment extending device for aircraft |
| CN201240505Y (en) * | 2008-07-22 | 2009-05-20 | 山西亚太数字遥感新技术有限公司 | Apparatus for hitching airborne laser LIDAR apparatus with 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 |
-
2013
- 2013-11-28 CN CN201310614285.3A patent/CN103640705B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1713851A1 (en) * | 1989-09-11 | 1992-02-23 | Предприятие П/Я В-2141 | Device for fastening searchlight to rescue hydroplane |
| JPH1129098A (en) * | 1997-07-14 | 1999-02-02 | Kawada Kogyo Kk | Accessory equipment extending device for aircraft |
| CN201240505Y (en) * | 2008-07-22 | 2009-05-20 | 山西亚太数字遥感新技术有限公司 | Apparatus for hitching airborne laser LIDAR apparatus with 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103640705A (en) | 2014-03-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20120318913A1 (en) | On-board aircraft auxiliary power systems having dual auxiliary power units | |
| CN103274046A (en) | Modularized pilotless helicopter for task loads | |
| CN204696229U (en) | A kind of skin antenna integral structure | |
| CN102139757A (en) | Framed front center fuselage suitable for unmanned plane and model plane | |
| CN103640705B (en) | One plug-in device anchor fitting on Small General Aircraft | |
| CN110803280A (en) | Pure electric manned vehicle | |
| CN205022847U (en) | A high performance fixed wing uavs device for cruising monitoring | |
| CN208134595U (en) | A kind of 20 feather weight long endurance unmanned aircraft of load | |
| CN203391991U (en) | Task load-oriented modularized unmanned helicopter | |
| CN205216194U (en) | But fixed -wing aircraft of VTOL | |
| CN203958603U (en) | A kind of aerial survey unmanned plane | |
| CN105836147B (en) | A kind of rotor wing unmanned aerial vehicle protective device | |
| CN202506125U (en) | Quick-dismounting structure for wings | |
| CN104210642B (en) | A kind of depopulated helicopter airframe structure of housing load | |
| CN204056285U (en) | A kind of depopulated helicopter airframe structure of housing load | |
| CN211435086U (en) | Novel power model airplane | |
| CN115214904A (en) | eVTOL aircraft flight test bench | |
| CN211033007U (en) | Pure electric manned aircraft | |
| CN210618450U (en) | Airplane baseline device | |
| CN204688408U (en) | A kind of four rotor unmanned aircrafts | |
| CN211059607U (en) | Target drone avionics system shock absorption and fixing device | |
| CN105667816A (en) | Fixing device with externally-hung pod and fixed-wing unmanned aerial vehicle | |
| CN201494628U (en) | Airplane drop tank with wing | |
| CN203845020U (en) | External hanging type high altitude aerial photography platform | |
| CN205060002U (en) | Three gyroplane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| 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 |