CN204250346U - A kind of anti-rollover airframe steel framework structure - Google Patents
A kind of anti-rollover airframe steel framework structure Download PDFInfo
- Publication number
- CN204250346U CN204250346U CN201420648911.0U CN201420648911U CN204250346U CN 204250346 U CN204250346 U CN 204250346U CN 201420648911 U CN201420648911 U CN 201420648911U CN 204250346 U CN204250346 U CN 204250346U
- Authority
- CN
- China
- Prior art keywords
- steel
- steel structure
- fuel tank
- steel pipe
- airframe
- 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.)
- Expired - Fee Related
Links
Abstract
The utility model relates to a kind of anti-rollover airframe steel framework structure, belongs to technical field of aircraft structure design.It comprises Steel Structure fuel tank area, Steel Structure hopper region and Steel Structure cockpit area; Fuel tank both sides are fixed on the first steel pipe of fuselage Steel Structure both sides by standard band, and tank bottoms is then fixed on the grooved part bottom fuselage Steel Structure by standard band; Front end, Steel Structure fuel tank area makes it to form triangular structure III with Steel Structure by the second steel pipe; Rear end, Steel Structure fuel tank area makes it to form triangular structure I with Steel Structure by the 3rd steel pipe; Steel Structure hopper region and Steel Structure cockpit area make it to form triangular structure II with the central wing back rest, Steel Structure by the 4th steel pipe.The utility model is applicable to the dopey such as general-purpose aircraft, agricultural aircraft, has that structure is simple, safety performance is high, the advantage of low cost of manufacture.
Description
Technical field
The utility model relates to a kind of anti-rollover airframe steel framework structure, belongs to technical field of aircraft structure design.
Background technology
Agricultural aircraft airport condition is generally poor, and the situation that rubble etc. break screw propeller is comparatively general, is ensure the distance between screw propeller blade tip and ground, rear bikini and the Landing Gear Design form of not folding and unfolding is very general.This design has been raised head and has been increased the angle of attack of wing, and its advantage is conducive to taking off, but because alighting gear main wheel is before the center of gravity of airplane, deficient in stability when aircraft slides forward and emergency landing is disturbed, airframe is very easily turned on one's side.And once there is the unforeseen circumstancess such as rollover in aircraft, aircraft body structure very easily occurs that large distortion even fractures, cannot meet technical requirements and the economic requirement of some aircraft, the life security of chaufeur also can be subject to serious threat, thus the safety and reliability of extreme influence aircraft landing.
Summary of the invention
In order to overcome above-mentioned defect, the utility model object is to provide a kind of anti-rollover airframe steel framework structure.
To achieve these goals, the utility model adopts following technical scheme:
A kind of anti-rollover airframe steel framework structure, it comprises Steel Structure fuel tank area, Steel Structure hopper region and Steel Structure cockpit area;
Fuel tank both sides are fixed on the first steel pipe of fuselage Steel Structure both sides by standard band, and tank bottoms is then fixed on the grooved part bottom fuselage Steel Structure by standard band;
Front end, Steel Structure fuel tank area makes it to form triangular structure III with Steel Structure by the second steel pipe;
Rear end, Steel Structure fuel tank area makes it to form triangular structure I with Steel Structure by the 3rd steel pipe;
Steel Structure hopper region and Steel Structure cockpit area make it to form triangular structure II with the central wing back rest, Steel Structure by the 4th steel pipe.
Front beam splice in Steel Structure hopper region makes the 5th steel pipe be connected with central wing front-axle beam.
Rear beam splice in Steel Structure hopper region makes the 6th steel pipe be connected with the central wing back rest.
The beneficial effects of the utility model:
The utility model longitudinal loading coefficient when bearing emergency landing generation overturning is forward 9.0, is upwards the ultimate load of 3.0, on the basis of aircraft original passenger cabin skeleton steel framework, the stress of balance airplane emergency landing is carried out by improving Steel Structure design, bin structure design and fuel tank binding Steel Structure, thus strengthen the stability of aircraft emergency landing, effectively prevent aircraft from turning on one's side.The utility model is applicable to the dopey such as general-purpose aircraft, agricultural aircraft, has that structure is simple, safety performance is high, the advantage of low cost of manufacture.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is A-A generalized section in Fig. 1;
Fig. 3 is B-B generalized section in Fig. 1;
Fig. 4 be in Fig. 1 C to schematic diagram;
Fig. 5 be in Fig. 1 D to schematic diagram;
Fig. 6 is I face close-up schematic view in Fig. 1;
Fig. 7 is II face close-up schematic view in Fig. 1.
Detailed description of the invention
Be described in detail below in conjunction with accompanying drawing 1 ~ 7 pair of the utility model:
A kind of anti-rollover airframe steel framework structure, it comprises Steel Structure fuel tank area 1, Steel Structure hopper region 2 and Steel Structure cockpit area 3;
Fuel tank both sides are fixed on the first steel pipe 4 of fuselage Steel Structure both sides by standard band, and tank bottoms is then fixed on the grooved part 13 bottom fuselage Steel Structure by standard band;
Front end, Steel Structure fuel tank area 1 makes it to form triangular structure III 12 with Steel Structure 5 by the second steel pipe 11; Increase stability.
Rear end, Steel Structure fuel tank area 1 makes it to form triangular structure I 6 with Steel Structure 5 by the 3rd steel pipe 7; Increase stability
Steel Structure hopper region 2 and Steel Structure cockpit area 3 make it to form triangular structure II 10 with the central wing back rest 8, Steel Structure 5 by the 4th steel pipe 9.Increase stability.
Front beam splice 16 in Steel Structure hopper region 2 makes the 5th steel pipe 15 be connected with central wing front-axle beam 14, increases stress balance.
Rear beam splice 18 in Steel Structure hopper region 2 makes the 6th steel pipe 17 be connected with the central wing back rest 8, increases stress balance.
Claims (3)
1. an anti-rollover airframe steel framework structure, is characterized in that: it comprises Steel Structure fuel tank area (1), Steel Structure hopper region (2) and Steel Structure cockpit area (3);
It is characterized in that: fuel tank both sides are fixed on first steel pipe (4) of fuselage Steel Structure both sides by standard band, tank bottoms is then fixed on the grooved part (13) bottom fuselage Steel Structure by standard band;
Steel Structure fuel tank area (1) front end makes it to form triangular structure III (12) with Steel Structure (5) by the second steel pipe (11);
Steel Structure fuel tank area (1) rear end makes it to form triangular structure I (6) with Steel Structure (5) by the 3rd steel pipe (7);
Steel Structure hopper region (2) and Steel Structure cockpit area (3) make it to form triangular structure II (10) with the central wing back rest (8), Steel Structure (5) by the 4th steel pipe (9).
2. anti-rollover airframe steel framework structure according to claim 1, is characterized in that: the front beam splice (16) in Steel Structure hopper region (2) makes the 5th steel pipe (15) be connected with central wing front-axle beam (14).
3. anti-rollover airframe steel framework structure according to claim 1, is characterized in that: the rear beam splice (18) in Steel Structure hopper region (2) makes the 6th steel pipe (17) be connected with the central wing back rest (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420648911.0U CN204250346U (en) | 2014-11-04 | 2014-11-04 | A kind of anti-rollover airframe steel framework structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420648911.0U CN204250346U (en) | 2014-11-04 | 2014-11-04 | A kind of anti-rollover airframe steel framework structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204250346U true CN204250346U (en) | 2015-04-08 |
Family
ID=52954678
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420648911.0U Expired - Fee Related CN204250346U (en) | 2014-11-04 | 2014-11-04 | A kind of anti-rollover airframe steel framework structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204250346U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104386239A (en) * | 2014-11-04 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Rollover prevention airframe steel framework structure |
| CN104890888A (en) * | 2015-04-24 | 2015-09-09 | 江西洪都航空工业集团有限责任公司 | Novel mounting and maintaining structure of oil tank |
-
2014
- 2014-11-04 CN CN201420648911.0U patent/CN204250346U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104386239A (en) * | 2014-11-04 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Rollover prevention airframe steel framework structure |
| CN104890888A (en) * | 2015-04-24 | 2015-09-09 | 江西洪都航空工业集团有限责任公司 | Novel mounting and maintaining structure of oil tank |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204452934U (en) | The double mode aircraft of rotor, fixed-wing | |
| CN204399465U (en) | A kind of anury all-wing aircraft many controlsurfaces unmanned plane | |
| RU2011141267A (en) | AIRCRAFT WITH OPERATION TYPE "COD TAIL" AND WITH REAR ENGINE | |
| WO2014058351A3 (en) | Aircraft | |
| CN107521695B (en) | Wing body fusion connection wing aircraft | |
| CN101973393A (en) | High-strength cage-type undercarriage of unmanned helicopter | |
| CN204250346U (en) | A kind of anti-rollover airframe steel framework structure | |
| CN204250357U (en) | A kind of anti-bird of aircraft leading edge arranging inside panel hits structure | |
| CN204250350U (en) | A kind of anti-bird of aircraft leading edge arranging monocline plate hits structure | |
| CN104386239B (en) | A kind of anti-rollover airframe steel framework structure | |
| WO2013045852A3 (en) | Improved front landing-gear well | |
| CN204750551U (en) | Transportation class aircraft of all -wing aircraft overall arrangement | |
| CN204433031U (en) | Portable fast assembling-disassembling unmanned plane | |
| CN105270603A (en) | Unmanned fixed-wing aircraft with large aspect ratio | |
| CN206068176U (en) | A kind of nacelle arrangement of fixed-wing aerial survey unmanned plane | |
| CN204279912U (en) | A kind of Novel turnover-preventing structure | |
| CN109383755A (en) | It is a kind of can the aircraft leading edge structure hit of anti-bird | |
| CN111017190A (en) | Large-scale civil passenger plane of integration overall arrangement | |
| CN108382589A (en) | A kind of pair of overall aerodynamic arrangement for sending out unmanned plane and its short take-off and landing method | |
| CN203780794U (en) | Lightweight wing tip structure for protecting wing | |
| CN211055359U (en) | Tail structure suitable for multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle | |
| CN204250354U (en) | A kind of anti-bird of aircraft leading edge arranging short beam hits structure | |
| CN204250352U (en) | The anti-bird of a kind of plane nose hits turnup structure | |
| CN202379089U (en) | Novel unmanned aerial vehicle | |
| CN209008868U (en) | It is a kind of for protecting the banjo fixing butt jointing of unmanned plane wing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20150408 Termination date: 20181104 |