CN109131904A - A kind of shock proof aircraft integral tank - Google Patents
A kind of shock proof aircraft integral tank Download PDFInfo
- Publication number
- CN109131904A CN109131904A CN201811134979.6A CN201811134979A CN109131904A CN 109131904 A CN109131904 A CN 109131904A CN 201811134979 A CN201811134979 A CN 201811134979A CN 109131904 A CN109131904 A CN 109131904A
- Authority
- CN
- China
- Prior art keywords
- partition
- integral tank
- lightening hole
- bulkhead
- shock proof
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
- B64D37/08—Internal partitioning
Abstract
The application belongs to aircaft configuration field, is related to a kind of integral tank, especially a kind of aircraft integral tank.A kind of shock proof aircraft integral tank including the integral tank that preceding bulkhead, rear bulkhead, floor, covering surround, and is to resist to block the impact of landing bring fuel oil and increased partition, partition middle and upper part are provided with lightening hole.When aircraft arrestment is landed, since inertia is acutely sprung up forward, impact oil pressure is born fuel oil by preceding bulkhead and partition.Since oil pressure is incremented by from back to front, the area of lightening hole is incremented by gradient from front to back, and partition web thickness, rib height equidimension are successively successively decreased from front to back, to mitigate weight.The quantity of partition and position can be increased or decreased according to oil pressure load.
Description
Technical field
The application belongs to aircaft configuration field, is related to a kind of integral tank, especially a kind of carrier-borne aircraft integral tank.
Background technique
Fixed-wing carrier-borne aircraft carries out short distance braked landing by arresting system, big overload and temporary impact when landing
Under, the fuel oil in integral tank is acutely sprung up forward, and very big oil pressure is caused to fuel tank bulkhead, causes fuel tank may be because deforming
Oil leak greatly, or even destroy.
Existing carrier-borne aircraft generallys use the mode of increase bulkhead to increase fuel tank bay section, fuel oil is divided into several lesser
Part, to reduce oil pressure, but the increase of bulkhead causes construction weight and is significantly increased.
Summary of the invention
It is simply whole that the purpose of the application is to provide a kind of oil pressure, lighter in weight and structure that landing is blocked in energy resistance
Fuel tank.
To achieve the above object, technical solution used by the application is:
A kind of shock proof aircraft integral tank, including preceding bulkhead 1, rear bulkhead 2, floor 3 and covering 4, preceding bulkhead 1 and after every
First partition 5, second partition 6, third partition 7 are additionally provided between frame 2.
The first partition 5, second partition 6 are respectively arranged with the first lightening hole 8, the second lightening hole 9 on third partition 7
With third lightening hole 10.
The area of first lightening hole 8, the second lightening hole 9 and third lightening hole 10 is incremented by successively.
The first partition 5, second partition 6, third partition 7 web thickness successively successively decrease.
The application has the following beneficial effects: that integral tank intensity and toughness is good, and structure type is simple, lighter in weight.
Detailed description of the invention
Fig. 1 is the overall structure diagram of the application.
Specific embodiment
The application is described further with reference to the accompanying drawing:
Referring to Fig. 1, a kind of shock proof aircraft integral tank surrounds whole including preceding bulkhead 1, rear bulkhead 2, floor 3, covering 4
Body fuel tank, and block landing bring fuel oil for resistance and impact and increased first partition 5, second partition 6, third partition 7.
First partition 5, second partition 6,7 middle and upper part of third partition have the first lightening hole 8, the second lightening hole 9 and third and mitigate
Hole 10.
The working principle of the application is: when blocking landing, fuel oil since inertia is acutely sprung up forward, oil pressure by bulkhead 1, every
Plate 5, partition 6, partition 7 are born.Fuel oil pressure values p=ρ × g × (L- △ x) suffered by point in fuel tank away from preceding bulkhead distance for △ x
×Nx.In formula, ρ is fuel density, and g is acceleration of gravity, and L is the distance of preceding bulkhead 1 and rear bulkhead 2, NxFor the x for blocking landing
To overload.
It can be seen that oil pressure is incremented by from back to front, therefore the first lightening hole 8, the second lightening hole 9 and third lightening hole 10
Area is incremented by gradient, and first partition 5, second partition 6, the web thickness of third partition 7, rib height equidimension are successively passed
Subtract, to mitigate weight.
In the application, the quantity of partition and position can be increased or decreased according to oil pressure load.
Claims (4)
1. a kind of shock proof aircraft integral tank, which is characterized in that including preceding bulkhead, rear bulkhead, floor and covering, it is preceding every
First partition, second partition, third partition are additionally provided between frame and rear bulkhead.
2. a kind of shock proof aircraft integral tank according to claim 1, which is characterized in that the first partition, second
The first lightening hole, the second lightening hole and third lightening hole are respectively arranged on partition, third partition.
3. a kind of shock proof aircraft integral tank according to claim 1, which is characterized in that first lightening hole,
The area of two lightening holes and third lightening hole is incremented by successively.
4. a kind of shock proof aircraft integral tank according to claim 1, which is characterized in that the first partition, second
Partition, third partition web thickness successively successively decrease.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811134979.6A CN109131904A (en) | 2018-09-28 | 2018-09-28 | A kind of shock proof aircraft integral tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811134979.6A CN109131904A (en) | 2018-09-28 | 2018-09-28 | A kind of shock proof aircraft integral tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109131904A true CN109131904A (en) | 2019-01-04 |
Family
ID=64813128
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811134979.6A Pending CN109131904A (en) | 2018-09-28 | 2018-09-28 | A kind of shock proof aircraft integral tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109131904A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115636094A (en) * | 2022-12-23 | 2023-01-24 | 西安远飞航空技术发展有限公司 | Connecting structure of skin and partition plate, manufacturing method of connecting structure and aircraft oil tank |
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| US20120024418A1 (en) * | 2010-07-29 | 2012-02-02 | Airbus Operations Limited | Refuel valve assembly and method for refuelling an aircraft |
| US20150041592A1 (en) * | 2012-03-26 | 2015-02-12 | Mitsubishi Heavy Industries, Ltd. | Fuel tank, main wing, aircraft fuselage, aircraft, and mobile body |
| CN204279054U (en) * | 2014-12-09 | 2015-04-22 | 江西洪都航空工业集团有限责任公司 | A kind of fuel tank anti-shake dividing plate |
| CN104640913A (en) * | 2012-10-09 | 2015-05-20 | 三菱重工业株式会社 | Structural material for structure, fuel tank, main wing, and aircraft |
| CN205076027U (en) * | 2015-08-13 | 2016-03-09 | 中国航空工业集团公司西安飞机设计研究所 | Wing overall structure oil tank that has hole of collaborating on long purlin |
| US20160355273A1 (en) * | 2015-06-03 | 2016-12-08 | The Boeing Company | Quick installation fuel dam |
| CN205970834U (en) * | 2016-08-12 | 2017-02-22 | 徐州徐工矿山机械有限公司 | Structure strenghthened type mining dump truck oil tank |
| US20170073079A1 (en) * | 2015-09-11 | 2017-03-16 | Michael D. Williams | Block Foam Method of Accomplishing Ignition Mitigation in Aircraft Fuel Tanks |
| CN206750163U (en) * | 2017-09-25 | 2017-12-15 | 西安天问智能科技有限公司 | Anti-oscillating liquid fuel tank and rotor craft |
-
2018
- 2018-09-28 CN CN201811134979.6A patent/CN109131904A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB559490A (en) * | 1942-08-21 | 1944-02-22 | Southern Aircraft Gatwick Ltd | Improvements in and relating to jettison fuel tanks for aircraft |
| KR20050117351A (en) * | 2004-06-10 | 2005-12-14 | 기아자동차주식회사 | Structure of baffle plate in fuel tank for automobile |
| US20120024418A1 (en) * | 2010-07-29 | 2012-02-02 | Airbus Operations Limited | Refuel valve assembly and method for refuelling an aircraft |
| US20150041592A1 (en) * | 2012-03-26 | 2015-02-12 | Mitsubishi Heavy Industries, Ltd. | Fuel tank, main wing, aircraft fuselage, aircraft, and mobile body |
| CN104640913A (en) * | 2012-10-09 | 2015-05-20 | 三菱重工业株式会社 | Structural material for structure, fuel tank, main wing, and aircraft |
| CN204279054U (en) * | 2014-12-09 | 2015-04-22 | 江西洪都航空工业集团有限责任公司 | A kind of fuel tank anti-shake dividing plate |
| US20160355273A1 (en) * | 2015-06-03 | 2016-12-08 | The Boeing Company | Quick installation fuel dam |
| CN205076027U (en) * | 2015-08-13 | 2016-03-09 | 中国航空工业集团公司西安飞机设计研究所 | Wing overall structure oil tank that has hole of collaborating on long purlin |
| US20170073079A1 (en) * | 2015-09-11 | 2017-03-16 | Michael D. Williams | Block Foam Method of Accomplishing Ignition Mitigation in Aircraft Fuel Tanks |
| CN205970834U (en) * | 2016-08-12 | 2017-02-22 | 徐州徐工矿山机械有限公司 | Structure strenghthened type mining dump truck oil tank |
| CN206750163U (en) * | 2017-09-25 | 2017-12-15 | 西安天问智能科技有限公司 | Anti-oscillating liquid fuel tank and rotor craft |
Non-Patent Citations (2)
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| 唐克兵等: "舰载无人机弹射战位及指挥***设计", 《舰船电子工程》 * |
| 唐克兵等: "舰载无人机弹射战位及指挥***设计", 《舰船电子工程》, 31 March 2018 (2018-03-31), pages 21 - 24 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115636094A (en) * | 2022-12-23 | 2023-01-24 | 西安远飞航空技术发展有限公司 | Connecting structure of skin and partition plate, manufacturing method of connecting structure and aircraft oil tank |
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