CN103723279A - Shock-resisting oil tank structure - Google Patents
Shock-resisting oil tank structure Download PDFInfo
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- CN103723279A CN103723279A CN201310332597.5A CN201310332597A CN103723279A CN 103723279 A CN103723279 A CN 103723279A CN 201310332597 A CN201310332597 A CN 201310332597A CN 103723279 A CN103723279 A CN 103723279A
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- oil tank
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- pushing device
- fuel tank
- collision
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Abstract
The invention discloses a shock-resisting oil tank structure which is characterized in that the structure is composed of an oil tank shell and a telescopic inflator type pushing device mounted inside an oil tank, the oil tank shell is composed of three layers from outside to inside, namely an edge covering layer, a ceramic layer and a collision layer, and the three layers are bonded with adhesives; in the oil tank shell, the edge covering layer is made of a fibrous composite or a polycarbonate film, the ceramic layer is composed of corundum elements, or silicon carbide elements or boron carbide elements, the collision layer is made of a steel plate or a titanium alloy plate, the two ends of the telescopic inflator type pushing device inside the oil tank are connected to wall panels of the oil tank through adhesives, the diameter of the pushing device is 20-100mm, the density of the pushing device is 10-20/m<2>, and multi-point triggering, buffering and energy absorption can be achieved. The composite bulletproof material has good buffering, energy absorption and collision and shock energy consumption performance, can be repaired, and can serve as a material against small and medium caliber type (7.62mm or above) armor-piercing incendiaries.
Description
Technical field
Patent of the present invention relates to a kind of shock proof Oiltank structure that supports, and especially solves aircraft fuel tank and clashes into the injury bringing.
Background information
Key property, work life, reliability and the maintainability of aircraft fuel system, depend on the structure of fuel tank in many aspects.Performance, center of gravity and the inertia of fuel tank layout to aircraft, to the design of aircraft fuel system, especially the weight to fuel oil system and reliability have a great impact, and are the bases of fuel oil system design.At present, in numerous aircraft easily worn parts and structure, wing tank is exposed to the Vulnerable Area maximum that firepower threatens.And the length and width size of fuel tank should be taken into account and can not cause acutely rocking of fuel oil awing, make gravity center shift that fuel flow causes in tolerance interval.When bullet, high-explosive projectile sheet or engine debris are clashed into when the fuel tank of fuel oil is housed, its high kinetic energy impacts and very easily makes the accident such as explosion caused of aircraft because of energy, has a strong impact on operational state.In order to design the Oiltank structure with high viability, just need response and the failure mode of Research on Oil casing under penetrator or blast shell fragment shock.From eighties of last century the seventies, start to have carried out correlative study abroad, and carried out a large amount of coherent analyses and viability test in the remodeling of some aircrafts and novel model design, but the document of publishing is up to now little.
The people such as the Chen Liang of Northwestern Polytechnical University are after analyzing the impact of fuel tanker hydraulic efficiency impact vulnerability, show that fuel tank is destroyed because hitting the fuel oil hydraulic efficiency impact producing in this system, even aircaft configuration is badly damaged very easily to cause casing to break, and flight and fuel oil state have considerable influence to aircraft chief threat direction, Vulnerable Area and kill probability.
Application number is that 201120227963.7 patent discloses taper slide formula aircraft fuel tank in the two casees of a kind of anti-airplane crash, include internal box, outer case, oil inlet and oil outlet, can effectively solve after aeroplane accident, prevent the problem of blast and the burning of fuel tank, but Applicable scope only limits to civil aircraft.And in modern military application, warplane will be far away higher than this to the performance requriements of fuel tank.Not only need to suppress fuel fluctuation problem, more requirement can be resisted effective impact of bullet.
Summary of the invention
For addressing the above problem, the present invention discloses a kind of shock resistance Oiltank structure, can effectively solve aircraft and in flight course, is subject to projectile impact and causes the problems such as the catching fire of fuel tank, blast.It is characterized in that being formed by tank envelope and the scalable inflater type pressing device that is installed on fuel tank internal.Tank envelope is comprised of three-decker from outside to inside, is respectively limit coating, ceramic layer, collision layer.Fuel tank bomb-proof material of the present invention, each layer of shell is by adhesive agent strong bond, and limit coating 10 is comprised of fiber composite materials or polycarbonate film material, preferentially selects Kafra fiber composite material; Ceramic layer 20 is comprised of corundum or carborundum or boron carbide element, and ceramic component can be graininess, can be also tabular, preferentially selects corundum ceramic plate; Collision layer 30 is comprised of steel plate or titanium alloy sheet.Fuel tank internal is scalable inflater type pressing device, and its structure two ends are connected in fuel tank wallboard by adhesion agent, and diameter is 20～100mm, and density is every sq m 10-20, can realize multiple spot and trigger, the effect of buffering energy-absorbing.
The invention has the advantages that: (1) has the function of good buffering, energy-absorbing and consumption collision impact energy; (2) simple in structure, low cost of manufacture; (3) scalable inflater type pressing device can absorption of residual complementary energy, realizes multiple spot and triggers, the effect of buffering energy-absorbing; (4) pressing device also can effectively reduce due to the concussion of fuel tank internal cause in press the problem of liter.
Accompanying drawing explanation
A kind of shock resistance Oiltank structure of Fig. 1 schematic diagram
In figure, 10 is limit coating, and 20 is ceramic layer, and 30 is collision layer, and 40 is the scalable skeleton symbol pressing device of inflating.
The specific embodiment
Below in conjunction with specific embodiment, further illustrate the present invention, should understand these embodiment is only not used in and limits the scope of the invention for the present invention is described, after having read the present invention, those skilled in the art all fall within the application's claims to the modification of the various equivalent form of values of the present invention and limit.
Embodiment 1
In tank envelope, limit coating 10 is the thick Kafra fiber composite panel of 2mm, and surface density is 0.29g/cm
2; Ceramic layer 20 is the thick corundum ceramic piece of 3mm, and surface density is 0.87g/cm
2; Collision layer 30 is 2mm plate iron, and surface density is 1.57g/cm
2; Fuel tank internal adds scalable inflater type crash energy absorption equipment.
Above are only several specific embodiment of the present invention, but design concept of the present invention is not limited to this, allly utilizes this design to carry out the change of unsubstantiality to the present invention, all should belong to the behavior of invading the scope of protection of the invention.
Claims (5)
1. a shock resistance Oiltank structure, it is characterized in that being formed by tank envelope and the scalable inflater type pressing device that is installed on fuel tank internal, tank envelope is comprised of three-decker from outside to inside, is respectively limit coating, ceramic layer, collision layer, and each layer bonding by adhesive agent.
2. according to structure claimed in claim 1, it is characterized in that described limit coating is comprised of fiber composite materials or polycarbonate film material, preferentially selects Kafra fiber composite material.
3. according to structure claimed in claim 1, it is characterized in that described ceramic layer is comprised of corundum or carborundum or boron carbide element, ceramic component can be graininess, can be also tabular, preferentially selects corundum ceramic plate.
4. according to structure claimed in claim 1, it is characterized in that described collision layer is comprised of steel plate or titanium alloy sheet.
5. according to structure claimed in claim 1, it is characterized in that the described scalable inflater type pressing device of fuel tank internal diameter is 20～100mm, density is every sq m 10-20, and structure two ends are connected in fuel tank wallboard by adhesion agent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310332597.5A CN103723279A (en) | 2013-08-02 | 2013-08-02 | Shock-resisting oil tank structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310332597.5A CN103723279A (en) | 2013-08-02 | 2013-08-02 | Shock-resisting oil tank structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103723279A true CN103723279A (en) | 2014-04-16 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310332597.5A Pending CN103723279A (en) | 2013-08-02 | 2013-08-02 | Shock-resisting oil tank structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN103723279A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525668A (en) * | 2019-09-26 | 2019-12-03 | 上海啸风航空科技有限公司 | A kind of fuel bunker of novel belt axial limiting compression |
| CN111361234A (en) * | 2020-03-11 | 2020-07-03 | 沈阳和世泰通用钛业有限公司 | Titanium alloy ceramic composite material and preparation method thereof |
| CN112635889A (en) * | 2020-12-10 | 2021-04-09 | 东风汽车集团有限公司 | Explosion-proof battery |
| CN114771848A (en) * | 2022-06-20 | 2022-07-22 | 中国飞机强度研究所 | Water hammer effect suppression system and method for airplane structure impact resistance test |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB562387A (en) * | 1942-12-14 | 1944-06-29 | William Openshaw Street | Improvements in or relating to liquid containers |
| US4469295A (en) * | 1978-12-21 | 1984-09-04 | Rockwell International Corporation | Hydrodynamic ram attenuating fuel tank |
| US6019316A (en) * | 1997-05-14 | 2000-02-01 | Eurocopter | Device for suspending an aircraft tank |
| US6220472B1 (en) * | 1998-12-09 | 2001-04-24 | Bae Systems Plc | Baffle for a liquid tank |
| US20050089661A1 (en) * | 2003-10-11 | 2005-04-28 | The Boeing Company | Cryogenic fuel tank insulation assembly |
| CN1798686A (en) * | 2003-05-30 | 2006-07-05 | 米兰综合工科大学 | Crashworthiness structure and method |
| CN202481321U (en) * | 2011-12-20 | 2012-10-10 | 中国直升机设计研究所 | Anti-crash fuel tank of helicopter |
-
2013
- 2013-08-02 CN CN201310332597.5A patent/CN103723279A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB562387A (en) * | 1942-12-14 | 1944-06-29 | William Openshaw Street | Improvements in or relating to liquid containers |
| US4469295A (en) * | 1978-12-21 | 1984-09-04 | Rockwell International Corporation | Hydrodynamic ram attenuating fuel tank |
| US6019316A (en) * | 1997-05-14 | 2000-02-01 | Eurocopter | Device for suspending an aircraft tank |
| US6220472B1 (en) * | 1998-12-09 | 2001-04-24 | Bae Systems Plc | Baffle for a liquid tank |
| CN1798686A (en) * | 2003-05-30 | 2006-07-05 | 米兰综合工科大学 | Crashworthiness structure and method |
| US20050089661A1 (en) * | 2003-10-11 | 2005-04-28 | The Boeing Company | Cryogenic fuel tank insulation assembly |
| CN202481321U (en) * | 2011-12-20 | 2012-10-10 | 中国直升机设计研究所 | Anti-crash fuel tank of helicopter |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525668A (en) * | 2019-09-26 | 2019-12-03 | 上海啸风航空科技有限公司 | A kind of fuel bunker of novel belt axial limiting compression |
| CN111361234A (en) * | 2020-03-11 | 2020-07-03 | 沈阳和世泰通用钛业有限公司 | Titanium alloy ceramic composite material and preparation method thereof |
| CN112635889A (en) * | 2020-12-10 | 2021-04-09 | 东风汽车集团有限公司 | Explosion-proof battery |
| CN114771848A (en) * | 2022-06-20 | 2022-07-22 | 中国飞机强度研究所 | Water hammer effect suppression system and method for airplane structure impact resistance test |
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| DD01 | Delivery of document by public notice |
Addressee: TAICANG PAIOU TECHNOLOGY CONSULTATION SERVICE CO., LTD. Document name: Notification of Passing Preliminary Examination of the Application for Invention |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| C12 | Rejection of a patent application after its publication | ||
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Application publication date: 20140416 |