CN104477395A - Body and fuel tank integrated aircraft - Google Patents
Body and fuel tank integrated aircraft Download PDFInfo
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- CN104477395A CN104477395A CN201410699803.0A CN201410699803A CN104477395A CN 104477395 A CN104477395 A CN 104477395A CN 201410699803 A CN201410699803 A CN 201410699803A CN 104477395 A CN104477395 A CN 104477395A
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- aircraft
- storage tank
- fuselage
- withstand voltage
- voltage storage
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention relates to a body and fuel tank integrated aircraft. The body and fuel tank integrated aircraft comprises an aircraft body, a device compartment, wings, an undercarriage and an empennage; the device compartment is arranged at the front end of the aircraft body; the wings are arranged on the top end of the aircraft body; the undercarriage is arranged at the bottom end of the aircraft body; the empennage is arranged at the tail end of the aircraft body; the aircraft body is a pressure-resistant tank. The body and fuel tank integrated aircraft has the advantages that the pressure-resistant bank is used as the aircraft, so that a force transmission line of the aircraft under various loads is simplified, the difficulty at the structural design is reduced, and the structural efficiency is raised; by treating pressure-resistant bank as the aircraft, the weight of the aircraft body structure is greatly saved, and therefore, the whole-aircraft fuel carrying capacity is improved.
Description
Technical field
The present invention relates to field of aerospace technology, be specifically related to a kind of fuselage and fuel reservoir integral type aircraft.
Background technology
The gaseous fuels such as hydrogen, natural fuels, methane are generally acknowledged clean energy resourcies.The relative conventional petroleum energy, these fuel have combustion heat value high (calorific value of such as hydrogen is 2.7 times of gasoline, 3.54 times of coal, and the calorific value of methane is 1.2 times of gasoline), density is little, residues of combustion is pollution-free, acquiring way is various, can the various ways such as gaseous state or liquid state be used, energy utilization rate advantages of higher.Because calorific value is high, energy conversion efficiency is high, when Gas Energy Source is used for aircraft fuel, the fuel oil carrying amount of aircraft can be reduced, increase the capacity weight of aircraft, improve economy, or the cruise duration making aircraft acquisition longer carry the prerequisite of mass conservation at fuel under.
(be 0.0899g/L under hydrogen state because the density of this class A fuel A under usual conditions is little, be 70.8kg/m3 time liquid), therefore the fuel storage volume used is large, quality large, causes storing gravimetric efficiency (fuel mass/fuel and storage tank total mass) low.Store gravimetric efficiency to reduce aerodynamic drag that storage volume brings greatly and improving, adopt the aircraft of liquid state or high-pressure gaseous fuel-in-storage all to tend to adopt the storage tank form that the surface area-to-volume ratios such as spherical, cylindricality storage are less; And wing, fuselage can not be distributed in everywhere as traditional fuel tank, general only in fuselage interior centralized stores.Nonetheless, the insulation of blue gas, the pressure-resistance structure of high pressure gas still need to pay larger quality cost, the potential income that these costs will have a strong impact on gaseous fuel and bring.
Usually, liquefied gas storage needs the Thermo Isolation Technique adopting multilayer functional material+vacuum, to make liquefied fuel gas maintain in the low temperature environment of less than-180 DEG C, and the pressure that the leakage heat that storage tank also will bear trace simultaneously makes liquefied gas evaporation gasification produce.When adopting high pressure gas as fuel, gas storage tank is in order to improve storage gravimetric efficiency, and need the mode adopting high pressure to store, storage tank internal pressure can reach more than 70MPa.Two kinds of storage modes (especially pressure gas storage tank) all need to adopt high strength, fatigue proof materials and structures, thus bring larger architecture quality, make fuel conservation gravimetric efficiency be difficult to improve.On the other hand, the fuselage of aircraft, as main load-carrying construction, needs to transmit airfoil lift, alighting gear impulsive force, engine thrust, also may bear overload and cabin inside and outside differential pressure that load brings.If the load of fuselage can be required to combine with the structural function of the fuel reservoir of gaseous fuel aircraft, then significantly can improve the fuel oil coefficient (fuel mass/aircraft total mass) of gaseous fuel aircraft, be equivalent to indirectly improve fuel conservation gravimetric efficiency, thus the advantage of gaseous fuel can be given full play to.
Summary of the invention
The technical problem to be solved in the present invention is: provide a kind of fuselage and fuel reservoir integral type aircraft, solve the defect that aircraft fuel carrying capacity is low in the past.
The technical solution adopted for the present invention to solve the technical problems is: a kind of fuselage and fuel reservoir integral type aircraft, comprise fuselage, equipment compartment, wing, alighting gear and empennage, described equipment compartment is arranged on the front end of fuselage, described wing is arranged on the top of fuselage, described alighting gear is arranged on the bottom of fuselage, and described empennage is arranged on the tail end of fuselage; Described fuselage is withstand voltage storage tank.
Further, the front end of described withstand voltage storage tank is provided with several the first attachment lugs, and described equipment compartment is connected to the front end of withstand voltage storage tank through each first attachment lug;
The top of described withstand voltage storage tank is provided with several the second attachment lugs, and described wing is connected on withstand voltage storage tank through each second attachment lug;
The tail end of described withstand voltage storage tank is provided with several the 3rd attachment lugs, and described empennage is connected on withstand voltage storage tank through each 3rd attachment lug.
Further, described withstand voltage storage tank is the withstand voltage storage tank of 70MPa.
The invention has the beneficial effects as follows: after fuselage adopts withstand voltage storage tank, simplify the load path of aircraft under various load, reduce structure design difficulty, improve structure efficiency; Withstand voltage storage tank is double does airframe structure, saves a large amount of airframe structure weight, is equivalent to improve full machine fuel carrying capacity.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the present invention is further described.
Fig. 1 is the structural representation of fuselage of the present invention;
Fig. 2 is the structural representation of aircraft of the present invention;
Fig. 3 is the distribution of force figure of aircraft under state of flight;
Fig. 4 is the distribution of force figure of aircraft when landing;
The stress system that Fig. 5 aircraft causes on withstand voltage storage tank at state of flight lower wing;
Fig. 6 is, during 3g forward overload, the maximum stress of 70MPa storage tank occurs in the schematic diagram at inwall place, storage tank rear end;
In figure, 1, fuselage, 2, equipment compartment, 3, wing, 4, empennage, the 5, first attachment lug, the 6, second attachment lug, the 7, the 3rd attachment lug.
Detailed description of the invention
In conjunction with the accompanying drawings, the present invention is further detailed explanation.These accompanying drawings are the schematic diagram of simplification, only basic structure of the present invention are described in a schematic way, and therefore it only shows the formation relevant with the present invention.
As shown in Fig. 1 Fig. 2, a kind of fuselage and fuel reservoir integral type aircraft, comprise fuselage 1, equipment compartment 2, wing 3, alighting gear and empennage 4, equipment compartment 2 is arranged on the front end of fuselage 1, wing 3 is arranged on the top of fuselage 1, alighting gear is arranged on the bottom of fuselage 1, and empennage 4 is arranged on the tail end of fuselage 1; Fuselage 1 is withstand voltage storage tank.
The front end of withstand voltage storage tank is provided with several the first attachment lugs 5, and equipment compartment 2 is connected to the front end of withstand voltage storage tank through each first attachment lug 5; The top of withstand voltage storage tank is provided with several the second attachment lugs 6, and wing 3 is connected on withstand voltage storage tank through each second attachment lug 6; The tail end of withstand voltage storage tank is provided with several the 3rd attachment lugs 7, and empennage 4 is connected on withstand voltage storage tank through each 3rd attachment lug 7.
As shown in Figure 3, the force diagram of aircraft in flight course, the bending load M that aircraft is mainly subject to fuselage 1 lift F, deadweight G, empennage 4 balancing load, driving engine tensile force f, resistance f and various load are formed in wing 3 fuselage 1 junction.The overload factor of aircraft gets 1.5 ~ 3, and safety factor gets 1 ~ 2, then can calculate the basic flight load of aircraft.Force diagram and moment diagram is drawn according to Fig. 3 flight load, adopt the method for calculating of strength of material and theory of structure, just the stress at each section place can be calculated, from stress analysis, the flight load of normal arrangement hydrogen fuel unmanned plane will increase the stress of fuselage 1 the first half, and reduces the stress of fuselage 1 the latter half.In calculating, the cross sectional moment of inertia of thin circular cylinder can be calculated as follows:
In aircraft landing process, the load that fuselage bears, in the landing incipient stage, aircraft two points ground fault is sliding to be run, and airfoil lift load is comparatively large, and main landing gear withstands shocks load simultaneously, aircraft 3 ground connection are slided subsequently, and airfoil lift load reduces gradually, and landing-gear load increases gradually.
As shown in Figure 4, the force diagram of aircraft in stopping process; Aircraft is mainly subject to support reaction N, the gravity loading G of aircraft and the moment M of formation of alighting gear; according to Fig. 4; shut down load and draw force diagram and moment diagram; adopt the method for calculating of strength of material and theory of structure; just the stress at each section place can be calculated; from stress analysis, the shutdown load of normal arrangement hydrogen fuel unmanned plane will reduce the stress of fuselage 1 the first half, and increases the stress of fuselage 1 the latter half.
As shown in Figure 5, the stress system that causes on withstand voltage storage tank at state of flight lower wing 3 of aircraft; As can be seen from the figure (dark color is stress smaller part, and light color is stress larger part), during 3g forward overload, the maximum Mises stress that wing 3 produces on storage tank occurs in attachment lug root, is about 20MPa.
As shown in Figure 6, the distribution of stress under state of flight on 70MPa storage tank; During 3g forward overload, the maximum stress of 70MPa storage tank occurs in storage tank rear end inwall, is about 428MPa.
And withstand voltage storage tank is the withstand voltage storage tank of 70MPa, 70MPa is withstand voltage its pulling force born of storage tank is than airframe 1 structure average axial force height 1-2 magnitude; By force analysis, find that the maximum stress that the structure-integrated withstand voltage storage tank of this 70MPa typical fuselage causes because of fuel pressure is about 428MPa, be positioned at tank body rear end; And the additional stress maxim that 3g overload condition lower wing 3 lift causes in wing 3 and storage tank junction is only 20MPa, need 1/21 of the stress considered less than fuel reservoir Intensity Design.Because withstand voltage fuel reservoir has more than 2 times Intensity Design margins of safety usually, this illustrates, if the requirement meeting tolerance fuel pressure of storage tank, then can meet the requirement of transmitting fuselage load completely.
After fuselage 1 adopts withstand voltage storage tank, simplify the load path of aircraft under various load, reduce structure design difficulty, improve structure efficiency; Withstand voltage storage tank is double does fuselage 1 structure, saves a large amount of fuselage 1 structural weights, is equivalent to improve full machine fuel carrying capacity.
With above-mentioned according to desirable embodiment of the present invention for enlightenment, by above-mentioned description, relevant staff in the scope not departing from this invention technological thought, can carry out various change and amendment completely.The technical scope of this invention is not limited to the content on specification sheets, must determine its technical scope according to right.
Claims (3)
1. a fuselage and fuel reservoir integral type aircraft, it is characterized in that, comprise fuselage (1), equipment compartment (2), wing (3), alighting gear and empennage (4), described equipment compartment (2) is arranged on the front end of fuselage (1), described wing (3) is arranged on the top of fuselage (1), described alighting gear is arranged on the bottom of fuselage (1), and described empennage (4) is arranged on the tail end of fuselage (1); Described fuselage (1) is withstand voltage storage tank.
2. a kind of fuselage according to claim 1 and fuel reservoir integral type aircraft, it is characterized in that, the front end of described withstand voltage storage tank is provided with several the first attachment lugs (5), and described equipment compartment (2) is connected to the front end of withstand voltage storage tank through each first attachment lug (5);
The top of described withstand voltage storage tank is provided with several the second attachment lugs (6), and described wing (3) is connected on withstand voltage storage tank through each second attachment lug (6);
The tail end of described withstand voltage storage tank is provided with several the 3rd attachment lugs (7), and described empennage (4) is connected on withstand voltage storage tank through each 3rd attachment lug (7).
3. a kind of fuselage according to claim 1 and fuel reservoir integral type aircraft, is characterized in that, described withstand voltage storage tank is the withstand voltage storage tank of 70MPa.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410699803.0A CN104477395A (en) | 2014-11-26 | 2014-11-26 | Body and fuel tank integrated aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410699803.0A CN104477395A (en) | 2014-11-26 | 2014-11-26 | Body and fuel tank integrated aircraft |
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| Publication Number | Publication Date |
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| CN104477395A true CN104477395A (en) | 2015-04-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410699803.0A Pending CN104477395A (en) | 2014-11-26 | 2014-11-26 | Body and fuel tank integrated aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106218906A (en) * | 2016-08-31 | 2016-12-14 | 河南翱翔航空科技有限公司 | Unmanned plane body fuel tank |
| CN114313270A (en) * | 2020-09-29 | 2022-04-12 | 海鹰航空通用装备有限责任公司 | Built-in cartridge magazine mechanism containing soft oil tank and invisible airplane with built-in cartridge magazine mechanism |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1435355A (en) * | 2002-12-04 | 2003-08-13 | 韩国庆 | Light buzzard-type wing jet plane and its use, and aircaft carrier using it as ship plane |
| WO2010113793A1 (en) * | 2009-03-30 | 2010-10-07 | 三菱重工業株式会社 | Fuel tank for aircraft |
| CN104192313A (en) * | 2014-08-12 | 2014-12-10 | 青岛爱琪电子科技有限公司 | Blast protection unmanned aerial vehicle |
-
2014
- 2014-11-26 CN CN201410699803.0A patent/CN104477395A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1435355A (en) * | 2002-12-04 | 2003-08-13 | 韩国庆 | Light buzzard-type wing jet plane and its use, and aircaft carrier using it as ship plane |
| WO2010113793A1 (en) * | 2009-03-30 | 2010-10-07 | 三菱重工業株式会社 | Fuel tank for aircraft |
| CN104192313A (en) * | 2014-08-12 | 2014-12-10 | 青岛爱琪电子科技有限公司 | Blast protection unmanned aerial vehicle |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106218906A (en) * | 2016-08-31 | 2016-12-14 | 河南翱翔航空科技有限公司 | Unmanned plane body fuel tank |
| CN114313270A (en) * | 2020-09-29 | 2022-04-12 | 海鹰航空通用装备有限责任公司 | Built-in cartridge magazine mechanism containing soft oil tank and invisible airplane with built-in cartridge magazine mechanism |
| CN114313270B (en) * | 2020-09-29 | 2023-11-03 | 海鹰航空通用装备有限责任公司 | Built-in missile cabin mechanism containing soft oil tank and invisible aircraft with built-in missile cabin mechanism |
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