CN202244090U - Parallel distributed oil tank system - Google Patents
Parallel distributed oil tank system Download PDFInfo
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- CN202244090U CN202244090U CN2011203271882U CN201120327188U CN202244090U CN 202244090 U CN202244090 U CN 202244090U CN 2011203271882 U CN2011203271882 U CN 2011203271882U CN 201120327188 U CN201120327188 U CN 201120327188U CN 202244090 U CN202244090 U CN 202244090U
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- fuel
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Abstract
The utility model discloses a parallel distributed oil tank system. Five oil tanks are sequentially distributed along the longitudinal direction of an airplane and are symmetrically distributed along a longitudinal axis and a transverse axis of a body axis system which takes the gravity center of the airplane as an original point. Two bubble-proof oil tanks or counterweights are symmetrically distributed on the left side and the right side of the airplane. The oil tanks are sequentially connected through connecting pieces and soft rubber oil pipes according to a regulated oil supply line. The defect that the position of the gravity center of the flying-wing airplane is obviously changed because fuel is consumed can be overcome. Under the situation that an engine on one side flames out during flying or oil is not evenly sucked because the power of engines on two sides is not symmetrical, the position of the gravity center can be ensured to be unchanged. Besides, the parallel distributed oil tank system has the advantages of simplicity in fabrication, low cost, short cycle, high practicability and reliability and convenience in use. Various large-size and small-size fuel systems can be fabricated according to the specific size of the airplane. The parallel distributed oil tank system is particularly suitable for small-size turbojet flying-wing unmanned demonstrators.
Description
Technical field
The present invention relates to a kind of oil tank system, especially to a kind of oil tank system of small-sized all-wing aircraft layout unmanned plane design-calculated.
Background technology
Compare with the normal arrangement aircraft, flying wing type aerodynamic arrangement mainly contains advantages such as loss of weight, drag reduction.But, adopt the all-wing aircraft layout also to bring a series of problems, as fore-and-aft stability a little less than, aircraft is to the sensitivity of longitudinal center of gravity position, vertically problem of trim or the like.In recent years, the domestic many-side research that has also launched gradually all-wing aircraft layout aircraft.Along with the fast development of remote controlled model plane technology and automatic control technology, contracting more and more comes into one's own owing to its low cost, low-risk and short-period characteristics than proof machine flight test technology.
For small-sized all-wing aircraft layout verification machine, in order to reach better verification the verifying results, guarantee the validity of flight test, and guarantee that enough fuel loadings fly for a long time, need to adopt higher fuel oil coefficient design usually.The fuel tank of the aeromodelling airplane of existing turbojet engine adopts glass-felt plastic to make more; Cost of manufacture is low, good reliability, but the fuel loading amount is limited; Unmanned plane for the very high turbojet engine of installed specific fuel consumption; Can not guarantee to fly for a long time, the hang time is too short, thereby is difficult to actv. and makes a flight test.
When the design fuel oil coefficient of unmanned plane is higher, for the normal arrangement aircraft, because fuselage size is relatively large; And the longitudinal stability remaining of aircraft is generally all bigger; Thereby can directly increase the fuel tank volume at the center-of-gravity position place, in the fuel oil consumption process, can not produce tangible influence.But for the all-wing aircraft layout unmanned plane that wing body merges, fuel oil coefficient designing requirement meeting is higher on the one hand, and fuselage thickness is limited, is difficult to meet the demands through direct increase fuel tank volume; On the other hand; Because all-wing aircraft layout aircraft is responsive to longitudinal center of gravity, if simple increase fuel tank volume may cause center-of-gravity position bigger variation to occur because fuel oil rocks in flight course; Thereby cause the deficiency of aircraft handling and trim problem, influence safe flight.
Summary of the invention
In order to overcome prior art causes all-wing aircraft layout aircraft owing to fuel oil consumption center-of-gravity position significant change; Cause the deficiency of aircraft handling and trim problem; The present invention is on the basis of the fuel tank manufacturing technology of existing model airplane aircraft; Designed the fuel oil system that a kind of arranged side by side distributed fuel tank of special use is formed to small-sized all-wing aircraft layout unmanned plane, guaranteed any period in normal flight, the center-of-gravity position of aircraft bigger change can not occur.
The technical solution adopted for the present invention to solve the technical problems is: comprise seven fuel tanks, comprising five volumes equal main oil tank and two anti-bubble fuel tanks that volume equates.No. 1 to No. 5 fuel tank vertically distributes along aircraft as main oil tank successively, and the edge is that the longitudinal axis and the transverse axis during the axon of initial point is is symmetrically distributed with the center of gravity of airplane; No. 6 fuel tanks and No. 7 fuel tanks are symmetrically distributed in the aircraft left and right sides as anti-bubble fuel tank, and particular location can load layout according to fuselage interior and adjust, as long as satisfy body nodal point trim requirement.Be connected with soft rubber oil pipe fuel feeding route order according to the rules through attaching parts between each fuel tank.Anti-bubble fuel tank is at first filled it up with oil when refueling, and air is wherein all got rid of, and begins then to refuel to main oil tank; In the fuel oil consumption process, remain full oil in the anti-bubble fuel tank, intact up to all fuel oil consumptions, can guarantee that driving engine can not suck bubble directly for engine oil through these two fuel tanks.The quantity of nominal increase main oil tank; The volume that reduces single fuel tank can better reach the effect of keeping center-of-gravity position; But on the one hand every increase one-level fuel tank all can cause refueling and during fuel feeding the pressure drag between each fuel tank increase, influence adds speed oil and fuel feeding efficient; Increase the fuel tank number on the other hand and can increase the connection between the fuel tank, make connection complicated more, increase again simultaneously and weight.Therefore weigh the advantages and disadvantages, and, finally adopt the layout of slender acanthopanax two according to the size of fuel oil coefficient.
6, No. 7 fuel tanks are directly given the left and right side engine oil respectively; No. 3 fuel tank links to each other with 6, No. 7 fuel tanks respectively simultaneously; 2, No. 4 fuel tanks link to each other with No. 3 fuel tanks respectively, and No. 5 fuel tank links to each other with No. 2 fuel tanks, and No. 1 fuel tank links to each other with No. 4 fuel tanks; Draw air inlet pipe respectively with the top of No. 5 fuel tanks No. 1 and be connected, guarantee that the oil suction of oil pump for engine is smooth and easy with atmosphere.The two-way oil pipe of being drawn respectively by 6, No. 7 fuel tanks connects through the airtight element threeway of metal; Drawing another road binders pipe links to each other with the airtight element of fuel tap that receives of special use; This element keeps unimpeded when adding/pumping the mouth element in connection, otherwise SELF CL guarantees the air-tightness of oil circuit with this.
Unmanned plane for single-shot; Only need use an anti-bubble fuel tank directly to give engine oil; Promptly adopt the layout of slender acanthopanax one, No. 1 to No. 5 fuel tank vertically distributes along aircraft as main oil tank successively, and the edge is that the longitudinal axis and the transverse axis during the axon of initial point is is symmetrically distributed with the center of gravity of airplane; No. 6 anti-bubble fuel tanks of fuel tank conduct are in any side of aircraft, and clump weight of opposite side symmetrical distribution prevents that bubble fuel tank particular location can load layout according to fuselage interior and adjust, and other connection mode all unmanned planes with two is the same.
In the fuel oil consumption process; According to siphonage; Fuel oil sucks respectively No. 4 and No. 2 fuel tanks by in No. 1 and No. 5 fuel tanks earlier, sucks fuel tank then simultaneously No. 3, sucks respectively No. 6 and No. 7 fuel tanks again; Make these two anti-bubble fuel tanks remain full oil, guarantee in flight course, to give the driving engine continuous oil supply.When refueling before the flight, the oil filling port insertion being received fuel tap, fill it up with two anti-bubble fuel tanks earlier, is No. 3 fuel tanks then successively, and 2, No. 4 fuel tanks are filled it up with No. 1 and No. 5 fuel tanks at last.After flight finished, through can remaining fuel oil be extracted out fully by fuel tap, the oil pumping order was identical with the order of engine consumes fuel oil equally.
The invention has the beneficial effects as follows: the center-of-gravity position that fuel tank is filled it up with behind the oil overlaps with the center-of-gravity position of aircraft; Arrange fuel oil system in this way; Can guarantee any period in normal flight, the center-of-gravity position of aircraft can or not have influence on safe flight than about-face.An if side engine off in flight course; Perhaps the power of both sides driving engine is asymmetric causes oil suction uneven; Because shared No. 3 main oil tanks that are positioned at center of gravity of airplane position; Thereby can not cause the relative transverse axis of other four main oil tanks asymmetric, cause that center-of-gravity position moves along aircraft longitudinal axis.Owing to only have the fuel oil position in two main oil tanks wherein to move along transverse axis in the fuel oil consumption process, and the aircraft transversary weight distribution of all-wing aircraft layout is even, thereby the moving influence of fuel oil center of gravity is very little on X direction with the aircraft double swerve.
If in flight course because the speed that some uncertain factor causes lefthand engine fuel feeding and righthand engine fuel feeding deviation to some extent; Because No. 5, No. 2 fuel tanks in the fuel feeding route of left side and No. 1, No. 4 fuel tanks cross-distribution on the aircraft longitudinal axis direction in the fuel feeding route of left side, thereby can minimally reduce moving of machine gravity position.Because the size of single main oil tank is vertically relatively very little aircraft; Therefore no matter new line take off and the landing process in; When perhaps the pitch angle in the flight course had bigger variation, the fuel oil in the single fuel tank moved and all can not cause the influence bigger to machine gravity.
Description of drawings
Fig. 1: the fuel tank arranged distribution is overlooked schematic diagram;
Fig. 2: fuel feeding route schematic diagram;
Fig. 3: fuel oil system structural representation;
Fig. 4: main oil tank structural representation;
Fig. 5: anti-bubble Oiltank structure scheme drawing;
Fig. 6: attaching parts 1 structural representation;
Fig. 7: attaching parts 2 structural representations;
Wherein: the 1-1 fuel tank; The 2-2 fuel tank; The 3-3 fuel tank; The 4-4 fuel tank; The 5-5 fuel tank; The 6-6 fuel tank; The 7-7 fuel tank; 8-lefthand engine fuel feed pipe; 9-righthand engine fuel feed pipe; The 10-threeway; 11-receives fuel tap; 12-attaching parts 2; 13-attaching parts 1; The 14-weight.
The specific embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is further specified.
Present embodiment is to be used for the fuel oil system that a small capacity double is sent out whirlpool spray all-wing aircraft layout unmanned plane, takes off the about 45kg of gross weight, fuel oil gross weight 11kg.
As shown in Figure 3, the present invention comprises seven fuel tanks altogether, and composition fuel-feed system in order links together.All fuel tanks all are made with glass-felt plastic.As shown in Figure 4,1,2,4, No. 5 fuel tank is all respectively reserved a hole in the center of side and upper surface; No. 3 a hole is respectively stayed in the fuel tank two sides, and upper surface stays two holes; As shown in Figure 5,6, No. 7 anti-bubble fuel tank upper and lower surfaces respectively stays a hole, and a hole is stayed in side, the place ahead; Porose diameter be 16mm.
As shown in Figure 6, attaching parts 1 is formed through adhering with epoxy resin by the copper pipe (basis brass workpiece) of an aluminum metal part (common duralumin workpiece) and corresponding size, and aluminum metal part size guarantees just to be buckled on the hole of fuel tank reservation; After assurance of copper pipe length and aluminum metal part are bonding, in fuel tank, stretch out 1mm, protruding 6mm is used for connecting the soft rubber oil pipe; Bondingly directly its button is bonded on the hole of upper and lower surfaces of upper surface hole and anti-bubble fuel tank of main oil tank after firmly with epoxy resin.As shown in Figure 7, the aluminum metal part of attaching parts 2 is the same with attaching parts 1, method for making too, just copper pipe length guarantee with the aluminum metal part bonding after, in fuel tank, stretch out 10mm, protruding 6mm; The soft rubber oil pipe that after completing inboard copper pipe and length is about corresponding fuel tank length 2/3 links to each other, and the terminal weight that connects of oil pipe is to guarantee that oil suction is from the beginning of fuel tank bottom; Then weight is filled in the fuel tank, cemented attaching parts 2 and fuel tank residue hole button solid with epoxy resin.Attaching parts 1 is all adopted in the hole of the upper surface of all main oil tanks, and attaching parts 2 is adopted in the hole of both sides; Attaching parts 1 is adopted in the hole of the upper and lower surfaces of anti-bubble fuel tank, and the front side face adopts attaching parts 2.Attention: all to use more coarse sand paper with the gluing of surfaces hacking before all bonding carrying out, and clean with alcohol wipe, bonding firm to guarantee.
Whether the air-tightness of fuel tank is detected respectively after all fuel tanks all cement again, pressurize in fuel tank through air pump, putting into the water inspection has gas leakage mouthful.If find gas leakage, use the sand paper hacking with around the air-leak section, and clean with alcohol wipe, with the epoxy resin of glass woven fabric and alcohol dilution air-leak section is repaired then, use the layer 2-3 glass woven fabric according to the gas leakage order of severity.
After having inspected, as shown in Figure 3, with the consistent lubricant pipe each fuel tank is linked together: the attaching parts of the upper surface of No. 1 and No. 5 fuel tank is drawn air inlet pipe respectively and is surrounded on above the fuel tank; The attaching parts of No. 1 fuel tank side is drawn oil pipe and is linked to each other with No. 4 fuel tank top attaching partss, and the attaching parts of No. 4 fuel tank sides is drawn oil pipe and linked to each other with the attaching parts of No. 3 fuel tank top left; The attaching parts of No. 5 fuel tank sides is drawn oil pipe and is linked to each other with No. 2 fuel tank top attaching partss, and the attaching parts of No. 2 fuel tank sides is drawn oil pipe and linked to each other with the attaching parts on the right, No. 3 fuel tank tops; No. 3 fuel tank left and right sides draw respectively oil pipe with about two anti-bubble fuel tank top attaching partss link to each other; Two anti-bubble fuel tanks are drawn oil pipe by the attaching parts of front side, link to each other with the engine oil path of the left and right sides respectively, give engine oil; Attaching parts bottom two anti-bubble fuel tanks connects the two-way oil pipe that and connects through the airtight element threeway of metal; Drawing another road binders pipe links to each other with the airtight element of fuel tap that receives of special use; Be fixed on the control panel at aircraft back, refuel before the aspect flight and the oil pumping of flight back.
Unmanned plane for single-shot; Only need use an anti-bubble fuel tank directly to give engine oil, promptly adopt the layout of slender acanthopanax one, comprise six fuel tanks; Comprising five volumes equal main oil tank and an anti-bubble fuel tank; No. 1 to No. 5 fuel tank vertically distributes along aircraft as main oil tank successively, and the edge is that the longitudinal axis and the transverse axis during the axon of initial point is is symmetrically distributed with the center of gravity of airplane, and No. 6 anti-bubble fuel tanks of fuel tank conduct are in any side of aircraft; Clump weight of opposite side symmetrical distribution is connected with soft rubber oil pipe fuel feeding route order according to the rules through attaching parts between each fuel tank; No. 6 fuel tank is directly given engine oil, and No. 3 fuel tank links to each other with No. 6 fuel tanks; 2, No. 4 fuel tanks link to each other with No. 3 fuel tanks respectively, and No. 5 fuel tank links to each other with No. 2 fuel tanks, and No. 1 fuel tank links to each other with No. 4 fuel tanks; Drawing air inlet pipe respectively with the top of No. 5 fuel tanks No. 1 is connected with atmosphere; The two-way oil pipe of being drawn respectively by No. 6 fuel tanks connects through the airtight element threeway of metal, draw another road binders pipe and link to each other with the airtight element of fuel tap that receives of special use, when this element adds/pump the mouth element in connection maintenance unimpeded, otherwise SELF CL.
Claims (2)
1. distributed oil tank system arranged side by side; Comprise seven fuel tanks; It is characterized in that: comprising five volumes equal main oil tank and two anti-bubble fuel tanks that volume equates; No. 1 to No. 5 fuel tank vertically distributes along aircraft as main oil tank successively; The edge is that the longitudinal axis and the transverse axis during the axon of initial point is is symmetrically distributed with the center of gravity of airplane, and No. 6 fuel tanks and No. 7 fuel tanks are connected with soft rubber oil pipe fuel feeding route order according to the rules through attaching parts between each fuel tank as the symmetrical distribution in the aircraft left and right sides of anti-bubble fuel tanks; 6, No. 7 fuel tanks are directly given the left and right side engine oil respectively; No. 3 fuel tank links to each other with 6, No. 7 fuel tanks respectively simultaneously; 2, No. 4 fuel tanks link to each other with No. 3 fuel tanks respectively, and No. 5 fuel tank links to each other with No. 2 fuel tanks, and No. 1 fuel tank links to each other with No. 4 fuel tanks; Drawing air inlet pipe respectively with the top of No. 5 fuel tanks No. 1 is connected with atmosphere; The two-way oil pipe of being drawn respectively by 6, No. 7 fuel tanks connects through the airtight element threeway of metal, draw another road binders pipe and link to each other with the airtight element of fuel tap that receives of special use, when this element adds/pump the mouth element in connection maintenance unimpeded, otherwise SELF CL.
2. distributed oil tank system arranged side by side according to claim 1; It is characterized in that: comprise six fuel tanks; Comprising five volumes equal main oil tank and an anti-bubble fuel tank; No. 1 to No. 5 fuel tank vertically distributes along aircraft as main oil tank successively, and the edge is that the longitudinal axis and the transverse axis during the axon of initial point is is symmetrically distributed with the center of gravity of airplane, and No. 6 anti-bubble fuel tanks of fuel tank conduct are in any side of aircraft; Clump weight of opposite side symmetrical distribution is connected with soft rubber oil pipe fuel feeding route order according to the rules through attaching parts between each fuel tank; No. 6 fuel tank is directly given engine oil, and No. 3 fuel tank links to each other with No. 6 fuel tanks; 2, No. 4 fuel tanks link to each other with No. 3 fuel tanks respectively, and No. 5 fuel tank links to each other with No. 2 fuel tanks, and No. 1 fuel tank links to each other with No. 4 fuel tanks; Drawing air inlet pipe respectively with the top of No. 5 fuel tanks No. 1 is connected with atmosphere; The two-way oil pipe of being drawn respectively by No. 6 fuel tanks connects through the airtight element threeway of metal, draw another road binders pipe and link to each other with the airtight element of fuel tap that receives of special use, when this element adds/pump the mouth element in connection maintenance unimpeded, otherwise SELF CL.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203271882U CN202244090U (en) | 2011-09-01 | 2011-09-01 | Parallel distributed oil tank system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203271882U CN202244090U (en) | 2011-09-01 | 2011-09-01 | Parallel distributed oil tank system |
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| Publication Number | Publication Date |
|---|---|
| CN202244090U true CN202244090U (en) | 2012-05-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2011203271882U Withdrawn - After Issue CN202244090U (en) | 2011-09-01 | 2011-09-01 | Parallel distributed oil tank system |
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| CN (1) | CN202244090U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102358429A (en) * | 2011-09-01 | 2012-02-22 | 西北工业大学 | Side-by-side distribution-typed oil tank system |
| CN104648681A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | High-reliability fuel supplying and conveying system with gravity center adjusting capability |
-
2011
- 2011-09-01 CN CN2011203271882U patent/CN202244090U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102358429A (en) * | 2011-09-01 | 2012-02-22 | 西北工业大学 | Side-by-side distribution-typed oil tank system |
| CN104648681A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | High-reliability fuel supplying and conveying system with gravity center adjusting capability |
| CN104648681B (en) * | 2013-11-22 | 2017-02-22 | 中国航空工业集团公司西安飞机设计研究所 | High-reliability fuel supplying and conveying system with gravity center adjusting capability |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20120530 Effective date of abandoning: 20140514 |
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| RGAV | Abandon patent right to avoid regrant |