CN105620772A - Small airplane fuel supply system - Google Patents
Small airplane fuel supply system Download PDFInfo
- Publication number
- CN105620772A CN105620772A CN201410589258.XA CN201410589258A CN105620772A CN 105620772 A CN105620772 A CN 105620772A CN 201410589258 A CN201410589258 A CN 201410589258A CN 105620772 A CN105620772 A CN 105620772A
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- Prior art keywords
- fuel
- oil
- tank
- supply system
- sump tank
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Abstract
The invention belongs to the technical field of airplane fuel supply system design and relates to a small airplane fuel supply system. Two fuel suction ports are designed in the lower positions of the front portion and the rear portion of a left wing fuel tank and two fuel suction ports are designed in the lower positions of the front portion and the rear portion of a right wing fuel tank. Fuel collection grooves are designed at the positions of the suction ports. After fuel of fuel supply pipelines at the front portion and the rear portion of the left wing fuel tank and fuel supply pipelines at the front portion and the rear portion of the right wing fuel tank is collected, the fuel then passes through a fuel selector, is input into a small fuel collection tank through gravity and then passes through an auxiliary fuel pump, a fuel cut-off valve, a fuel filter and a fuel supply fireproof hose assembly into an engine fuel inlet. A fuel return pipeline is arranged between the fuel collection tank and an engine fuel adjusting component and provided with a one-way valve. The fuel return pipeline is connected through a fuel return fireproof hose in a fire region. Fuel steam generated in a fuel pipe in hot weather can be effectively reduced, maintainability is improved, and the requirement for fireproof design is met. A ventilation pipeline is arranged at the upper portion of the fuel collection tank and the fuel collection tank is connected with a whole wing fuel tank 1 through the ventilation pipeline. By the adoption of the small airplane fuel supply system, it can be guaranteed that the fuel can be supplied to an engine continuously and reliably in various flight attitudes and the airplane flight safety is improved.
Description
Technical field
The invention belongs to aircraft oil supply system technical field, relate to a kind of oil supply system for baby plane.
Background technology
Baby plane for field, low latitude, it is easy to jolt, flight attitude unstable, the unlimited two point form Fuel System entry design of traditional left and right wing tank, it is easy to causing that fuel oil suction inlet is unsettled, engine oil is discontinuous; Traditional oil supply system design, in oil feed line, gas cannot be discharged in time, it is easy to causes that fuel feeding is not smooth, electromotor easily causes cavitation erosion, influential system operation stability, affects flight safety.
Summary of the invention
A kind of baby plane oil supply system method for designing, it is characterized in that, left and right wing tank 1 lower position separately designs two fuel oil suction inlets 3, suction inlet design has oil trap 13, before and after the wing tank of left and right fuel feed pipeline collect respectively after then through fuel oil selector 12, by gravity input small-sized oil sump tank 5, then through auxiliary fuel pump 11, fuel-cut valve 10, fuel filter 9 and fuel feeding fire prevention hose 14, enter electromotor 6. One return line is set between oil sump tank 5 and electromotor 6, return line is provided with check valve 8, and return line adopts oil return fire prevention flexible pipe 7 to connect in flame range, it is possible to the fuel-steam effectively reduced under hot climate in fuel pipe, improve maintainability, meet fire protection design requirement. Oil sump tank 5 top is provided with vent line, is connected with integral wing tank 1 vent line 2.
The advantageous effect of this invention: this invention can ensure that aircraft is under various state of flights, oil supply system pressure on request and flow continue reliably to supply fuel oil to electromotor, oil feed line arranges fuel oil selector can maintain left and right wing fuel balance, oil sump tank top arranges vent line can be discharged into fuel tanker gas-phase space by fuel pipe and oil sump tank top fuel-steam in time in time, effectively prevent electromotor from cavitating, return line is set between electromotor and oil sump tank and guarantees that hot weather issues the fuel oil temperature of motivation entrance and meets requirement, reduce the fuel-steam in fuel pipe, check valve is set and is effectively increased fuel system maintainability, supply in flame range, return line adopts fire prevention hose to be connected with electromotor, reduce the impact that fuel system is brought by engine luggine, strengthen flexible compensation ability and fire protection design requirement, improve Flight Safety.
Accompanying drawing explanation
Fig. 1 is schematic diagram of the present invention. Wherein: integral wing tank 1; Vent line 2; Fuel oil suction inlet 3; Oil sump tank breather 4; Oil sump tank 5; Electromotor 6; Oil return fire prevention flexible pipe 7; Return check valve 8; Fuel filter 9; Stop valve 10; Fuel pump 11; Fuel oil selector 12; Oil trap 13; Fuel feeding fire prevention flexible pipe 14.
Detailed description of the invention
The detailed description of the invention that should invent is described in conjunction with invention diagram. Such as Fig. 1, left and right wing tank 1 lower position separately designs two fuel oil suction inlets 3, the design of each fuel oil suction inlet 3 has oil trap 13, it can be ensured that aircraft has at least a fuel oil suction inlet 3 can suck fuel oil under various flight attitudes, it is ensured that continue reliable to electromotor supply fuel oil; Left and right wing tank oil feed line collects after fuel oil selector 12, can maintain left and right wing fuel balance; The design of oil feed line lower position has oil sump tank 5, it is generally in full oil condition, upper design has vent line 4, it is connected with wing tank vent line 2, in oil feed line and oil sump tank 5, gas can be discharged to integral wing tank 1 gas-phase space in time, guarantee to continue reliably to supply fuel oil to electromotor under various flight attitudes, effectively prevent electromotor from cavitating; Between oil feed line upper oil-header 5 and electromotor 6 fuel oil suction inlet, design has auxiliary fuel pump 11, fuel-cut valve 10, fuel filter 11 and fuel feeding fire prevention flexible pipe 14, between electromotor 6 and oil sump tank 5, design has return line, guarantee that the fuel oil temperature that hot weather issues motivation entrance meets requirement, reduce the fuel-steam in fuel pipe; On return line, design has return check valve 8, has put forward maintainability; Supply in flame range, return line adopts fire prevention hose to be connected with electromotor, reduces the impact that fuel system is brought by engine luggine, strengthens flexible compensation ability and fire protection design requirement, improve Flight Safety.
Claims (4)
1. a baby plane oil supply system, it is characterized by, described oil supply system includes, fuel oil suction inlet (3), oil sump tank (5), electromotor (6), fuel filter (9), stop valve (10), fuel pump (11), fuel oil selector (12) and fuel feeding fire prevention flexible pipe (14);
Fuel oil suction inlet (3) is arranged in the front and back lower position of left and right integral wing tank (1);
The petroleum pipeline of left and right wing tank is linked together by fuel oil selector (12), the outfan of fuel oil selector (12) is linked together by the oil inlet end of petroleum pipeline Yu oil sump tank (5), and the height of oil sump tank (5) is lower than integral wing tank (1);
The oil outlet end of oil sump tank (5) is connected with fuel pump (11), stop valve (10) and fuel filter (9) in turn, and the outfan of fuel filter (9) and the input of electromotor (6) are linked together by fuel feeding fire prevention flexible pipe (14).
2. baby plane oil supply system according to claim 1, is characterized by: fuel oil suction inlet (3) place is provided with oil trap (13).
3. baby plane oil supply system according to claim 1, it is characterized by: electromotor (6) and oil sump tank (5) are linked together by oil return flexible pipe (7) of preventing fires, and are provided with return check valve (8) between.
4. the baby plane oil supply system according to any of the above-described claim, it is characterized by: the top of oil sump tank has been provided with oil sump tank breather (4), and oil tank breather (4) and wing tank vent line (2) link together.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589258.XA CN105620772A (en) | 2014-10-28 | 2014-10-28 | Small airplane fuel supply system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589258.XA CN105620772A (en) | 2014-10-28 | 2014-10-28 | Small airplane fuel supply system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105620772A true CN105620772A (en) | 2016-06-01 |
Family
ID=56036199
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410589258.XA Pending CN105620772A (en) | 2014-10-28 | 2014-10-28 | Small airplane fuel supply system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105620772A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107128496A (en) * | 2017-04-19 | 2017-09-05 | 中国航空工业集团公司西安飞机设计研究所 | One kind four sends out whirlpool oar aircraft fuel delivery system |
| CN107150811A (en) * | 2017-04-19 | 2017-09-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft oil pumping system |
| CN109625297A (en) * | 2018-12-11 | 2019-04-16 | 石家庄飞机工业有限责任公司 | A kind of fuel system for Small General Aircraft |
| CN110588996A (en) * | 2019-10-16 | 2019-12-20 | 中国商用飞机有限责任公司 | Cross-linking system and method for fuel transfer and fuel tank inerting of aircraft |
| CN111498124A (en) * | 2020-04-29 | 2020-08-07 | 中国商用飞机有限责任公司 | Aircraft fuel supply system and auxiliary fuel control method |
| CN112644721A (en) * | 2020-12-23 | 2021-04-13 | 河北利翔航空科技有限公司 | Aircraft oil supply and delivery system and control method thereof |
| CN113772107A (en) * | 2021-09-30 | 2021-12-10 | 中国商用飞机有限责任公司 | Ventilation device of aircraft auxiliary fuel tank, ventilation control system and aircraft fuel supply system |
| CN114044152A (en) * | 2021-12-17 | 2022-02-15 | 中国航空工业集团公司西安飞机设计研究所 | Bidirectional oil supply balancing system and correcting method for internal combustion oil tank of left wing and right wing of airplane |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3419233A (en) * | 1966-01-31 | 1968-12-31 | British Aircraft Corp Ltd | Aircraft fuel supply arrangements |
| US4913380A (en) * | 1988-10-13 | 1990-04-03 | Omac, Inc. | Fuel system for Canard aircraft |
| EP0915250A1 (en) * | 1997-11-06 | 1999-05-12 | The Cessna Aircraft Company | Fuel systems for avgas with broad volatility |
| US20080173763A1 (en) * | 2007-01-19 | 2008-07-24 | Sikorsky Aircraft Corporation | Fuel jettison system |
| CN201941978U (en) * | 2010-12-27 | 2011-08-24 | 江西洪都航空工业集团有限责任公司 | Continuous oil supply system for aerocraft in maneuver flight |
-
2014
- 2014-10-28 CN CN201410589258.XA patent/CN105620772A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3419233A (en) * | 1966-01-31 | 1968-12-31 | British Aircraft Corp Ltd | Aircraft fuel supply arrangements |
| US4913380A (en) * | 1988-10-13 | 1990-04-03 | Omac, Inc. | Fuel system for Canard aircraft |
| EP0915250A1 (en) * | 1997-11-06 | 1999-05-12 | The Cessna Aircraft Company | Fuel systems for avgas with broad volatility |
| US20080173763A1 (en) * | 2007-01-19 | 2008-07-24 | Sikorsky Aircraft Corporation | Fuel jettison system |
| CN201941978U (en) * | 2010-12-27 | 2011-08-24 | 江西洪都航空工业集团有限责任公司 | Continuous oil supply system for aerocraft in maneuver flight |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107128496A (en) * | 2017-04-19 | 2017-09-05 | 中国航空工业集团公司西安飞机设计研究所 | One kind four sends out whirlpool oar aircraft fuel delivery system |
| CN107150811A (en) * | 2017-04-19 | 2017-09-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft oil pumping system |
| CN107128496B (en) * | 2017-04-19 | 2021-07-09 | 中国航空工业集团公司西安飞机设计研究所 | Four-engine turboprop aircraft oil supply and delivery system |
| CN109625297A (en) * | 2018-12-11 | 2019-04-16 | 石家庄飞机工业有限责任公司 | A kind of fuel system for Small General Aircraft |
| CN110588996A (en) * | 2019-10-16 | 2019-12-20 | 中国商用飞机有限责任公司 | Cross-linking system and method for fuel transfer and fuel tank inerting of aircraft |
| CN111498124A (en) * | 2020-04-29 | 2020-08-07 | 中国商用飞机有限责任公司 | Aircraft fuel supply system and auxiliary fuel control method |
| CN112644721A (en) * | 2020-12-23 | 2021-04-13 | 河北利翔航空科技有限公司 | Aircraft oil supply and delivery system and control method thereof |
| CN113772107A (en) * | 2021-09-30 | 2021-12-10 | 中国商用飞机有限责任公司 | Ventilation device of aircraft auxiliary fuel tank, ventilation control system and aircraft fuel supply system |
| CN114044152A (en) * | 2021-12-17 | 2022-02-15 | 中国航空工业集团公司西安飞机设计研究所 | Bidirectional oil supply balancing system and correcting method for internal combustion oil tank of left wing and right wing of airplane |
| CN114044152B (en) * | 2021-12-17 | 2023-11-28 | 中国航空工业集团公司西安飞机设计研究所 | Bidirectional oil supply balance system and correction method for internal combustion oil tanks of left and right wings of aircraft |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160601 |
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| WD01 | Invention patent application deemed withdrawn after publication |