CN112173139B - Helicopter fuel pipeline integrated system - Google Patents
Helicopter fuel pipeline integrated system Download PDFInfo
- Publication number
- CN112173139B CN112173139B CN202011028734.2A CN202011028734A CN112173139B CN 112173139 B CN112173139 B CN 112173139B CN 202011028734 A CN202011028734 A CN 202011028734A CN 112173139 B CN112173139 B CN 112173139B
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- Prior art keywords
- control valve
- fuel
- fuel tank
- oil
- pipeline
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- 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
- B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
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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
Abstract
The invention belongs to the technical field of helicopter fuel systems, and discloses a helicopter fuel pipeline integration system. The hydraulic control system consists of a first control valve, a second control valve, a third control valve, a fourth control valve, a fifth control valve, a sixth control valve, a seventh control valve, a transfer pump, a pressure oil filler cap, a one-way valve, a booster pump, a pressure oil filling control valve, a first oil tank, a second oil tank, a first externally hung oil tank and a second externally hung oil tank. The functions of fuel oil transfer, pressure refueling and external fuel tank fuel delivery are respectively realized by using a set of pipelines.
Description
Technical Field
The invention belongs to the technical field of helicopter fuel systems, and particularly relates to a helicopter fuel pipeline integrated system.
Background
The existing helicopter fuel system has independent pipeline systems with functions of fuel transfer, pressure refueling, external fuel tank fuel delivery and the like, and the required installation space is large.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a helicopter fuel pipeline integrated system; pipeline integration through helicopter fuel oil is defeated, pressure refuels, external oil tank oil delivery can reduce the pipeline and lay the space, reduces pipeline installation quantity, is favorable to the helicopter to subtract heavy.
The technical scheme of the invention is as follows:
a helicopter fuel piping integration system comprising: the system comprises a first fuel tank, a second fuel tank, a first pressure refueling control valve, a second pressure refueling control valve, a first control valve, a second control valve, a third control valve, a fourth control valve, a fifth control valve and a transfer pump;
one end of the first pressure refueling control valve is connected with the first fuel tank, and the other end of the first pressure refueling control valve is connected with the first control valve through a pipeline; the other end of the first control valve is connected with one end of a third control valve through a pipeline, the other end of the third control valve is connected with one end of a fifth control valve through a pipeline, the other end of the fifth control valve is connected with one end of a second pressure oil filling control valve through a pipeline, and the second pressure oil filling control valve is connected with a second fuel tank;
one end of the second control valve is connected to a pipeline between the first control valve and the third control valve through a first three-way joint,
one end of the fourth control valve is connected to a pipeline between the third control valve and the fifth control valve through a second three-way joint,
the transfer pump is connected between the second control valve and the fourth control valve.
Further, the system further comprises: the pressure filler cap is connected to a pipeline between the second three-way joint and the fifth control valve and used for pressure filling of the first fuel tank and the second fuel tank.
Further, the system further comprises: the sixth control valve, the first one-way valve, the first booster pump and the first externally hung oil tank;
one end of the sixth control valve is connected to a pipeline between the first control valve and the first three-way joint through a pipeline; the other end of the first booster pump is connected with one end of the first booster pump through a one-way valve, and the other end of the first booster pump is connected with a first external oil tank.
Further, the system further comprises: the seventh control valve, the second one-way valve, the second booster pump and the second externally-hung oil tank;
one end of the seventh control valve is connected to a pipeline between the fifth control valve and the second three-way joint through a pipeline; the other end of the second booster pump is connected with one end of a second booster pump through a one-way valve, and the other end of the second booster pump is connected with a second externally-hung oil tank.
Further, controlling the first control valve, the third control valve and the fifth control valve to be communicated; closing the second control valve, the fourth control valve, the sixth control valve and the seventh control valve, and simultaneously filling the first fuel tank and the second fuel tank with fuel through the pressure filler cap;
controlling the first control valve and the third control valve to be communicated; closing the second control valve, the fourth control valve, the fifth control valve, the sixth control valve and the seventh control valve, and filling the first fuel tank with oil through a pressure oil filler cap;
controlling the fifth control valve to be communicated; and closing the first control valve, the second control valve, the third control valve, the fourth control valve, the sixth control valve and the seventh control valve, and filling the second fuel tank with oil through the pressure oil filling cover.
Further, controlling the first control valve, the second control valve, the fourth control valve and the fifth control valve to be communicated; the third control valve, the sixth control valve and the seventh control valve are closed; transferring the fuel oil of the first fuel oil tank to a second fuel oil tank through a transfer pump; or the fuel in the second fuel tank is transferred to the first fuel tank through the reverse rotation of the transfer pump.
Further, controlling the first control valve, the third control valve, the fifth control valve and the sixth control valve to be communicated; the second control valve, the fourth control valve and the seventh control valve are closed, and the first booster pump is opened to transfer the fuel oil in the first external fuel tank to the first fuel tank and the second fuel tank;
controlling the first control valve, the third control valve, the fifth control valve and the seventh control valve to be communicated; and the second control valve, the fourth control valve and the sixth control valve are closed, and the second booster pump is opened to transfer the fuel in the second outer hanging fuel tank to the first fuel tank and the second fuel tank.
Further, controlling the first control valve and the sixth control valve to be communicated; the second control valve, the third control valve, the fourth control valve, the fifth control valve and the seventh control valve are closed, and the first booster pump is opened to transfer the fuel oil in the first external fuel tank to the first fuel tank;
controlling the third control valve, the fifth control valve and the sixth control valve to be communicated; and the first control valve, the second control valve, the fourth control valve and the seventh control valve are closed, and the first booster pump is opened to transfer the fuel oil in the first external fuel tank to the second fuel tank.
Further, controlling the first control valve, the third control valve and the seventh control valve to be communicated; the second control valve, the fourth control valve, the fifth control valve and the sixth control valve are closed, and a second booster pump is opened to transfer the fuel oil in the second outer hanging fuel tank to the first fuel tank;
controlling the fifth control valve and the seventh control valve to be communicated; and the first control valve, the second control valve, the third control valve, the fourth control valve and the sixth control valve are closed, and the second booster pump is opened to transfer the fuel oil in the second external fuel tank to the second fuel tank.
The invention has the beneficial technical effects that: the helicopter fuel pipeline integration system provided by the invention integrates a fuel tank transfer pipeline, an external fuel tank oil pipeline, an internal auxiliary fuel tank oil pipeline and a pressure fuel filling pipeline, and realizes corresponding functions by changing the on/off states of seven control valves and comprehensively controlling. Reduce the pipeline laying space, scientifically subtract heavy.
Drawings
FIG. 1 is a schematic diagram of a helicopter fuel piping integration system;
FIG. 2 is a schematic diagram of a first fuel tank and a second fuel tank simultaneously pressurized;
FIG. 3 is a schematic diagram of a first fuel tank pressure refueling alone;
FIG. 4 is a schematic diagram of pressure refueling of a second fuel tank alone;
FIG. 5 is a schematic illustration of a transfer between a first fuel tank and a second fuel tank;
FIG. 6 is a schematic view of a first external tank delivering fuel to a first fuel tank and a second fuel tank;
FIG. 7 is a schematic illustration of the second spill reservoir delivering fuel to the first fuel tank and the second fuel tank;
FIG. 8 is a schematic view of the first external tank alone delivering fuel to the first fuel tank;
FIG. 9 is a schematic diagram of the first externally hung fuel tank independently delivering fuel to the second fuel tank;
FIG. 10 is a schematic view of the second outer fuel tank alone delivering fuel to the first fuel tank;
FIG. 11 is a schematic diagram of the second spill reservoir delivering fuel separately to the second fuel reservoir;
description of reference numerals: 1-a first control valve, 2-a second control valve, 3-a third control valve, 4-a fourth control valve, 5-a fifth control valve, 6-a sixth control valve, 7-a seventh control valve, 8-a transfer pump, 9-a pressure oil filler cap, 10-a one-way valve, 11-a booster pump, 12-a pressure oil filling control valve, 13-a first fuel tank, 14-a second fuel tank, 15-a first external fuel tank and 16-a second external fuel tank.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
According to the helicopter fuel pipeline integrated system disclosed by the invention, as shown in fig. 1, one end of a first pressure refueling control valve is connected with a first fuel tank, and the other end of the first pressure refueling control valve is connected with one end of a first control valve. The other end of the first control valve is connected with one end of a third control valve through a first three-way joint, the other end of the third control valve is connected with one end of a fifth control valve through a second three-way joint, the other end of the fifth control valve is connected with one end of a second pressure oiling control valve, and the other end of the second pressure oiling control valve is connected with a second fuel tank. One end of the second control valve is connected with the first three-way joint, the other end of the second control valve is connected with one end of the transfer pump, the other end of the transfer pump is connected with one end of the fourth control valve, and the other end of the fourth control valve is connected with the second three-way joint. One end of the sixth control valve is connected to a pipeline between the first control valve and the first three-way joint through a pipeline; the other end of the first booster pump is connected with one end of the first booster pump through a one-way valve, and the other end of the first booster pump is connected with a first external oil tank. One end of the seventh control valve is connected to a pipeline between the fifth control valve and the second three-way joint through a pipeline; the other end of the second booster pump is connected with one end of a second booster pump through a one-way valve, and the other end of the second booster pump is connected with a second externally-hung oil tank. The functions of pressure refueling, fuel oil transferring and external fuel tank fuel transferring are realized through control logic.
A helicopter fuel pipeline integrated system working mode is as follows:
1) Controlling the first control valve, the third control valve and the fifth control valve to be communicated; the second, fourth, sixth and seventh control valves are closed and the first and second fuel tanks are filled simultaneously by pressurized filler caps, as shown in fig. 2;
controlling the first control valve and the third control valve to be communicated; the second control valve, the fourth control valve, the fifth control valve, the sixth control valve and the seventh control valve are closed, and the first fuel tank is refueled through the pressure filler cap, as shown in fig. 3;
controlling the fifth control valve to be communicated; the first control valve, the second control valve, the third control valve, the fourth control valve, the sixth control valve and the seventh control valve are closed and the second fuel tank is refueled by the pressure fuel cap as shown in fig. 4.
2) Controlling the first control valve, the second control valve, the fourth control valve and the fifth control valve to be communicated; the third control valve, the sixth control valve and the seventh control valve are closed; transferring the fuel oil of the first fuel oil tank to a second fuel oil tank through a transfer pump; or the fuel in the second fuel tank is transferred to the first fuel tank by reversing the transfer pump, as shown in fig. 5.
3) Controlling the first control valve, the third control valve, the fifth control valve and the sixth control valve to be communicated; the second control valve, the fourth control valve and the seventh control valve are closed, and the first booster pump is opened to transfer the fuel in the first external fuel tank to the first fuel tank and the second fuel tank, as shown in FIG. 6;
controlling the first control valve, the third control valve, the fifth control valve and the seventh control valve to be communicated; the second control valve, the fourth control valve and the sixth control valve are closed and the second booster pump is opened to transfer the fuel in the second external tank to the first fuel tank and the second fuel tank, as shown in fig. 7.
4) Controlling the first control valve and the sixth control valve to be communicated; the second control valve, the third control valve, the fourth control valve, the fifth control valve and the seventh control valve are closed, and the first booster pump is opened to transfer the fuel in the first external fuel tank to the first fuel tank, as shown in fig. 8;
controlling the third control valve, the fifth control valve and the sixth control valve to be communicated; the first control valve, the second control valve, the fourth control valve, and the seventh control valve are closed, and the first boost pump is opened to transfer the fuel in the first external fuel tank to the second fuel tank, as shown in fig. 9.
5) Controlling the first control valve, the third control valve and the seventh control valve to be communicated; the second control valve, the fourth control valve, the fifth control valve and the sixth control valve are closed, and the second booster pump is opened to transfer the fuel in the second outer fuel tank to the first fuel tank, as shown in fig. 10;
controlling the fifth control valve and the seventh control valve to be communicated; the first control valve, the second control valve, the third control valve, the fourth control valve and the sixth control valve are closed, and the second booster pump is opened to transfer the fuel in the second outer hanger tank to the second fuel tank, as shown in fig. 11.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. A helicopter fuel pipeline integrated system which characterized in that: the system comprises: the system comprises a first fuel tank, a second fuel tank, a first pressure refueling control valve, a second pressure refueling control valve, a first control valve, a second control valve, a third control valve, a fourth control valve, a fifth control valve and a transfer pump;
one end of the first pressure refueling control valve is connected with the first fuel tank, and the other end of the first pressure refueling control valve is connected with the first control valve through a pipeline; the other end of the first control valve is connected with one end of a third control valve through a pipeline, the other end of the third control valve is connected with one end of a fifth control valve through a pipeline, the other end of the fifth control valve is connected with one end of a second pressure oiling control valve through a pipeline, and the second pressure oiling control valve is connected with a second fuel tank;
one end of the second control valve is connected to a pipeline between the first control valve and the third control valve through a first three-way joint,
one end of the fourth control valve is connected to a pipeline between the third control valve and the fifth control valve through a second three-way joint,
the transfer pump is connected between the second control valve and the fourth control valve.
2. A helicopter fuel line integration system according to claim 1, further comprising: the system further comprises: the pressure filler cap is connected to a pipeline between the second three-way joint and the fifth control valve and used for pressure filling of the first fuel tank and the second fuel tank.
3. A helicopter fuel line integration system according to claim 2, wherein: the system further comprises: the sixth control valve, the first one-way valve, the first booster pump and the first externally hung oil tank;
one end of the sixth control valve is connected to a pipeline between the first control valve and the first three-way joint through a pipeline; the other end of the first booster pump is connected with one end of the first booster pump through a one-way valve, and the other end of the first booster pump is connected with a first externally hung oil tank.
4. A helicopter fuel line integration system according to claim 3, wherein: the system further comprises: the seventh control valve, the second one-way valve, the second booster pump and the second externally-hung oil tank;
one end of the seventh control valve is connected to a pipeline between the fifth control valve and the second three-way joint through a pipeline; the other end of the second booster pump is connected with one end of a second booster pump through a one-way valve, and the other end of the second booster pump is connected with a second externally-hung oil tank.
5. A helicopter fuel line integration system according to claim 4, wherein: controlling the first control valve, the third control valve and the fifth control valve to be communicated; closing the second control valve, the fourth control valve, the sixth control valve and the seventh control valve, and simultaneously filling the first fuel tank and the second fuel tank with fuel through the pressure filler cap;
controlling the first control valve and the third control valve to be communicated; closing the second control valve, the fourth control valve, the fifth control valve, the sixth control valve and the seventh control valve, and filling the first fuel tank with oil through a pressure oil filler cap;
controlling the fifth control valve to be communicated; and closing the first control valve, the second control valve, the third control valve, the fourth control valve, the sixth control valve and the seventh control valve, and filling the second fuel tank with oil through the pressure oil filling cover.
6. A helicopter fuel line integration system according to claim 4, wherein: controlling the first control valve, the second control valve, the fourth control valve and the fifth control valve to be communicated; the third control valve, the sixth control valve and the seventh control valve are closed; transferring the fuel oil of the first fuel oil tank to a second fuel oil tank through a transfer pump; or the fuel in the second fuel tank is transferred to the first fuel tank through the reverse rotation of the transfer pump.
7. A helicopter fuel line integration system according to claim 4, wherein:
controlling the first control valve, the third control valve, the fifth control valve and the sixth control valve to be communicated; the second control valve, the fourth control valve and the seventh control valve are closed, and the first booster pump is opened to transfer the fuel oil in the first external fuel tank to the first fuel tank and the second fuel tank;
controlling the first control valve, the third control valve, the fifth control valve and the seventh control valve to be communicated; and the second control valve, the fourth control valve and the sixth control valve are closed, and the second booster pump is opened to transfer the fuel in the second outer hanging fuel tank to the first fuel tank and the second fuel tank.
8. A helicopter fuel line integration system according to claim 4, wherein:
controlling the first control valve and the sixth control valve to be communicated; the second control valve, the third control valve, the fourth control valve, the fifth control valve and the seventh control valve are closed, and the first booster pump is opened to transfer the fuel oil in the first external fuel tank to the first fuel tank;
controlling the third control valve, the fifth control valve and the sixth control valve to be communicated; and the first control valve, the second control valve, the fourth control valve and the seventh control valve are closed, and the first booster pump is opened to transfer the fuel oil in the first external fuel tank to the second fuel tank.
9. A helicopter fuel line integration system according to claim 4, wherein:
controlling the first control valve, the third control valve and the seventh control valve to be communicated; the second control valve, the fourth control valve, the fifth control valve and the sixth control valve are closed, and a second booster pump is opened to transfer the fuel in the second external fuel tank to the first fuel tank;
controlling the fifth control valve and the seventh control valve to be communicated; and the first control valve, the second control valve, the third control valve, the fourth control valve and the sixth control valve are closed, and the second booster pump is opened to transfer the fuel oil in the second external fuel tank to the second fuel tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011028734.2A CN112173139B (en) | 2020-09-25 | 2020-09-25 | Helicopter fuel pipeline integrated system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011028734.2A CN112173139B (en) | 2020-09-25 | 2020-09-25 | Helicopter fuel pipeline integrated system |
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| Publication Number | Publication Date |
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| CN112173139A CN112173139A (en) | 2021-01-05 |
| CN112173139B true CN112173139B (en) | 2022-11-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011028734.2A Active CN112173139B (en) | 2020-09-25 | 2020-09-25 | Helicopter fuel pipeline integrated system |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1153040A (en) * | 1966-06-14 | 1969-05-21 | United Aircraft Corp | Improvements in and relating to an Auxillary Fuel System Especially for Aircraft |
| GB1193008A (en) * | 1967-04-03 | 1970-05-28 | United Aircraft Corp | In-Flight Pressure Refueling Probe |
| US4591115A (en) * | 1984-10-18 | 1986-05-27 | The United States Of America As Represented By The Secretary Of The Navy | Automatic/manual fuel tank supply balance system |
| SU642925A1 (en) * | 1977-08-09 | 1986-10-07 | Предприятие П/Я В-2323 | Helicopter fuel system |
| US4932609A (en) * | 1989-02-27 | 1990-06-12 | United Technologies Corporation | Fuel transfer system for aircraft |
| RU2021168C1 (en) * | 1992-04-10 | 1994-10-15 | Товарищество с ограниченной ответственностью "Аэротон" | Method of use of fuel from tank and fuel system of aircraft |
| RU4733U1 (en) * | 1996-03-29 | 1997-08-16 | Акционерное общество открытого типа "Московский вертолетный завод им.М.Л.Миля" | FUEL HELICOPTER SYSTEM |
| CN106697308A (en) * | 2016-12-15 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Fuel oil transferring method for large airplane |
-
2020
- 2020-09-25 CN CN202011028734.2A patent/CN112173139B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1153040A (en) * | 1966-06-14 | 1969-05-21 | United Aircraft Corp | Improvements in and relating to an Auxillary Fuel System Especially for Aircraft |
| GB1193008A (en) * | 1967-04-03 | 1970-05-28 | United Aircraft Corp | In-Flight Pressure Refueling Probe |
| SU642925A1 (en) * | 1977-08-09 | 1986-10-07 | Предприятие П/Я В-2323 | Helicopter fuel system |
| US4591115A (en) * | 1984-10-18 | 1986-05-27 | The United States Of America As Represented By The Secretary Of The Navy | Automatic/manual fuel tank supply balance system |
| US4932609A (en) * | 1989-02-27 | 1990-06-12 | United Technologies Corporation | Fuel transfer system for aircraft |
| RU2021168C1 (en) * | 1992-04-10 | 1994-10-15 | Товарищество с ограниченной ответственностью "Аэротон" | Method of use of fuel from tank and fuel system of aircraft |
| RU4733U1 (en) * | 1996-03-29 | 1997-08-16 | Акционерное общество открытого типа "Московский вертолетный завод им.М.Л.Миля" | FUEL HELICOPTER SYSTEM |
| CN106697308A (en) * | 2016-12-15 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Fuel oil transferring method for large airplane |
Non-Patent Citations (1)
| Title |
|---|
| 燃油系统气塞导致发动机空中停车的一起典型故障分析;刘龙魁;《工艺设计改造及检测检修》;20140531(第10期);第126页 * |
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| CN112173139A (en) | 2021-01-05 |
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