CN110887623B - Fuel leakage detection system and method for civil aviation passenger plane - Google Patents
Fuel leakage detection system and method for civil aviation passenger plane Download PDFInfo
- Publication number
- CN110887623B CN110887623B CN201911192135.1A CN201911192135A CN110887623B CN 110887623 B CN110887623 B CN 110887623B CN 201911192135 A CN201911192135 A CN 201911192135A CN 110887623 B CN110887623 B CN 110887623B
- Authority
- CN
- China
- Prior art keywords
- fuel
- oil tank
- wing
- tank
- branch pipeline
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
- G01M3/32—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors for containers, e.g. radiators
- G01M3/3236—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors for containers, e.g. radiators by monitoring the interior space of the containers
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The invention discloses a fuel leakage detection system for a civil aircraft, which relates to the technical field of aircraft fuel detection and comprises a nitrogen generator, an air duct, a main electric valve, a slave electric valve, a position sensor, an oil full annunciator, a one-way valve, a pressure sensor, a safety valve and a manual valve. The invention also discloses a fuel leakage detection method for the civil aircraft. The invention also discloses a detection method, when the remote interface unit of the airborne fuel system detects that the wheel-mounted signal is effective, all fuel valves are closed, the fuel booster pump does not work, the fuel tank is not in the maximum full fuel state, the engine does not work, the APU does not work, and the slave electric valve in the ventilation fuel tank is closed, nitrogen is filled into the outboard fuel tank and the inboard fuel tank of the wing, so that the outboard fuel tank and the inboard fuel tank of the wing are pressurized, the timing change rate of the pressure is measured, and the fuel leakage conditions of the outboard fuel tank and the inboard fuel tank of the wing are obtained. The invention does not need to empty the oil tank, and reduces the manpower required by the detection of the leakage condition of the oil tank.
Description
Technical Field
The invention relates to the technical field of aircraft fuel detection, in particular to a fuel leakage detection system and a fuel leakage detection method for a civil aircraft.
Background
The leakage of the fuel tank of the civil aircraft is caused by various reasons, such as excessive fuel tank structure deformation, sealant cracking, sealant aging, accidental damage, incorrect rivet riveting and the like. Fuel leaking from the fuel tank can be ignited by different sources of fire with catastrophic consequences to the flight, and it is therefore important to find any form of fuel leakage before the aircraft takes off.
Among the aviation accidents that have been recorded, there are several accidents caused by fuel leakage from fuel tanks, and even the latest aircraft boeing 787 has ever suffered from fuel leakage accidents. Not only does a fuel leakage incident cause an emergency landing of the aircraft, but even multiple occurrences of events that cause fire and catastrophic consequences when fuel leaks onto the surfaces of engines, APUs, brakes, etc., until now, no on-board system has been able to detect fuel leakage in the fuel tank. Some aircraft provide for indirect determination of fuel leakage by observing engine or fuel spray, gross fuel reduction anomalies, or fuel imbalances. This method is however greatly limited because many factors can cause fuel imbalance between the two tanks: sensor harness defects, fuel contamination, fuel booster pump check valve leaks, fuel booster pump unbalanced fuel flow, transfer valve or inlet valve opening anomalies, fuel delivery pipe breaks, and the like.
Several methods are commonly used to perform fuel tank leak tests during aircraft maintenance checks. One common method is to completely empty the tank, then manually apply a special material to the inside surface of the tank, and then apply compressed air to the suspected leak outside the tank. This method has the disadvantage of requiring maintenance personnel to enter the tank, increasing the risk of explosion of the tank if safety precautions are not strictly followed. To enter the tank before using compressed air in the suspect area, the tank must be completely dry and must therefore be purged with dry air for at least 16 hours, while to avoid electrostatic sparks, all tools must be charged electrostatically, personnel need to wear safety shoes, etc. However, if the leak location is unknown, this process can be very time consuming. In some cases, personnel cannot enter the fuel tank interior, such as a fuel center of gravity adjustment fuel tank interior of an aircraft butt.
Other leak detection methods seal the fuel vent by venting the aircraft tank and installing an exhaust valve to the fuel vent, and then use a pressure gauge to generate a negative pressure no greater than a certain pressure. The location of the leak is determined by creating a negative pressure in the tank through the dummy door and then applying a dye to the outer surface of the tank. A disadvantage of this method is that it requires personnel to enter the tank and is time consuming. Special equipment and qualified personnel are also required to perform leak testing.
Disclosure of Invention
Aiming at the prior art, the invention provides a fuel leakage detection system and a fuel leakage detection method for a civil aviation airliner, which can quickly detect the leakage condition of a fuel tank before the take-off of the airplane, and send the leakage condition of the fuel tank to a management computer, so that the fuel tank does not need to be emptied, the manpower required by the detection of the leakage condition of the fuel tank is reduced, and the efficiency is improved.
The invention also discloses a fuel leakage detection method for the civil aviation passenger plane, which is characterized in that when the plane is in a ground shutdown state, the fuel tank on the outer side of the wing and the fuel tank on the inner side of the wing are pressurized by nitrogen, and the pressure change in a period of time is measured, so that whether the fuel tank on the outer side of the wing and the fuel tank on the inner side of the wing leak or not can be detected.
The invention is realized by the following technical scheme: the fuel leakage detection system for the civil aircraft comprises a nitrogen generator, an air duct connected with each fuel tank of the aircraft, a plurality of sensors arranged in each fuel tank of the aircraft and a plurality of main electric valves; the aircraft oil tank comprises a ventilation oil tank, an outboard oil tank and an inboard oil tank;
a nitrogen generator: externally connecting air, separating nitrogen from the air, and outputting the nitrogen to each oil tank of the airplane;
an air duct: the nitrogen generator comprises a main pipeline, a first branch pipeline and a second branch pipeline, wherein the first branch pipeline and the second branch pipeline are communicated with the main pipeline; the first branch pipeline is sequentially communicated with an oil tank on the outer side of the wing and a ventilation oil tank; the second branch pipeline is sequentially communicated with an oil tank on the inner side of the wing and a ventilation oil tank; filling nitrogen output by the nitrogen generator into each oil tank of the airplane for pressurizing each oil tank of the airplane;
a sensor: the device is arranged in each oil tank of the airplane and used for detecting the air pressure of each oil tank of the airplane and whether the oil tank of the airplane is in a full oil state;
a main electric valve: the main electric valves positioned on the first branch pipeline and the second branch pipeline are positioned between the main pipeline and an oil tank on the outer side of the wing and an oil tank on the inner side of the wing;
each sensor and the main electric valve are externally connected with an onboard fuel system remote interface unit; the airborne fuel remote interface unit receives detection data of each sensor, detects the opening and closing state of a main electric valve, the opening and closing state of a fuel valve of an airplane, the opening and closing state of a fuel booster pump and the working states of an engine and an APU (auxiliary Power Unit); and the remote interface unit of the airborne fuel system sends the detection result to an alarm computer and an airplane comprehensive display.
Further, the sensor comprises a pressure sensor and an oil full annunciator; each oil tank of the airplane is provided with a pressure sensor, and the oil tanks on the outer sides of the wings and the oil tanks on the inner sides of the wings are provided with full oil annunciators; the pressure sensor and the full oil annunciator are respectively electrically connected with the remote interface unit of the airborne fuel system. The pressure sensor is used for detecting the air pressure in each oil tank of the airplane; the full oil annunciator is used for detecting whether the oil tank on the outer side of the wing and the oil tank on the inner side of the wing are in the maximum full oil state or not.
Furthermore, the parts of the first branch pipeline and the second branch pipeline distributed in the ventilation oil tank are respectively provided with at least one slave electric valve, and the slave electric valves are distributed at different positions of the ventilation oil tank and are used for respectively controlling the communication between the first branch pipeline and the second branch pipeline and the oil tank on the outer side of the wing and the oil tank on the inner side of the wing.
Furthermore, each slave electric valve and each master electric valve are also correspondingly provided with a position sensor; for detecting the position of each slave and master electric valve; the slave electric valve, the master electric valve and the position sensor are electrically connected with the remote interface unit of the airborne fuel system.
Furthermore, the first branch pipeline and the second branch pipeline are respectively provided with a one-way valve, and the one-way valves are respectively positioned between the main electric valve and the oil tank on the outer side of the wing and between the main electric valve and the oil tank on the inner side of the wing.
Furthermore, the first branch pipeline and the second branch pipeline are respectively provided with a manual valve at the part distributed in the ventilation oil tank, so that after the slave electric valve is damaged and fails, the communication between the first wing outer side oil tank, the wing inner side oil tank and the ventilation oil tank can be controlled through the manual valves.
Furthermore, safety valves are respectively arranged on the first branch pipeline and the second branch pipeline and are electrically connected with the remote interface unit of the onboard fuel system.
The invention also discloses a fuel leakage detection method of the civil aviation passenger plane, and by adopting the fuel leakage detection system of the civil aviation passenger plane, when the remote interface unit of the onboard fuel system detects that the wheel-load signal is effective, all fuel valves are closed, the fuel booster pump does not work, the fuel tank is not in the maximum full fuel state, the engine does not work, the APU does not work, and the slave electric valve in the ventilation fuel tank is closed, nitrogen is filled into the fuel tank at the outer side of the wing and the fuel tank at the inner side of the wing, so that the fuel tank at the outer side of the wing and the fuel tank at the inner side of the wing are boosted, and the timing change rate of pressure is measured, and the fuel leakage conditions of the fuel tank at the outer side of the wing and the fuel tank at the inner side of the wing are obtained.
Furthermore, a manual valve is also arranged on the first branch pipeline and the second branch pipeline which are distributed in the ventilation oil tank; when the remote interface unit of the airborne fuel system detects that the slave electric valve in the ventilation oil tank is invalid and is in a closed state, the manual valves on the first branch pipeline and the second branch pipeline are opened, and the airplane is guaranteed to be signed and dispatched in time.
Further, the air pressure in the oil tank on the outer side of the wing and the oil tank on the inner side of the wing is too high, and the safety valve is opened; after the remote interface unit of the onboard fuel system detects that the safety valve is opened, the main electric valve is closed; stopping inflating and pressurizing the oil tank on the outer side of the wing and the oil tank on the inner side of the wing; the failure of the detection system is avoided, and the aircraft fuel tank is over-pressurized, so that the wing structure is damaged.
Compared with the prior art, the invention has the following advantages and beneficial effects:
(1) the fuel leakage detection system of the civil aviation airliner, provided by the invention, replaces a fuel vent in a ventilation oil tank by a manual valve, a slave electric valve and a safety valve, a position sensor feeds back the opening position information of the master electric valve and the slave electric valve, and a pressure sensor monitors the air pressure of the ventilation oil tank; a pressure sensor and a full oil annunciator in an oil tank on the outer side of the wing or in the oil tank on the inner side of the wing respectively monitor an air pressure signal and a full oil level signal in the oil tank; the nitrogen generated by the nitrogen generating device passes through the first main electric valve, then outputs nitrogen with certain air pressure, and then passes through the first electric valve and the second main electric valve outside the oil tank and is output to a designated oil tank; under the condition that the ground is in a stop state and the oil tank is not full of oil, the oil tank is pressurized by nitrogen, the pressure change rate in a period of pressure is measured, whether the oil tank leaks or not can be independently or simultaneously detected, and the leakage state of the oil tank is sent to an alarm computer and an airplane comprehensive display.
(2) The fuel leakage detection method for the civil aviation passenger plane can quickly detect any fuel tank leakage before the plane takes off, and sends the fuel tank leakage state to the alarm computer and the plane comprehensive display, so that only low manpower is needed, and professional and complex operations for emptying the fuel tank are avoided.
(3) The fuel oil leakage detection system and the detection method thereof for the civil aircraft enable the civil aircraft to independently detect whether the fuel oil tank leaks or not under the condition that the ground is stopped and the fuel oil tank on the inner side of the wing or the fuel oil tank on the outer side of the wing is not full of fuel, and the leakage detection time of a single fuel oil tank is not more than 5 min; and in addition, the invention has the function of measuring the air pressure of the oil tank on the inner side of the wing, the oil tank on the outer side of the wing and the air tank.
(4) The fuel oil leakage detection system and the fuel oil leakage detection method for the civil aviation airliner, provided by the invention, can be used for quickly judging whether the aircraft fuel tank leaks or not in an airport terminal building, so that the leakage elimination time and manpower are reduced, and the safety of the aircraft and the safety of the working environment of maintenance personnel can be improved.
Drawings
FIG. 1 is a schematic structural view of the present invention;
wherein: 100-ventilating oil tank, 200-outboard oil tank, 300-inboard oil tank, 400-onboard fuel system remote interface unit, 1-nitrogen generator, 21-main pipeline, 22-first branch pipeline, 23-second branch pipeline, 3-main electric valve, 4-pressure sensor, 5-full oil annunciator, 6-slave electric valve, 7-position sensor, 8-one-way valve, 9-manual valve and 10-safety valve.
Detailed Description
The present invention will be described in further detail with reference to examples, but the embodiments of the present invention are not limited thereto.
The on-board fuel system remote interface unit 400 in the present invention adopts the on-board fuel system remote interface unit 400 disclosed in patent CN 105329450 a. The airplane fuel tank comprises an outboard fuel tank 200, an inboard fuel tank 300 and a ventilation fuel tank 100; the nitrogen generator 1 is an air separation device communicated with air, separates nitrogen from the air, and fills the nitrogen into each oil tank of the airplane through an air duct.
As shown in figure 1, the fuel leakage detection system for the civil aircraft comprises a nitrogen generator 1, an air duct, a main electric valve 3, a slave electric valve 6, a position sensor 7, an oil full annunciator 5, a one-way valve 8, a pressure sensor 4, a safety valve 10 and a manual valve 9.
The main electric valve 3 comprises a first main electric valve, a second main electric valve and a third main electric valve; the slave electric valve 6 includes a first slave electric valve, a second slave electric valve, a third slave electric valve and a fourth slave electric valve; the position sensor 7 comprises a first position sensor, a second position sensor, a third position sensor, a fourth position sensor, a fifth position sensor, a sixth position sensor and a seventh position sensor; the full oil annunciator 5 comprises a first full oil annunciator and a second full oil annunciator; the check valve 8 comprises a first check valve and a second check valve; the pressure sensor 4 comprises a first pressure sensor, a second pressure sensor and a third pressure sensor; the safety valve 10 includes a first safety valve, a second safety valve; the manual valve 9 includes a first manual valve and a second manual valve.
An air duct: comprises a main pipeline 21, a first branch pipeline 22 and a second branch pipeline 23 which are communicated with the main pipeline 21, wherein the main pipeline 21 is communicated with the nitrogen generator 1; the first branch pipeline 22 is communicated with the wing outside oil tank 200 and the ventilating oil tank 100 in sequence; the second branch pipe 23 is communicated with the wing inside fuel tank 300 and the ventilation fuel tank 100 in sequence.
The first main electric valve 3 is arranged on the main pipeline 21 and used for controlling the access of the main pipeline 21; a second main electric valve is mounted on the first branch duct 22 for controlling the passage of the first branch duct 22; the third electric valve is arranged on the second branch pipe 23 and is used for controlling the passage of the second branch pipe 23; the first to fourth slave electric valves are installed in the ventilation tank 100 and control the ports of the first branch pipe 22 and the second branch pipe 23 arranged in the ventilation tank 100; the first position sensor to the third position sensor are respectively electrically connected with the first main electric valve to the third main electric valve and are used for sending position information of the first main electric valve, the second main electric valve and the third main electric valve to the remote interface unit 400 of the onboard fuel system; the fourth to seventh position sensors are electrically connected with the first to fourth slave electric valves respectively and are used for sending position information of the first to fourth slave electric valves to the onboard fuel system remote interface unit 400; the first full oil annunciator is arranged in the outboard oil tank 200 and used for detecting whether the oil amount in the outboard oil tank 200 reaches the maximum full oil amount state; the second full oil annunciator is arranged in the wing inner side oil tank 300 and used for detecting whether the oil amount in the wing inner side oil tank 300 reaches the maximum full oil amount state; the first pressure sensor to the third pressure sensor are respectively arranged in the wing outer side oil tank 200, the wing inner side oil tank 300 and the ventilation oil tank 100 and are used for detecting the air pressure of the wing outer side oil tank 200, the wing inner side oil tank 300 and the ventilation oil tank 100; the first manual valve is arranged on the first branch pipeline 22, the second manual valve is arranged on the second branch pipeline 23, and the first manual valve and the second manual valve are both positioned in the ventilation oil tank 100; the first safety valve is arranged on the first branch pipeline 22 and is communicated with air when opened; the second safety valve is mounted on the second branch duct 23 and communicates with the air when opened.
The main electric valve 3, the slave electric valve 6, the position sensor 7, the full oil annunciator 5, the pressure sensor 4 and the safety valve 10 are all electrically connected with the onboard fuel system remote interface unit 400.
During detection, when the onboard fuel system remote interface unit 400 detects that a wheel-mounted signal of the airplane is valid, all fuel valves are closed, a fuel booster pump does not work, a fuel tank is not in a maximum full-oil state, an engine does not work, an APU does not work, and a slave electric valve 6 in the ventilation fuel tank 100 is closed, the nitrogen generator 1 and the master electric valve 3 are started, nitrogen is filled into the outboard fuel tank 200 and the inboard fuel tank 300 of the wing through a ventilation pipeline, so that the outboard fuel tank 200 and the inboard fuel tank 300 of the wing are boosted, the pressure change rate in a period of time is measured, whether the outboard fuel tank 200 and the inboard fuel tank 300 of the wing leak or not can be obtained, and the fuel tank leakage state is sent to an alarm computer and the airplane comprehensive display.
Before the aircraft takes off, if the on-board fuel system remote interface unit 400 detects that the slave electric valve 6 in the ventilation tank 100 is out of order and in the closed position, the on-board fuel system remote interface unit 400 sends a warning signal to the cockpit through the ARINC 429 bus, and the ground crew can open the manual valve 9 in the ventilation tank 100 to ensure that the aircraft is signed in time.
If the detection system fails to work and causes overpressure in the fuel tank, in order to prevent the wing structure from being damaged, the safety valve 10 is opened to enable the wing outer side fuel tank 200 and the wing inner side fuel tank 300 to be communicated with the atmosphere, and after the remote interface unit 400 of the onboard fuel system detects that the opening state of the safety valve 10 is fed back, the first main electric valve is closed to stop introducing nitrogen, so that pressurization of the wing outer side fuel tank 200 and the wing inner side fuel tank 300 is stopped.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (2)
1. Civil aviation passenger plane fuel leakage detection system, its characterized in that: the device comprises a nitrogen generator, an air duct connected with each oil tank of the airplane, a plurality of sensors arranged in each oil tank of the airplane and a plurality of main electric valves;
the aircraft oil tank comprises a ventilation oil tank, an outboard oil tank and an inboard oil tank;
a nitrogen generator: externally connecting air and outputting nitrogen;
an air duct: the nitrogen generator comprises a main pipeline, a first branch pipeline and a second branch pipeline, wherein the first branch pipeline and the second branch pipeline are communicated with the main pipeline; the first branch pipeline is sequentially communicated with an oil tank on the outer side of the wing and a ventilation oil tank; the second branch pipeline is sequentially communicated with an oil tank on the inner side of the wing and a ventilation oil tank;
a sensor: the oil tanks are arranged in each oil tank of the airplane;
a main electric valve: the main electric valves positioned on the first branch pipeline and the second branch pipeline are positioned between the main pipeline and an oil tank on the outer side of the wing and an oil tank on the inner side of the wing;
each sensor and the main electric valve are externally connected with an onboard fuel system remote interface unit;
the sensor comprises a pressure sensor and an oil full annunciator; each oil tank of the airplane is provided with a pressure sensor, and the oil tanks on the outer sides of the wings and the oil tanks on the inner sides of the wings are provided with full oil annunciators; the pressure sensor and the full oil annunciator are respectively electrically connected with the remote interface unit of the airborne fuel system;
the parts of the first branch pipeline and the second branch pipeline, which are distributed in the ventilation oil tank, are respectively provided with at least one slave electric valve, and the slave electric valves are distributed at different positions of the ventilation oil tank;
each slave electric valve and each master electric valve are also correspondingly provided with a position sensor; the slave electric valve, the master electric valve and the position sensor are electrically connected with the remote interface unit of the airborne fuel system;
the first branch pipeline and the second branch pipeline are respectively provided with a one-way valve, and the one-way valves are respectively positioned between the main electric valve and the oil tank on the outer side of the wing and the oil tank on the inner side of the wing;
the parts of the first branch pipeline and the second branch pipeline distributed in the ventilation oil tank are respectively provided with a manual valve;
and the first branch pipeline and the second branch pipeline are respectively provided with a safety valve, and the safety valves are electrically connected with the remote interface unit of the onboard fuel system.
2. The fuel leakage detection method for the civil aircraft is characterized by comprising the following steps: by adopting the fuel leakage detection system of the civil aviation passenger plane as claimed in claim 1, when the onboard fuel system remote interface unit detects that the wheel-load signal is valid, all fuel valves are closed, the fuel booster pump does not work, the fuel tank is not in the maximum full-oil state, the engine does not work, the APU does not work, and the slave electric valve in the ventilation fuel tank is closed, nitrogen is filled into the wing outside fuel tank and the wing inside fuel tank, so that the wing outside fuel tank and the wing inside fuel tank are pressurized, and the timing change rate of the pressure is measured to obtain the fuel leakage conditions of the wing outside fuel tank and the wing inside fuel tank;
manual valves are also arranged on the first branch pipeline and the second branch pipeline which are distributed in the ventilation oil tank; when the remote interface unit of the onboard fuel system detects that the slave electric valve in the ventilation oil tank is failed and is in a closed state, the manual valves on the first branch pipeline and the second branch pipeline are opened;
the air pressure in the oil tank at the outer side of the wing and the oil tank at the inner side of the wing is too high, and the safety valve is opened; after the remote interface unit of the onboard fuel system detects that the safety valve is opened, the main electric valve is closed; and stopping inflating and pressurizing the oil tank on the outer side of the wing and the oil tank on the inner side of the wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911192135.1A CN110887623B (en) | 2019-11-28 | 2019-11-28 | Fuel leakage detection system and method for civil aviation passenger plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911192135.1A CN110887623B (en) | 2019-11-28 | 2019-11-28 | Fuel leakage detection system and method for civil aviation passenger plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110887623A CN110887623A (en) | 2020-03-17 |
| CN110887623B true CN110887623B (en) | 2021-09-10 |
Family
ID=69749284
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911192135.1A Active CN110887623B (en) | 2019-11-28 | 2019-11-28 | Fuel leakage detection system and method for civil aviation passenger plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110887623B (en) |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201417199Y (en) * | 2009-06-26 | 2010-03-03 | 博益(天津)气动技术研究所有限公司 | Leak detection device for aircraft oil tank |
| US9045237B2 (en) * | 2010-08-31 | 2015-06-02 | C. Kirk Nance | Automated inspection of aircraft landing gear internal fluid levels |
| GB2501733A (en) * | 2012-05-02 | 2013-11-06 | Eaton Aerospace Ltd | Aircraft fuel tank inerting system |
| CN105599908A (en) * | 2014-10-28 | 2016-05-25 | 中国航空工业集团公司西安飞机设计研究所 | Universal ventilation system for aircraft wing oil tanks |
| CN207257998U (en) * | 2017-10-17 | 2018-04-20 | 重庆通用航空产业集团有限公司 | UAV Fuel air-breather |
| CN208887871U (en) * | 2018-11-27 | 2019-05-21 | 中航通飞华南飞机工业有限公司 | A kind of aircraft system air tightness tester |
-
2019
- 2019-11-28 CN CN201911192135.1A patent/CN110887623B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110887623A (en) | 2020-03-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6823719B2 (en) | Method and apparatus to locally test pressure seal | |
| WO2017168199A1 (en) | System, apparatus, and method of preventing fuel tank explosion | |
| US8437889B2 (en) | Test equipment for testing an additional center tank (ACT) system of an aircraft | |
| US10041849B2 (en) | System for detecting a pressure difference between the interior and the exterior of an aircraft | |
| EP2947002B1 (en) | Drain mast seal having segregated chambers | |
| CN110887623B (en) | Fuel leakage detection system and method for civil aviation passenger plane | |
| CN101365625B (en) | Process and system for controlling the pressure in an aircraft cabin | |
| US5083451A (en) | Method and apparatus for monitoring aircraft fuselage deterioration | |
| CA2705384A1 (en) | Apparatus and method for pressurising an aircraft cabin structure and measuring the amount of leakage of the aircraft cabin structure | |
| KR102266496B1 (en) | Air flow control valve performance test simulation device | |
| CN103344499B (en) | Passenger plane fuselage pressure and tightness test equipment | |
| CN110160555B (en) | Aircraft differential pressure sensor detection device | |
| Behbahani-Pour et al. | Fuel leak detection on large transport airplanes | |
| CN105260529B (en) | The verification method of airplane brake system mean repair time | |
| WO2023050615A1 (en) | Venting device and venting control system for auxiliary tank of aircraft, and aircraft fuel supply system | |
| RU2318703C2 (en) | Method of and device for operation of aircraft equipment depending on its state | |
| CN109911238B (en) | Method for refueling seaplane | |
| CA2727184A1 (en) | Housing assembly for an electrical device | |
| US10843805B2 (en) | Systems to prevent inadvertent in-flight deployment of inflatable aircraft emergency evacuation slides | |
| CN101085645A (en) | Test device for testing additive center tank (ACT) of aircraft | |
| CN218646552U (en) | Slide rail sleeve limit air pressure testing device | |
| WO2017171688A1 (en) | Method of external suspension installation diagnostics and repair as required of for small loads | |
| Norwood et al. | Full scale aircraft drop test program for the F-35C carrier variant | |
| UA99607U (en) | A method for airworthiness and serviceability support of facilities of operated aircraft | |
| Massat | A310 hydraulic power system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |