CN114379798B - Concealed aircraft oil receiving system - Google Patents
Concealed aircraft oil receiving system Download PDFInfo
- Publication number
- CN114379798B CN114379798B CN202011106820.0A CN202011106820A CN114379798B CN 114379798 B CN114379798 B CN 114379798B CN 202011106820 A CN202011106820 A CN 202011106820A CN 114379798 B CN114379798 B CN 114379798B
- Authority
- CN
- China
- Prior art keywords
- oil receiving
- oil
- control system
- rod
- limiting
- 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.)
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Links
- 239000000446 fuel Substances 0.000 claims description 33
- 239000000945 filler Substances 0.000 claims description 19
- 238000007789 sealing Methods 0.000 claims description 12
- 239000000463 material Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 claims 1
- 239000003921 oil Substances 0.000 description 129
- 238000010586 diagram Methods 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- 230000001174 ascending effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D39/00—Refuelling during flight
- B64D39/02—Means for paying-in or out hose
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The oil receiving system of the hidden aircraft comprises an oil tank, an oil receiving pipeline, a supporting structure, a driving device, a limiting device and a control system, wherein an oil filling port and an oil filling port cover are arranged on an aircraft body, the opening and closing of the oil filling port cover are controlled by the control system, the oil receiving system is positioned in the aircraft body, the rear end of the oil receiving pipeline is communicated with the oil tank, the front end of the oil receiving pipeline is connected with the supporting structure, and the front end of the oil receiving pipeline and the supporting structure can extend out or retract from the oil filling port of the aircraft body under the control of the driving device, the limiting device and the control system.
Description
Technical Field
The invention relates to the field of aircraft aerial refueling, in particular to a concealed oil receiving system of an aircraft.
Background
With the popularization of the fifth generation of stealth fighters worldwide, how to refuel stealth fighters becomes a major problem. At present, a non-invisible fighter adopts an external oiling pipe at the right side of a machine head to carry out aerial oil receiving, and the oiling machine adopts a hose oiling mode to provide oil. The oil receiving mode corresponding to the hose oil filling is an external oil receiving rod, but the oil filling mode of the external oil receiving rod is not suitable for the invisible fighter, the radar refraction area of the invisible fighter is damaged, the stealth performance and the aerodynamic performance of the aircraft are damaged, and great potential safety hazards are caused to the aircraft.
Disclosure of Invention
The invention aims to provide a hidden oil receiving system of an aircraft, which aims to solve the problem that a stealth fighter cannot use an external oil receiving rod to carry out air refueling.
The hidden aircraft oil receiving system comprises an oil tank, an oil receiving pipeline, a supporting structure, a driving device, a limiting device and a control system, and is characterized in that an oil filling port and an oil filler cap are arranged on an aircraft body, the opening and the closing of the oil filler cap are controlled by the control system, the oil receiving system is positioned in the aircraft body, the rear end of the oil receiving pipeline is communicated with the oil tank, the front end of the oil receiving pipeline is connected with the supporting structure, and the front end of the oil receiving pipeline and the supporting structure can extend or retract from the oil filling port of the aircraft body under the control of the driving device, the limiting device and the control system.
The oil receiving pipeline comprises a rigid oil receiving rod and a fuel oil hose, the rigid oil receiving rod is positioned at the front end of the fuel oil hose, the rear end of the fuel oil hose is connected with an oil tank, the supporting structure comprises a track and an oil receiving strut, the driving device comprises a first driver and a second driver, the limiting device comprises a limiting block and a limiting sensor, the oil receiving strut of the supporting structure can reciprocate along the track under the driving of the first driver, a first limiting block which reciprocates is arranged on the oil receiving strut, an uplink limiting sensor and a downlink limiting sensor which correspond to the limiting movement position of the first limiting block are arranged on the track, the oil receiving rod is embedded in the oil receiving strut, the oil receiving rod can reciprocate along the oil receiving strut under the driving of the second driver, and the uplink limiting sensor and the downlink limiting sensor which correspond to the limiting movement position of the second limiting block are further fixed on the movement track of the second limiting block.
The driving device also comprises a retraction wheel of the fuel hose, and the retraction wheel can release or tighten the length of the fuel hose under the control of the control system.
When oil is required to be received, the oil filler cap is opened through the control system, the control system controls the first driver to drive the oil receiving support rod to move upwards along the track and extend out of the oil filler, when the oil receiving support rod moves to a preset position, the first limiting block arranged on the oil receiving support rod triggers the corresponding uplink limiting sensor, and the control system receives signals of the limiting sensor and controls the first driver to keep the current situation of the oil receiving support rod; the control system controls the second driver to drive the oil receiving rod to extend out of the oil receiving support rod, and when the oil receiving rod moves to a preset position, a second limiting block arranged on the oil receiving rod triggers a corresponding limiting sensor, and the control system receives signals of the limiting sensor and controls the second driver to keep the current situation of the oil receiving rod; meanwhile, the control system controls the retraction wheel to release the length of the fuel hose, 2) after oil receiving is finished, the control system controls the first driver to drive the oil receiving support rod to move downwards along the track, the oil filling port is retracted into the aircraft body, when the oil receiving support rod moves downwards to a preset position, a first limiting block arranged on the oil receiving support rod triggers a corresponding downlink limiting sensor, and the control system receives a signal of the downlink limiting sensor and controls the first driver to stop working; the control system controls the second driver to drive the oil receiving rod to retract into the oil receiving support rod, and when the oil receiving rod moves to a preset position, the second limiting block arranged on the oil receiving rod triggers the corresponding downlink limiting sensor, and the control system receives the signal of the downlink limiting sensor and controls the second driver to stop working; and meanwhile, the control system controls the retraction wheel to tighten the length of the fuel hose.
The beneficial effects of this application lie in: according to the hidden oil receiving system of the aircraft, the oil receiving pipe extends out of the oil receiving port of the aircraft when receiving oil, and automatically retracts into the aircraft body after receiving oil, so that the problem that a hose air refueling mode is not suitable for an external oil receiving rod invisible fighter aircraft can not be installed is solved, and the stealth performance and the pneumatic performance of the oil receiving pipe are ensured.
The present application is described in further detail below with reference to the drawings of embodiments.
Drawings
Fig. 1 is a schematic structural diagram of a hidden aircraft oil receiving system in an oil-free state.
Fig. 2 is a schematic structural diagram of the oil receiving system of the hidden aircraft in an oil receiving state.
FIG. 3 is a schematic view of a seal cap.
Fig. 4 is a control logic block diagram of the control system.
The numbering in the figures illustrates: the oil filler cap 1, the hydraulic telescopic rod 2, the sealing hole cap 3, the track 4, the oil receiving strut 5, the oil receiving strut 6, the first driver 7, the second driver 8, the first limiting block 9, the second limiting block 10, the fuel hose 11, the retractable wheel 12, the fuel pump 13, the oil receiving strut ascending position sensor 14, the oil receiving strut ascending position sensor 15, the oil receiving strut descending position sensor 16, the oil receiving strut descending position sensor 17, the aircraft body 18, the oil tank 19 and the oil filler cap 20.
Detailed Description
Referring to the drawings, the hidden aircraft oil receiving system of the application comprises an oil tank 19, an oil receiving pipeline, a supporting structure, a driving device, a limiting device and a control system, wherein an oil filling port and an oil filler cap 1 are arranged on the skin of an aircraft body 18, the oil filler cap 1 is connected with the control system through a hydraulic telescopic rod 2, and the control system controls the opening or closing of the oil filler cap through the hydraulic telescopic rod 2. In practice, in order to ensure the sealing of the aircraft body, the oil filling port is positioned in a sealing cavity, a sealing hole cover 3 is arranged on the cavity wall of the sealing cavity, the sealing hole cover 3 is made of flexible materials, a rice-shaped opening is arranged on the sealing hole cover, and the front end of the oil receiving pipeline and the supporting structure can enter the sealing cavity through the sealing hole cover and extend out of or retract from the oil filling port of the aircraft body.
The oil receiving system is positioned in the aircraft body, the rear end of the oil receiving pipeline is communicated with the oil tank 19, the front end of the oil receiving pipeline is connected with the supporting structure, and the front end of the oil receiving pipeline and the supporting structure can extend or retract from the oil filling port of the aircraft body under the control of the driving device, the limiting device and the control system. The oil receiving pipeline comprises a rigid oil receiving rod 6 and a fuel hose 11, the rigid oil receiving rod 6 is positioned at the front end of the fuel hose 11, the rear end of the fuel hose 11 is connected with an oil tank 19, the supporting structure comprises a track 4 and an oil receiving strut 5, the driving device comprises a first driver 7 and a second driver 8, the limiting device comprises a first limiting block 9, a second limiting block 10, an oil receiving strut up limiting sensor 15 corresponding to the first limiting block 9, an oil receiving strut down limiting sensor 17, an oil receiving rod up limiting sensor 14 corresponding to the second limiting block 10 and an oil receiving rod up limiting sensor 16, the oil receiving strut 5 of the supporting structure can reciprocate along the track 4 under the driving of the first driver 7, the oil receiving strut up limiting sensor 15 and the oil receiving strut down limiting sensor 17 corresponding to the limit movement position of the first limiting block are arranged on the track 4, the oil receiving rod 6 can reciprocate along the track 10 in the second driving rod up limiting block 10 and the second limiting block 6, and the oil receiving strut 5 can reciprocate along the track 10 and the second limiting rod up limiting sensor 10 is arranged on the track 5.
The drive device further comprises a retraction wheel 12 for the fuel hose 11, the retraction wheel 12 being adapted to release or tighten the length of the fuel hose 11 under control of the control system. The driving device also comprises a fuel pump 13, and when the fuel is received, the control system drives the fuel pump 13 to receive the fuel of the fuel feeding machine through a fuel receiving pipeline and input the fuel into a fuel tank 19.
When oil is required to be received, the oil filler cap 1 is opened through the control system, the control system controls the first driver 7 to drive the oil receiving support rod 5 to move upwards along the track 4, the oil filler extends out of the aircraft body 18, when the oil receiving support rod 5 moves to a preset position, the first limiting block 9 arranged on the oil receiving support rod 5 triggers the corresponding oil receiving support rod uplink limiting sensor 15, and the control system receives signals of the limiting sensor and controls the first driver 7 to keep the current situation of the oil receiving support rod 5; the control system controls the second driver 8 to drive the oil receiving rod 6 to extend out of the oil receiving support rod 5, when the oil receiving rod 6 moves to a preset position, the second limiting block 10 arranged on the oil receiving rod 6 triggers the corresponding oil receiving rod uplink limiting sensor 14, and the control system receives the limiting sensor signal and controls the second driver 10 to keep the current state of the oil receiving rod 6; at the same time, the control system controls the retraction wheel 12 to release the length of the fuel hose 11, and at the moment, the front end of the fuel receiving rod 6 is positioned outside the aircraft body and can be butted with the fueling cover 20 of the fueling machine to carry out aerial fueling. After oil receiving is finished, the control system controls the first driver 7 to drive the oil receiving support rod 5 to move downwards along the track, the oil filling port is retracted into the aircraft body 18, when the oil receiving support rod 5 moves downwards to a preset position, the first limiting block 9 arranged on the oil receiving support rod 5 touches the corresponding oil receiving support rod downlink limiting sensor 17, and the control system receives signals of the downlink limiting sensor and controls the first driver 7 to stop working; the control system controls the second driver 8 to drive the oil receiving rod 6 to retract into the oil receiving support rod 5, when the oil receiving rod 6 moves to a preset position, the second limiting block 10 arranged on the oil receiving rod 6 triggers the corresponding oil receiving rod descending limiting sensor 16, and the control system receives the signal of the descending limiting sensor and controls the second driver 8 to stop working; and the control system controls the retraction wheel 12 to tighten the length of the fuel hose 11.
Claims (5)
1. A hidden aircraft oil receiving system comprises an oil tank, an oil receiving pipeline, a supporting structure, a driving device, a limiting device and a control system, and is characterized in that an oil filling port and an oil filler cap are arranged on an aircraft body, the opening and closing of the oil filler cap are controlled by the control system, the oil receiving system is positioned in the aircraft body, the rear end of the oil receiving pipeline is communicated with the oil tank, the front end of the oil receiving pipeline is connected with the supporting structure, the front end of the oil receiving pipeline and the supporting structure can extend out or retract from the oil filling port of the aircraft body under the control of the driving device, the limiting device and the control system, the oil receiving pipeline comprises a rigid oil receiving rod and a fuel hose, the rigid oil receiving rod is positioned at the front end of the fuel hose, the rear end of the fuel hose is connected with the oil tank, the supporting structure comprises a track and an oil receiving strut, the driving device comprises a first driver and a second driver, the limiting device comprises a limiting block and a limiting sensor, the oil receiving support rod of the supporting structure can reciprocate along the track under the driving of the first driver, the oil receiving support rod is provided with a first limiting block which reciprocates, the track is provided with an uplink limiting sensor and a downlink limiting sensor which correspond to the limit movement position of the first limiting block, the oil receiving rod is embedded in the oil receiving support rod, the oil receiving rod can reciprocate along the oil receiving support rod under the driving of the second driver, the oil receiving rod is provided with a second limiting block which reciprocates, and the uplink limiting sensor and the downlink limiting sensor which correspond to the limit movement position of the second limiting block are fixed on the movement track of the second limiting block.
2. The concealed aircraft oil system of claim 1 wherein the oil filler cap is connected to the control system by a hydraulic telescoping rod.
3. A concealed aircraft fuel system as claimed in claim 2 wherein the fuel filler is located in a sealed chamber and a sealing orifice cover is provided on the wall of the sealed chamber, the sealing orifice cover being of flexible material and having a chevron opening therein, the fuel filler pipe forward end and support structure being capable of entering the sealed chamber through the sealing orifice cover and extending or retracting from the fuel filler of the aircraft body.
4. A concealed aircraft fuel system as claimed in claim 1 wherein the drive means further comprises a fuel hose retraction wheel which is operable to release or retract the length of the fuel hose under control of the control system.
5. -a method of oil-receiving a concealed aircraft oil-receiving system according to any one of claims 1 to 4, characterized by comprising the following: 1) When oil is required to be received, the oil filler cap is opened through the control system, the control system controls the first driver to drive the oil receiving support rod to move upwards along the track and extend out of the oil filler, when the oil receiving support rod moves to a preset position, the first limiting block arranged on the oil receiving support rod triggers the corresponding uplink limiting sensor, and the control system receives signals of the limiting sensor and controls the first driver to keep the current situation of the oil receiving support rod; the control system controls the second driver to drive the oil receiving rod to extend out of the oil receiving support rod, and when the oil receiving rod moves to a preset position, a second limiting block arranged on the oil receiving rod triggers a corresponding limiting sensor, and the control system receives signals of the limiting sensor and controls the second driver to keep the current situation of the oil receiving rod; meanwhile, the control system controls the retraction wheel to release the length of the fuel hose, 2) after oil receiving is finished, the control system controls the first driver to drive the oil receiving support rod to move downwards along the track, the oil filling port is retracted into the aircraft body, when the oil receiving support rod moves downwards to a preset position, a first limiting block arranged on the oil receiving support rod triggers a corresponding downlink limiting sensor, and the control system receives a signal of the downlink limiting sensor and controls the first driver to stop working; the control system controls the second driver to drive the oil receiving rod to retract into the oil receiving support rod, and when the oil receiving rod moves to a preset position, the second limiting block arranged on the oil receiving rod triggers the corresponding downlink limiting sensor, and the control system receives the signal of the downlink limiting sensor and controls the second driver to stop working; and meanwhile, the control system controls the retraction wheel to tighten the length of the fuel hose.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011106820.0A CN114379798B (en) | 2020-10-16 | 2020-10-16 | Concealed aircraft oil receiving system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011106820.0A CN114379798B (en) | 2020-10-16 | 2020-10-16 | Concealed aircraft oil receiving system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114379798A CN114379798A (en) | 2022-04-22 |
| CN114379798B true CN114379798B (en) | 2024-04-09 |
Family
ID=81194041
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011106820.0A Active CN114379798B (en) | 2020-10-16 | 2020-10-16 | Concealed aircraft oil receiving system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114379798B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115675892B (en) * | 2022-12-29 | 2023-04-18 | 中国航空工业集团公司西安飞机设计研究所 | Air refueling hose connector device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6786455B1 (en) * | 2002-09-05 | 2004-09-07 | Asher Bartov | Method for engaging a probe and drogue for aerial refueling |
| CN101863308A (en) * | 2010-03-15 | 2010-10-20 | 王雪松 | Air-refueling device |
| CN207191386U (en) * | 2017-08-31 | 2018-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft is by oil probe hatch door |
| CN209581913U (en) * | 2018-12-11 | 2019-11-05 | 四川航空工业川西机器有限责任公司 | A kind of telescopic probe |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7185854B2 (en) * | 2004-06-18 | 2007-03-06 | The Boeing Company | In-flight refueling system and method for extending and retracting an in-flight refueling device |
| US9284061B2 (en) * | 2013-08-06 | 2016-03-15 | The Boeing Company | Multipurpose flying boom |
-
2020
- 2020-10-16 CN CN202011106820.0A patent/CN114379798B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6786455B1 (en) * | 2002-09-05 | 2004-09-07 | Asher Bartov | Method for engaging a probe and drogue for aerial refueling |
| CN101863308A (en) * | 2010-03-15 | 2010-10-20 | 王雪松 | Air-refueling device |
| CN207191386U (en) * | 2017-08-31 | 2018-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft is by oil probe hatch door |
| CN209581913U (en) * | 2018-12-11 | 2019-11-05 | 四川航空工业川西机器有限责任公司 | A kind of telescopic probe |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114379798A (en) | 2022-04-22 |
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