CN112623239A - Air-isolated refueling system for air force military aircraft and use method - Google Patents
Air-isolated refueling system for air force military aircraft and use method Download PDFInfo
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- CN112623239A CN112623239A CN202011554018.8A CN202011554018A CN112623239A CN 112623239 A CN112623239 A CN 112623239A CN 202011554018 A CN202011554018 A CN 202011554018A CN 112623239 A CN112623239 A CN 112623239A
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000007789 sealing Methods 0.000 claims abstract description 36
- 239000000446 fuel Substances 0.000 claims description 15
- 230000005484 gravity Effects 0.000 claims description 5
- 230000007423 decrease Effects 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 11
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000003032 molecular docking Methods 0.000 abstract description 4
- 239000003921 oil Substances 0.000 description 112
- 210000001503 joint Anatomy 0.000 description 10
- 229910000831 Steel Inorganic materials 0.000 description 8
- 239000000295 fuel oil Substances 0.000 description 8
- 239000010959 steel Substances 0.000 description 8
- 239000002828 fuel tank Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 239000013013 elastic material Substances 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
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- 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
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- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
本发明公开了空军军用飞机隔空加油系统及使用方法，主要涉及军事技术领域；包括加油机、受油机，所述加油机的尾部设有弹射管，所述弹射管的外壁上设有调节油缸，所述弹射管用于存放球形油弹，所述弹射管远离加油机的一端设有弹性密封圈，所述弹射管远离弹性密封圈的一端设有密封盖，所述密封盖上设有加压气嘴；所述受油机上设有吸能减震受油舱，所述吸能减震受油舱的顶部设有可自动开关的受油舱盖；本发明采用隔空加油的方式，避免了对接要求高，容易失败，还容易损伤机体及触发事故的风险，会合加油的时间大大地缩短，多的油弹可放进机身内备用，不但可以减少受油机空中加油的次数而且还能飞更远的航程，制造成本相对较低，容易实施。
The invention discloses an air-to-air refueling system and a method for using the air force military aircraft, which mainly relate to the field of military technology. The oil cylinder, the ejection tube is used for storing spherical oil bombs, the end of the ejection tube away from the oil tanker is provided with an elastic sealing ring, the end of the ejection tube away from the elastic sealing ring is provided with a sealing cover, and the sealing cover is provided with a sealing cover. air compressor; the oil receiver is provided with an energy-absorbing and shock-absorbing oil-receiving tank, and the top of the energy-absorbing and shock-absorbing oil receiving tank is provided with an oil-receiving hatch cover that can be automatically opened and closed; It avoids the risk of high docking requirements, easy failure, and easy damage to the body and triggering accidents. The time for refueling at the rendezvous is greatly shortened, and more oil bombs can be put into the fuselage for backup, which can not only reduce the number of aerial refueling of the oil receiver but also It can also fly farther, the manufacturing cost is relatively low, and it is easy to implement.
Description
Technical Field
The invention relates to the technical field of military, in particular to an air-isolated refueling system for an air military aircraft and a using method thereof.
Background
The air refueling technology is a technology for replenishing fuel oil to other oil-receiving airplanes by a refueling machine in flight, so that the cruising ability of a military airplane can be obviously improved, the dependence of the military airplane on an airport is reduced, the dispatching space of the airport is increased, and the like. The air refueling technology has an extremely important supporting role for air force troops in battle in strategic or tactical aspects.
At present, the mature aerial refueling modes in the world mainly comprise two modes, wherein one mode is hose type aerial refueling equipment and is also called a hose-floating anchor type refueling system; another type is flying truss type telescopic truss type aerial refueling equipment, also called hard refueling equipment. The operation of modern airborne fueling techniques is a complex process, with the fueling sequence typically having four stages, convergence-docking-fueling-disengagement.
Although the last hundred years have passed since the advent of airborne fueling, the basic principles of airborne fueling have not changed, whether hose fueling or hard-hose fueling, which still requires equipment to connect the fuel tank and the fuel rail, and in practice, presents a number of problems, such as:
1) the air refueling needs a high flying technology and extremely delicate coordination, and during refueling, the refuelling machine and the refueling machine have no defense capability and are extremely easy to be stolen by enemy aircraft and need to be protected by other military aircrafts;
2) one hard tube type oiling machine can only refuel one military aircraft, and other aircraft can only wait, so that the refueling efficiency is low, and the time consumption is long;
3) the hose and other equipment of the oiling machine are also professional equipment, so that the maintenance cost is higher; in addition, the refueling hose is sensitive to atmospheric turbulence, so that the docking is difficult, and the technical requirement on a driver is high; secondly, the hose oil conveying speed is slow, about 1500 liters per minute, and the time for refueling a large airplane is long;
4) rigid connection is adopted in hard tube type oiling, no buffer exists when the hard tube type oiling machine is subjected to other forces, the hard tube type oiling machine can only be hard to touch, and as a result, the damage of a connection part is easy to cause;
5) the existing hard tube type air refueling is characterized in that two flying airplanes are connected through an oil delivery pipe for oil delivery, a rigid oil pipe is connected between the two moving airplanes, if the two flying airplanes are subjected to the acting force of air flow, the oil delivery pipe cannot be deformed, and only can be blown by wind, the high-altitude air flow is turbulent, the connection strength is greatly tested, and in addition, the two flying airplanes are in motion, and the relative speed of the two flying airplanes is difficult to control;
6) during docking, the hard tube type air refueling needs an operator on the refueling machine to operate a fine oil delivery pipe to extend to a small oil receiving hole above the oil receiving machine which is several meters away, which is undoubtedly a very challenging work and has the risks of docking failure, damage to the body and easy accident triggering.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provides an air-separating refueling system for military aircrafts and a using method thereof.
In order to achieve the purpose, the invention is realized by the following technical scheme:
the air force military aircraft air-to-air refueling system comprises a refueling machine and a refueling machine, wherein a catapult pipe is arranged at the tail of the refueling machine, one end of the catapult pipe is inserted into the refueling machine and is hinged with the refueling machine, an adjusting oil cylinder is arranged on the outer wall of the catapult pipe, one end of the adjusting oil cylinder is hinged with the refueling machine, the other end of the adjusting oil cylinder is hinged with the catapult pipe, the catapult pipe is used for storing spherical oil bullets, each spherical oil bullet comprises an elastic shell and aviation fuel oil stored in the elastic shell, an elastic sealing ring is arranged at one end of the catapult pipe, away from the refueling machine, the inner diameter of the elastic sealing ring is smaller than the outer diameter of the spherical;
the energy-absorbing shock-absorbing oil receiving tank is arranged on the oil receiving machine, an oil receiving tank cover capable of being automatically opened and closed is arranged at the top of the energy-absorbing shock-absorbing oil receiving tank, and an oil bomb pipeline is arranged at the bottom of the energy-absorbing shock-absorbing oil receiving tank.
Preferably, the ejection pipe is a telescopic pipe, the ejection pipe is composed of a plurality of telescopic joints, the outer diameters of the telescopic joints are gradually reduced from top to bottom, and the adjusting oil cylinder is hinged to the telescopic joint at the uppermost end.
Preferably, an electric winch is installed in the refueling machine, a winch steel wire is wound on the electric winch, and one end of the winch steel wire is connected with the bottom end of the lowest expansion joint.
Preferably, one end of the winch wire is connected with the bottom end of the lowest telescopic joint through a wire fixing pin.
Preferably, the number of the telescopic joints is three.
Preferably, one end of the sealing cover is hinged with the ejection tube, and the other end of the sealing cover is provided with a locking device.
Preferably, a valve is arranged on the elastic shell.
The use method of the air-spaced refueling system of the air military aircraft comprises the following steps:
s1, manufacturing a spherical oil bullet;
s2, loading the spherical oil bomb into an ejection tube;
s3, taking off the oiling machine and converging the oiling machine with the oil receiving machine;
s4, when the oiling machine and the oil receiver are kept relatively still, the oil-receiving cabin cover on the oil receiver is opened, and the direction of the ejection tube is adjusted, so that the ejection tube aims at a hatch of the energy-absorbing and shock-absorbing oil-receiving cabin;
s5, pressurizing the ejection tube from the top end of the ejection tube by using a pressurizing machine on the oiling machine until the spherical oil bomb can overcome the resistance of the elastic sealing ring, flying to the energy-absorbing shock-absorbing oil-receiving cabin in a spaced manner, and then falling into an oiling point along an oil bomb pipeline under the action of the self gravity of the spherical oil bomb to perform oiling;
and S6, after the oil receiving machine receives the oil, the oil receiving machine decelerates and rapidly separates from the oiling area to be separated from the oiling machine, and the oiling machine returns or refuels other oil receiving machines.
Compared with the prior art, the invention has the beneficial effects that:
1. the direct contact and the accurate butt joint of the oiling machine and the oil receiving machine are avoided, and the aerial fuel is transmitted between the oiling machine and the oil receiving machine in an air-isolated mode, so that the defects of hose type aerial refueling and hard pipe type aerial refueling are overcome, parts at the rigid connection part are not damaged due to the influence of speed difference or high-altitude airflow, the high butt joint requirement and the high possibility of failure are avoided, the machine body is easily damaged, and the risk of accidents is avoided.
2. The time for meeting and refueling of the refueling machine and the receiving machine is greatly shortened, the prior art transfers aviation fuel through the butt joint contact of the refueling oil pipe and the oil pipe of the two machines, the air-isolated refueling technology refuels the oil in the receiving machine after the two machines are separated, the time for meeting and refueling the two machines is shortened, and the probability that the two machines are easily attacked by enemy machines when meeting and refueling is reduced.
3. The aviation fuel oil of the prior refueling technology is transported in a liquid state for refueling, while the aviation fuel oil of the air-isolated refueling technology of the invention is ejected and transferred by an independently packaged solid spherical fuel oil bomb, when the fuel tank of the refueling machine is full, the aviation fuel oil in the liquid state cannot be added, the aviation fuel oil in the solid packaging state can be added, and the spherical fuel oil bombs can be put into the machine body for standby, so that the times of refueling in the air by the refueling machine can be reduced, and the aircraft can fly to a longer voyage.
4. Compared with the prior air refueling technology, the invention has no complex technology, relatively low manufacturing cost and easy implementation.
Drawings
FIG. 1 is a schematic structural view of the present invention;
figure 2 is a top view of the present invention.
The reference numbers in the drawings:
1. an oiling machine; 11. ejecting a tube; 12. adjusting the oil cylinder; 13. an elastic sealing ring; 14. a sealing cover; 15. a pressurizing air nozzle; 16. an electric capstan; 17. a winch wire; 18. a steel wire fixing pin;
2. an oil receiving machine; 21. an energy-absorbing and shock-absorbing oil receiving tank; 22. an oil-receiving hatch; 23. an oil bomb conduit;
3. spherical oil ball.
Detailed Description
The invention will be further illustrated with reference to the following specific examples. It should be understood that these examples are for illustrative purposes only and are not intended to limit the scope of the present invention. Further, it should be understood that various changes or modifications of the present invention may be made by those skilled in the art after reading the teaching of the present invention, and these equivalents also fall within the scope of the present application.
Example (b): as shown in the attached fig. 1-2, the invention relates to an air-spaced refueling system for military aircraft, which comprises a refueling machine 1 and a receiving machine 2,
the tail of the oiling machine 1 is provided with an ejection tube 11, one end of the ejection tube 11 is inserted into the oiling machine 1 and is hinged to the oiling machine 1, the outer wall of the ejection tube 11 is provided with an adjusting oil cylinder 12, one end of the adjusting oil cylinder 12 is hinged to the oiling machine 1, the other end of the adjusting oil cylinder is hinged to the ejection tube 11, the angle of the ejection tube 11 can be adjusted by the adjusting oil cylinder 12, and the ejection tube 11 can be retracted. The ejection tube 11 is used for storing the spherical oil bullet 3, the spherical oil bullet 3 includes elastic housing and the aviation fuel of depositing in the elastic housing, and is preferred, in order to facilitate the taking out of aviation fuel, be equipped with the valve on the elastic housing. An elastic sealing ring 13 is arranged at one end, far away from the oiling machine 1, of the ejection tube 11, the inner diameter of the elastic sealing ring 13 is smaller than the outer diameter of the spherical oil bomb 3, and the elastic sealing ring 13 is used for preventing the spherical oil bomb 3 from sliding out of the ejection tube 11 due to self gravity. One end of the ejection tube 11, which is far away from the elastic sealing ring 13, is provided with a sealing cover 14, the sealing cover 14 is provided with a pressurizing air nozzle 15, the ejection tube 11 is pressurized through the pressurizing air nozzle 15, the pressure at the top in the ejection tube 11 is improved, and when the spherical oil bomb 3 is pressurized to a state that the resistance of the elastic sealing ring 13 can be overcome (the inner ring of the elastic sealing ring 13 deforms and expands), the spherical oil bomb 3 is ejected from the ejection tube 11.
The energy-absorbing and shock-absorbing oil receiving tank 21 is arranged on the oil receiving machine 2, the energy-absorbing and shock-absorbing oil receiving tank 21 is used for receiving the spherical oil bullets 3 popped up by the ejection pipes 11 and can buffer the impact of the spherical oil bullets 3, an oil receiving tank cover 22 capable of being automatically opened and closed is arranged at the top of the energy-absorbing and shock-absorbing oil receiving tank 21, and an oil bullet pipeline 23 is arranged at the bottom of the energy-absorbing and shock-absorbing oil receiving tank 21.
Preferably, launch pipe 11 and be flexible pipe, launch pipe 11 and constitute by a plurality of telescopic joint, and a plurality of the external diameter top-down of telescopic joint reduces gradually, adjust the telescopic joint articulated of hydro-cylinder 12 and the top, can reduce the space of launching pipe 11 and occupy, the return journey of tanker aircraft 1 of being convenient for. Further, an electric winch 16 is installed in the fuel dispenser 1, a winch steel wire 17 is wound on the electric winch 16, one end of the winch steel wire 17 is connected with the bottom end of the lowest expansion joint, and the electric winch 16 controls the winch steel wire 17 to extend out or retract so as to control the expansion and contraction of the ejection pipe 11. Further, one end of the winch wire 17 is connected to the bottom end of the lowermost telescopic joint by a wire fixing pin 18. Furthermore, the number of the telescopic joints is three, and the telescopic joints are a first telescopic joint, a second telescopic joint and a third telescopic joint from top to bottom in sequence.
Preferably, in order to facilitate the opening and closing of the sealing cover, one end of the sealing cover 14 is hinged with the ejector tube 11, and the other end is provided with a locking device.
The working principle of the invention is that the oiling machine 1 and the oil receiving machine 2 keep the two airplanes flying at constant speed, same speed and same direction outside the safe distance by using an advanced flight control system, and a series of procedures of loading, converging, aiming, oiling, dispersing and the like are completed under the relative static condition to complete the oiling in the air.
A use method of an air-to-air refueling system of an air military aircraft comprises the following steps:
and S1, manufacturing the spherical oil bullet 3.
And S2, loading, specifically, after the fuel dispenser 1 receives an instruction that a military aircraft needs to carry out air refueling in the air, the fuel dispenser 1 enters a loading working procedure. In order to reduce the convergence time of the oiling machine 1 and the oil receiving machine 2, the oiling machine 1 needs to be provided with the spherical oil bombs 3 in advance, taking the number of the telescopic joints as three as an example, at this time, the adjusting oil cylinder 12 at the tail part of the body of the oiling machine 1 presses the first telescopic joint out of the body to be in a tail inclined state, then under the driving of the electric winch 16, the second telescopic joint and the third telescopic joint are pushed out outwards through a winch steel wire 17 fixed on a steel wire fixing pin 18, and when the second telescopic joint and the third telescopic joint are pushed to be in a completely extended state, the electric winch 16 stops working; and then the sealing cover 14 is opened in the body of the oiling machine 1 according to the direction of an arc arrow in the figure 1, the spherical oil bomb 3 is filled into the three-section expansion joint, the surface layer of the spherical oil bomb 3 is made of elastic materials with good air tightness, and the inside of the spherical oil bomb is filled with the aviation fuel. A plurality of spherical oil bullets 3 continue to freely roll towards the pipe orifice of the third telescopic joint under the action of self gravity, and when the spherical oil bullet 3 closest to the pipe orifice is blocked by the elastic sealing ring 13 at the pipe orifice and stops rolling, the diameter of the elastic sealing ring 13 is smaller than that of the spherical oil bullet 3, so that the spherical oil bullet 3 is blocked to fall out of the pipe orifice; when the first telescopic joint can not be refilled with the cartridge, the cartridge is full, the sealing cover 14 is covered, and the loading process is finished.
S3, convergence, specifically, the convergence mode of the air-isolated refueling is similar to that of the prior refueling technology, and the convergence of the two air-isolated refueling machines has four modes: the oil receiving machine 1 and the oil adding machine 2 meet at a certain position on the same route; secondly, convergence is performed at regular time, and the oiling machine 1 and the oil receiving machine 2 are required to determine oiling coordination requirements and specific convergence time and converge at a designated airspace on time; thirdly, the two airplanes fly together in front, namely the two airplanes fly together in front, then the oil receiver 1 makes a 180-degree turn according to the advancing direction of the oiling machine 2, the course is turned to the direction of the oiling machine, and the oiling is prepared at the position about 5 kilometers ahead; and fourthly, standby convergence, namely, the aerial early warning machine is in communication with the oiling machine 1 and the oil receiving machine 2, a course and speed instruction is sent to the oiling machine 1, the oil receiving machine 2 is guided to converge with the oiling machine 1 at the same time until a pilot of the oil receiving machine 2 can find the oiling machine 1 by radar or vision, and then the oil receiving machine 2 enters the oil receiving position again. No matter what convergence mode is adopted, the height of the oil receiving machine 2 is 60 meters lower than that of the oiling machine 1; when the oiling machine 1 and the oil receiving machine 2 keep the same direction, the same speed and the uniform speed, the two machines keep relatively static. At this time, the convergence procedure of the two machines is completed.
S4, aiming, specifically, when the oiling machine 1 and the oil receiving machine 2 are kept relatively still, the oil receiving cabin cover 22 in the middle of the two wings of the oil receiving machine 2 automatically opens backwards in the direction of an arrow in the figure 1 to expose a wide hatch of the energy-absorbing shock-absorbing oil receiving cabin 21, and meanwhile, the pipe orifice of the third expansion joint on the oiling machine 1 is quickly aligned to the hatch of the energy-absorbing shock-absorbing oil receiving cabin 21 under the regulation of the auxiliary and regulating oil cylinder 12 of the aiming control system, so that the aiming work procedures of the two machines are finished.
S5, oiling, specifically, after the aiming work procedure is finished, a pressurizer carried by the oiling machine 1 pressurizes the ejection tube 11 through a pressurizing air nozzle 15, when the pressure in the ejection tube 11 reaches a certain value, the spherical oil bomb 3 at the tube opening of the third section of telescopic joint flies to the cabin opening of the energy-absorbing shock-absorbing oil cabin 21 in the direction of an arrow in the figure 1 in the direction of the resistance of the elastic sealing ring 13 in the air separation direction, then the spherical oil bomb stops bouncing and does not move quickly, then the oil bomb rolls to the oiling point in the machine body along the oil bomb pipeline 23 under the action of self gravity to carry out manual or automatic oiling, meanwhile, after the oil bomb at the tube opening of the ejection tube 11 is ejected and flies out, the later oil bomb automatically rolls to the inner side of the ejection elastic sealing ring 13 to generate sealing automatically, and the air pressure in the ejection tube 11 is prevented from leaking. In addition, the fuel dispenser 1 can eject the amount of spherical fuel balls 3 required to be filled by the fuel receiver 2 according to the instruction of the fuel receiver 2. The spherical oil bomb 3 in the ejection tube 11 can be ejected by a single spherical oil bomb 3 or by a plurality of spherical oil bombs 3 continuously according to the requirement of the refueling amount, and the ejection speed is controlled by the pressure of the air pressure provided by the pressurizing air nozzle 15. After the oil receiving machine 2 adds the required number of the spherical oil bullets 3, the oil receiving hatch cover 22 is closed, and the outer skin of the spherical oil bullets 3 after the oil is added can be recycled, so that the oiling working procedures of the two machines are finished.
S6, resolving, specifically, after the oil receiving machine 2 receives the oil, the oil receiving machine 2 decelerates and rapidly separates from the oil filling area to be separated from the oil filling machine 1; at the moment, the oiling machine 1 can continue to carry out aerial oiling on the next military aircraft needing aerial oiling; if no oiling instruction is given, the oiling machine 1 performs pipe collecting work, at the moment, the sealing cover 14 is opened, the residual air pressure in the ejection pipe 11 is released, the electric winch 16 is started again, the third section of expansion joint and the second section of expansion joint are collected into the first section of expansion joint, the residual spherical oil is returned into the machine body, the three sections of expansion joints are collected into the machine body through the adjusting oil cylinder 12, and the task of performing air-separated oiling of the oiling machine 1 is finished.
Claims (8)
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011554018.8A CN112623239A (en) | 2020-12-24 | 2020-12-24 | Air-isolated refueling system for air force military aircraft and use method |
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| CN202011554018.8A CN112623239A (en) | 2020-12-24 | 2020-12-24 | Air-isolated refueling system for air force military aircraft and use method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114313281A (en) * | 2021-12-29 | 2022-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A method for determining the space interval constraints of oil plugs |
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| US20060000950A1 (en) * | 2004-06-18 | 2006-01-05 | The Boeing Company | In-flight refueling system and method for extending and retracting an in-flight refueling device |
| EP2535273A1 (en) * | 2011-06-17 | 2012-12-19 | EADS Construcciones Aeronauticas, S.A. | Aircraft refueling boom with a nozzle illuminating module |
| CN108290638A (en) * | 2015-11-30 | 2018-07-17 | 狄芬萨工程国际有限公司 | The system and oiling method of gradual automation air refuelling are carried out when for detecting oiling pipe end and vessel port, flight with winged purlin |
| CN111252263A (en) * | 2020-03-06 | 2020-06-09 | 杨剑 | Rotary catapult-assisted take-off platform of carrier-borne aircraft of aircraft carrier |
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2020
- 2020-12-24 CN CN202011554018.8A patent/CN112623239A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060000950A1 (en) * | 2004-06-18 | 2006-01-05 | The Boeing Company | In-flight refueling system and method for extending and retracting an in-flight refueling device |
| EP2535273A1 (en) * | 2011-06-17 | 2012-12-19 | EADS Construcciones Aeronauticas, S.A. | Aircraft refueling boom with a nozzle illuminating module |
| CN108290638A (en) * | 2015-11-30 | 2018-07-17 | 狄芬萨工程国际有限公司 | The system and oiling method of gradual automation air refuelling are carried out when for detecting oiling pipe end and vessel port, flight with winged purlin |
| CN111252263A (en) * | 2020-03-06 | 2020-06-09 | 杨剑 | Rotary catapult-assisted take-off platform of carrier-borne aircraft of aircraft carrier |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114313281A (en) * | 2021-12-29 | 2022-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A method for determining the space interval constraints of oil plugs |
| CN114313281B (en) * | 2021-12-29 | 2024-05-07 | 中国航空工业集团公司西安飞机设计研究所 | A method for determining the space interval constraint of oil receiving plug |
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Application publication date: 20210409 |