CN115416858A - Stability augmentation ring for taper sleeve for air refueling - Google Patents
Stability augmentation ring for taper sleeve for air refueling Download PDFInfo
- Publication number
- CN115416858A CN115416858A CN202211029614.3A CN202211029614A CN115416858A CN 115416858 A CN115416858 A CN 115416858A CN 202211029614 A CN202211029614 A CN 202211029614A CN 115416858 A CN115416858 A CN 115416858A
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- Prior art keywords
- taper sleeve
- resistance
- ring
- refueling
- ring body
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Links
- 230000003416 augmentation Effects 0.000 title claims abstract description 18
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 7
- 230000000087 stabilizing effect Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 10
- 210000001503 joint Anatomy 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000013459 approach Methods 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
Images
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
- B64D39/06—Connecting hose to aircraft; Disconnecting hose therefrom
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The invention discloses an aerial refueling taper sleeve stability augmentation ring, which relates to the technical field of aerial refueling and adopts the technical scheme that: the steering gear comprises a plurality of steering gears, a plurality of resistance surfaces and a ring body; the end parts of the resistance surfaces are movably connected with the end part of the ring body; the side walls of the resistance surfaces close to the inner part of the ring body are provided with resistance surface supporting rods; the steering gears are all located in the ring body, the output ends of the steering gears are all provided with steering gear rocker arms, and the end portions, far away from the steering gears, of the steering gear rocker arms are connected with the end portions, far away from the resisting surfaces, of the resisting surface supporting rods. The refueling taper sleeve stability augmentation ring can inhibit the phenomena of swinging and head waves of a hose taper sleeve system in the process of air refueling and butt joint, improve the butt joint efficiency of the taper sleeve and reduce the occurrence of air refueling accidents; meanwhile, the stability augmentation ring can control the sinking amount of the taper sleeve, so that the oiling machine can carry out air oiling at different speeds, and the oiling envelope line of the oiling machine is greatly enlarged.
Description
Technical Field
The invention relates to the technical field of aerial refueling, in particular to an aerial refueling taper sleeve stability augmentation ring.
Background
The application of the air refueling technology increases the range of the airplane, obviously improves the survivability of the fighter plane, increases the effective rate and the like, and makes the tasks which cannot be completed originally possible. In addition, the air refueling technology subverts the traditional concept of the warplane for executing the task types in the past, so that people have brand-new knowledge on the fighting capacity of the air refueling machine for supporting the warplanes.
For the current hose type air refueling mode, due to the existence of atmospheric turbulence and the influence of head waves generated by a front body of the oil refueling machine and the flexibility of the refueling hose, the spatial position of the refueling taper sleeve relative to the refueling machine cannot be fixed, and a fluttering phenomenon exists in a certain range; meanwhile, more than 75% of the total resistance of the prior hose type air refueling taper sleeve is provided by the umbrella coat, so the sinking amount of the taper sleeve depends on the windward area of the umbrella coat, the umbrella coat is divided into a high-speed umbrella coat and a low-speed umbrella coat for controlling the refueling taper sleeve of the refueling machine at high speed and low speed, the refueling machine is limited to finish air refueling only in a certain speed range after being provided with a hose type air refueling taper sleeve device, and the wrapping wire of the refueling machine is greatly limited.
At present, the soft air refueling mode has three disadvantages:
1. the taper sleeve has a fluttering phenomenon, so that the oiling and butting link is longer;
2. when the oil receiving machine approaches the oil filling taper sleeve, the front body head wave of the oil receiving machine can induce the oil filling taper sleeve to vibrate so as to cause related oil filling accidents;
3. the traditional hose type aerial refueling taper sleeve can not realize aerial refueling of the refueling machine at high speed and low speed, and greatly limits a refueling covered wire of the refueling machine.
Disclosure of Invention
The invention aims to provide an air refueling taper sleeve stability augmentation ring which can inhibit the phenomena of swinging and head waves of a hose taper sleeve system in the air refueling butt joint process, improve the butt joint efficiency and precision of the taper sleeve and reduce the occurrence of accidents; meanwhile, the stability augmentation ring can control the sinking amount of the taper sleeve, so that the oiling machine can carry out air oiling at different speeds, and the oiling envelope line of the oiling machine is greatly enlarged.
The technical purpose of the invention is realized by the following technical scheme: an air refueling taper sleeve stability augmentation ring comprises a plurality of steering engines, a plurality of resistance surfaces and a ring body; the end parts of the resistance surfaces are movably connected with the end part of the ring body; the side walls of the plurality of resistance surfaces, which are close to the inner part of the ring body, are provided with resistance surface supporting rods; it is a plurality of the steering wheel all is located the ring body, and is a plurality of the output of steering wheel all is equipped with the steering wheel rocking arm, the tip that the steering wheel was kept away from to the steering wheel rocking arm and the end connection that resistance face was kept away from to resistance face branch.
Through adopting above-mentioned technical scheme, be connected the output and the steering wheel rocking arm of steering wheel, the steering wheel rocking arm simultaneously with be connected with the resistance face through resistance face branch, can realize the open angle of each steering wheel control corresponding resistance face like this to control the taper sleeve gesture, make the taper sleeve all stable at whole release and recovery process, improved the stability and the security of taper sleeve release and recovery process.
The invention is further configured to: a battery and a flight control are arranged in the ring body.
Through adopting above-mentioned technical scheme, fly to control through this internal installation of ring, can record data such as speed, gesture and the position of taper sleeve to control a plurality of steering engines respectively and realize the taper sleeve gesture.
The invention is further configured to: and a propping support is arranged at the end part of the ring body far away from the resistance surface.
By adopting the technical scheme, the stability augmentation ring is sleeved on the front part of the taper sleeve, and the taper sleeve and the stability augmentation ring are connected by screwing the jacking screw on the jacking support in the stability augmentation ring.
The invention is further configured to: and a jacking screw is arranged on the side wall of the jacking support.
Through adopting above-mentioned technical scheme, at the side wall mounting top tight screw of the tight support in top for fix the tight support in top.
In conclusion, the invention has the following beneficial effects:
1. the output end of each steering engine is connected with the corresponding steering engine rocker arm, and the steering engine rocker arm is connected with the resistance surface through the resistance surface support rod, so that each steering engine can control the opening angle of the corresponding resistance surface, the posture of the taper sleeve is controlled, the taper sleeve is stable in the whole releasing and recovering process, and the stability and the safety of the taper sleeve releasing and recovering process are improved;
2. through at this internal installation of ring and fly the accuse, can record data such as speed, gesture and the position of taper sleeve to control a plurality of steering engines respectively and realize the taper sleeve gesture.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of the invention in which a resistance surface of a taper sleeve stability augmentation ring is in an unopened state;
FIG. 2 is a schematic structural diagram of an open state of a resistance surface of a taper sleeve stability augmentation ring for aerial refueling according to an embodiment of the present invention;
FIG. 3 is an assembly drawing of a taper sleeve stabilizing ring and a taper sleeve for aerial refueling according to an embodiment of the present invention;
FIG. 4 is a connection diagram between a rocker arm of a steering engine and a resistance surface in the embodiment of the invention;
FIG. 5 is a diagram illustrating the connection between the tightening screw and the tightening support according to an embodiment of the present invention.
In the figure: 1. a resistance surface; 2. flight control; 3. jacking the screw; 4. a resistance surface rotating shaft; 5. a resistance surface support rod; 6. a steering engine rocker arm; 7. a battery; 8. tightly supporting the support; 9. a steering engine; 10. a ring body; 11. a taper sleeve.
Detailed Description
The present invention is described in further detail below with reference to figures 1-3.
The embodiment is as follows: an air refueling taper sleeve stability augmentation ring is shown in figures 1 to 3 and comprises 4 steering engines 9, 4 resistance surfaces 1 and a ring body 10; as shown in fig. 1 and 2, the end of the 4 resistance surfaces 1 is hinged to the end of the ring body 10; as shown in fig. 4, the side walls of the 4 resistance surfaces 1 close to the interior of the ring body 10 are all connected with resistance surface struts 5;4 steering wheel 9 all are located ring body 10, and 4 steering wheel 9's output shaft all is connected with steering wheel rocking arm 6, and the tip that steering wheel 9 was kept away from to steering wheel rocking arm 6 and the end connection that resistance face 1 was kept away from to resistance face branch 5.
The ring body 10 is internally and fixedly provided with a battery 7 and a flight control 2.
The end part of the ring body 10 far away from the resistance surface 1 is fixedly provided with a jacking support 8.
As shown in fig. 5, a tightening screw 3 is mounted on the side wall of the tightening support 8, the thread in the tightening support is connected with the tightening screw in a matching manner, and the ring body is connected with the taper sleeve through the tightening screw.
The working principle is as follows: in the air refueling process, the oiling machine reaches a preset flight path, the taper sleeve 11 is released, under the action of resistance, the umbrella coat is opened and the umbrella ribs are also opened, according to the type of the oil receiving machine, the oiling machine flies at a corresponding cruising speed, after data processing such as speed measurement through the flight control 2 and the like, 4 steering engines 9 are controlled to rotate at different consistent angles, the steering engine rocker arms 6 are driven to rotate at different angles, the steering engine rocker arms 6 drive the supporting rods of the resisting surfaces 1 to generate different displacements, the 4 resisting surfaces 1 are opened at different consistent angles around the rotating shafts of the resisting surfaces, different windward areas are generated in the incoming flow direction, resistance with different sizes is generated, the resistance characteristic of the taper sleeve 11 is changed, and the taper sleeve 11 has certain sinking amount at different speeds. When the oil receiving machine is a low-speed aircraft such as a helicopter, the taper sleeve 11 can reach a corresponding sinking position only by increasing the resistance, and the resistance of the taper sleeve 11 can be increased by increasing the opening angle of the resistance surface 1, so that the sinking amount of the taper sleeve 11 is increased to enable the taper sleeve to reach a preset position; when the oil receiving machine is a jet aircraft, the taper sleeve 11 can reach a corresponding sinking position only by reducing the resistance, and the resistance of the taper sleeve 11 can be reduced by reducing the opening angle of the resistance surface 1, so that the sinking amount of the taper sleeve 11 is reduced to enable the taper sleeve to reach a preset position. In the process of refueling, the flight control 2 is used for measuring data such as the speed, the posture and the position of the taper sleeve 11, controlling the 4 steering engines 9 to rotate at different angles to drive the steering engine rocker arms 6 to rotate at different angles, the steering engine rocker arms 6 drive the support rods of the resistance surfaces 1 to generate different displacements, so that the 4 resistance surfaces 1 open at different angles around the rotating shafts of the resistance surfaces, different windward areas are generated in the incoming flow direction, resistance with different sizes is generated to enable the resistance to generate differential resistance so as to control the posture of the taper sleeve 11, the taper sleeve 11 is stable in the whole releasing process, in the process, an oil receiving machine follows behind, when the taper sleeve 11 is released to a preset position, the oil receiving machine accelerates to approach, the oil receiving machine slowly approaches to the region and simultaneously stretches to start to be butted with the taper sleeve 11, in the process of butting the oil receiving pipe with the taper sleeve 11, the flight control 2 is used for controlling the steering engines 9 to rotate, so that the differential force generated by the different angles of the opening of the resistance surfaces 1 inhibits the phenomenon of head waves generated by the oil receiving machine approaching the front body of the refueling taper sleeve 11, and enables the oil receiving machine to finish the butting to start to be butted to be in the air refueling; after air refueling is completed, the refueler flies away, the refueling machine starts to recover the taper sleeve 11, the resistance surface 1 is also controlled to generate differential force in the process, the posture of the taper sleeve 11 is controlled to inhibit the taper sleeve from floating, the taper sleeve 11 is recovered into the refueling machine, and the whole air refueling is completed. This scheme is applicable to simultaneously there being aerial refueling of man-machine and unmanned aerial vehicle.
The present embodiment is only for explaining the present invention, and it is not limited to the present invention, and those skilled in the art can make modifications without inventive contribution to the present embodiment as required after reading the present specification, but all of them are protected by patent law within the scope of the present invention.
Claims (4)
1. An aerial refueling taper sleeve stability augmentation ring is characterized in that: comprises a plurality of steering engines (9), a plurality of resistance surfaces (1) and a ring body (10); the end parts of the resistance surfaces (1) are movably connected with the end part of the ring body (10); the side walls of the resistance surfaces (1) close to the inner part of the ring body (10) are provided with support rods of the resistance surfaces (1); a plurality of steering wheel (9) all are located ring body (10), and a plurality of the output of steering wheel (9) all is equipped with steering wheel rocking arm (6), the tip that steering wheel (9) were kept away from in steering wheel rocking arm (6) and resistance face (1) branch keep away from the end connection of resistance face (1).
2. The air refueling drogue stabilizing ring as recited in claim 1, wherein: a battery (7) and a flight control device (2) are arranged in the ring body (10).
3. The air refueling taper sleeve stability augmentation ring as claimed in claim 1, wherein: the end part of the ring body (10) far away from the resistance surface (1) is provided with a propping support (8).
4. The air refueling taper sleeve stability augmentation ring as claimed in claim 3, wherein: and a jacking screw (3) is arranged on the side wall of the jacking support (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211029614.3A CN115416858A (en) | 2022-08-25 | 2022-08-25 | Stability augmentation ring for taper sleeve for air refueling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211029614.3A CN115416858A (en) | 2022-08-25 | 2022-08-25 | Stability augmentation ring for taper sleeve for air refueling |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115416858A true CN115416858A (en) | 2022-12-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211029614.3A Pending CN115416858A (en) | 2022-08-25 | 2022-08-25 | Stability augmentation ring for taper sleeve for air refueling |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115416858A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115783337A (en) * | 2023-02-09 | 2023-03-14 | 中国空气动力研究与发展中心空天技术研究所 | Active taper sleeve for aerial recovery of unmanned aerial vehicle |
| CN115871941A (en) * | 2023-03-08 | 2023-03-31 | 中国空气动力研究与发展中心空天技术研究所 | Gyro-type rotating stability-increasing air refueling taper sleeve |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201254296Y (en) * | 2008-05-26 | 2009-06-10 | 廖志明 | Airfoil fuel filling taper sleeve of aerial tanker |
| CN103192993A (en) * | 2013-03-28 | 2013-07-10 | 西北工业大学 | Aerial tanker taper sleeve with winglets |
| CN205891268U (en) * | 2016-08-05 | 2017-01-18 | 中国人民解放军空军工程大学 | Attitude control device of air refueling taper sleeve |
| CN207773470U (en) * | 2017-12-15 | 2018-08-28 | 江西希德防务***技术有限公司 | A kind of vector power tailstock formula double side wings unmanned plane |
| CN111017193A (en) * | 2019-12-20 | 2020-04-17 | 北京空天技术研究所 | Carrying aircraft and load delivery method |
| CN112660398A (en) * | 2020-12-29 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Device for soft type air active refueling butt joint |
| CN114577431A (en) * | 2022-02-28 | 2022-06-03 | 西北工业大学 | Autonomous aerial refueling test taper sleeve based on control surface |
-
2022
- 2022-08-25 CN CN202211029614.3A patent/CN115416858A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201254296Y (en) * | 2008-05-26 | 2009-06-10 | 廖志明 | Airfoil fuel filling taper sleeve of aerial tanker |
| CN103192993A (en) * | 2013-03-28 | 2013-07-10 | 西北工业大学 | Aerial tanker taper sleeve with winglets |
| CN205891268U (en) * | 2016-08-05 | 2017-01-18 | 中国人民解放军空军工程大学 | Attitude control device of air refueling taper sleeve |
| CN207773470U (en) * | 2017-12-15 | 2018-08-28 | 江西希德防务***技术有限公司 | A kind of vector power tailstock formula double side wings unmanned plane |
| CN111017193A (en) * | 2019-12-20 | 2020-04-17 | 北京空天技术研究所 | Carrying aircraft and load delivery method |
| CN112660398A (en) * | 2020-12-29 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Device for soft type air active refueling butt joint |
| CN114577431A (en) * | 2022-02-28 | 2022-06-03 | 西北工业大学 | Autonomous aerial refueling test taper sleeve based on control surface |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115783337A (en) * | 2023-02-09 | 2023-03-14 | 中国空气动力研究与发展中心空天技术研究所 | Active taper sleeve for aerial recovery of unmanned aerial vehicle |
| CN115871941A (en) * | 2023-03-08 | 2023-03-31 | 中国空气动力研究与发展中心空天技术研究所 | Gyro-type rotating stability-increasing air refueling taper sleeve |
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