CN106184803B - Takeoff method of aircraft carrier takeoff device - Google Patents
Takeoff method of aircraft carrier takeoff device Download PDFInfo
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- CN106184803B CN106184803B CN201610876042.0A CN201610876042A CN106184803B CN 106184803 B CN106184803 B CN 106184803B CN 201610876042 A CN201610876042 A CN 201610876042A CN 106184803 B CN106184803 B CN 106184803B
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- 238000000034 method Methods 0.000 title claims abstract description 8
- 230000001174 ascending effect Effects 0.000 claims abstract description 30
- 230000000903 blocking effect Effects 0.000 claims abstract description 4
- 230000008859 change Effects 0.000 claims description 10
- 238000007664 blowing Methods 0.000 claims description 5
- 238000002955 isolation Methods 0.000 claims description 4
- 230000003993 interaction Effects 0.000 claims description 3
- 238000007599 discharging Methods 0.000 claims description 2
- 238000005452 bending Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
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Abstract
The working method of the aircraft carrier takeoff device comprises a sliding platform, an air outlet and an airflow generator, and is characterized by comprising the following steps: the aircraft is pushed to move on the sliding platform through the horizontal power A, and the aircraft is obliquely sent out of the upturned tail end of the sliding platform through the inertia force which is opposite to the body of the aircraft and the bottom of the wing for blocking the ascending airflow and generates the lifting force to touch the aircraft; the tail end of the sliding platform is upwarped, an air outlet is arranged at the upwarped tail end of the sliding platform, at least one group of air outlets is transversely arranged at the upwarped tail end of the sliding platform, an opening of the air outlet is upward or obliquely upward to form an ascending air flow, an included angle is formed between the ascending air flow and the upwarped tail end of the sliding platform and the front part of the sliding platform, through the oblique arrangement of a group at the front end of the air deflector, one row of the front-end air deflector is arranged to one row of the tail-end air deflector, each row is gradually arranged and erected to generate; and the forced aircraft deviation ascending step, the airflow direction changing step, the airflow isolating step and the energy saving step are carried out simultaneously.
Description
Technical Field
The invention relates to a take-off device, in particular to a take-off method of a take-off device of an aircraft carrier.
Background
Chinese patent document No. CN102120497A discloses a steam catapult for a closed cylinder aircraft carrier in 2011, month 07 and 13, and the purpose of catapulting an aircraft to take off can be achieved by providing the steam catapult for the closed cylinder aircraft carrier. The steam catapult for the sealed cylinder aircraft carrier provided by the invention has the advantages that a traction belt penetrates through a well-lubricated and sealed cylinder sliding hole, two ends of the traction belt are respectively connected with a piston and a tractor, and the traction belt is reversed by a reversing tension wheel to form a specific circulating motion mechanism of the catapult. The piston drives the tractor to move by utilizing the traction belt, and further drives the plane to catapult and take off. The traction belt is made of high-elasticity material, the section of the traction belt is flat, and the traction belt has a smaller bending radius in the flat direction. When the traction belt passes through the reversing tension wheel, the traction belt is bent to be in a complete elastic deformation state, and cannot be damaged due to bending fatigue. The device has the advantages of flexible operation, reliable performance, high efficiency, small volume, water saving, simple structure, easy manufacture, small infrared characteristic and the like, is suitable for the installation and the use of the aircraft carrier, and has great significance for accelerating the development speed of the aircraft carrier in China and improving the fighting capacity and the viability of the aircraft carrier.
Due to the complicated structure and large volume of the steam ejector, further improvement is needed.
Disclosure of Invention
The invention aims to provide a takeoff method of the aircraft carrier takeoff device, which has the advantages of simple and reasonable structure, convenient operation, durability and reliable performance, and has simple structure and low cost so as to overcome the defects in the prior art.
The takeoff method of the aircraft carrier takeoff device designed according to the purpose comprises the following steps: a deviation ascent step for changing the direction of movement of the aircraft: the aircraft is pushed to move on the sliding platform through the horizontal power A, the airflow generator on the upwarping tail end of the sliding platform generates airflow, the airflow is output through the air outlet to convert ascending airflow, and the ascending airflow is combined with the horizontal power of the aircraft to change the moving direction of the aircraft; the aircraft is obliquely sent out of the upturned tail end of the sliding platform by the inertial force of the aircraft which is generated by blocking the ascending airflow at the bottom of the body and the wing of the aircraft and relatively generating the lifting force to touch the aircraft; the tail end of the sliding platform is provided with an air outlet, at least one group of air outlets are transversely arranged at the upwarping tail end of the sliding platform, the opening of each air outlet is upward or obliquely upward to form an ascending airflow, the ascending airflow and the upwarping tail end of the sliding platform form an included angle with the front part of the sliding platform, the ascending airflow blows towards the bottom of an aircraft on the sliding platform to form a lifting force or a lifting airflow surface to change the horizontal moving direction of the aircraft, the ascending airflow is guided to incline in a row through the inclined arrangement of the group at the front end of the air deflectors, the bottom surface of the aircraft blows forwards and upwards to lift at least part of weight of the aircraft, the air deflectors at the front ends are arranged from one row to one row at the tail end, and each row is gradually arranged and erected to generate a three;
the aircraft is sent to the upwarp tail end of the sliding platform in an inclined and upward manner to realize deviation and rise; and generating airflow diversion:
the air outlet is intersected with the upwarp tail end of the sliding platform; the air outlet is arranged in a directional air outlet mode or in an adjustable direction air outlet mode, and the direction of the adjustable direction air outlet is changed by airflow achieved by rotation of the adjustable air deflector;
the blowing force of the three-dimensional ascending airflow is consistent with the blowing force of the air deflector from the inclined front end to the inclined rear end and touches the inertia force of the aircraft; the adjustable air deflector can adjust the air outlet direction of the air outlet to adapt to take off of aircrafts with different weights; the air outlet direction of the air outlet is upward or obliquely upward; the air outlet gradually rises from the front end to the tail end to form an inclined air outlet surface;
the air deflectors of the air outlet are erected to be obliquely and orderly arranged, or the air deflectors of the air outlet are obliquely and orderly arranged along the advancing moving direction of the aircraft; through interaction between the upturned tail end of the sliding platform and the updraft, horizontal power A of the aircraft is converted into uplifted thrust through obstruction of the updraft and the area of the bottom of the aircraft, and the aircraft is gradually lifted and sent out of the upturned tail end of the sliding platform; the air outlet is communicated with the airflow generator, the airflow generator is arranged in the upturned tail end of the sliding platform, and the air inlet of the airflow generator is arranged on one side or two sides or the bottom of the upturned tail end of the sliding platform or the upper part of the front end of the sliding platform;
the airflow generator is a turbine fan or a blade fan or a cross-flow fan and is uniformly distributed at the lower part of the air outlet or the front end of the air outlet;
the air deflector is rotatably connected with the electric control assembly, the electric control assembly is provided with a motor, a gear and a connecting rod, the air deflector is movably connected with the connecting rod, and the connecting rod drives the air deflector to swing back and forth;
the air outlet is arranged into a strip-shaped reticular platform, and the air deflector is arranged to be a part of the strip-shaped reticular platform of the air outlet;
the air inlet of the airflow generator is arranged at the side part or the bottom part of the upturned tail end of the sliding platform, and an included angle is formed between the air inlet and the air outlet to eliminate rotating airflow generated by air inlet or air outlet;
and (3) airflow isolation: the air deflectors on the outer sides of each group of air outlets obliquely exhaust air to the outside, so that external ambient airflow is blocked outwards to form an isolated airflow wall, and airflow isolation caused by the influence of the ambient airflow on the takeoff of the aircraft is reduced; the air guide plates on the outer sides of the air outlets of each group are used for obliquely discharging air to the outside and blocking the outside ambient airflow to the outside to form an isolated airflow wall, so that the influence of the ambient airflow on the take-off of the aircraft is reduced, the ascending airflow is ensured to be combined with the horizontal power of the aircraft to change the moving direction of the aircraft to deviate and ascend, and the aircraft is forced to deviate and ascend.
The step of changing the direction of the airflow; the front end of the air deflector is obliquely arranged to guide the air outlet flow to be inclined in rows, the bottom surface of the aircraft is blown forwards and upwards to support at least part of the weight of the aircraft, the front end air deflector is arranged from one row to the tail end air deflector, and each row is gradually arranged and erected to generate a three-dimensional ascending air flow inclined to be erected.
The step of changing the direction of the airflow; the air outlet is communicated with the air flow generator, the air flow generator is arranged in the upwarping tail end of the sliding platform, and the air inlet of the air flow generator is arranged on one side or two sides or the bottom of the upwarping tail end of the sliding platform or the upper part of the front end of the sliding platform.
The step of changing the direction of the airflow;
the airflow generator is a turbine fan or a blade fan or a cross flow fan and is uniformly distributed at the lower part of the air outlet or the front end of the air outlet.
The step of changing the direction of the airflow;
the air deflector is rotatably connected with the electric control assembly, the electric control assembly is provided with a motor, a gear and a connecting rod, the air deflector is movably connected with the connecting rod, and the connecting rod drives the air deflector to swing back and forth.
The step of changing the direction of the airflow;
the air outlet is arranged into a strip-shaped reticular platform, and the air deflector is arranged to be a part of the strip-shaped reticular platform of the air outlet.
The invention uses the aircraft carrier take-off device, the body includes sliding platform, air outlet, airflow generator, characterized by that: the tail end upwarping position of the sliding platform is provided with an air outlet, at least one group of air outlets are transversely arranged at the upwarping tail end of the sliding platform, an opening of each air outlet is upward or obliquely upward to form an updraft, the updraft and the upwarping tail end of the sliding platform form an included angle with the front portion of the sliding platform, the updraft blows towards the bottom of an aircraft on the sliding platform to form a direction for lifting force or lifting airflow surface to change the horizontal movement of the aircraft, and the aircraft is obliquely and upwardly conveyed away from the upwarping tail end of the sliding platform.
The air outlet is intersected with the upwarp tail end of the sliding platform;
the air outlet is arranged in a directional air outlet mode or in an adjustable direction air outlet mode, and the adjustable direction air outlet is realized by rotating the adjustable air deflector.
The air outlet direction of the air outlet is upward or obliquely upward; the air outlet gradually rises from the front end to the tail end to form an inclined air outlet surface;
the air deflectors of the air outlet are arranged in order from vertical to inclined, or the air deflectors of the air outlet are arranged in order from inclined to vertical along the advancing moving direction of the aircraft.
The front end of the air deflector is obliquely arranged to guide the air outlet flow to be inclined in rows, the bottom surface of the aircraft is blown forwards and upwards to support at least part of the weight of the aircraft, the front end air deflector is arranged from one row to the tail end air deflector, and each row is gradually arranged and erected to generate a three-dimensional ascending air flow inclined to be erected.
The air outlet is in through connection with the airflow generator, the airflow generator is arranged inside the upwarping tail end of the sliding platform, and the air inlet of the airflow generator is arranged on one side or two sides or the bottom of the upwarping tail end of the sliding platform or the upper portion of the front end of the sliding platform.
The airflow generator is a turbine fan or a blade fan or a cross-flow fan and is uniformly distributed at the lower part of the air outlet or the front end of the air outlet;
the air inlet of the airflow generator is arranged at the side part or the bottom part of the upturned tail end of the sliding platform, and an included angle is formed between the air inlet and the air outlet to eliminate rotating airflow generated by air inlet or air outlet;
the air deflectors on the outer sides of each group of air outlets incline to the outside to exhaust air, so that outside ambient airflow is blocked outwards, an isolated airflow wall is formed, and the influence of the ambient airflow on the takeoff of the aircraft is reduced.
The air deflector is rotatably connected with the electric control assembly, the electric control assembly is provided with a motor, a gear and a connecting rod, the air deflector is movably connected with the connecting rod, and the connecting rod drives the air deflector to swing back and forth.
The air outlet is arranged into a strip-shaped reticular platform, and the air deflector is arranged to be a part of the strip-shaped reticular platform of the air outlet.
According to the invention, through interaction between the upwarp tail end of the sliding platform and the updraft, the horizontal power A of the aircraft is converted into the upwarp thrust through the obstruction of the updraft and the area of the bottom of the aircraft, and the aircraft is gradually lifted and sent out of the upwarp tail end of the sliding platform, so that the effect of four or two thousands of thousands.
The working procedures can be carried out circularly, and the working efficiency is greatly improved. The device has the characteristics of simple and reasonable structure, convenience in operation, durability and reliable performance.
Drawings
Fig. 1 is a schematic view of a sliding platform according to a first embodiment of the present invention.
Fig. 2 is a schematic top view of a sliding platform according to a first embodiment of the present invention.
Fig. 3 is a front view schematically illustrating a sliding platform according to a first embodiment of the present invention.
Fig. 4 is a partially enlarged schematic view of the sliding platform according to the first embodiment of the present invention.
Detailed Description
The invention is further described with reference to the following figures and examples.
Reference example (see FIGS. 1-4)
Aircraft carrier take-off device, the main part is including sliding platform 11, air outlet 10, airflow generator 7, its characterized in that: the tail end upwarping position of the sliding platform 11 is provided with an air outlet 10, at least one group of air outlets 10 are transversely arranged at the upwarping tail end of the sliding platform 11, an opening of each air outlet 10 is upward or obliquely upward to form an updraft 8, the upwarping tail ends of the updraft 8 and the sliding platform 11 and the front portion of the sliding platform 11 form an included angle, the updraft 8 blows towards the bottom of the aircraft 1 on the sliding platform 11 to form a lifting force or a lifting airflow surface to change the horizontal moving direction of the aircraft 1, and the aircraft 1 is obliquely and upwards conveyed away from the upwarping tail end of the sliding platform 11.
The air outlet 10 is intersected with the upwarp tail end of the sliding platform 11;
the air outlet 10 is arranged for directional air outlet or adjustable directional air outlet, and the adjustable directional air outlet is realized by rotating the adjustable air deflector 2.
The air outlet direction of the air outlet 10 is upward or obliquely upward; the air outlet 10 gradually rises from the front end to the tail end to form an inclined air outlet surface;
the air deflectors 2 of the air outlet 10 are arranged in order from vertical to inclined, or the air deflectors 2 of the air outlet 10 are arranged in order from inclined to vertical along the advancing moving direction of the aircraft 1.
The front end of the air deflector 2 is obliquely arranged in a group to guide the air outlet flow to be inclined in rows, the bottom of the aircraft 1 is blown forwards and upwards to support at least part of the weight of the aircraft 1, the front end air deflector 2 is arranged from one row to the tail end air deflector 2, each row is gradually arranged vertically, and a three-dimensional ascending air flow 8 inclined to be vertical is generated.
The air outlet 10 is communicated with the air flow generator 7, the air flow generator 7 is arranged in the upwarping tail end of the sliding platform 11, and the air inlet 9 of the air flow generator 7 is arranged on one side or two sides or the bottom of the upwarping tail end of the sliding platform 11 or the upper part of the front end of the sliding platform 11.
The airflow generator 7 is a turbo fan or a blade fan or a cross flow fan 3 and is uniformly distributed at the lower part of the air outlet 10 or at the front end of the air outlet 10;
the air inlet 9 of the airflow generator 7 is arranged at the side part or the bottom part of the upturned tail end of the sliding platform 11, and an included angle is formed between the air inlet 9 and the air outlet 10, so that rotary airflow generated by air inlet or air outlet is eliminated;
the air deflectors on the outer sides of each group of air outlets 10 incline outwards to exhaust air 14, so that the external ambient airflow 13 is blocked outwards, an isolated airflow wall is formed, and the influence of the ambient airflow 13 on the takeoff of the aircraft 1 is reduced.
The air deflector 2 is rotatably connected with the electric control component 4, the electric control component 4 is provided with a motor, a gear and a connecting rod 6, the air deflector 2 is movably connected with the connecting rod 6, and the connecting rod drives the air deflector 2 to swing back and forth.
The air outlet 10 is configured as a strip-shaped mesh platform, and the air deflector 2 is configured as a part of the strip-shaped mesh platform of the air outlet 10.
The aircraft 1 is pushed to move on the sliding platform 11 through the horizontal power A, the airflow generator 7 on the upwarping tail end of the sliding platform 11 generates airflow and the airflow is discharged through the air outlet 10 to convert ascending airflow, and the ascending airflow is combined with the horizontal power of the aircraft 1 to change the moving direction of the aircraft 1 to deviate from ascending;
the airframe and the bottom of the wing of the aircraft 1 block the ascending airflow and generate the inertia force of the lifting force which touches the aircraft 1, so that the aircraft 1 is obliquely sent out of the upturned tail end of the sliding platform 11;
the front end of the air deflector 2 is obliquely arranged in a group to guide the air outlet flow to be oblique in rows, the bottom of the aircraft 1 is blown forwards and upwards to support at least part of the weight of the aircraft 1, the front end air deflector 2 is arranged from one row to the tail end air deflector 2, each row is gradually arranged vertically, and the generated vertical air flow is obliquely sent out of the upturned tail end of the sliding platform 11 by the inertia force of the air deflector 1 contacting the vertical air flow;
the air deflectors on the outer sides of each group of air outlets 10 obliquely exhaust air 14 outwards, external ambient airflow 13 is blocked outwards to form an isolated airflow wall, the influence of the ambient airflow 13 on the takeoff of the aircraft 1 is reduced, and the ascending airflow is enabled to be combined with the horizontal power of the aircraft 1 to change the moving direction of the aircraft 1 to deviate from ascending; each row is arranged to be higher and vertical gradually, and generates the inertia force that the three-dimensional ascending airflow with the blowing force being consistent with that of the vertical front end to the rear end touches the aircraft 1 to obliquely send the aircraft 1 out of the upturned tail end of the sliding platform 11.
The adjustable air deflector 2 can adjust the air outlet direction of the air outlet to adapt to take off of the aircrafts 1 with different weights.
The foregoing is a preferred embodiment of the present invention, and the basic principles, principal features and advantages of the invention are shown and described. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are intended to illustrate the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, and the invention is intended to be protected by the following claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (1)
1. The takeoff method of the aircraft carrier takeoff device comprises the following steps: a deviating ascent step for changing the direction of movement of the aircraft (1): the aircraft (1) is pushed to move on the sliding platform (11) through the horizontal power A, the airflow generator (7) on the upwarping tail end of the sliding platform (11) generates airflow and the airflow flows out through the air outlet (10) to convert the updraft, and the updraft is combined with the horizontal power of the aircraft (1) to change the moving direction of the aircraft (1); the aircraft (1) is obliquely sent out of the upturned tail end of the sliding platform (11) by blocking ascending airflow at the bottom of the wing and the body of the aircraft (1) and generating inertia force of lifting force which is opposite to the aircraft (1) to touch the aircraft (1); the tail end of the sliding platform is provided with an air outlet, at least one group of air outlets are transversely arranged at the upwarping tail end of the sliding platform, the opening of each air outlet is upward or obliquely upward to form an ascending airflow, the ascending airflow and the upwarping tail end of the sliding platform form an included angle with the front part of the sliding platform, the ascending airflow blows towards the bottom of an aircraft on the sliding platform to form a lifting force or a lifting airflow surface to change the horizontal moving direction of the aircraft, the ascending airflow is guided to incline in a row through the inclined arrangement of the group at the front end of the air deflectors, the bottom surface of the aircraft blows forwards and upwards to lift at least part of weight of the aircraft, the air deflectors at the front ends are arranged from one row to one row at the tail end, and each row is gradually arranged and erected to generate a three;
the aircraft is sent to the upwarp tail end of the sliding platform in an inclined and upward manner to realize deviation and rise; and generating airflow diversion:
the air outlet is intersected with the upwarp tail end of the sliding platform; the air outlet is arranged in a directional air outlet mode or in an adjustable direction air outlet mode, and the direction of the adjustable direction air outlet is changed by airflow achieved by rotation of the adjustable air deflector;
the blowing force of the three-dimensional ascending airflow is consistent with the blowing force of the air deflector (2) from the inclined front end to the inclined rear end and touches the inertia force of the aircraft (1); the adjustable air deflector (2) can adjust the air outlet direction of the air outlet to adapt to take-off of aircrafts (1) with different weights; the air outlet direction of the air outlet is upward or obliquely upward; the air outlet gradually rises from the front end to the tail end to form an inclined air outlet surface;
the air deflectors of the air outlet are erected to be obliquely and orderly arranged, or the air deflectors of the air outlet are obliquely and orderly arranged along the advancing moving direction of the aircraft; through interaction between the upturned tail end of the sliding platform and the updraft, horizontal power A of the aircraft is converted into uplifted thrust through obstruction of the updraft and the area of the bottom of the aircraft, and the aircraft is gradually lifted and sent out of the upturned tail end of the sliding platform; the air outlet is communicated with the airflow generator, the airflow generator is arranged in the upturned tail end of the sliding platform, and the air inlet of the airflow generator is arranged on one side or two sides or the bottom of the upturned tail end of the sliding platform or the upper part of the front end of the sliding platform;
the airflow generator is a turbine fan or a blade fan or a cross-flow fan and is uniformly distributed at the lower part of the air outlet or the front end of the air outlet;
the air deflector is rotatably connected with the electric control assembly, the electric control assembly is provided with a motor, a gear and a connecting rod, the air deflector is movably connected with the connecting rod, and the connecting rod drives the air deflector to swing back and forth;
the air outlet is arranged into a strip-shaped reticular platform, and the air deflector is arranged to be a part of the strip-shaped reticular platform of the air outlet;
the air inlet of the airflow generator is arranged at the side part or the bottom part of the upturned tail end of the sliding platform, and an included angle is formed between the air inlet and the air outlet to eliminate rotating airflow generated by air inlet or air outlet;
and (3) airflow isolation: the air deflectors on the outer sides of each group of air outlets obliquely exhaust air to the outside, so that external ambient airflow is blocked outwards to form an isolated airflow wall, and airflow isolation caused by the influence of the ambient airflow on the takeoff of the aircraft is reduced; the air guide plates on the outer sides of the air outlets (10) are used for obliquely discharging air (14) to the outside, so that the outside environment airflow (13) is blocked outwards to form an isolated airflow wall, the influence of the environment airflow (13) on the takeoff of the aircraft (1) is reduced, the ascending airflow is ensured to be combined with the horizontal power of the aircraft (1) to change the moving direction of the aircraft (1) to deviate and ascend, and the aircraft (1) is forced to deviate and ascend.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610876042.0A CN106184803B (en) | 2016-10-08 | 2016-10-08 | Takeoff method of aircraft carrier takeoff device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610876042.0A CN106184803B (en) | 2016-10-08 | 2016-10-08 | Takeoff method of aircraft carrier takeoff device |
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| CN106184803A CN106184803A (en) | 2016-12-07 |
| CN106184803B true CN106184803B (en) | 2020-04-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610876042.0A Active CN106184803B (en) | 2016-10-08 | 2016-10-08 | Takeoff method of aircraft carrier takeoff device |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101244764A (en) * | 2008-03-07 | 2008-08-20 | 王刚 | Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane |
| CN102745333A (en) * | 2012-07-31 | 2012-10-24 | 李文铎 | Internal combustion steam boosting take-off unit of airplane |
| CN104670447A (en) * | 2015-01-29 | 2015-06-03 | 赵凤银 | Aircraft carrier, ship and land-water jet runway system with efficient short-range slide or vertical take-off and landing aircraft units |
| CN105035343A (en) * | 2015-08-13 | 2015-11-11 | 济南环太机电技术有限公司 | Vapor emission type shipboard aircraft carrier catapult |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9783322B2 (en) * | 2013-08-27 | 2017-10-10 | Engineered Arresting Systems Corporation | Electric unmanned aerial vehicle launcher |
-
2016
- 2016-10-08 CN CN201610876042.0A patent/CN106184803B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101244764A (en) * | 2008-03-07 | 2008-08-20 | 王刚 | Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane |
| CN102745333A (en) * | 2012-07-31 | 2012-10-24 | 李文铎 | Internal combustion steam boosting take-off unit of airplane |
| CN104670447A (en) * | 2015-01-29 | 2015-06-03 | 赵凤银 | Aircraft carrier, ship and land-water jet runway system with efficient short-range slide or vertical take-off and landing aircraft units |
| CN105035343A (en) * | 2015-08-13 | 2015-11-11 | 济南环太机电技术有限公司 | Vapor emission type shipboard aircraft carrier catapult |
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| CN106184803A (en) | 2016-12-07 |
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