CN102267570A - Method for realizing take-off by utilizing gravitational potential energy of aircraft to nose down and accelerate - Google Patents
Method for realizing take-off by utilizing gravitational potential energy of aircraft to nose down and accelerate Download PDFInfo
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- CN102267570A CN102267570A CN201110115077XA CN201110115077A CN102267570A CN 102267570 A CN102267570 A CN 102267570A CN 201110115077X A CN201110115077X A CN 201110115077XA CN 201110115077 A CN201110115077 A CN 201110115077A CN 102267570 A CN102267570 A CN 102267570A
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- aircraft
- runway
- take
- running
- downward
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/80—Energy efficient operational measures, e.g. ground operations or mission management
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Abstract
The invention discloses a method for realizing take-off by utilizing a gravitational potential energy of an aircraft to nose down and accelerate. The method is characterized in that the aircraft 1 is placed at the upper end of a runway 2 which is at a certain altitude and is inclined downward or extended downward, thereby enabling the running of the aircraft 1 from a static state to a take-off stage to be the nosed down running from the high altitude to the inclined downward or downward position. The runway 2 for supporting or loading the accelerated running of the aircraft is at a certain altitude, is inclined downward or extended downward, has a certain turning radian along the longitudinal direction and is finally smoothly converted into the runway extended along the horizontal direction or inclined upward direction, so as to immediately change the running of the aircraft 1 at a nosed down state into the high-speed running along the horizontal direction or inclined upward direction, and then the aircraft 1 is veered off the runway by virtue of own motive power, thereby achieving the take-off purpose of the aircraft 1. The method provided by the invention can be used for shortening a rollout distance and saving a large number of fuels and energy sources for the take-off process of the aircraft.
Description
Technical field
The present invention relates to a kind of method of taking off of aircraft, specifically, relate to and utilize aircraft self gravitation potential energy to make its acceleration of diving realize the method for taking off.
Background technology
At present, the method for taking off of aircraft is respectively aircraft and quickens, launches and quicken the mode of taking off to sliding race of horizontal direction, and the mode of taking off of launch craft vertically upward.All consider to utilize aircraft self gravitation potential energy to be convertible into the principle of kinetic energy, the acceleration/accel when increasing aircraft takeoff reaches the purpose that the aircraft acceleration is taken off.Cause the takeoff phase of present aircraft, consume a large amount of fuel, the energy, take huge space, waste is serious.
Summary of the invention
The technical problem to be solved in the present invention provides the method that a kind of aircraft acceleration is taken off.
Solution of the present invention is to utilize aircraft self gravitation potential energy that it is dived and quicken the method that realization is taken off.Referring to accompanying drawing, aircraft 1 placed have certain altitude, to tiltedly down or runway 2 upper ends of extending, below, make the operation of aircraft 1 from static to takeoff phase, at first by eminence to tiltedly down or the below dive.The runway 2 that supports or carry aircraft acceleration operation has certain altitude, extend to down oblique or below, and certain radian that curves is arranged vertically, final changing into tends to horizontal direction or oblique upper extension smooth-goingly, make aircraft 1 service direction of dive status change into trend horizontal direction or oblique upper high-speed cruising, reach the purpose that aircraft 1 takes off.
Principle of work of the present invention is that the function transfer principle that utilizes releaser body weight power potential energy can obtain kinetic energy solves the problems of the technologies described above.
Useful result of the present invention is, improves and save that the present aircraft takeoff stage exists, and consumes a large amount of fuel, the energy, takies serious waste phenomenons such as huge space.
Description of drawings
Accompanying drawing is the scheme drawing of the inventive method.
Be labeled as among the figure: 1---aircraft, 2---runway.
The specific embodiment
The invention will be further described below by shown in the accompanying drawing.
Aircraft 1 placed have certain altitude,, open aircraft power, unclamp the aircraft brakes device, make aircraft 1 under the effect of self power and gravitional force, quicken operation to diving from static along runway 2 to tiltedly down or runway 2 upper ends of extending, below.The runway 2 that supports or carry aircraft acceleration operation has certain altitude, extend to down oblique or below, and certain radian that curves is arranged vertically, final changing into tends to horizontal direction or oblique upper extension smooth-goingly, even change into trend horizontal direction or oblique upper high-speed cruising with aircraft 1 service direction of dive status, after aircraft 1 obtains the speed of very high trend horizontal direction or oblique upper, rely on self power gun off the runway, finish take-off process.
The present invention can be taking off of aircraft, shortens ground run distance, saves a large amount of fuel, the energy.
In the above-described embodiments, supporting or carry the runway 2 of aircraft acceleration operation, can be the building of solidifying, and also can be the mechanical tracks device according to the prior art self design.
Claims (3)
1. utilize aircraft self gravitation potential energy that it is dived and quicken the method that realization is taken off, it is characterized in that, aircraft is by static operation to takeoff phase, be at first to dive to down oblique or below to quickening operation by eminence, under the effect of the runway that supports or carry the aircraft operation, change trend horizontal direction or oblique upper high-speed cruising into subsequently.
2. the runway of support according to claim 1 or the operation of carrying aircraft, it is characterized in that having certain height, extend to down oblique or below by eminence, it vertically has certain radian that curves, and finally changes trend horizontal direction or oblique upper smooth-goingly into and extends.
3. the runway of support according to claim 1 or the operation of carrying aircraft is characterized in that, can be the building of solidifying, and also can be the mechanical tracks device that manufactures and designs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110115077XA CN102267570A (en) | 2011-05-05 | 2011-05-05 | Method for realizing take-off by utilizing gravitational potential energy of aircraft to nose down and accelerate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110115077XA CN102267570A (en) | 2011-05-05 | 2011-05-05 | Method for realizing take-off by utilizing gravitational potential energy of aircraft to nose down and accelerate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102267570A true CN102267570A (en) | 2011-12-07 |
Family
ID=45050065
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110115077XA Pending CN102267570A (en) | 2011-05-05 | 2011-05-05 | Method for realizing take-off by utilizing gravitational potential energy of aircraft to nose down and accelerate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102267570A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014032295A1 (en) * | 2012-09-01 | 2014-03-06 | Zhao Tianshuo | Slope downward-sliding takeoff platform for carrier-based aircraft, application aircraft carrier and realization method |
| CN104108473A (en) * | 2013-04-22 | 2014-10-22 | 陈俞任 | Runway-free multi-aircraft simultaneous take-off high-speed aircraft carrier with submarines |
| CN105015789A (en) * | 2014-08-25 | 2015-11-04 | 韩淮生 | Potential-energy runway |
| WO2018133640A1 (en) * | 2017-01-21 | 2018-07-26 | 秦赵修 | Low-wind-resistance tubular track, stratosphere-simulating low-wind-resistance tube having built-in track, carrier rocket spacecraft launching system, and method for reducing resistance of tubular track |
| CN108791938A (en) * | 2018-05-08 | 2018-11-13 | 西北工业大学 | A kind of fixed-wing UAV launched by warship method |
| WO2020107902A1 (en) * | 2018-11-26 | 2020-06-04 | 姚黎明 | Facility used for increasing rocket launching thrust |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1106094A (en) * | 1993-12-22 | 1995-08-02 | 李焕山 | Periodically curved road |
| CN1199004A (en) * | 1997-01-29 | 1998-11-18 | 任俊超 | Flyer lauching method |
| US20030102407A1 (en) * | 2001-12-03 | 2003-06-05 | Wood John R. | Short runway aircraft launching and landing system |
| CN101100836A (en) * | 2007-07-30 | 2008-01-09 | 戴维国 | Airplane runway |
-
2011
- 2011-05-05 CN CN201110115077XA patent/CN102267570A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1106094A (en) * | 1993-12-22 | 1995-08-02 | 李焕山 | Periodically curved road |
| CN1199004A (en) * | 1997-01-29 | 1998-11-18 | 任俊超 | Flyer lauching method |
| US20030102407A1 (en) * | 2001-12-03 | 2003-06-05 | Wood John R. | Short runway aircraft launching and landing system |
| CN101100836A (en) * | 2007-07-30 | 2008-01-09 | 戴维国 | Airplane runway |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014032295A1 (en) * | 2012-09-01 | 2014-03-06 | Zhao Tianshuo | Slope downward-sliding takeoff platform for carrier-based aircraft, application aircraft carrier and realization method |
| CN104108473A (en) * | 2013-04-22 | 2014-10-22 | 陈俞任 | Runway-free multi-aircraft simultaneous take-off high-speed aircraft carrier with submarines |
| CN104108473B (en) * | 2013-04-22 | 2016-07-27 | 陈俞任 | Exempt from runway multimachine with flying band submarine high speed aircraft carrier |
| CN105015789A (en) * | 2014-08-25 | 2015-11-04 | 韩淮生 | Potential-energy runway |
| WO2018133640A1 (en) * | 2017-01-21 | 2018-07-26 | 秦赵修 | Low-wind-resistance tubular track, stratosphere-simulating low-wind-resistance tube having built-in track, carrier rocket spacecraft launching system, and method for reducing resistance of tubular track |
| CN108791938A (en) * | 2018-05-08 | 2018-11-13 | 西北工业大学 | A kind of fixed-wing UAV launched by warship method |
| CN108791938B (en) * | 2018-05-08 | 2021-09-28 | 西北工业大学 | Shipborne launching method of fixed-wing unmanned aircraft |
| WO2020107902A1 (en) * | 2018-11-26 | 2020-06-04 | 姚黎明 | Facility used for increasing rocket launching thrust |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| DD01 | Delivery of document by public notice |
Addressee: Lei Hong Document name: the First Notification of an Office Action |
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| DD01 | Delivery of document by public notice |
Addressee: Lei Hong Document name: Notification that Application Deemed to be Withdrawn |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20111207 |
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| WD01 | Invention patent application deemed withdrawn after publication |