CN105752357A - Permanent magnet suspension aircraft carrier electromagnetic catapult - Google Patents

Permanent magnet suspension aircraft carrier electromagnetic catapult Download PDF

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Publication number
CN105752357A
CN105752357A CN201610241495.6A CN201610241495A CN105752357A CN 105752357 A CN105752357 A CN 105752357A CN 201610241495 A CN201610241495 A CN 201610241495A CN 105752357 A CN105752357 A CN 105752357A
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CN
China
Prior art keywords
permanent magnet
aircraft
flat pad
suspension
magnet suspension
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Pending
Application number
CN201610241495.6A
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Chinese (zh)
Inventor
苏伟
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Individual
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Individual
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Priority to CN201610241495.6A priority Critical patent/CN105752357A/en
Publication of CN105752357A publication Critical patent/CN105752357A/en
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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64FGROUND 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
    • B64F1/00Ground or aircraft-carrier-deck installations
    • B64F1/04Ground or aircraft-carrier-deck installations for launching aircraft
    • B64F1/06Ground or aircraft-carrier-deck installations for launching aircraft using catapults

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)

Abstract

The invention discloses a permanent magnet suspension aircraft carrier electromagnetic catapult, which comprises reverse coils, permanent magnet guide rails, a forward coil, permanent magnet suspension guide rails, a permanent magnet suspension launching platform and a power supply. The permanent magnet guide rails are embedded into NdFeB (neodymium iron boron) permanent magnets to form launching rails, the launching platform is placed into the rails, magnetic poles are as shown in figures, then the launching platform can be suspended highly, and after an aircraft is placed on the launching platform, a suspension height is reduced. At the moment, cutting areas of the coils and the permanent magnets of the launching platform are the maximum; large currents are switched into the coils; then the launching platform carries the aircraft to be launched along the rails; when the launching platform reaches the reverse coils, the launching platform is blocked from moving forwards and stops under the action of a reverse acting force; the aircraft is inertially separated from the launching platform to be blasted off.

Description

A kind of permanent magnet suspension electromagnetic aircraft ejector
Technical field
The invention belongs to magnetic levitation technology field, be specifically related to a kind of permanent magnet suspension electromagnetic aircraft ejector.
Background technology
Modern magnetic levitation technology is primarily referred to as electromagnetic suspension technology, is with current induced magnetic field on the basis of Coulomb's law, makes object suspend by the repulsion of multiple points or attraction.Necessarily generating heat with current induced magnetic field, the time one is long, will burn out circuit, will solve problem it is necessary to there is heat sink, makes electromagnetic suspension complicated, expensive.Make object suspend and also have approach, i.e. a permanent magnet suspension, make object suspend by the mutually exclusive of permanent magnet or attraction.It is simply cheap, does not expend energy environment protection.And permanent magnet suspension is denied.Because having individual grace to continue theorem, it is determined that permanent magnet suspension is impossible, so abroad seldom there being research, and China is because the development of rare earth permanent magnet has many people to study, and the Li Guokun such as Lanzhou CAS Institute of Physics establishes and scolds dianoetic, push and pull theory.The Qian Kunxi of Jiangsu University teaches gyroscopic theory etc..
The applicant establishes thruster theory after applying for magnetic suspension bearing patent in 15 years, it is achieved thereby that permanent magnetic suspension technology: two permanent magnet same sexes exclude each other time just relative within the scope of h1, attract each other within the scope of h2.It does not meet the same sex of Coulomb's law and repels mutually, and the size of active force is not more and square being inversely proportional to of distance.During two same sex permanent magnet monoclinic phases pair, excluding each other within the scope of h1, it has repulsive force not only in the vertical direction this moment, also occurs a power in the horizontal direction, grows power such as Lip river logical sequence, and this power only exists in the width of permanent magnet own, and this power is side-thrust.Side-thrust and the captivation avoided within the scope of h2 is used namely to be combined into permanent magnet suspension.
Present aircraft carrier ejector has steam and two kinds of ejectors of electromagnetism, and steam catapult is inevitable replaced by electromagnetic launch due to big caloric value, and Electromagnetical ejector is the direction of China's research and development, and aircraft is launched by linear electric motors principle by it in type aircraft carrier deck.The tire of aircraft repeatedly high speed scroll in type aircraft carrier deck, will necessarily cause abrasion and high temperature, thus reducing service life.
It is desirable to provide a kind of new permanent magnet suspension electromagnetic aircraft ejector.
Summary of the invention
The purpose of the present invention can be achieved through the following technical solutions:
It is an object of the invention to provide a kind of new permanent magnet suspension electromagnetic aircraft ejector.
A kind of new permanent magnet suspension electromagnetic aircraft ejector, comprising:
Reverse winding, permanent magnetic guideway, forward coil, permanent magnet suspension guide rail, permanent magnet suspension flat pad, power supply;
As shown in Figure 1, being bumped into Nd-Fe-B permanent magnet at permanent magnetic guideway, form launching trajectory as shown in Figure 2, flat pad is put into track, magnetic pole is as it can be seen, flat pad gets final product high higher suspension, and after aircraft laid by flat pad, hoverheight declines.Now coil is maximum with permanent magnet cutting area in flat pad guide rail, coil passes into big electric current, flat pad with band aircraft along orbit launching, when arriving reverse winding, flat pad is subject to opposition, stopping of being obstructed of advancing, airplane inertial departs from flat pad, launching, flat pad returns to transmitting starting point under counteracting force, prepares to launch next time.
Flat pad is to suspend with the side-thrust by vertical direction, and the repulsive force of permanent magnet plays the effect preventing from swinging in only the horizontal direction.
Having the beneficial effect that with maglev of hinge structure of the present invention
(1) principle is different, existing magnetic levitation technology is on the basis of coulomb theorem, in accordance with the magnetic suspension that existing theory completes, including existing permanent magnet suspension, it does not have theoretic breakthrough, and my permanent magnetic suspension technology is the permanent magnet suspension that the thruster set up at me completes in theory, it is successful on the basis of negative coulomb theorem, we must obey objective law, practical, and anyone can not denial of facts.
(2) active force is different, existing magnetic suspension is all the magnetic suspension produced under the effect of repulsive force and captivation, it is single power, have to multiple points power combination realize suspend, such as five degree of freedom magnetic suspension, and my permanent magnet suspension is the permanent magnet suspension realized with the side-thrust combination that I found that on the basis of repulsive force and captivation, it is composite force.
(3) permanent magnet suspension of the present invention is simple, cheap, stable, and environmental requirement is low, adapts to high/low temperature condition, and these are superconduction and the unapproachable requirement of routine conductive maglev, and existing permanent magnet suspension is not carried out real suspension, immature is not promoted.
(4) routine conductive maglev and super-conductive magnetic suspension are difficult to miniaturization, microminiaturized and maximization and industrialization, and my permanent magnetic suspension technology can realize.
(5) permanent magnet suspension maintains not against power consumption, can stable suspersion for a long time, and superconduction and routine conductive maglev can not leave electricity a moment, electricity is not had just not suspend, routine conductive maglev and super-conductive magnetic suspension need to be continuously replenished energy, can because of power-off, high temperature, cooling etc. is broken down, can not run continuously for many years, and my permanent magnet suspension can suspend continuously decades, do not expend any energy, if do not demagnetized, can permanent suspension, this is for the long-term satellite run continuously, airship, heart pumps etc. have special meaning, it is the real mythology alive for evermore of our machinery industry.The thorough end solve an abrasion difficult problem.
Accompanying drawing explanation
Fig. 1 is the sectional drawing of permanent magnet suspension electromagnetic aircraft ejector of the present invention.
1, reverse winding;2, permanent magnetic guideway;3, forward coil;4, permanent magnet suspension guide rail;5, permanent magnet suspension flat pad;6, power supply.
Fig. 2 is the plane graph of permanent magnet suspension electromagnetic aircraft ejector of the present invention.
1, permanent magnet suspension guide rail;2, permanent magnet suspension flat pad;3, coil;4 permanent magnetic guideway.
Detailed description of the invention
Embodiment 1:
A kind of new permanent magnet suspension electromagnetic aircraft ejector, it includes as shown in Figure 1:
1, reverse winding;2, permanent magnetic guideway;3, forward coil;4, permanent magnet suspension guide rail;5, permanent magnet suspension flat pad;6, power supply.
Embodiment 2:
A kind of permanent magnet suspension electromagnetic aircraft ejector, as in figure 2 it is shown, comprising:
1, permanent magnet suspension guide rail;2, permanent magnet suspension flat pad;3, coil;4 permanent magnetic guideway.
Embodiment 3:
As shown in Figure 1, being bumped into Nd-Fe-B permanent magnet at permanent magnetic guideway, form launching trajectory as shown in Figure 2, flat pad is put into track, magnetic pole is as it can be seen, flat pad gets final product high higher suspension, and after aircraft laid by flat pad, hoverheight declines.Now coil is maximum with permanent magnet cutting area in flat pad guide rail, coil passes into big electric current, flat pad with band aircraft along orbit launching, when arriving reverse winding, flat pad is subject to opposition, stopping of being obstructed of advancing, airplane inertial departs from flat pad, launching, flat pad returns to transmitting starting point under counteracting force, prepares to launch next time.
Flat pad is to suspend with the side-thrust by vertical direction, and the repulsive force of permanent magnet plays the effect preventing from swinging in only the horizontal direction.
As can be seen here, the present invention utilizes permanent magnet technology, launches a guided missile and does not result in abrasion and high temperature, thus improving service life.Solve aircraft carrier and launch heating, poor efficiency, energy consumption issues.
The above; it is only the present invention preferably detailed description of the invention; but protection scope of the present invention is not limited thereto; any those familiar with the art is in the technical scope that the invention discloses; it is equal to replacement according to technical scheme and inventive concept thereof or is changed, all should be encompassed within protection scope of the present invention.

Claims (5)

1. a permanent magnet suspension electromagnetic aircraft ejector, comprising:
Reverse winding, permanent magnetic guideway, forward coil, permanent magnet suspension guide rail, permanent magnet suspension flat pad, power supply.
2. the permanent magnet suspension electromagnetic aircraft ejector described in claim 1, it is characterised in that its using method is as follows:
Being bumped into Nd-Fe-B permanent magnet at permanent magnetic guideway, form launching trajectory, flat pad is put into track, magnetic pole is as it can be seen, flat pad gets final product high higher suspension, and after aircraft laid by flat pad, hoverheight declines;Now coil is maximum with permanent magnet cutting area in flat pad guide rail, coil passes into big electric current, flat pad with band aircraft along orbit launching, when arriving reverse winding, flat pad is subject to opposition, stopping of being obstructed of advancing, airplane inertial departs from flat pad, launching, flat pad returns to transmitting starting point under counteracting force, prepares to launch next time.
3. the permanent magnet suspension electromagnetic aircraft ejector described in claim 1, it is characterised in that:
Described ejector utilizes thruster theoretical: two permanent magnet same sexes exclude each other time just relative within the scope of h1, attract each other within the scope of h2;It does not meet the same sex of Coulomb's law and repels mutually, and the size of active force is not more and square being inversely proportional to of distance;During two same sex permanent magnet monoclinic phases pair, excluding each other within the scope of h1, it has repulsive force not only in the vertical direction this moment, also occurs a power in the horizontal direction, grows power such as Lip river logical sequence, and this power only exists in the width of permanent magnet own, and this power is side-thrust;Side-thrust and the captivation avoided within the scope of h2 is used namely to be combined into permanent magnet suspension.
4. the permanent magnet suspension electromagnetic aircraft ejector described in claim 1, it is characterised in that:
Flat pad is to suspend with the side-thrust by vertical direction, and the repulsive force of permanent magnet plays the effect preventing from swinging in only the horizontal direction.
5. the application of the permanent magnet suspension electromagnetic aircraft ejector described in claim 1, it is characterised in that:
On other platforms such as it is arranged on aircraft carrier is aircraft carrier ejector, it is also possible to be arranged on land, empty sky, ocean, space shuttle, satellite etc. can also be launched, substitute carrier rocket, it is also possible to launch unmanned plane, guided missile, shell, magnetic artillery bullet etc. is used for attacking interception empty sky target, substitutes rocket fuel.
CN201610241495.6A 2016-04-19 2016-04-19 Permanent magnet suspension aircraft carrier electromagnetic catapult Pending CN105752357A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201610241495.6A CN105752357A (en) 2016-04-19 2016-04-19 Permanent magnet suspension aircraft carrier electromagnetic catapult

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201610241495.6A CN105752357A (en) 2016-04-19 2016-04-19 Permanent magnet suspension aircraft carrier electromagnetic catapult

Publications (1)

Publication Number Publication Date
CN105752357A true CN105752357A (en) 2016-07-13

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU172944U1 (en) * 2017-01-09 2017-08-01 федеральное государственное бюджетное образовательное учреждение высшего образования "Уфимский государственный авиационный технический университет" CATAPULT FOR STARTING UNMANNED AIRCRAFT
CN107804472A (en) * 2017-10-06 2018-03-16 廖忠民 Express locomotive assist system
CN110224515A (en) * 2019-06-13 2019-09-10 张保龙 Motor
CN113148216A (en) * 2021-06-02 2021-07-23 南京联汇智能科技有限公司 Ejection type unmanned aerial vehicle

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1958365A (en) * 2005-11-01 2007-05-09 李岭群 Structural technology system of pathway and vehicle in magnetic suspension on grooved rail
CN102689694A (en) * 2012-05-11 2012-09-26 田太康 Permanent magnet suspension electromagnetic ejection platform for airplane
CN103662024A (en) * 2012-09-16 2014-03-26 卓向东 Permanent magnet like-pole repulsion magnetic levitation track special for unmanned aerial vehicle catapult
CN104401501A (en) * 2014-11-25 2015-03-11 南京艾凌节能技术有限公司 Permanent magnetic suspension type ejecting and flying assisting system
CN104653619A (en) * 2015-02-02 2015-05-27 苏伟 Full permanent magnet full magnetic bearing

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1958365A (en) * 2005-11-01 2007-05-09 李岭群 Structural technology system of pathway and vehicle in magnetic suspension on grooved rail
CN102689694A (en) * 2012-05-11 2012-09-26 田太康 Permanent magnet suspension electromagnetic ejection platform for airplane
CN103662024A (en) * 2012-09-16 2014-03-26 卓向东 Permanent magnet like-pole repulsion magnetic levitation track special for unmanned aerial vehicle catapult
CN104401501A (en) * 2014-11-25 2015-03-11 南京艾凌节能技术有限公司 Permanent magnetic suspension type ejecting and flying assisting system
CN104653619A (en) * 2015-02-02 2015-05-27 苏伟 Full permanent magnet full magnetic bearing

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
魏庆朝等: "直线电机交通模式及技术经济特性", 《都市快轨交通》 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU172944U1 (en) * 2017-01-09 2017-08-01 федеральное государственное бюджетное образовательное учреждение высшего образования "Уфимский государственный авиационный технический университет" CATAPULT FOR STARTING UNMANNED AIRCRAFT
CN107804472A (en) * 2017-10-06 2018-03-16 廖忠民 Express locomotive assist system
CN110224515A (en) * 2019-06-13 2019-09-10 张保龙 Motor
CN113148216A (en) * 2021-06-02 2021-07-23 南京联汇智能科技有限公司 Ejection type unmanned aerial vehicle

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Application publication date: 20160713