CN1248539A - Power unit - Google Patents
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- CN1248539A CN1248539A CN99118230A CN99118230A CN1248539A CN 1248539 A CN1248539 A CN 1248539A CN 99118230 A CN99118230 A CN 99118230A CN 99118230 A CN99118230 A CN 99118230A CN 1248539 A CN1248539 A CN 1248539A
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- stator
- rotor
- engine installation
- power
- coil
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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
- Y02T50/50—On board measures aiming to increase energy efficiency
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- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The present invention relates to a new type power device. It can be used as power device of ship and automobile, and is more suitable for power device of aerospace vehicle. It is matched with nuclear engine and solar cell technology, and is used in the field of aerospace industry, and can enhance great progress and is favourable for human to probe the cosmic space.
Description
The present invention relates generally to the aerospace power technology.
Present aerospace flight all is to utilize simple recoil to be used for providing power.As aviation flight, the most employing with the air is working medium, and makes it recoil so that power to be provided, and minority is utilized Space Dynamic's technical flying; Space travel all is by burning of working medium such as liquid hydrogen liquid oxygen and recoil, so that the power of flight to be provided.Although aeronautical and space technology is progressive constantly, the mankind always fail to break away from and utilize simple and simple recoil effect to provide power this method, make aerospace to further develop, and are difficult to, and the utilization of recoil is near the limit.
People simply and are mistakenly being derived by the law of conservation of momentum, flight has only the irreversible working medium of leaning on to recoil provides power judgement constraint down, only paid attention to how improving repercussion effect, and to " utilization physics be the basis, seeks under specific circumstances, uses the special working medium that can be recycled; other form energies; be converted into the mechanical energy of aircraft as electric energy, and and then invents a kind of later-model engine installation ", this one side is but paid seldom.
Purpose of the present invention just provides later-model engine installation, electric energy can be converted into the mechanical energy of aircraft by engine installation, and to adopt the present invention distinctive be working medium with the rotor, and recycle in use, this device also can as in the water, the engine installation of the water surface, road surface transportation thing.More can be as the engine installation of water, land and air three usefulness transportation thing; Solved engine installation to consume the problem that irreversible working medium is cost, capacity usage ratio also will improve simultaneously.
Engine installation of the present invention is observed physics principles such as the conservation of momentum.Existing aircraft is to lean on the recoil effect of working medium that power is provided, and makes aircraft and working medium set up conservation of momentum relation: d (M
FlyV
Fly)+d (M
The workerV
The worker)=constant.And the present invention sets up conservation of momentum relation with the moment of momentum that rotatablely moves of working medium and the linear momentum of aircraft: d (M
FlyV
Fly)+d (M
The workerω r
2)=constant.It is limited that the rotating speed of rotor improves, and it also is limited that quality improves, and is head it off, and the present invention adopts electrical generator to link to each other with the working medium rotor by driving device such as belt, increases resisting moment and resistance momentum when working medium is rotated.Be d (M
FlyV
Fly)+d (M
The workerV
The worker)+M
Δ t=constant.
In the system, aircraft and rotor, electrical generator are set up conservation of momentum relation because aircraft and rotor, electrical generator coexist, if rotor and electrical generator quantity all are one, what then aircraft obtained is moment of momentum, and aircraft just rotates.And need aircraft to do motion of translation when most when really flying.
Be head it off, in apparatus of the present invention, adopt stator and rotor by electromagnetism, mutual action, the application force that stator obtains drives aircraft movements, and the application force that rotor is subjected to makes rotor be subjected to moment loading, and rotation.The quantity of stator, rotor, electrical generator is answered more than two, and is the center symmetry or distributes according to certain rules with the aircraft barycenter, makes stator offer the power of aircraft motion of translation, and the support effect of rotor, electrical generator cancels out each other for the moment of aircraft.
Stator in the engine installation is full bag rotor unlike common motor, but part is wrapped rotor, and stator is moment loading but not force couple role to the effect of rotor.Therefore waste of power is bigger in stator and the rotor mechanism, and head it off can adopt superconductor technology or adopt controller control current size, make-and-break time and direction, when making effective acting, the useful effect coil gets electric, during invalid acting, and the useful effect coil blackout.Also can and use two kinds of methods.For reducing electric energy loss, the electric energy that electrical generator sends also can reuse, and fills in storage battery by charging unit.If aircraft overcomes the static relatively or uniform movement of graviational interaction, self mechanical energy does not change, after aircraft moves a section and moves, and the ENERGY E=F of Xiao Haoing then
EmptyS+E
Decrease, F
EmptyS represents that aircraft overcomes air resistance work, E
DecreaseExpression aircraft in-to-in friction equal loss.In view of this, overcome graviational interaction at aircraft.During the relative no change of mechanical energy, the energy of consumption seldom not aircraft-likely needs to consume big energy and overcome graviational interaction.
Embodiment describes the present invention below in conjunction with accompanying drawing.
Conservation of momentum relation between figure one, expression linear momentum and moment of momentum.
The lateral plan of figure two, expression engine installation.
The birds-eye view of figure three, expression engine installation.
The constructional drawing of figure four, expression stator and rotor.
Figure one: conservation of momentum relation between expression linear momentum and moment of momentum.Comprise: flyer 1, explosive 2, working medium 3, working medium mass axis 4, arrow 5,6,7.
Native system is not considered the external force effect, and after explosive 2 was ignited, flyer 1 was subjected to the application force of direction shown in the arrow 5, and makes flyer do motion of translation along arrow 5 directions.Working medium 3 is subjected to directive effect power shown in the arrow 6, makes working medium 3 along mass axis 4 rotations, and direction is shown in the arrow 7.According to the law of conservation of momentum: M
FlyV
Fly+ M
The workerω r
2=0, V
FlyThe relative mass axis 4 of direction opposite with the ω direction.The power of the bright aircraft of this illustration can be by the rotation of working medium but not the recoil effect provide, but in this example, working medium 3 still belongs to irreversible, after explosive 2 was ignited, flyer promptly separated with working medium 3.
What figure two represented is the lateral plan of engine installation of the present invention.
It comprises: stator 1, stator coil 2, rotor 3, rotor active coil 4, rotor dead coil 5, rotor axle sleeve 6, rotor centroid axle 7, driving band 8, rotor support 9, electric controller, charger and storage battery 10, arrow 11,12,13, direction of current 14,15, rotor junction box 16, electric wire 17, engine installation support 18, generator unit stator 19, generator amature 20, electrical generator mass axis 21, generator pit 22, electrical generator connection box 23, arrow 24, electrical generator 25, arrow 26, engine installation mass axis 27, arrow 28, engine installation 29.
External power (electrical generator etc.) links to each other with controller 10 by lead 17, and when not receiving run signal, controller 10 mainly fills accumulators 10 by charger 10 with electric energy, to guarantee its electric energy abundance.When needs engine installation 29 operation, can be after lead 17 to give controller 10 with electric signal by switch etc., controller 10 is mainly distributed to stator 1 and rotor 3 (also can distribute to stator 1 and rotor 3 through storage battery 10) by lead 17 with electric energy.
When engine installation 29 need provide when rotatablely moving, the electric current by controller 10 control stators 1, rotor 3 makes the application force difference of two stators, thereby makes moment loading that engine installation 29 needing to obtain with rotation.
Rotor 3 and stator 1 mutual action, rotor 3 rotates under torque, and presses direction shown in the arrow 24 through the rotor 20 of driving device (belt 8) drive electrical generator 25 and rotate.Generator unit stator 19 gives rotor 20 with the resisting moment effect in rotation, their effect realizes that by electromagnetic action resisting moment can be converted into electric energy with the kinetic energy of rotor 20, and transfers to charger 10 through lead 17, electric energy is filled accumulators 10, for repeated usage.Resisting moment also reduces the rotating speed of rotor 3 and rotor 20, and has buffer action.
In the mutual action of stator 19 and rotor 20, stator 19 also has been subjected to the antagonistic force that rotor 20 is given, and gives engine installation 29 with moment loading by support 22 and engine installation support 18, for overcoming this problem, will illustrate specially in the explanation of figure three.
Be to reduce power consumption, stator coil 2, rotor dead coil 5 can be used superconductor technologies, rotor active coil 4 utilizes controller 10 its electric currents of control, and is electric to guarantee that rotor active coil 4 gets when the effective acting, cuts off the power supply during invalid acting.
The birds-eye view of figure three expression engine installations.
Figure number 1-figure number 29 among the figure two is identical with figure three, and also comprises engine installation mass axis 31,32 support check screws 30, a in the stator 1, b, four stators of c, d, the A in the rotor 3, B, four rotors of C, D, two electrical generators of the E in the electrical generator, F.
Stator a, b shown in the figure two change A, B, the side schematic view of electrical generator E etc.
Described in figure two explanation, the stator 19 of electrical generator E is subjected to the antagonistic force of rotor 20, produced the moment that engine installation 29 is rotated, same in figure three stator 19 of electrical generator F also be subjected to antagonistic force, and produced moment loading.Because electrical generator E, F mass axis, on same straight line, and the mass axis 27,31,32 with engine installation 29 is symmetrically distributed, by controller 10 control electrical generator E, the charging current size of F and the size of current of stator 1 and rotor 3, make the stator moment equal and opposite in direction (or approaching) of electrical generator E, F, so that two rightabout stator moments of electrical generator E, F are offset, be force couple role because of stator moment again, so offset result is the endogenetic process of engine installation 29, promptly, produce the elastic force effect by support 18 and support 22.
For making electrical generator E, F stator moment direction opposite, rotor A, C hand of rotation are identical, and rotor B, D hand of rotation are identical, and driving band 8 intersects between electrical generator F and rotor C, do not intersect between electrical generator F and rotor D.
In engine installation 29, four control charging current condensers link to each other by lead 17, coordinated with each other, stator 1, rotor 3, electrical generator 25 are unified control, can make engine installation 29 provide with mass axis 31,32 is the moment loading at center, with so that aircraft turns to, and can provide the power of doing motion of translation along mass axis 27, be center of circle steering torque and do motion of translation power but can not provide along mass axis 31 or 32 with mass axis 27.Be head it off, in figure four explanations, will be narrated.
The lateral plan of figure four expressions engine installation of the present invention.
Figure number 1-32 among the figure four is with identical shown in figure two, the figure three, it is corresponding newly to add stator 1 and 3 pairs of aA groups of rotor among arrow 33,34 and auxiliary stator 35 (a ', b ', c ', d ') and the figure three, bB group, cC group, dD group again, form aa ' A group, bb ' B group, cc ' C group, dd ' D group, stator 1 in every group, stator 35 and rotor 3 mutual actions.On, it is consistent to the applied moment direction of rotor 3 that the stator 1 in every group and stator 35 are done the time spent at the same time, and situation stator 1 obtains directive effect power shown in the arrow 11 in figure two, and in such cases, stator 35 is subjected to directive effect power shown in the arrow 33,34.Because a ', b ' in the stator 35 group and c ', d ' group are symmetrically distributed with mass axis 27,31,32 respectively, regulate the electric current of stator 35 and rotor 3 by controller 10, make a ', b ', c ', d ' stator in the stator 35 produce the application force of identical size and Orientation, moment loading between them supports mutually like this, and generation makes engine installation 29 do the power of direction motion of translation shown in the arrow 33,34 along mass axis 32.Change the direction of current of stator 35 or rotor 3, also can do and rightabout linear power shown in the arrow 33,34.The size of current of regulating stator 35 and rotor 3 by control adjuster 10 produces stator 35, with particle axle 27 and mass axis 31 rotating moment, gives the torque that engine installation 29 provides to be needed.
Like this, in the engine installation 29 shown in the figure four, increased auxiliary stator 35, figure three described problems are promptly done motion of translation and are rotated along three mass axis along two mass axis, are achieved.
Claims (8)
1, engine installation of the present invention, consumed power offers aircraft power, electric energy is converted into the mechanical energy of aircraft flight.It is characterized in that stator 1, auxiliary stator 35 pass through electromagnetic action with rotor 3, make rotor 3 be subjected to the moment (non-couple) of stator to be used for rotating, and by 20 rotations of driving device 8 drive generator amatures, the antagonistic force that stator 1, auxiliary stator 35 are subjected to rotor 3 is as power, in order to the power resources of aircraft flight to be provided.
2, engine installation according to claim 1, it is characterized in that utilizing rotor 3, generator amature 20 and driving device 8 to form the working medium that can be recycled, 19 pairs of generator amatures 20 of generator unit stator produce the force couple role that hinders its rotation by electromagnetic action.The momentum that this effect produces and the momentum of aircraft flight, the momentum of working medium is formed conservation of momentum system.This effect makes electrical generator send electricity simultaneously, and fills accumulators 10 for repeated usage by charger 10.
3, engine installation according to claim 1 and 2 is characterized in that: controller is by the coil current size and Orientation of control stator 1, auxiliary stator 35, rotor 3, and the charging stream of control charger is big or small and then the power of control engine installation generation, satisfies the various needs of aircraft flight.
4, it is characterized in that according to claim 1 or 2 or 3 described engine installations: each stator in stator 1 and the stator 35 and each electrical generator in the electrical generator 25 are all with engine installation mass axis or evenly (or the according to certain rules) distribution of aircraft mass axis, the moment loading that stator is produced offsets, and transfer to and do motion of translation power, the force couple role of generator unit stator is supported mutually, produce corresponding elastic force effect.
5, it is characterized in that according to claim 1 or 2 or 3 or 4 described engine installations: can have a kind of between stator 1, auxiliary stator 35 and the rotor 3 is permanent magnet, but can not both be all permanent magnet, the analogy of magnetic field that magnetic field that permanent magnet produces and coil produce.
6, it is characterized in that according to claim 1 or 2 or 3 or 4 or 5 described engine installations: stator coil 2, rotor active coil 4, rotor dead coil 5 can be utilized superconductor technology to reduce power consumption, or the electric current by controller 10 control rotor active coils 4, so that active coil 4 gets when effective acting is electric, cut off the power supply during invalid acting.Or adopt two kinds of methods to combine to reduce power consumption.
7, according to claim 1 or 2 or 3 or 4 or 5 or 6 described engine installations, it is characterized in that:, can add Vane wheel at the spindle nose place of rotor 3, and engine installation is sealed for making the engine installation heat radiation and reducing noise, one end is put into gas port, end dress muffling and exhausting device.
8, according to claim 1 or 2 or 3 or 4 or 5 or 6 or 7 described engine installations, it is characterized in that: replacements such as the also available chain of driving device 8, gear case, and can in driving device, also can add flywheel to play buffering and energy-conserving action.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN99118230A CN1248539A (en) | 1999-08-23 | 1999-08-23 | Power unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN99118230A CN1248539A (en) | 1999-08-23 | 1999-08-23 | Power unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1248539A true CN1248539A (en) | 2000-03-29 |
Family
ID=5280384
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN99118230A Pending CN1248539A (en) | 1999-08-23 | 1999-08-23 | Power unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1248539A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112874820A (en) * | 2021-03-12 | 2021-06-01 | 李奕樵 | Power unit of internal power engine and working method of power unit |
-
1999
- 1999-08-23 CN CN99118230A patent/CN1248539A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112874820A (en) * | 2021-03-12 | 2021-06-01 | 李奕樵 | Power unit of internal power engine and working method of power unit |
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| PB01 | Publication | ||
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |