CN1329247C - Contactless plate type emitter electromagnetic propulsion system - Google Patents
Contactless plate type emitter electromagnetic propulsion system Download PDFInfo
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- CN1329247C CN1329247C CNB031324932A CN03132493A CN1329247C CN 1329247 C CN1329247 C CN 1329247C CN B031324932 A CNB031324932 A CN B031324932A CN 03132493 A CN03132493 A CN 03132493A CN 1329247 C CN1329247 C CN 1329247C
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Abstract
The present invention provides a contactless platy emitter electromagnetic propulsion system, and relates to a straight-line electromagnetic propeller in high pulse heavy current discharge technique. The present invention comprises a conveying device, wings and two groups of electromagnetic propellers, wherein the wings are symmetrically fixed on both sides of the conveying device; the two groups of electromagnetic propellers are symmetrically arranged on the left side and the right side of the conveying device by using the central line of the conveying device as a symmetry axis; the center of each of the electromagnetic propellers is provided with a straight-line wing running channel which is communicated with space where the conveying device is; the wings on both of the two sides of the conveying device are respectively arranged in the wing running channels in the two groups of electromagnetic propellers; each group of the electromagnetic propellers comprises double-row coils which are respectively arranged above and below the wing running channels, upper coils and lower coils of the double-row coils; the amplitude values, the directions and the alternative frequencies and input current of the double-row coils are identical; the upper coils and the lower coils are symmetrically arranged up and down by using the horizontal central surfaces of the wing running channels as symmetry planes. The present invention has the advantages of low cost, good controllability, low unit load transportation cost and repeated use.
Description
Technical field: the linear electromagnetic propelling unit that the present invention relates to a kind of high impulse heavy-current discharge technology.
Background technology: the existing space vehicle relies on traditional gunpowder propulsion mode, and its shortcoming is that vehicle costs an arm and a leg, capacity weight is low, load per unit cost of transportation height, vehicle can not repeated usagies and launch preparation time is long.
Summary of the invention: for solving the expensive problem that the existing space vehicle exists, the present invention develops the tabular emitter electromagnetic propulsion of a kind of no touch system.The present invention comprises wing 4-1 that vehicle 4, symmetry be fixed on vehicle 4 both sides, be two groups of electromagnetic propellers 6 that axis of symmetry is symmetricly set on vehicle 4 left and right sides with the line of centers of vehicle 4; The center of electromagnetic propeller 6 be provided with connect with space, vehicle 4 place and the wing operation passage 3 of shape linearly, the wing 4-1 of vehicle 4 both sides is separately positioned in two groups of wings operation passages 3 in the electromagnetic propeller 6; Every group of electromagnetic propeller 6 comprises the biserial coil that is separately positioned on wing operation passage 3 upper and lowers, and the last coil 6-1 of the biserial coil that the current amplitude of feeding, direction and sweep frequency are all identical and lower coil 6-2 are that the plane of symmetry is symmetrical arranged up and down mutually with the horizontal central plane of wing operation passage 3.The present invention is a kind of biserial no touch linear electromagnetic propelling unit, and this invention obtains the good speed characteristic of emitter by rational electromagnetic structure design.The present invention has that cost is low, controllability is good, low, the reusable advantage of load per unit cost of transportation.
Description of drawings: Fig. 1 is a structural representation of the present invention, and Fig. 2 is the structural representation of one group of electromagnetic propeller 6, and Fig. 3 is the circuit diagram of the specific embodiment one, and Fig. 4 is the structural representation of the specific embodiment two, and Fig. 5 is the circuit diagram of the specific embodiment two.
The specific embodiment one: consult Fig. 1, Fig. 2, Fig. 3, present embodiment is fixed on the wing 4-1 of vehicle 4 both sides, is that two groups of electromagnetic propellers 6 that axis of symmetry is symmetricly set on vehicle 4 left and right sides are formed with the line of centers of vehicle 4 by alternating source 13, pressure regulator 14, charger 15, high voltage silicon rectifier stack 16, current-limiting resistance 17, discharge switch 18, impulse capacitor group 19, vehicle 4, symmetry; The center of electromagnetic propeller 6 be provided with connect with space, vehicle 4 place and the wing operation passage 3 of shape linearly, the wing 4-1 of vehicle 4 both sides is separately positioned in two groups of wings operation passages 3 in the electromagnetic propeller 6; Every group of electromagnetic propeller 6 comprises the biserial coil that is separately positioned on wing operation passage 3 upper and lowers and forms, and the last coil 6-1 of the biserial coil that the current amplitude of feeding, direction and sweep frequency are all identical and lower coil 6-2 are that the plane of symmetry is symmetrical arranged up and down mutually with the horizontal central plane of wing operation passage 3.Alternating source 13 two ends are connected with two input ends of pressure regulator 14 respectively, two mouths of pressure regulator 14 are connected with two input ends of charger 15 respectively, a mouth of charger 15 links to each other with the positive pole of high voltage silicon rectifier stack 16, one end of the negative pole connecting resistance 17 of high voltage silicon rectifier stack 16, the positive pole of another termination cond group 19 of resistance 17, the negative pole of cond group 19 connects another mouth and the ground connection of charger 15, and is in parallel with impulse capacitor group 19 after the coil of the series connected electromagnetic propeller 6 of biserial coil is connected with discharge switch 18.Must the structure strict symmetry of the bilateral drive coil of present embodiment (about comprising, about), this structure guarantees that the electromagnetic force that emitter is subjected to is in symmetry status (above-below direction and left and right directions), has saved the emitter levitation device.Accelerating part comprises emitter empennage or flank, when reaching final velocity, starts tripper, and redundance will break away from automatically.
The specific embodiment two: consult Fig. 4, Fig. 5, what present embodiment and the specific embodiment one were different is, every group of electromagnetic propeller 6 has n to the biserial coil, and individual upward coil 6-1 of its n and lower coil 6-are word order respectively along the sense of motion of vehicle 4, and are installed on the fixed mount 5.The side that coil 6-1 and lower coil 6-2 are positioned at wing 4-1 sense of motion on each respectively is provided with a position transduser 7.Coil 6-1 and lower coil 6-2 are connected in series on every pair, the break of last coil 6-1 and the disconnected termination charge switch of lower coil 6-2 10-1, discharge switch 10-2 is connected in parallel on the contact heel and lower coil 6-2 and last coil 6-1 front of motor of charge switch 10-1, and the pulse power 11 is connected in parallel on the two ends of discharge switch 10-2.Outside at two groups of electromagnetic propellers 6 of vehicle 4 both sides is covered with a screening can 1, and electromagnetic propeller 6 is respectively equipped with screen layer 8 along the front and back side of vehicle 4 sense of motions in screening can I, has vehicle emission port 20 on screen layer 8 and the screening can 1.Initiating terminal at wing operation passage 3 is provided with mechanical catapult-launching gear 2.The outside of the screen layer 8 outside being positioned at also is provided with can be with the plate washer 9 of its vehicle emission port 20 opening and closing.The speed of the emitter of single-stage electromagnetic launcher is limited, and practical space vehicle need be made multilevel hierarchy.Multistage electromagnetic propulsion system comprises two major parts: prepare radiating portion and emitter propulsive units, total system conductively-closed shell 1 is isolated from the outside.The height up and down of preparing to carry out in the radiating portion emitter and about the adjustment of distance.Enter second portion after being ready to, emitter can certain speed enter (mechanical device springs into), also can be placed on a certain position in the first order coil.The emitter propulsive units mainly is that a plurality of single-stage biserial non-contact type electromagnetic propellers are formed, and coil is made up of last coil 6-1 and lower coil 6-2, and coil links to each other with the pulse power 11 with 10-2 by switch 10-1.After the pulse power is ready to, close switch 10-1, the pulse power charges to coil inductance, when the electric current in the coil reaches maxim, close switch 10-2.From the second stage, the current"on"time of drive coil is by position transduser 7 control, and position transduser and the drive coil frame 5 that is fixed is fixed together.Emitter velocity increment through every grade of coil is unequal under the same conditions.The speed of emitter is recorded by speed sensor, and when emitter reached the speed that needs, follow-up drive coil just can be disconnected power supply.Open baffle plate 9 when emitter reaches afterbody, emitter breaks away from this electromagnetic propulsion system, and unnecessary accelerating part will break away from automatically.Drive coil progression how much be the velocity magnitude decision that needs by emitter.The specific embodiment one and two circuit structure can exchange.
The specific embodiment three: consult Fig. 4, what present embodiment and the specific embodiment two were different is that screening can 1 inside is evacuated.Can reduce air resistance and radiation like this.
Claims (9)
1, the tabular emitter electromagnetic propulsion of no touch system is characterized in that wing (4-1) that it comprises vehicle (4), symmetry and be fixed on vehicle (4) both sides, is two groups of electromagnetic propellers (6) that axis of symmetry is symmetricly set on vehicle (4) left and right sides with the line of centers of vehicle (4); Wing operation passage (3) that the center of electromagnetic propeller (6) is provided with and vehicle (4) space, place connects and linearly shape, the wing that the wing (4-1) of vehicle (4) both sides is separately positioned in two groups of electromagnetic propellers (6) moves in the passage (3); Every group of electromagnetic propeller (6) comprises the biserial coil that is separately positioned on wing operation passage (3) upper and lower, and the last coil (6-1) of the biserial coil that the current amplitude of feeding, direction and sweep frequency are all identical and lower coil (6-2) are that the plane of symmetry is symmetrical arranged up and down mutually with the horizontal central plane of wing operation passage (3).
2, the tabular emitter electromagnetic propulsion of no touch according to claim 1 system, it is characterized in that it also includes alternating source (13), pressure regulator (14), charger (15), high voltage silicon rectifier stack (16), current-limiting resistance (17), discharge switch (18), impulse capacitor group (19), alternating source (13) two ends are connected with two input ends of pressure regulator (14) respectively, two mouths of pressure regulator (14) are connected with the input end of charger (15) respectively, a mouth of charger (15) links to each other with the positive pole of high voltage silicon rectifier stack (16), one end of the negative pole connecting resistance (17) of high voltage silicon rectifier stack (16), the positive pole of another termination cond group (19) of resistance (17), the negative pole of cond group (19) connects another mouth and the ground connection of charger (15), and is in parallel with impulse capacitor group (19) after the series connected electromagnetic propeller of biserial coil (6) is connected with discharge switch (18).
3, the tabular emitter electromagnetic propulsion of no touch according to claim 1 system, it is characterized in that every group of electromagnetic propeller (6) has n to the biserial coil, individual upward coil (6-1) of its n and lower coil (6-2) are word order respectively along the sense of motion of vehicle (4), and are installed on the fixed mount (5).
4, the tabular emitter electromagnetic propulsion of no touch according to claim 3 system is characterized in that the side that coil on each (6-1) and lower coil (6-2) are positioned at wing (4) sense of motion respectively is provided with a position transduser (7).
5, according to claim 3 or the tabular emitter electromagnetic propulsion of 4 described no touchs system, it is characterized in that every pair of last coil (6-1) and lower coil (6-2) are connected in series, the break of last coil (6-1) and the disconnected termination charge switch of lower coil (6-2) (10-1), discharge switch (10-2) is connected in parallel on the contact heel and lower coil (6-2) and last coil (6-1) front of motor of charge switch (10-1), and the pulse power (11) is connected in parallel on the two ends of discharge switch (10-2).
6, the tabular emitter electromagnetic propulsion of no touch according to claim 3 system, it is characterized in that being covered with a screening can (1) in the outside of two groups of electromagnetic propellers (6) of vehicle (4) both sides, electromagnetic propeller (6) is respectively equipped with screen layer (8) along the front and back side of vehicle (4) sense of motion in screening can (1), and screen layer (8) and screening can (1) have vehicle emission port (20).
7, the tabular emitter electromagnetic propulsion of no touch according to claim 3 system is characterized in that being provided with mechanical catapult-launching gear (2) at the initiating terminal of wing operation passage (3).
8, the tabular emitter electromagnetic propulsion of no touch according to claim 6 system, the outside of the screen layer (8) outside it is characterized in that being positioned at also is provided with can be with the plate washer (9) of its vehicle emission port (20) opening and closing.
9, the tabular emitter electromagnetic propulsion of no touch according to claim 8 system is characterized in that screening can (1) inside is evacuated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031324932A CN1329247C (en) | 2003-07-09 | 2003-07-09 | Contactless plate type emitter electromagnetic propulsion system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031324932A CN1329247C (en) | 2003-07-09 | 2003-07-09 | Contactless plate type emitter electromagnetic propulsion system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1477029A CN1477029A (en) | 2004-02-25 |
| CN1329247C true CN1329247C (en) | 2007-08-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB031324932A Expired - Lifetime CN1329247C (en) | 2003-07-09 | 2003-07-09 | Contactless plate type emitter electromagnetic propulsion system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1892209B (en) * | 2005-07-07 | 2010-05-26 | 日本特殊陶业株式会社 | Lamina-type gas sensor element and gas sensor |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009076793A1 (en) * | 2007-12-17 | 2009-06-25 | Yang, Hong | Electromagnetic ejector for mini-sitellite and spacecraft on the moon |
| CN101823562A (en) * | 2009-10-29 | 2010-09-08 | 杨伦华 | Electromagnetic aircraft launch system for small scientific satellite spacecrafts on moon |
| CN105048762A (en) * | 2015-08-24 | 2015-11-11 | 中国科学院电工研究所 | 7-phase multistage linear induced electromagnetic propeller |
| CN106585961A (en) * | 2015-10-14 | 2017-04-26 | 熵零控股股份有限公司 | Fixed-wing aircraft |
| CN108407824B (en) * | 2018-04-26 | 2020-04-28 | 西南交通大学 | Multi-wing reconnection type electromagnetic propulsion device for train driving and use method |
| CN108680058B (en) * | 2018-07-18 | 2023-06-27 | 西南交通大学 | Multilayer multi-wing type reconnection electromagnetic emission device |
| CN111780615A (en) * | 2019-04-04 | 2020-10-16 | 南京理工大学 | Electromagnetic coil emitting device capable of automatically adjusting initial speed |
-
2003
- 2003-07-09 CN CNB031324932A patent/CN1329247C/en not_active Expired - Lifetime
Non-Patent Citations (3)
| Title |
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| A single-stage reconnection gun c.r.hummer,c.e.hollandsworth,NTIS 1992 * |
| A single-stage reconnection gun c.r.hummer,c.e.hollandsworth,NTIS 1992;STARTRAM:a new approach for low-cost earth-to-orbittransport james R.powell等,IEEE,Vol.2001年第5卷 2001 * |
| STARTRAM:a new approach for low-cost earth-to-orbittransport james R.powell等,IEEE,Vol.2001年第5卷 2001 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1892209B (en) * | 2005-07-07 | 2010-05-26 | 日本特殊陶业株式会社 | Lamina-type gas sensor element and gas sensor |
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| CN1477029A (en) | 2004-02-25 |
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Granted publication date: 20070801 |