阅读说明：本技术 一种脉冲磁震弹射器 (Pulse magnetic vibration catapult ) 是由 肖瑞文 于 2020-12-30 设计创作，主要内容包括：一种脉冲磁震弹射器,包括电源、供电控制板、与供电控制板连接的U型弹射导轨以及设置在U型弹射导轨上滑动连接的弹射牵引器,弹射牵引器是框架结构滑块,滑块内嵌有至少四对上下两块对称配置的正负磁极相间的磁铁；U型弹射导轨的左右两侧壁对称嵌装有绕组沿长度方向串联连接构成的矽钢片绕组单元阵列；矽钢片绕组单元包括两个相向配置的线圈,矽钢片绕组单元由电源供电产生磁场,电源是超大功率变频脉冲发生器。本发明结构简单,技术难度小,制作成本低,维护方便,节能显著。同等条件下与现有使用永磁直线同步电机的电磁弹射器对比,节能至少40％。本发明采用无地线方式供电不仅可以降低脉冲幅度,降低电刷消耗量,而且省去了地线。(A pulse magnetic shock catapult comprises a power supply, a power supply control panel, a U-shaped catapult guide rail connected with the power supply control panel and a catapult tractor arranged on the U-shaped catapult guide rail in a sliding connection manner, wherein the catapult tractor is a frame structure slide block, and at least four pairs of magnets with alternate positive and negative magnetic poles which are symmetrically arranged up and down are embedded in the slide block; the left side wall and the right side wall of the U-shaped ejection guide rail are symmetrically embedded with a silicon steel sheet winding unit array formed by connecting windings in series along the length direction; the silicon steel sheet winding unit comprises two coils which are arranged oppositely, the silicon steel sheet winding unit is powered by a power supply to generate a magnetic field, and the power supply is an ultra-high power variable frequency pulse generator. The invention has the advantages of simple structure, small technical difficulty, low manufacturing cost, convenient maintenance and obvious energy saving. Compared with the existing electromagnetic catapult using the permanent magnet linear synchronous motor under the same condition, the energy is saved by at least 40 percent. The invention adopts the mode of no ground wire to supply power, which not only can reduce the pulse amplitude and reduce the consumption of the electric brush, but also saves the ground wire.)

1. The utility model provides a pulse magnetism shakes catapult, including the power, with power supply control board that the power is connected, with the U type that power supply control board is connected launches the guide rail, and set up and be in on the U type launches the guide rail and with U type launches guide rail sliding connection's ejection tractor, the U type launch the guide rail with it constitutes high thrust density's sharp advancing device to launch the tractor, its characterized in that:

the ejection tractor is a frame structure sliding block consisting of a bottom plate and a frame, at least four pairs of magnets with alternate positive and negative magnetic poles which are symmetrically arranged up and down are embedded in the sliding block, the frame is fixed on the bottom plate, the arrangement and combination of the magnets in the ejection tractor meet the condition of a closed-loop magnetic circuit, all magnetic lines of force of the magnets in the ejection tractor are shielded in the U-shaped ejection guide rail, and the ejection tractor is electrically connected with the power supply control board;

the U-shaped ejection guide rail is a U-shaped slot, silicon steel sheet winding unit arrays formed by sequentially connecting windings in series forwards along the length direction are symmetrically embedded in the left side wall and the right side wall of the U-shaped slot, and the number of the silicon steel sheet winding units is at least several times of the number of magnets in the ejection retractor;

the silicon steel sheet winding unit comprises two coils which are oppositely arranged on the left side wall and the right side wall of the U-shaped slot respectively, the wire inlet end of the left coil is connected with the wire outlet end of the right coil of the previous silicon steel sheet winding unit, the wire outlet end of the left coil is connected with the wire inlet end of the right coil, the wire outlet end of the right coil is connected with the wire inlet end of the left coil of the next silicon steel sheet winding unit, the closed-loop magnetic circuit condition is met according to the right-hand rule, and the silicon steel sheet winding unit and the internal magnet of the ejection tractor form a closed-loop magnetic circuit;

the silicon steel sheet winding units in the U-shaped ejection guide rail are powered by the power supply to generate a magnetic field, if the magnetic polarities of one silicon steel sheet winding unit in the silicon steel sheet winding unit array and one magnet in the ejection tractor are the same, electromagnetic oscillation, namely magnetic vibration, is generated to form huge repulsive force, a magnetic field moving forwards is formed between the silicon steel sheet winding units in the U-shaped ejection guide rail, and the magnet in the ejection tractor in the magnetic field and the ejection tractor slide forwards along the U-shaped ejection guide rail under the action of ampere force;

the power is super large power frequency conversion pulse generator, and the frequency conversion pulse signal that the synchronous positive negative pulse of output constitutes is low frequency pulse signal when launching the start, launch the low-speed forward slip of tractor, be high frequency pulse signal when launching, it slides to the front to launch the tractor high-speed.

2. The pulsed magnetic shock ejector of claim 1, wherein: .

The ultra-high power variable frequency pulse generator is connected with the silicon steel sheet winding unit in the U-shaped ejection guide rail in a ground-wire-free mode through the power supply control board and the electric brush.

3. The pulsed magnetic shock ejector according to claim 1 or 2, wherein:

the power of a synchronous positive and negative pulse signal output by the ultra-high power frequency conversion pulse generator is at least 5 kilovolt-ampere, the voltage amplitude is at least 145 volt, the current amplitude is at least 225 ampere, the pulse frequency is at most 650 Hz, and the pulse width is closely related to the number of turns of a coil of a silicon steel sheet winding unit in the U-shaped ejection guide rail and the magnetic permeability of the silicon steel sheet.

4. The pulsed magnetic shock ejector of claim 1, wherein:

the utility model discloses a silicon steel sheet winding unit, including silicon steel sheet winding unit, power supply control board, serial number in the brush, the brush one end that is the odd number in the brush and the negative pulse output of power are connected, the other end that the serial number is the odd number in the brush passes through the gleitbretter and corresponds silicon steel sheet winding unit links, the brush one end that the serial number is the even number in the brush with the positive pulse output of power is connected, the other end that the serial number is the even number in the brush passes through the gleitbretter and corresponds silicon steel sheet winding unit links, only is the local power supply of a part of silicon steel sheet winding unit that is in operating condition.

5. The pulsed magnetic shock ejector of claim 1 or 4 wherein:

the power supply control board is characterized in that the front end of the power supply control board is provided with an ejection locking pile for limiting the farthest position of the ejection tractor sliding towards the front, and the rear end of the power supply control board is provided with a reset locking pile for limiting the reset position of the ejection tractor sliding towards the rear.

6. The pulsed magnetic shock ejector of claim 1, wherein:

the bottom plate of the ejection tractor is one of an aluminum alloy bottom plate and a high-strength bakelite bottom plate, the frame of the ejection tractor is a bakelite frame, and the frame is fixed on the bottom plate through bolts.

7. The pulsed magnetic shock ejector according to claim 1 or 6, wherein:

the ejection tractor is provided with an aircraft carrier hook, and a front wheel of an aircraft carrier waiting for ejection is hooked on the aircraft carrier hook.

8. The pulsed magnetic shock ejector of claim 1, wherein:

the silicon steel sheet lamination thickness of the silicon steel sheet winding unit in the U-shaped ejection guide rail is at least 0.5 m.

9. The pulsed magnetic shock ejector of claim 1 or 8 wherein:

the length of the U-shaped ejection guide rail is at least 100 meters.

10. The pulsed magnetic shock ejector of claim 1 or 8 wherein:

the U-shaped ejection guide rail is arranged on a front platform of the carrier-based aircraft hangar at the rear half part of the aircraft carrier sliding deck, and the rear edge of the U-shaped ejection guide rail is connected with the ground of the carrier-based aircraft hangar in the same plane.

Technical Field

The invention relates to an object ejection device, in particular to a pulse magnetic vibration ejector.

Background

The electromagnetic ejection technology is a new energy ejection linear propulsion technology, and belongs to one of core technologies of aircraft carriers (hereinafter referred to as aircraft carriers). The electromagnetic energy is adopted to push the ejected object to be linearly propelled outwards, the ejected object does not start a power device of the ejected object but takes off by the aid of starting power given by the ejector, and the electromagnetic energy catapult is suitable for short-distance launching, such as accelerating an aircraft carrier with the weight of about 30 tons to the ship-off speed of more than 140 nautical miles per hour within a distance of less than 100 meters, and has wide application prospect in military, civil and industrial fields. An electromagnetic catapult adopted by the existing aircraft carrier-based aircraft sequentially cuts magnetic induction lines by electrifying an electrifying coil stator which is laid flat and fixed on a guide rail and cannot move to generate Lorentz force, the ampere force accumulated by the Lorentz force is vertical to the position of the electrifying coil stator, and the aircraft carrier-based aircraft serving as a movable body rotor is propelled forwards along a linear guide rail under the action of the ampere force. The ampere force is in direct proportion to the square of the current, and as long as enough current is input, enough propelling force can be generated, so that the ejected aircraft carrier has higher speed. The electromagnetic catapult has replaced a steam catapult to become the mainstream due to the advantages of low use cost, small power loss, capability of being adjusted according to the tonnage of an aircraft carrier and the like. The nuclear power aircraft carrier directly converts the power output by the engine into electric energy by adopting the full-electric propulsion aircraft carrier, avoids the loss of a transmission mechanism, has smaller loss in the energy transmission process, can reserve richer electric energy for the electromagnetic catapult theoretically, and is really more suitable for being assembled with the electromagnetic catapult from the selection of a power system. Compared with a conventional power aircraft carrier, the nuclear power aircraft carrier is more abundant in power, so that more energy can be remained for generating power after the power required by the ship for sailing is supplied. However, the power supply devices of the electromagnetic ejection systems used by the existing non-nuclear power aircraft carriers are all permanent magnet linear synchronous motor type, and have the defects of complex structure, high technical difficulty, extremely strict requirements on electric power and high electric power requirement. The pulse magnetic shock catapult applied to catapult carrier-based aircraft of the aircraft carrier is not found in the Chinese patent database.

Disclosure of Invention

The invention aims to provide a pulse magnetic vibration ejector to solve the technical problems in the prior art.

Therefore, the invention provides a pulse magnetic vibration ejector.

The pulse magnetic shock ejector comprises a power supply, a power supply control board connected with the power supply, a U-shaped ejection guide rail connected with the power supply control board, and an ejection tractor arranged on the U-shaped ejection guide rail and connected with the U-shaped ejection guide rail in a sliding manner, wherein the U-shaped ejection guide rail and the ejection tractor form a high-thrust-density linear propulsion device.

The pulse magnetic vibration catapult is characterized in that:

the ejection tractor is a frame construction slider of compriseing bottom plate and frame, and the slider is embedded to have four at least alternate magnets of positive and negative magnetic pole to two piece upper and lower symmetric configurations, the frame is fixed on the bottom plate, the permutation and combination of the interior magnet of ejection tractor satisfies closed loop magnetic circuit condition, all magnetic lines of force of the interior magnet of ejection tractor are all shielded in the U type ejection guide rail, can not cause magnetic interference to the instrument of the aircraft carrier that the ejection tractor was towed, the magnetism of the interior magnet of ejection tractor is stronger, and the ejection energy that contributes is big more, ejection tractor with no electric connection between the power supply control board, ejection tractor does not consume the electric energy, can compensate the current electromagnetism that uses permanent magnetism linear synchronous motor and launch the defect that the system needs the forceful electric energy.

The U-shaped ejection guide rail is a U-shaped slot, silicon steel sheet winding unit arrays formed by sequentially connecting windings in series forwards along the length direction are symmetrically embedded in the left side wall and the right side wall of the U-shaped slot, and the number of the silicon steel sheet winding units is at least several times that of magnets in the ejection retractor.

The silicon steel sheet winding unit comprises two coils which are oppositely arranged on the left side wall and the right side wall of the U-shaped slot, the wire inlet end of the left coil is connected with the wire outlet end of the right coil of the previous silicon steel sheet winding unit, the wire outlet end of the left coil is connected with the wire inlet end of the right coil, the wire outlet end of the right coil is connected with the wire inlet end of the left coil of the next silicon steel sheet winding unit, the closed-loop magnetic circuit condition is met according to the right-hand rule, and the silicon steel sheet winding unit and the magnet in the ejection tractor form a closed-loop magnetic circuit.

The silicon steel sheet winding units in the U-shaped ejection guide rail are powered by the power supply to generate a magnetic field, if the magnetic polarities of one silicon steel sheet winding unit of the silicon steel sheet winding unit array and one magnet in the ejection tractor are the same, electromagnetic oscillation, namely magnetic vibration, is generated to form huge repulsive force, a magnetic field moving forward is formed between the silicon steel sheet winding units in the U-shaped ejection guide rail, the ampere force accumulated by the Lorentz force generated by the magnetic field is vertical to the position of the electrified silicon steel sheet winding unit, the magnet in the ejection tractor in the magnetic field and the ejection tractor slide along the U-shaped ejection guide rail to the front under the action of the ampere force, and the ejection tractor drives a carrier aircraft carrier to eject and fly away from a ship along the U-shaped ejection guide rail to the front, so that magnetic ejection vibration is realized.

The power is super large power frequency conversion pulse generator, and the frequency conversion pulse signal that the synchronous positive and negative pulse of output constitutes is low frequency pulse signal when launching the start, launch the low-speed forward slip of tractor, be high frequency pulse signal when launching, launch the high-speed forward slip of tractor, adopt pulse power supply can also avoid silicon steel sheet winding unit to produce the magnetic saturation phenomenon, the coil is very little from the loss, further compensaties that current electromagnetic that uses permanent magnetism linear synchronous motor launches the defect that the system structure is complicated, the technical difficulty is big and need the forceful electric energy.

Preferably, the invention can also have the following technical features:

the ultra-high power variable frequency pulse generator is connected with the silicon steel sheet winding unit in the U-shaped ejection guide rail in a ground-free mode through the power supply control board and the electric brush, so that the pulse amplitude can be reduced, the consumption of the electric brush is reduced, and the defects that the existing electromagnetic ejection system using the permanent magnet linear synchronous motor is complex in structure, high in technical difficulty and high in electric energy requirement are further overcome.

The power of a synchronous positive and negative pulse signal output by the ultra-high power frequency conversion pulse generator is at least 5 kilovolt-ampere, the voltage amplitude is at least 145 volt, the current amplitude is at least 225 ampere, the pulse frequency is at most 650 Hz, the pulse width is closely related to the number of turns of a coil of a silicon steel sheet winding unit in the U-shaped ejection guide rail and the magnetic permeability of the silicon steel sheet, and the pulse width is adjusted and determined in a test run.

The power supply control board is arranged below the U-shaped ejection guide rail, the power supply control board is provided with electric brushes the number of which is half of that of the silicon steel sheet winding units along the length direction, one end of the brush with the odd number in the brushes is connected with the negative pulse output end of the power supply, the other end of the brush with the odd number in the brushes is linked with the corresponding silicon steel sheet winding unit through a slide sheet, one end of the electric brush with the even number in the electric brushes is connected with the positive pulse output end of the power supply, the other end of each brush with the even number is linked with the corresponding silicon steel sheet winding unit through a sliding sheet, only a part of silicon steel sheet winding units in a working state are locally powered, and the defects that an existing electromagnetic ejection system using the permanent magnet linear synchronous motor is complex in structure, high in technical difficulty and high in electric energy requirement are further overcome.

Preferably, the present invention may also have the following further technical features:

the power supply control board is characterized in that the front end of the power supply control board is provided with an ejection locking pile for limiting the farthest position of the ejection tractor sliding towards the front, and the rear end of the power supply control board is provided with a reset locking pile for limiting the reset position of the ejection tractor sliding towards the rear.

The bottom plate of the ejection tractor is one of an aluminum alloy bottom plate and a high-strength bakelite bottom plate, the frame of the ejection tractor is a bakelite frame, and the frame is fixed on the bottom plate through bolts.

The ejection tractor is provided with an aircraft carrier hook, and a front wheel of an aircraft carrier waiting for ejection is hooked on the aircraft carrier hook.

The silicon steel sheet lamination thickness of the silicon steel sheet winding unit in the U-shaped ejection guide rail is at least 0.5 m.

The length of the U-shaped ejection guide rail is at least 100 meters.

The U-shaped ejection guide rail is arranged on a front platform of the carrier-based aircraft hangar at the rear half part of the aircraft carrier sliding deck, and the rear edge of the U-shaped ejection guide rail is connected with the ground of the carrier-based aircraft hangar in the same plane.

Compared with the prior art, the invention has the following beneficial effects:

the structure is simple, the technical difficulty is small, the manufacturing cost is low, the maintenance is convenient, and the energy conservation is remarkable. Compared with the existing electromagnetic catapult using the permanent magnet linear synchronous motor, the energy is saved by at least 40 percent under the same condition. The energy-saving technical measures comprise: the ejection tractor is not electrically connected with the power supply control board, the ejection tractor does not consume electric energy, the pulse power supply can also avoid the magnetic saturation phenomenon of the silicon steel sheet winding unit, the coil self-loss is very small, and the power supply control board only supplies power to part of the silicon steel sheet winding unit in the working state. The energy-saving technical measures also include that in the preferred scheme, the pulse amplitude can be reduced and the consumption of the electric brush can be reduced by adopting a ground wire-free mode for power supply, and the ground wire is omitted, so that the further technical effect of being beneficial to the safety of a power supply circuit is achieved.

Drawings

FIG. 1 is a schematic diagram of the external appearance of an embodiment of the present invention;

figure 2 is a cross-sectional schematic view of the U-shaped ejector rail and ejector retractor of figure 1;

figure 3 is an operational schematic view of the ejection retractor of figure 1 during ejection.

The numbers in the above figures are labeled as follows:

the device comprises a power supply 1, a power supply control board 2, a U-shaped ejection guide rail 3, an ejection tractor 4, an aluminum alloy bottom plate 5, a bakelite frame 6, a magnet 7, a bolt 8, an aircraft carrier hook 9, a silicon steel sheet winding unit 10, an electric brush 11, an ejection lock pile 12, a reset lock pile 13, a left coil incoming line end 14 and a right coil outgoing line end 15.

Detailed Description

The foregoing has outlined rather broadly the features and technical advantages of the present invention in order that the detailed description of the invention that follows may be better understood, and in order that the detailed description of the invention that follows may be better understood. It should be appreciated by those skilled in the art that the conception and specific embodiment disclosed may be readily utilized as a basis for modifying or designing other structures for carrying out the same purposes of the present invention. It should also be realized by those skilled in the art that such equivalent constructions do not depart from the spirit and scope of the invention. The novel features which are believed to be characteristic of the invention, both as to its organization and method of operation, together with further objects and advantages will be better understood from the following description when considered in connection with the accompanying figures. It is to be expressly understood, however, that each of the figures is provided for the purpose of illustration and description only and is not intended as a definition of the limits of the present invention.

The invention relates to an international patent classification chart with main functionality, belonging to aircraft carrier deck facilities and further belonging to a launching or dragging device of an aircraft carrier-based aircraft using an ejector; the classification of international patent classification with auxiliary applicability belongs to a propulsion system which makes a rigid body move along a path under the mutual electric action between an object and a magnetic field traveling along the path.

Non-limiting and non-exclusive embodiments will now be described with reference to figures 1, 2, and 3, in which like reference numerals refer to like parts throughout figures 1, 2, and 3, unless otherwise specifically noted.

Example (b): pulse magnetic shock ejector for aircraft carrier

The pulse magnetic shock catapult for the aircraft carrier is arranged on the rear half part of a sliding deck of an aircraft carrier and comprises a power supply 1, a power supply control board 2 connected with the power supply 1, a U-shaped catapult guide rail 3 connected with the power supply control board 2, and a catapult tractor 4 arranged on the U-shaped catapult guide rail 3 and connected with the U-shaped catapult guide rail 3 in a sliding mode, wherein the U-shaped catapult guide rail 3 and the catapult tractor 4 form a high-thrust-density linear propulsion device, and the aircraft carrier waiting for catapult is arranged on the U-shaped catapult guide rail 3 in a crossing mode. The front end of the power supply control board 2 is provided with an ejection lock peg 12 for limiting the farthest position of the ejection retractor 4 sliding forward, and the rear end of the power supply control board 2 is provided with a reset lock peg 13 for limiting the reset position of the ejection retractor 4 sliding backward.

The ejection tractor 4 is a frame structure sliding block consisting of an aluminum alloy bottom plate 5 and a bakelite frame 6, at least four pairs of magnets 7 with alternate positive and negative magnetic poles which are symmetrically arranged up and down are embedded in the sliding block, the bakelite frame 6 is fixed on the aluminum alloy bottom plate 5 through bolts 8, the arrangement and combination of the magnets 7 in the ejection tractor 4 meet the condition of a closed-loop magnetic circuit, all magnetic lines of force of the magnets 7 in the ejection tractor 4 are shielded in the U-shaped ejection guide rail 3, and magnetic interference on instruments of an aircraft carrier pulled by the ejection tractor 4 cannot be caused. The catapult tractor 4 is provided with an aircraft carrier hook 9, and a front wheel of the aircraft carrier waiting for catapult is hooked on the aircraft carrier hook 9.

The U-shaped ejection guide rail 3 is a U-shaped slot with the length of 100 meters, the left side wall and the right side wall of the U-shaped slot are symmetrically embedded with silicon steel sheet winding unit 10 arrays formed by sequentially connecting windings in series forwards along the length direction, the number of the silicon steel sheet winding units 10 is at least multiple of the number of magnets 7 in the ejection tractor 4, the thickness of a silicon steel sheet laminated layer of the silicon steel sheet winding units 10 is 0.5 meter, the U-shaped ejection guide rail 3 is arranged on the front stage of a carrier-based hangar at the rear half part of an aircraft carrier sliding deck, and the rear side of the U-shaped ejection guide rail 3 is connected with the ground of the carrier-based hangar of the aircraft carrier in the same plane.

The power supply control board 2 is arranged below the U-shaped ejection guide rail 3, the power supply control board 2 is provided with electric brushes 11 the number of which is half of that of the silicon steel sheet winding units 10 along the length direction, one end of the electric brush with the odd number in the electric brushes 11 is connected with the negative pulse output end of the power supply 1, the other end of the electric brush with the odd number in the electric brushes 11 is linked with the corresponding silicon steel sheet winding unit 10 through a sliding sheet, one end of the electric brush with the even number in the electric brushes 11 is connected with the positive pulse output end of the power supply 1, the other end of the electric brush with the even number in the electric brushes 11 is linked with the corresponding silicon steel sheet winding unit 10 through a sliding sheet, only partial power supply is carried out on a part of the silicon steel sheet winding units 10 in the working state, and the structure complexity of the existing, technical difficulty and need of strong electric energy.

The front end of the power supply control board 2 is provided with an ejection lock peg 12 for limiting the farthest position of the ejection retractor 4 sliding forward, and the rear end of the power supply control board 2 is provided with a reset lock peg 13 for limiting the reset position of the ejection retractor 4 sliding backward.

The silicon steel sheet winding unit 10 comprises two coils which are oppositely arranged on the left side wall and the right side wall of a U-shaped slot, a left coil inlet end 14 is connected with a right coil outlet end of a previous silicon steel sheet winding unit 10, a left coil outlet end is connected with a right coil inlet end, a right coil outlet end 15 is connected with a left coil inlet end of a next silicon steel sheet winding unit 10, closed-loop magnetic circuit conditions are met according to right-hand rules, the silicon steel sheet winding unit 10 and an electromagnet 7 in an ejection tractor 4 form a closed-loop magnetic circuit, the ejection tractor 4 does not consume electric energy, and the defect that an existing electromagnetic ejection system using a permanent magnet linear synchronous motor needs strong electric energy can be overcome.

The silicon steel sheet winding units 10 in the U-shaped ejection guide rail 3 are powered by the power supply 1 to generate a magnetic field, if the magnetic polarities of one silicon steel sheet winding unit 10 in the silicon steel sheet winding unit array and one magnet 7 in the ejection tractor 4 are the same, electromagnetic oscillation, namely magnetic shock, is generated to form huge repulsive force, a magnetic field moving forward is formed between the silicon steel sheet winding units 10 in the U-shaped ejection guide rail 3, ampere force generated by the magnetic field and accumulated by Lorentz force is vertical to the position of the electrified silicon steel sheet winding unit 10, the magnet 7 in the ejection tractor 4 in the magnetic field and the ejection tractor 4 slide forward along the U-shaped ejection guide rail 3 under the action of the ampere force, and the ejection tractor 4 drives the aircraft carrier to eject forwards along the U-shaped ejection guide rail 3 to fly away from the aircraft carrier, so that magnetic shock ejection is realized.

The power source 1 is an ultra-high power frequency conversion pulse generator, outputs a frequency conversion pulse signal consisting of synchronous positive and negative pulses, the power of the synchronous positive and negative pulse signal output by the ultra-high power frequency conversion pulse generator is at least 5 kilovolt-ampere, the voltage amplitude is at least 145 volt, the current amplitude is at least 225 ampere, the pulse frequency is up to 650 Hz, the pulse width is closely related to the number of turns of a coil of a silicon steel sheet winding unit 10 in the U-shaped ejection guide rail 3 and the magnetic permeability of the silicon steel sheet, and the adjustment is determined in a trial run. The ultra-high power frequency conversion pulse generator is connected with a silicon steel sheet winding unit 10 in a U-shaped ejection guide rail 3 in a ground-wire-free mode through a power supply control board 2 and an electric brush 11, pulse low-frequency power supply is performed when ejection is started, an ejection tractor 4 slides to the front at a low speed, pulse high-frequency power supply is changed when ejection is performed, the ejection tractor 4 slides to the front at a high speed, and the power supply 1 is connected with the silicon steel sheet winding unit 10 in the U-shaped ejection guide rail 3 in a ground-wire-free mode, so that the pulse amplitude can be reduced, the consumption of the electric brush is reduced, and the defects that the existing electromagnetic ejection system using a permanent magnet linear synchronous motor is complex in structure.

The operation process of the ejection retractor of the embodiment in the ejection and reset is as follows:

the thickness of the laminated silicon steel sheet layer of the silicon steel sheet winding unit 10 of this embodiment is 0.5 m. The silicon steel sheet winding unit 10 is powered by the ultra-high power variable frequency pulse generator to push the ejection tractor 4 to be pushed forward, and the ejection tractor 4 is pushed forward by four positive and negative pulses in one cycle, wherein the number of the positive and negative pulses is about 2 meters, and one step is a quarter cycle.

When the power supply control board 2 lags behind the ejection tractor 4 by a quarter period, the magnetic polarity of the magnet 7 in the ejection tractor 4 is the same as the magnetic polarity of the corresponding winding of the silicon steel sheet winding unit 10 array, which is generated by the power supply 1, magnetic shock is generated to form a huge repulsive force, a magnetic field moving forward is formed between the silicon steel sheet winding units 10 in the U-shaped ejection guide rail 3, the ampere force generated by the Lorentz force generated by the magnetic field is vertical to the position of the electrified silicon steel sheet winding unit 10, the magnet 7 in the ejection tractor 4 in the magnetic field and the ejection tractor 4 slide along the U-shaped ejection guide rail 3 to the front under the action of the ampere force, and the ejection tractor 4 drives the carrier aircraft carrier to carry out ejection flight to the front along the U-shaped ejection guide rail 3, so that magnetic shock ejection is realized.

When the power supply control board 2 advances one fourth period relative to the ejection tractor 4, the magnetic polarity of the magnet 7 in the ejection tractor 4 is the same as the magnetic polarity generated by the power supply 1 of the corresponding winding of the silicon steel sheet winding unit 10 array, magnetic shock is generated, huge repulsive force is formed, a magnetic field moving backwards is formed between the silicon steel sheet winding units 10 in the U-shaped ejection guide rail 3, the ampere force generated by the Lorentz force generated by the magnetic field is vertical to the position of the electrified silicon steel sheet winding unit 10, the magnet 7 in the ejection tractor 4 in the magnetic field and the ejection tractor 4 slide backwards along the U-shaped ejection guide rail 3 under the action of the ampere force, and the ejection tractor 4 slides backwards along the U-shaped ejection guide rail 3 to complete resetting.

Those skilled in the art will recognize that numerous variations are possible in light of the above description, and thus the example is intended to describe only one particular implementation.

While there has been described and illustrated what are considered to be example embodiments of the present invention, it will be understood by those skilled in the art that various changes and substitutions may be made therein without departing from the spirit of the invention. In addition, many modifications may be made to adapt a particular situation to the teachings of the present invention without departing from the central concept described herein. Therefore, it is intended that the invention not be limited to the particular embodiments disclosed, but that the invention will include all embodiments and equivalents falling within the scope of the invention.