CN206411910U - Electromagnetic aircraft catapult-assisted take-off device demonstrating model - Google Patents
Electromagnetic aircraft catapult-assisted take-off device demonstrating model Download PDFInfo
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- CN206411910U CN206411910U CN201720095305.4U CN201720095305U CN206411910U CN 206411910 U CN206411910 U CN 206411910U CN 201720095305 U CN201720095305 U CN 201720095305U CN 206411910 U CN206411910 U CN 206411910U
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- ejection
- launching tube
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- deck
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- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims abstract description 14
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 14
- 239000010703 silicon Substances 0.000 claims abstract description 14
- 230000005611 electricity Effects 0.000 claims 2
- 239000000725 suspension Substances 0.000 abstract description 6
- 230000007246 mechanism Effects 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 4
- 230000001276 controlling effect Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003990 capacitor Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000005339 levitation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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Abstract
The utility model is related to a kind of demonstrating model toy；More particularly to a kind of electromagnetic aircraft catapult-assisted take-off device demonstrating model.The characteristics of demonstrating model is that ejection power plant includes launching tube, electromagnetism bullet, large bulk capacitance, booster, controllable silicon and magnet coil；Launching tube outer shroud sets equidistant ring magnet coil；Magnet coil connection control power supply；Launching tube one end is connected with ejection orbit；Large bulk capacitance is located at the other end of launching tube；Electromagnetism bullet is located in launching tube can launch road slip along along launching tube；Charge switch connects controllable silicon, controllable silicon connection booster, booster connection large bulk capacitance, the ejection switch connection large bulk capacitance other end.This electromagnetic aircraft ejector demonstrating model, the mechanical energy ejector capacity usage ratio than electrical energy drive motor is high；It is lower than magnetic suspension mechanism technical requirements precision be more easily implemented and also consume energy will be less than magnetic suspension transmitter, while volume-diminished, weight saving, cost reduction.
Description
Technical field
The utility model is related to a kind of demonstrating model toy；More particularly to a kind of electromagnetic aircraft ejector demonstrating model.
Background technology
Aircraft carrier accounts for the effect for serving flight transfer platform as maritime overlord in naval weapon.The crucial portion of aircraft carrier
One of part ejector is always the big difficult point in aircraft carrier technology.With being skyrocketed through for China's economy, scientific and technological level it is continuous
Lifting, China has had certain economic strength and technical capability to develop the aircraft carrier of oneself.The Liao Dynasty repacked into by watt good lattice number
Peaceful warship aircraft carrier is the real starting point of Chinese aircraft carrier, but it is from what Ukraine bought not complete what aircraft carrier was reequiped by China, at all
Critical component not including ejector, only relatively backward cunning jump formula take-off-helping deck.
Electromagnetic aircraft catapult-assisted take-off device demonstrating model, is the apparatus for demonstrating for simulating military aircraft carrier cataplane, usually controls
Sliding block towing aircraft of the panel control processed on ejection orbit carries out accelerating startup to be allowed to go up to the air.Existing demonstrating model is automatically controlled logical
Motor of overdriving realizes ejection to mechanical energy systems conversion, and energy transformation ratio is low.The ejection platform power consumption of magnetic levitation technology is excessive,
It is unfavorable for the limited aircraft carrier application of energy-storage system.The big cost of the big quality of magentic suspension demonstrating model volume is too high simultaneously.
Utility model content
It is converted into that the mechanical energy driving ejection system energy conversion ratio that does work indirectly is low for electric energy, energy loss is high, and magnetic
The too high problem of the big cost of the big quality of suspension demonstrating model volume, the utility model provides a kind of electromagnetic aircraft ejector demonstration mould
Type；A kind of electromagnetic aircraft catapult-assisted take-off device demonstrating model, includes the carrier-borne aircraft model and the placement carrier-borne aircraft model launched
And the ejection platform of guide rail is provided with, the ejection platform is filled provided with guidance panel, ejection power plant, for the ejection power
Put the charge power supply that energy is provided and maintain the control power supply of whole ejection platform operating；The guidance panel is opened provided with charging
Pass, voltage display, ejection switch and reset switch, the ejection platform are provided with ejection orbit, the ejection orbit and set
There is the traction sliding block that can be slided along ejection orbit, the reset switch connects the ejection power plant simultaneously and the traction is slided
Block；Power supply optical-electrical converter is provided between the charge power supply and the ejection power plant, the carrier-borne aircraft model prow leads to
Cross to buckle and be connected with the traction sliding block on the guide rail,
The ejection power plant includes launching tube, electromagnetism bullet, large bulk capacitance, booster and controllable silicon；The hair
The equidistant ring of shooting cylinder outer wall sets 3n magnet coil；The magnet coil connects the control power supply；Described launching tube one end with
The ejection orbit is connected；The large bulk capacitance is located at the other end of the launching tube；The electromagnetism bullet is located at the hair
Road slip can be launched in shooting cylinder along along the launching tube；The charge switch connects the controllable silicon, and the controllable silicon connects institute
Booster is stated, the booster connects one end of the large bulk capacitance, and it is another that the ejection switch connects the large bulk capacitance
One end.
Preferably, flying-off deck is additionally provided with the ejection platform, it is remote that the flying-off deck is located at the ejection platform
One end of the large bulk capacitance；Described flying-off deck one end and the ejection platform are hinged, under the flying-off deck other end
Electric-controlled hydraulic cylinder is provided between square and described ejection platform side wall, the guidance panel is provided with the regulation electric-controlled hydraulic cylinder
Deck controlling switch.
This electromagnetic aircraft ejector demonstrating model, the mechanical energy ejector capacity usage ratio than electrical energy drive motor is high；Than
Magnetic suspension mechanism technical requirements precision is low to be more easily implemented, and power consumption will be less than magnetic suspension transmitter, while volume-diminished, again
Amount mitigates, cost is substantially reduced.
Brief description of the drawings
Fig. 1 is the electromagnetic aircraft ejector demonstrating model battery schematic top plan view of embodiment 1.
Fig. 2 for embodiment 1 electromagnetic aircraft ejector demonstrating model emission state schematic top plan view.
Fig. 3 is the flying-off deck dimensional structure diagram of embodiment 2；
Fig. 4 for embodiment 2 electromagnetic aircraft ejector demonstrating model emission state schematic top plan view；
It is ejection platform 1, guidance panel 1-1, charge switch 1-1-1, voltage display 1-1-2, ejection switch 1-1-3, multiple
Bit switch 1-1-4, deck controlling switch 1-1-5, ejection power plant 1-2, launching tube 1-2-1, electromagnetism bullet 1-2-2, great Rong
Measure electric capacity 1-2-3, booster 1-2-4, controllable silicon 1-2-5, magnet coil 1-2-6, charge power supply 1-3, control power supply 1-4, bullet
Penetrate track 1-5, traction sliding block 1-5-1, flying-off deck 1-6, electric-controlled hydraulic cylinder 2.
Embodiment
As depicted in figs. 1 and 2, a kind of electromagnetic aircraft ejector demonstrating model, comprising the carrier-borne aircraft model that is launched and puts
The carrier-borne aircraft model and the ejection platform 1 provided with guide rail are put, the ejection platform 1 is provided with guidance panel 1-1, ejection power
Device 1-2, the charge power supply 1-3 that energy is provided for the ejection power plant 1-2 and the control for maintaining whole ejection platform 1 to operate
Power supply 1-4 processed；The guidance panel 1-1 provided with charge switch 1-1-1, voltage display 1-1-2, ejection switch 1-1-3 and
Reset switch 1-1-4, the ejection platform 1 is provided with ejection orbit 1-5, and the ejection orbit 1-5 is provided with can be along ejection rail
The traction sliding block 1-5-1 that road 1-5 is slided, the reset switch 1-1-4 connect the ejection power plant 1-2 and described led simultaneously
Draw sliding block 1-5-1；Power supply optical-electrical converter, the warship are provided between the charge power supply 1-3 and the ejection power plant 1-2
Carrier aircraft model prow is connected by buckling with the traction sliding block 1-5-1 on the guide rail.
The ejection power plant 1-2 includes launching tube 1-2-1, electromagnetism bullet 1-2-2, large bulk capacitance 1-2-3, boosting
Device 1-2-4 and controllable silicon 1-2-5；The equidistant ring of launching tube 1-2-1 outer walls sets 3n magnet coil 1-2-6；The electromagnetism
The coil 1-2-6 connections control power supply 1-4；Launching tube one end 1-2-1 is connected with the ejection orbit 1-5；It is described big
Capacity 1-2-3 is located at the other end of the launching tube 1-2-1；The electromagnetism bullet 1-2-2 is located at the launching tube 1-2-1
It is interior to launch road slip along along the launching tube 1-2-1；The charge switch 1-1-1 connections controllable silicon 1-2-5, it is described can
Control the silicon 1-2-5 connections booster 1-2-4, one end of the booster 1-2-4 connections large bulk capacitance 1-2-3, institute
State the ejection switch 1-1-3 connections large bulk capacitance 1-2-3 other ends.
As the demonstrating model of an aircraft carrier, the Control system architecture for being originally utility model ejection platform is prior art,
Technology focuses on the improvement of ejection power presentation mode, employs the approximate principle of magnetic artillery, and its course of work is：It is sharp first
Ejection sliding block is pulled to automatic reset device the end of the guide rail of ejection platform i.e. close to one end of launching tube, while by electromagnetism
Bullet pulls to the end of launching tube i.e. close to one end of electric capacity, recycles battery, is charged by booster to capacitor bank, when
When the magnitude of voltage that charging voltage display is shown does not increase, stop charging, the nose-gear of remote-controlled model aircraft is hung over into traction
The buckling of sliding block is put just, shifts the remote control switch that takes off onto maximum, remote-controlled model aircraft is in takeoff condition, and flicking ejection is opened
Close, capacitance group sparks, in the presence of magnet coil, the traction sliding block on electromagnetism bullet fast ram slide rail, sliding block band
Dynamic remote-controlled model aircraft so far completes catapult-assisted take-off operation by catapult-assisted take-off.
Before model aircraft startup, tail can be hung on an interceptor, and interceptor is position-limiting action, can use hook
The similar position limiting structure such as spring.Until after charging is finished, the moment of projectile strike sliding block, unclamp interceptor.
Data parameters are explained：Voltage display is conventional voltage table, and launching tube barrel material is the low metal of magnetic conductivity, is risen
Depressor is testing transformer；Electromagnetism bullet is the high metal derby of magnetic conductivity, and magnet coil n takes positive integer, controllable silicon model example
For KG5A-50A, large bulk capacitance example is EPCOS-BT262；The control of charge power supply voltage is in below 36V, control power supply 10V
To between 20V be less than charge power supply.Data above is only a sample, and concrete model and laying relation can be specific according to demand
Adjustment.
Power supply control circuit is controlled, electromagnetism bullet can be made by the power output of photoelectric controller regulating winding
Ramp up.High power capacity position can be changed, and be not only limited to launching tube end, as long as to bullet when can realize transmitting
Ball accelerates to provide energy.Launching tube length can be increased, increase bullet stroke, be allowed to sliding block collision rift together to previous
Segment distance.
Embodiment 2
As shown in Figure 3 and Figure 4, flying-off deck 1-6, the flying-off deck 1-6 are additionally provided with the ejection platform 1 and is located at institute
State the one end of ejection platform 1 away from the large bulk capacitance 1-2-3；Described flying-off deck 1-6 one end and the ejection platform 1 are cut with scissors
Connect, be provided with electric-controlled hydraulic cylinder 2, the operating surface below the flying-off deck 1-6 other ends between the side wall of the ejection platform 1
Plate 1-1 is provided with the deck controlling switch 1-1-5 for adjusting the electric-controlled hydraulic cylinder 2.
The holding circuit and operated key of flying-off deck, flying-off deck and ejection platform are set up on original guidance panel
It is hinged, ejection finishes rear and folding storage and saves volume, and flying-off deck surface is the circular arc of one section and ejection platform plane tangent
Mechanism, provides a small lift angle while model aircraft accelerates to take off, further reduces the knot of aircraft carrier ejection platform
There is provided more accurate demonstrating model extremely minutia for structure.Possess stronger theory teaching example and convincingness.
Above-described embodiment, has been carried out further to the purpose of the present invention, technical scheme and beneficial effect
Describe in detail, should be understood that the embodiment that the foregoing is only the present invention, be not limited to this hair
Bright, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc. should be included in the present invention
Protection domain within.
Claims (2)
1. a kind of electromagnetic aircraft catapult-assisted take-off device demonstrating model, includes the carrier-borne aircraft model and the placement carrier-borne aircraft mould launched
Type and the ejection platform (1) provided with guide rail, the ejection platform (1) are provided with guidance panel (1-1), ejection power plant (1-
2), provide the charge power supply (1-3) of energy for the ejection power plant (1-2) and maintain whole ejection platform (1) operating
Control power supply (1-4)；The guidance panel (1-1) is opened provided with charge switch (1-1-1), voltage display (1-1-2), ejection
(1-1-3) and reset switch (1-1-4) are closed, the ejection platform (1) is provided with ejection orbit (1-5), the ejection orbit (1-
5) provided with the traction sliding block (1-5-1) that can be slided along ejection orbit (1-5), the reset switch (1-1-4) while connecting institute
State ejection power plant (1-2) and the traction sliding block (1-5-1)；The charge power supply (1-3) and the ejection power plant
Power supply optical-electrical converter is provided between (1-2), the carrier-borne aircraft model prow is by buckling and the traction sliding block on the guide rail
(1-5-1) is connected, it is characterised in that
The ejection power plant (1-2) include launching tube (1-2-1), electromagnetism bullet (1-2-2), large bulk capacitance (1-2-3),
Booster (1-2-4) and controllable silicon (1-2-5)；The equidistant ring of launching tube (1-2-1) outer wall sets 3n magnet coil (1-2-
6)；Magnet coil (1-2-6) the connection control power supply (1-4)；Described launching tube (1-2-1) one end and the ejection rail
Road (1-5) is connected；The large bulk capacitance (1-2-3) is located at the other end of the launching tube (1-2-1)；The electromagnetism bullet
(1-2-2), which is located in the launching tube (1-2-1), to be slided in transmitting road along along the launching tube (1-2-1)；The charge switch
(1-1-1) connects the controllable silicon (1-2-5), and the controllable silicon (1-2-5) connects the booster (1-2-4), the boosting
Device (1-2-4) connects one end of the large bulk capacitance (1-2-3), and the ejection switch (1-1-3) connects the Large Copacity electricity
Hold (1-2-3) other end.
2. electromagnetic aircraft catapult-assisted take-off device demonstrating model according to claim 1, it is characterised in that the ejection platform
(1) flying-off deck (1-6) is additionally provided with, the flying-off deck (1-6) is located at the ejection platform (1) away from Large Copacity electricity
Hold the one end of (1-2-3)；Described flying-off deck (1-6) one end and the ejection platform (1) are hinged, the flying-off deck (1-6)
Electric-controlled hydraulic cylinder (2) is provided with below the other end between the wall of the ejection platform (1) side, the guidance panel (1-1) is provided with
Adjust the deck controlling switch (1-1-5) of the electric-controlled hydraulic cylinder (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720095305.4U CN206411910U (en) | 2017-01-24 | 2017-01-24 | Electromagnetic aircraft catapult-assisted take-off device demonstrating model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720095305.4U CN206411910U (en) | 2017-01-24 | 2017-01-24 | Electromagnetic aircraft catapult-assisted take-off device demonstrating model |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206411910U true CN206411910U (en) | 2017-08-15 |
Family
ID=59557439
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720095305.4U Expired - Fee Related CN206411910U (en) | 2017-01-24 | 2017-01-24 | Electromagnetic aircraft catapult-assisted take-off device demonstrating model |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206411910U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109102746A (en) * | 2018-09-04 | 2018-12-28 | 佛山科学技术学院 | A kind of electromagnetic ejection system |
| CN114504833A (en) * | 2022-02-25 | 2022-05-17 | 威康(深圳)智能有限公司 | Electromagnetic power intelligent ejection method and device |
-
2017
- 2017-01-24 CN CN201720095305.4U patent/CN206411910U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109102746A (en) * | 2018-09-04 | 2018-12-28 | 佛山科学技术学院 | A kind of electromagnetic ejection system |
| CN114504833A (en) * | 2022-02-25 | 2022-05-17 | 威康(深圳)智能有限公司 | Electromagnetic power intelligent ejection method and device |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170815 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |