CN208134648U - A kind of catapult for aeroplane - Google Patents
A kind of catapult for aeroplane Download PDFInfo
- Publication number
- CN208134648U CN208134648U CN201820673070.7U CN201820673070U CN208134648U CN 208134648 U CN208134648 U CN 208134648U CN 201820673070 U CN201820673070 U CN 201820673070U CN 208134648 U CN208134648 U CN 208134648U
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- slip portion
- track
- catapult
- aeroplane
- follower
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Abstract
The utility model provides a kind of catapult for aeroplane, it is related to vehicle launch technical field, the power device for solving catapult-launching gear existing in the prior art is mounted directly in orbit or extends the coasting distance before aircraft takeoff caused by being mounted on other tracks with parallel track.The catapult for aeroplane includes follower slip portion, active slip portion, the first track and the second track, wherein：First track is obliquely installed；Follower slip portion is slidably disposed on the first track；Active slip portion is slidably disposed on the second track；Active slip portion is connect with follower slip portion；For catapult for aeroplane in use, aircraft is mounted in follower slip portion, follower slip portion is initially located at the first track low order end；Active slip portion is slided on the second track drives follower slip portion accelerated slip on the first track, and when follower slip portion is slided to the first track high order end, aircraft is detached from transmitting from follower slip portion.The utility model is for reducing the distance that aircraft slides in orbit.
Description
Technical field
The utility model relates to vehicle launch technical fields, more particularly, to a kind of catapult for aeroplane.
Background technique
Before aircraft takeoff, needs to carry out accelerating sliding race on runway, just be taken off after having enough takeoff speeds
It takes off from the ground.In this process, engine is being worked always with maximum duty, extremely the consumption energy, and what is needed slides
Distance, to site requirements height.
To solve the above problems, the vehicle launch that aircraft catapult transmitting form is increasingly becoming mainstream in the world today rises
Fly form, is particularly suitable for small aircraft, such as unmanned plane, model plane.Common aircraft takeoff ejection side domestic and international at present
Formula can mainly be attributed to following a few classes：Booster rocket ejection, the ejection of pneumatic sliding rail, the ejection of hydraulic sliding rail, the ejection of electromagnetism sliding rail etc..
Catapult-launching gear using above-mentioned several ejection modes that take off includes two parts of track and power device, power dress
Set and drive aircraft accelerated slip in orbit, aircraft accelerated slip to certain speed or when having arrived rail flanges from slideway
Upper disengaging is taken off.
Above-mentioned aircraft takeoff ejection mode accelerates the sliding mode of taking off run with apparent advantage relative to parallel runways.
Applicant have discovered that it equally exists following technical problem：The power device of the catapult-launching gear of the prior art is mounted directly in-orbit
It on road or is mounted on other tracks with parallel track, the distance that aircraft slides on runway can be only achieved certain farther out
Take off initial velocity.
Utility model content
The purpose of this utility model is to provide a kind of catapult for aeroplane, to solve ejection existing in the prior art
The power device of device is mounted directly in orbit or extends caused by being mounted on other tracks with parallel track winged
Row device take off before coasting distance.Optimal technical scheme in many technical solutions provided by the utility model can be generated all
The elaboration as detailed below of more technical effects (energy conversion rate improves and shorten coasting distance).
To achieve the above object, the utility model provides following technical scheme：
A kind of catapult for aeroplane provided by the utility model, including follower slip portion, active slip portion, the first track
And second track, wherein：First track is obliquely installed；The follower slip portion is slidably disposed in first rail
On road；The active slip portion is slidably disposed on second track；The active slip portion and the follower slip
Portion's connection；The catapult for aeroplane is in use, aircraft is mounted in the follower slip portion, at the beginning of the follower slip portion
Begin to be located at the first track low order end；The active slip portion is slided on second track drives the follower slip portion
The accelerated slip on first track, when the follower slip portion is slided to the first track high order end, the flight
Device is detached from transmitting from the follower slip portion.
Preferably, second track is horizontally disposed.
Preferably, the catapult for aeroplane further includes that bracket is placed in ejection, and the aircraft is put by the ejection
Bracket is set to be mounted in the follower slip portion；The follower slip portion the active slip portion drive under accelerated slip when,
The ejection places bracket and controls aircraft accelerated slip together；Follower slip portion accelerated slip is to first rail
When road high order end, control of the bracket releasing to the aircraft is placed in the ejection.
Preferably, the catapult for aeroplane further includes traction mechanism, and the follower slip portion passes through the dragger
Structure is connect with the active slip portion, wherein：The traction mechanism includes the first traction rope and at least one angle pulley, institute
It states first traction rope one end to connect with the follower slip portion, the first traction rope other end is after angle pulley steering
It is connect with active slip portion one end.
Preferably, the traction mechanism further includes balancing spring, balancing spring one end fixed setting, the equilibrium bomb
The spring other end is connect with the active slip portion other end；When the catapult for aeroplane is in without using state, it is described from
Dynamic sliding part slides to the first track low order end under the effect of gravity and passes sequentially through first traction rope and described
Active slip portion stretches the balancing spring, and the balancing spring, which is stretched, to be generated pulling force and make the follower slip portion is static to set
It sets.
Preferably, the active slip portion is ferromagnetic bullet, and second track is Electromagnetic Launching pipe, the Electromagnetic Launching
Pipe can generate magnetic force after being powered and the ferromagnetic bullet is driven to accelerate sliding in the Electromagnetic Launching pipe.
Preferably, the Electromagnetic Launching pipe includes tube body, at least one level electromagnetic coil and circuit control system, wherein：
Electromagnetic coil described at least one level is wound in the tube surfaces, and the ferromagnetic bullet is set to the tubular body, the electricity
Path control system is powered to the electromagnetic coil, and the electromagnetic coil generates magnetic field force, and the ferromagnetic bullet is made to generate initial velocity.
Preferably, the catapult for aeroplane further includes support construction, and the support construction is set as triangular prism, described
First track is set on the inclined-plane of the triangular prism, and second track is set in the right-angle surface of the triangular prism.
A kind of catapult for aeroplane provided by the utility model, has the following technical effects：
(1) catapult for aeroplane being made of active slip portion, follower slip portion, the first track and the second track,
The active slip portion being placed on the second track drives and is placed in the follower slip portion on the first track being obliquely installed, to make to be placed in
Aircraft in follower slip portion is moved to high order end from low order end, compared with being placed in horizontal aircraft runway phase in technology
Than being greatly reduced the distance that aircraft slides on runway.
(2) preferred the second track of technical solution of the utility model is horizontal positioned, with the angled setting phase of the second track
Than the active slip portion being placed on the second track can be improved the sliding effect for driving the follower slip portion on the first track that is placed in
Rate reduces the waste of energy.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is only
It is some embodiments of the utility model, for those of ordinary skill in the art, in the premise not made the creative labor
Under, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is a kind of structural schematic diagram of catapult for aeroplane of the utility model；
Fig. 2 is the circuit diagram of the circuit control system of the utility model.
1, first track in figure；101, follower slip portion；2, the second track；201, active slip portion；22, ferromagnetic bullet；
3, bracket is placed in ejection；4, driven sliding block；5, the first traction rope；6, the first angle pulley；7, the second angle pulley；8, equilibrium bomb
Spring；9, Electromagnetic Launching pipe；91, tube body；92, electromagnetic coil；93, circuit control system；10, aircraft；11, support construction.
Specific embodiment
To keep the purpose of this utility model, technical solution and advantage clearer, below by the technology to the utility model
Scheme is described in detail.Obviously, the described embodiments are only a part of the embodiments of the utility model, rather than all
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are not before making creative work
Obtained all other embodiment is put, the range that the utility model is protected is belonged to.
A kind of catapult for aeroplane provided by the utility model, as shown in Figure 1, including follower slip portion 101, actively sliding
Dynamic portion 201, the first track 1 and the second track 2, follower slip portion 101 are slidably disposed at the first track 1 being obliquely installed
On, active slip portion 201 is slidably disposed on the second track 2, and active slip portion 201 is connect with follower slip portion 101, is driven
Follower slip portion 101 is slided, and specific implementation follows the steps below：
(1) aircraft 10 to be launched is placed in follower slip portion 101, follower slip portion 101 is initially located at the first track 1
Low order end；
(2) it when the active slip portion 201 on the second track 2 is to a Slideslip, drives follower slip portion 101 to slide, makes
Follower slip portion 101 slides into high order end from the acceleration of the low order end of the first track 1；
(3) when follower slip portion 101 is slided from 1 low order end of the first track to the first 1 high order end of track, aircraft 10 is obtained
Certain initial velocity is detached from from follower slip portion 101, completes emission state.
The power device of prior art catapult for aeroplane be generally all directly installed on on the same track of aircraft 10,
Or on the track parallel with aircraft 10, the initial velocity certain to acquisition of aircraft 10 needs to slide larger distance, and
Power device is placed on another track in the lower section angled with aircraft 10 by the utility model, the master as power device
Dynamic sliding part 201 drives follower slip portion 101 to slide into high order end from the low order end of the first track 1, greatly shortens existing
Aircraft 10 sliding distance when taking off.
Optionally embodiment, as shown in Figure 1, the second track 2 is horizontal positioned, with the angled setting of the second track 2
It compares, the active slip portion 201 being placed on the second track 2 can be improved drive and be placed in the follower slip portion 101 on the first track 1
Sliding efficiency, improve the conversion ratio of energy.
Optionally embodiment, as shown in Figure 1, catapult for aeroplane further includes that bracket 3, ejection are placed in ejection
Place bracket 3 be fixedly connected with follower slip portion 101, wherein follower slip portion 101 be driven sliding block 4, ejection place bracket 3 and
The specific connection type of driven sliding block 4 is to place 3 bottom plate center of bracket in ejection to make a call to four and four screw positions in driven sliding block 4
Set corresponding through-hole, when installation, the hole for first placing ejection on bracket 3 is corresponding with four threaded holes in driven sliding block 4,
One group of double nut is first installed, then respectively by four screw rotation such as threaded holes of driven sliding block 4, adjustment is to top spiral shell on screw
3 bottom plate of bracket is placed to ejection is held out against in female position, to achieve the purpose that fixed.
Follower slip portion 101 is in accelerated slip under active slip portion 201 drives, that is, driven sliding block 4 is sliding in active
When dynamic portion 201 drives lower accelerated slip, ejection places bracket 3 and controls the accelerated slip together of aircraft 10, and driven sliding block 4 accelerates to slide
Row to the first track 1 high order end when, be placed in ejection and place aircraft 10 on bracket 3 due to inertia motion, obtain one and rise
Control of the releasing of bracket 3 to aircraft 10 is placed in winged initial velocity, ejection.
Optionally embodiment, as shown in Figure 1, catapult for aeroplane further includes traction mechanism, wherein driven cunning
Block 4 is connect by traction mechanism with active slip portion 201, and traction mechanism includes the first traction rope 5 and two angle pulleies,
Wherein the first angle pulley 6 is placed in the high order end of the first track 1, and the second angle pulley 7 is placed on the second track 2, and is located at
The underface of first angle pulley 6,5 one end of the first traction rope are connect with driven sliding block 4, and 5 other end of the first traction rope is through first
Angle pulley 6 and the second angle pulley 7 are connect after turning to 201 one end of active slip portion.
The direction that the first traction rope 5 can be changed using two angle pulleies, connect it with active slip portion 201, again
The frictional force between the first traction rope 5 and the first track 1 and the second track 2 can be reduced, this kind of set-up mode is by sliding friction
It is converted into force of rolling friction, greatly improves energy conversion efficiency.
Optionally embodiment, as shown in Figure 1, traction mechanism further includes balancing spring 8,8 one end of balancing spring is solid
Fixed setting, the other end are connect with 201 other end of active slip portion.
When catapult for aeroplane is in without using state, oriented first track 1 is low under gravity for driven sliding block 4
The trend that slides of position end, and pass sequentially through the first traction rope 5 and active slip portion 201 stretches balancing spring 8, at this time equilibrium bomb
Spring 8 generates pulling force, is still in follower slip portion 101 on first track 1, avoids continuing sliding to the low order end of the first track 1
Row.
Optionally embodiment, as shown in Figure 1, active slip portion 201 is ferromagnetic bullet 22, the second track 2 is electricity
Magnetic transmitting tube 9 generates magnetic field force after Electromagnetic Launching pipe 9 is powered, and makes ferromagnetic bullet 22 by close to one end of the second deflecting roller
Accelerate sliding to one end far from the second deflecting roller, so that driven sliding block 4 is moved to a high position from low order end by the first traction rope 5
The transmitting of aircraft 10 is completed at end.
The wherein effect played in the preferred embodiment of balancing spring 8 is：Due to the quality phase of ferromagnetic bullet 22
It is light more for aircraft 10, therefore the phenomenon that will appear reverse drawing in towed flight device 10, i.e., ferromagnetic transmitting tube generation
Instantaneous high-intensity magnetic field attraction is generated to ferromagnetic bullet 22, it is winged to drive that ferromagnetic bullet 22 also will pull the first traction rope 5 simultaneously
Row device 10.According to Newton's law, active force is with the reaction force size same direction on the contrary, the aircraft 10 to be driven also can be right
Ferromagnetic bullet 22 generates counter pull, and ferromagnetic bullet 22 will be returned by reverse drawing, second level coil can not be reached, without subsequent power.
And after balancing spring 8 is connect with ferromagnetic bullet 22 at this time, when reverse drawing occurs, balancing spring 8 can also stretched, ferromagnetic bullet 22
Or it can be moved under rebound effect to the direction far from the second deflecting roller, it can be ensured that reach subsequent coil.Experiments have shown that
If a distance of the dragged advance very little of aircraft 10, ferromagnetic bullet 22 goes out transmitting tube by reverse drawing without balancing spring 8,
The wirerope that ferromagnetic bullet 22 is connected with driven sliding block 4 is in relaxation state or even wirerope can be from the first angle pulley 6 and
Two angle pulleies 7 fall off.More serious, aircraft 10 will not move completely, and only ferromagnetic bullet 22 is by reverse drawing.
Optionally embodiment, as shown in Figure 1, Electromagnetic Launching pipe 9 includes tube body 91, at least one level electromagnetic coil 92
And circuit control system 93, multistage electromagnetic coil 92 are wound in 91 surface of tube body, ferromagnetic bullet 22 is set to inside tube body 91,
Circuit control system 93 is powered to electromagnetic coil 92, and electromagnetic coil 92 generates magnetic field force, and ferromagnetic bullet is made to generate initial velocity, ferromagnetic
Bullet 22 is slided along the second track 2 to far from the second angle pulley 7.
Wherein, circuit control system 93 is broadly divided into two big modules, as shown in Fig. 2, being charging circuit and discharge circuit.
Charging circuit：The charged switch of power supply is connected to boost module, is then connected to capacitor, parallel with one another between capacitor；
First order discharge circuit：Power supply connects protective resistance and is connected to silicon-controlled control end, the anode of capacitor through discharge switch
One end of wiring circle, the cathode of capacitor connect silicon-controlled cathode, and silicon-controlled anode connects the other end in coil.From the point of view of simplifying,
Regard a switch, capacitor and coils from parallel connection of coils as silicon-controlled, only adds among the cathode line in its both threads in parallel
One " switch ", and silicon-controlled control is equivalent to control another " switch " of this " switch " opening, that is, opens electric discharge
Switch, silicon-controlled control grade have current signal input, then silicon-controlled internal circuit connection, at this moment the line of capacitor and coils from parallel connection of coils
Road is realized to coil discharge by access；
Following stages discharge circuit：Identical as first order discharge circuit, coil is in parallel with capacitor, accesses in parallel wire controllable
Silicon, which is not uniquely both silicon-controlled control, to be controlled by the control of optoelectronic switch.The anode and cathode of optoelectronic switch connects the yin of power supply respectively
The power supply of positive grade, optoelectronic switch individually can supply or be used in conjunction with same power supply.
Optionally embodiment, as shown in Figure 1, catapult for aeroplane further includes support construction 11, support construction
11 are set as triangular prism, and one of triangular prism right-angle surface is placed horizontally at ground, another direct face of triangular prism and are placed in first
For the first traction rope 5 between angle pulley 6 and the second angle pulley 7 at parallel line surface, the first track is placed in the inclined-plane of triangular prism
On, the second track is set in the right-angle surface of triangular prism being parallel to the horizontal plane.
Above description is only a specific implementation of the present invention, but the protection scope of the utility model is not limited to
In this, anyone skilled in the art within the technical scope disclosed by the utility model, can readily occur in variation
Or replacement, it should be covered within the scope of the utility model.Therefore, the protection scope of the utility model should be with the power
Subject to the protection scope that benefit requires.
Claims (8)
1. a kind of catapult for aeroplane, which is characterized in that including follower slip portion, active slip portion, the first track and
Two tracks, wherein：
First track is obliquely installed；The follower slip portion is slidably disposed on first track；The active
Sliding part is slidably disposed on second track；The active slip portion is connect with the follower slip portion；
For the catapult for aeroplane in use, aircraft is mounted in the follower slip portion, the follower slip portion is initial
Positioned at the first track low order end；The active slip portion is slided on second track drives the follower slip portion to exist
Accelerated slip on first track, when the follower slip portion is slided to the first track high order end, the aircraft
Transmitting is detached from from the follower slip portion.
2. catapult for aeroplane according to claim 1, which is characterized in that second track is horizontally disposed.
3. catapult for aeroplane according to claim 1, which is characterized in that the catapult for aeroplane further includes bullet
Placement bracket is penetrated, the aircraft is placed bracket by the ejection and is mounted in the follower slip portion；The follower slip
In accelerated slip under the active slip portion drives, the ejection places the bracket control aircraft and accelerates to slide together in portion
Row；When follower slip portion accelerated slip to the first track high order end, the ejection is placed bracket and released to fly to described
The control of row device.
4. catapult for aeroplane according to claim 3, which is characterized in that the catapult for aeroplane further includes leading
Draw mechanism, the follower slip portion is connect by the traction mechanism with the active slip portion, wherein：
The traction mechanism include the first traction rope and at least one angle pulley, first traction rope one end and it is described from
Dynamic sliding part connection, the first traction rope other end connect after angle pulley steering with active slip portion one end
It connects.
5. catapult for aeroplane according to claim 4, which is characterized in that the traction mechanism further includes equilibrium bomb
Spring, balancing spring one end fixed setting, the balancing spring other end are connect with the active slip portion other end；It is described
When catapult for aeroplane is in without using state, the follower slip portion is under the effect of gravity to the first track low order end
It slides and passes sequentially through first traction rope and the active slip portion stretches the balancing spring, the balancing spring quilt
Stretching generation pulling force makes the static setting in follower slip portion.
6. catapult for aeroplane according to claim 5, which is characterized in that the active slip portion is ferromagnetic bullet,
Second track is Electromagnetic Launching pipe, and the Electromagnetic Launching pipe can generate magnetic force after being powered and the ferromagnetic bullet is driven to exist
Accelerate sliding in the Electromagnetic Launching pipe.
7. catapult for aeroplane according to claim 6, which is characterized in that the Electromagnetic Launching pipe includes tube body, extremely
Few level-one electromagnetic coil and circuit control system, wherein：
Electromagnetic coil described at least one level is wound in the tube surfaces, and the ferromagnetic bullet is set to the tubular body, institute
It states circuit control system to be powered to the electromagnetic coil, the electromagnetic coil generates magnetic field force, generates the ferromagnetic bullet just
Speed.
8. -7 any catapult for aeroplane according to claim 1, which is characterized in that the catapult for aeroplane is also
Including support construction, the support construction is set as triangular prism, and first track is set on the inclined-plane of the triangular prism, institute
The second track is stated to be set in the right-angle surface of the triangular prism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820673070.7U CN208134648U (en) | 2018-05-07 | 2018-05-07 | A kind of catapult for aeroplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820673070.7U CN208134648U (en) | 2018-05-07 | 2018-05-07 | A kind of catapult for aeroplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208134648U true CN208134648U (en) | 2018-11-23 |
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ID=64313050
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820673070.7U Expired - Fee Related CN208134648U (en) | 2018-05-07 | 2018-05-07 | A kind of catapult for aeroplane |
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| Country | Link |
|---|---|
| CN (1) | CN208134648U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113353260A (en) * | 2021-06-17 | 2021-09-07 | 淮阴工学院 | Medium-short distance emission type transportation device and method |
-
2018
- 2018-05-07 CN CN201820673070.7U patent/CN208134648U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113353260A (en) * | 2021-06-17 | 2021-09-07 | 淮阴工学院 | Medium-short distance emission type transportation device and method |
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Legal Events
| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181123 Termination date: 20190507 |