CN106314796A - Ejection device - Google Patents
Ejection device Download PDFInfo
- Publication number
- CN106314796A CN106314796A CN201610805098.7A CN201610805098A CN106314796A CN 106314796 A CN106314796 A CN 106314796A CN 201610805098 A CN201610805098 A CN 201610805098A CN 106314796 A CN106314796 A CN 106314796A
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- CN
- China
- Prior art keywords
- nacelle
- catapult
- push rod
- launching gear
- transport facility
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000000694 effects Effects 0.000 claims description 5
- 230000011664 signaling Effects 0.000 claims 1
- 230000032258 transport Effects 0.000 description 19
- 238000007789 sealing Methods 0.000 description 12
- 239000000463 material Substances 0.000 description 8
- 230000035882 stress Effects 0.000 description 6
- 230000009429 distress Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 230000005611 electricity Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
- B64D1/12—Releasing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B27/00—Arrangement of ship-based loading or unloading equipment for cargo or passengers
- B63B27/26—Arrangement of ship-based loading or unloading equipment for cargo or passengers of devices with throwing action
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Ocean & Marine Engineering (AREA)
- Toys (AREA)
- Transmission Devices (AREA)
Abstract
The embodiment of the invention provides an ejection device. The ejection device mainly comprises a cabin body which is arranged on a transport facility and a push-out section which is electrically connected with a popup trigger circuit of the transport facility, wherein the push-out section comprises a push rod; the cabin body is a hollow cavity with an opening in one end; the push rod is located in the cabin body and is used for ejection movement in the direction toward the opening of the cabin body after the popup trigger circuit triggering signals sent from the transport facility are received, so as to enable the releasing object to be ejected out of the transport facility. The ejection device can ejects the releasing object in the transport facility, so that the releasing object falls into a target delivery area.
Description
Technical field
The present invention relates to traffic and transport field, in particular to a kind of catapult-launching gear.
Background technology
Along with the development of China Transportation Industry, aircraft is as a kind of important transport facility, except being used in people
Trip and tourism, be additionally operable to transport goods and materials, equipment.The area of emergency relief supplies is needed, owing to it is disadvantageous at some
Environment or position are inaccessible, it is also possible to utilize aircraft aloft to carry out the input of goods and materials or equipment.
Can be used in throw in goods and materials transport facility except aircraft, also spacecraft, submarine and submersible etc., flying
During row or navigation, for the resistance during reducing flight or navigating by water, its outer surface is usually designed to more smooth, if will
Air-drop article are attached on its outer surface, and can increase flight or the resistance of navigation, and conventional aerial delivery system is typically chosen missile
It is suspended on outside, when being transported to throw in area, then allows missile depart from aircraft.Conventional air-drop mode, uses and is hanged by missile
Hang over the outside of aircraft, spacecraft or submarine, the input of the easy goods and materials of energy, but increase flight or the resistance of navigation.
Summary of the invention
In view of this, the purpose of the embodiment of the present invention is to provide a kind of catapult-launching gear, it is possible to ejects and is arranged on traffic
Missile within means of transport, so that missile is in target throws in region.
Embodiments provide a kind of catapult-launching gear, including the nacelle being arranged on transport facility and traffic
Means of transport ejects the launched portion triggering circuit electrical connection, and described launched portion includes push rod;Described nacelle is in one end open
Cavity body;
Described push rod is positioned at inside described nacelle, and for receiving described transport facility ejection triggering circuit
After triggering signal, do sling movement towards the direction at the opening place of described nacelle, missile to be ejected described transportation
Instrument.
Preferably, embodiments providing a kind of catapult-launching gear, wherein, described launched portion also includes fixing lock and drives
The motor of dynamic described fixing lock, described push rod is provided with draw-in groove, and described fixing lock extend in described draw-in groove, with spacing described
Push rod;
Described motor electrically connects with described triggering circuit, for receiving described transport facility ejection triggering circuit
Triggering signal rear drive described in fix lock and stretch out described draw-in groove, so that described push rod is towards the side at the opening place of described nacelle
To doing sling movement, and then described missile is ejected described transport facility.
Preferably, embodiments providing a kind of catapult-launching gear, described fixing lock is circular.
Preferably, embodiments providing a kind of catapult-launching gear, wherein, described launched portion also includes that first launches
Device, described first ejector produces thrust for persistently.
Preferably, embodiments providing a kind of catapult-launching gear, wherein, described launched portion also includes that second launches
Device, described second ejector, for producing thrust after receiving described triggering signal.
Preferably, embodiments provide a kind of catapult-launching gear, wherein, also include the shell for carrying missile
And kayser;
Described kayser is for providing clamping force to described shell, so that described shell is fixing under the effect of described clamping force
In described nacelle;
Described thrust is more than described clamping force.
Preferably, a kind of catapult-launching gear is embodiments provided, wherein, including being arranged on described nacelle opening part
Baffle plate;
One end of described baffle plate is rotationally connected with the edge of described kick-off end;
The other end of described baffle plate extends to the center of described opening.
Preferably, embodiments provide a kind of catapult-launching gear, wherein, also include being arranged on described nacelle opening part
Lower plate and movable plate;
The center of described lower plate is provided with through hole, to form the opening of described nacelle;
Described lower plate ringwise, and is provided with telescopic chute on inwall;
Described movable plate is slidably connected with described telescopic chute, can move back and forth along described telescopic chute, to close or to open institute
State the opening of nacelle.
Preferably, embodiments providing a kind of catapult-launching gear, wherein, described nacelle contacts with described shell
Surface is matsurface.
Preferably, embodiments provide a kind of catapult-launching gear, wherein,
A kind of catapult-launching gear that the embodiment of the present invention provides, mainly include the nacelle that is arranged on transport facility and
Transport facility ejects the launched portion triggering circuit electrical connection, and launched portion includes push rod;Nacelle is the cavity of one end open
Body;Push rod is positioned at inside nacelle, and for after the triggering signal receiving transport facility ejection triggering circuit, towards cabin
Sling movement is done in the direction at the opening place of body, so that missile is ejected transport facility.The one that the present invention provides is launched
Device, it is possible to eject the missile within transport facility, so that missile falls into target and throws in region.
Accompanying drawing explanation
In order to be illustrated more clearly that the technical scheme of the embodiment of the present invention, below by embodiment required use attached
Figure is briefly described, it will be appreciated that the following drawings illustrate only certain embodiments of the present invention, and it is right to be therefore not construed as
The restriction of scope, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to according to this
A little accompanying drawings obtain other relevant accompanying drawings.
Fig. 1 shows the structural representation of a kind of catapult-launching gear that the embodiment of the present invention provided;
Fig. 2 show a kind of catapult-launching gear that the embodiment of the present invention is provided do sling movement before view;
Fig. 3 shows view when a kind of catapult-launching gear that the embodiment of the present invention is provided does sling movement;
Fig. 4 show a kind of catapult-launching gear that the embodiment of the present invention is provided do sling movement after view;
Fig. 5 shows that a kind of catapult-launching gear nacelle opening part that the embodiment of the present invention is provided only comprises the knot of a baffle plate
Structure schematic diagram;
Fig. 6 shows that a kind of catapult-launching gear nacelle opening part that the embodiment of the present invention is provided comprises the knot of each and every one baffle plates many
Structure schematic diagram;
Fig. 7 shows view when the another kind of catapult-launching gear that the embodiment of the present invention is provided does sling movement;
Fig. 8 shows the structural representation of a kind of catapult-launching gear nacelle opening part movable plate that the embodiment of the present invention provided
Figure;
Fig. 9 show the another kind of catapult-launching gear that the embodiment of the present invention is provided do sling movement after view.
In accompanying drawing, digitized representation meaning is as follows:
30-nacelle
31-push rod
32-sealing plate
33-baffle plate
34-movable plate
04-shell
Detailed description of the invention
Below in conjunction with accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Ground describes, it is clear that described embodiment is only a part of embodiment of the present invention rather than whole embodiments.Generally exist
Can arrange and design with various different configurations with the assembly of the embodiment of the present invention that illustrates described in accompanying drawing herein.Cause
This, be not intended to limit claimed invention to the detailed description of the embodiments of the invention provided in the accompanying drawings below
Scope, but it is merely representative of the selected embodiment of the present invention.Based on embodiments of the invention, those skilled in the art are not doing
The every other embodiment obtained on the premise of going out creative work, broadly falls into the scope of protection of the invention.
Can be used in throwing in the transport facility of goods and materials, such as aircraft, spacecraft and submarine etc., flying or navigation process
In, for the resistance during reducing flight or navigating by water, its outer surface is usually designed to more smooth, is attached to by air-drop article
On its outer surface, flight or the resistance of navigation can be increased, therefore conventional aerial delivery system is typically chosen and goods and materials are suspended on outside, transports
During to input area, then missile is allowed to depart from above-mentioned transport facility.Conventional input mode, goods and materials are suspended on aircraft,
Spacecraft or the outside of submarine, the input of the easy goods and materials of energy, but increase flight or the resistance of navigation.
A kind of catapult-launching gear that the embodiment of the present invention provides, as a example by being applied to during aircraft distress the black box within ejecting,
Being used the transport facility throwing in article is aircraft, and input article are black box, and this catapult-launching gear includes being arranged on aircraft
On nacelle 30 and aircraft eject and trigger circuit and electrically connect launched portion, described launched portion includes push rod 31;Described nacelle 30 is in one
The hollow cavity of end opening;
It is internal that described push rod 31 is positioned at described nacelle 30, and in the triggering receiving described aircraft ejection triggering circuit
After signal, do sling movement towards the direction at the opening place of described nacelle, so that described black box is ejected aircraft.
The concrete structure schematic diagram of ejection structure as it is shown in figure 1, during aircraft distress, the ejection that on aircraft, black box is used
Structure can eject black box, and the sling movement of ejecting structure is by the push rod 31 being arranged within nacelle 30, is receiving aircraft
Perform after ejecting the triggering signal of triggering circuit.Need exist for it is emphasized that above-mentioned nacelle 30 is preferably the cylindric chamber of hollow
Body, but it is not limited only to the cylindrical cavity of hollow, it is also possible to it is the hollow columnar cavity of other forms.Above-mentioned push rod 31 is bar
Shape push rod 31, but it is not limited only to shaft-like push rod 31, it is also possible to it is the launched portion form of one end connecting plate-shaped sealing plate 32, push rod
The sealing plate 32 of 31 ends is one-body molded with push rod 31.The sealing plate 32 of push rod 31 end is connected with nacelle 30 inner wall sealing,
The position being tightly connected can also install the bubble-tight parts of enhancing of similar cushion rubber additional.After push rod 31 terminates sling movement, seal
Plate 32 can fill up the opening of nacelle 30, to ensure the air-tightness within nacelle 30.
As a preferred version of a kind of catapult-launching gear that the embodiment of the present invention provides, described launched portion also includes fixing
Locking and drive the motor of described fixing lock, described push rod 31 is provided with draw-in groove, described fixing lock extend in described draw-in groove, with
Spacing described push rod 31;
Described motor electrically connects with described triggering circuit, at the triggering letter receiving described aircraft ejection triggering circuit
Fix lock described in number rear drive and stretch out described draw-in groove, so that described push rod 31 does towards the direction at the opening place of described nacelle 30
Sling movement, and then described first black box or described second black box are ejected aircraft.
Before aircraft distress, a fixing lock is needed to be fixed by push rod 31, so that push rod 31 keeps resting state, until
During aircraft distress, fixing lock is opened, and push rod 31 does sling movement, and black box is ejected aircraft.Concrete, motor is fixing for driving
Lock the driving source of on an off, due to motor and triggering circuit electrical connection, so in the triggering receiving aircraft ejection triggering circuit
After signal, electricity opportunity driven is fixed lock and is opened, and i.e. fixes lock and stretches out draw-in groove.Fixing lock is the most circular, but is not limited only to
Circular, it is also possible to be other shapes.Preferably, terminating sling movement at push rod 31, sealing plate 32 can fill up opening of nacelle 30
After Kou, motor can drive fixing lock, locks push rod 31.
As a preferred version of a kind of catapult-launching gear that the embodiment of the present invention provides, described launched portion also includes first
Ejector, described first ejector produces thrust for persistently.
For realizing sling movement, possible a kind of mode is that the push rod 31 in ejection structure is in stress all the time, logical
Cross fixing lock push rod 31 is fixed, after receiving the triggering signal that aircraft ejects triggering circuit, the fixing lock of electricity opportunity driven
Open, i.e. fix lock and stretch out draw-in groove.Now, the push rod 31 being in the most all the time under stress does sling movement.Make push rod 31
All the time being in stress need to have the first ejector to complete.First ejector is preferably reducible spring structure or is one
Motor-driven structure, during for motor-driven structure, motor is to one driving force of push rod so that push rod is in stress all the time.
As a preferred version of a kind of catapult-launching gear that the embodiment of the present invention provides, described launched portion also includes second
Ejector, described second ejector, for producing thrust after receiving described triggering signal.
Second ejector is different from the first ejector, and for making sling movement realize, possible another way is to launch knot
Push rod 31 in structure is in stress the most all the time, but after the triggering signal receiving aircraft ejection triggering circuit, second
Ejector produces a thrust to push rod 31.A second ejector concretely locking back-moving spring, push rod 31 is not at
During stress, back-moving spring is in compressive state under the restriction of lock, receives aircraft and ejects the triggering signal triggering circuit
After, lock is opened, spring reset, drives push rod to do sling movement.
As a preferred version of a kind of catapult-launching gear that the embodiment of the present invention provides, also include carrying outside black box
Shell 04 and kayser;
Described kayser is for providing clamping force, so that described shell 04 is at described clamping force to the shell 04 of described black box
Effect under be fixed in described nacelle 30;
Described thrust is more than described clamping force.
When launched portion exists thrust (when push rod 31 does sling movement), it is clamped on the shell in nacelle 30 by clamping force
04 can eject nacelle 30 under the effect of push rod 31 thrust.Concrete, kayser can be the retractable hook pawl of a kind of annular, installs
On push rod 31 end (when being provided with sealing plate 32 when push rod 31 end, be arranged on sealing plate 32) or the inwall of nacelle 30.
When push rod 31 does not does sling movement, hook pawl can stretch into shell 04 inside and be fixed by shell 04;When push rod 31 does sling movement, annular
Hook pawl can along be arranged on push rod 31 end or nacelle 30 inwall curved channel regain, with realize release shell 04 merit
Energy.The structure of the above kayser is a preferred version of the present embodiment, it is also possible to be the latching structure of other forms.
As a preferred version of a kind of catapult-launching gear that the embodiment of the present invention provides, also include being arranged on described nacelle
The baffle plate 33 of 30 opening parts;
One end of described baffle plate 33 is rotationally connected with the edge of described kick-off end;
The other end of described baffle plate 33 extends to the center of described opening.
Push rod 31 does the state before sling movement as in figure 2 it is shown, now, and shell 04 is fixed on the end of push rod 31 by kayser
Portion, baffle plate 33 is closed.When push rod 31 does sling movement, the thrust on push rod 31 passes to be fixed on push rod 31 end
The shell 04 in portion, so that shell 04 produces a thrust to baffle plate 33, baffle plate 33 is under the effect of thrust, and baffle plate 33 is to opening
One end that center extends is movable to aircraft exterior, and opening is gradually increased, as it is shown on figure 3, until shell 04 completely disengages from nacelle
30 openings, clamping force disappears, and shell 04 does projectile motion.
It is emphasized that the inwall of the hollow cavity that nacelle 30 is inner wall coarse, the outer surface of shell 04 and nacelle 30
Contacting, now, above-mentioned kayser is the inwall that nacelle 30 is coarse, and clamping force is the frictional force suffered by shell 04, and frictional force
Less than the thrust of push rod 31 when doing sling movement.
Push rod 31 is preferably the one end structure with sealing plate 32, and a similar piston rod, when shell 04 is pushed away by push rod 31
After going out nacelle 30, sealing plate 32 rests on the opening part of nacelle 30, and to ensure the air-tightness of nacelle 30, baffle plate 33 returns to originally
State, as shown in Figure 4.
The quantity of baffle plate 33 can arrange one and may also set up multiple.When baffle plate 33 arrange quantity be one time, such as Fig. 5 institute
Showing, if relative motion from left to right between external fluid and baffle plate 33, this on-off mode fluid can help baffle plate 33 to close
Close.When launching the missile in nacelle 30, owing to baffle plate 33 is ejected by missile, now fluid is to the closure function of baffle plate 33 just
Cannot realize.When baffle plate 33 arrange quantity be multiple time, the opening of the nacelle that looks up below nacelle 30 30, as shown in Figure 6, knot
Structure 1 is the situation of 30 two baffle plates 33 of cylinder nacelle;Structure 2 is the situation of 30 4 baffle plates 33 of cylinder nacelle;Structure 3 is square
The situation of 30 two baffle plates 33 of column nacelle.
As a preferred version of a kind of catapult-launching gear that the embodiment of the present invention 1 provides, also include being arranged on described cabin
The lower plate of body 30 opening part and movable plate 34;
The center of described lower plate is provided with through hole, to form the opening of described nacelle 30;
Described lower plate ringwise, and is provided with telescopic chute on inwall;
Described movable plate 34 is slidably connected with described telescopic chute, can move back and forth along described telescopic chute, to close or to open
The opening of described nacelle 30.
As it is shown in fig. 7, when push rod 31 does sling movement, the thrust on push rod 31 passes to be fixed on push rod 31 end
Shell 04, so that shell 04 produces a downward thrust, the position contacted due to movable plate 34 with shell 04 to movable plate 34
Putting is an inclined-plane, and downward thrust is carried out force resolution, and an available horizontal thrust, this horizontal thrust be enough to promote shifting
Dynamic plate 34 moves in telescopic chute.Movable plate 34 moves in telescopic chute, and opening is gradually increased, until shell 04 completely disengages from cabin
Body 30 opening, shell 04 does projectile motion.The structure of movable plate 34, looks up from the lower section of nacelle 30, as shown in Figure 8.Need
It is emphasized that above-mentioned movable plate 34 is the possible move mode of one of which to the mode that telescopic chute moves, movable plate 34 is also
The movable plate 34 movement in telescopic chute can have been driven by motor.
It is emphasized that the inwall of the hollow cavity that nacelle 30 is inner wall coarse, the outer surface of shell 04 and nacelle 30
Contacting, now, above-mentioned kayser is the inwall that nacelle 30 is coarse, and clamping force is the frictional force suffered by shell 04, and frictional force
Less than the thrust of push rod 31 when doing sling movement.
Push rod 31 is preferably the one end structure with sealing plate 32, and a similar piston rod, when shell 04 is pushed away by push rod 31
After going out nacelle 30, sealing plate 32 rests on the opening part of nacelle 30, to ensure the air-tightness of nacelle 30, at the beginning of movable plate 34 moves to
Beginning position.As shown in Figure 9.
As a preferred version of a kind of catapult-launching gear that the embodiment of the present invention provides, nacelle inwall is additionally provided with out
Mouthful, this opening is for from internally installed black box or other missiles.Do not lay missile in nacelle or missile thrown
When going out nacelle, nacelle is closed by a door-plate, and door-plate is provided with pressure responsive element.When the internal pressure with interior of aircraft of nacelle
When power has bigger difference, door-plate is driven to close, to avoid the unexpected drastic change of nacelle internal pressure to affect safety.It is noted here that
, the closedown of door-plate and the form of unlatching can be unlatching and the closed form of said baffle, it is also possible to be aforementioned lower plate and movement
Plate be slidably connected after unlatching and closed form.
In conjunction with such scheme, the above-mentioned opening part as installation black box or other missiles is additionally provided with Guan Bi door-plate,
The closedown of Guan Bi door-plate and the form of unlatching can be unlatching and the closed form of said baffle, it is also possible to be aforementioned lower plate and movable plate
Unlatching after being slidably connected and closed form.
In conjunction with such scheme, it is additionally provided with mobile roller at opening, when needing to put into the black box of nacelle or other throwings
Put thing overweight time, by mobile roller, needs can be installed inside black box nacelle within or missile feeding nacelle.
As a preferred version of a kind of catapult-launching gear that the embodiment of the present invention provides, also include supercharger, supercharger
For balancing the inside and outside air pressure of nacelle.
Concrete, if the air-tightness between nacelle and the external world is bad, or there is gas to enter into nacelle in launch process
Internal or be discharged into outside from nacelle, the pressure of nacelle will change.When the pressure differential internal and outside when nacelle is excessive, beat
The opening that the internal wall that opens the cabin is arranged arises that safety problem.After inside nacelle, supercharger is set, can balance in nacelle in the moment
The pressure in portion, is allowed to keep a less pressure differential with extraneous, to ensure to open safety during wall opening in nacelle.
It should be noted that when a kind of catapult-launching gear provided as the present invention is applied at submarine or submersible, above-mentioned supercharging
Machine can be replaced negative booster.Submarine or submersible, after throwing in article, may have liquid to enter inside nacelle, in opening nacelle
Before the opening in portion, negative booster can detach liquid in nacelle.
Above, the only detailed description of the invention of the present invention, but protection scope of the present invention is not limited thereto, and any familiar
Those skilled in the art, in the technical scope that the invention discloses, can readily occur in change or replace, should contain
Within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with scope of the claims.
Claims (10)
1. a catapult-launching gear, it is characterised in that include nacelle and the transport facility bullet being arranged on transport facility
Going out to trigger the launched portion of circuit electrical connection, described launched portion includes push rod;Described nacelle is the hollow cavity of one end open;
Described push rod is positioned at inside described nacelle, and in the triggering receiving described transport facility ejection triggering circuit
After signal, do sling movement towards the direction at the opening place of described nacelle, missile to be ejected described transport facility.
A kind of catapult-launching gear the most according to claim 1, it is characterised in that described launched portion also includes fixing lock and drives
The motor of described fixing lock, described push rod is provided with draw-in groove, and described fixing lock extend in described draw-in groove, pushes away described in spacing
Bar;
Described motor electrically connects with described triggering circuit, for receiving touching of described transport facility ejection triggering circuit
Fix lock described in signalling rear drive and stretch out described draw-in groove, so that described push rod does towards the direction at the opening place of described nacelle
Sling movement, and then described missile is ejected described transport facility.
A kind of catapult-launching gear the most according to claim 2, it is characterised in that described fixing lock is circular.
A kind of catapult-launching gear the most according to claim 1, it is characterised in that described launched portion also includes the first ejector,
Described first ejector produces thrust for persistently.
A kind of catapult-launching gear the most according to claim 1, it is characterised in that described launched portion also includes the second ejector,
Described second ejector, for producing thrust after receiving described triggering signal.
A kind of catapult-launching gear the most according to claim 1, it is characterised in that also include the shell for carrying missile and
Kayser;
Described kayser is for providing clamping force to described shell, so that described shell is fixed on institute under the effect of described clamping force
State in nacelle;Described thrust is more than described clamping force.
A kind of catapult-launching gear the most according to claim 1, it is characterised in that also include being arranged on described nacelle opening part
Baffle plate;
One end of described baffle plate is rotationally connected with the edge of described kick-off end;
The other end of described baffle plate extends to the center of described opening.
A kind of catapult-launching gear the most according to claim 1, it is characterised in that also include being arranged on described nacelle opening part
Lower plate and movable plate;
The center of described lower plate is provided with through hole, to form the opening of described nacelle;
Described lower plate ringwise, and is provided with telescopic chute on inwall;
Described movable plate is slidably connected with described telescopic chute, can move back and forth along described telescopic chute, to close or to open described cabin
The opening of body.
A kind of catapult-launching gear the most according to claim 1, it is characterised in that the table that described nacelle contacts with described shell
Face is matsurface.
A kind of catapult-launching gear the most according to claim 1, it is characterised in that also include supercharger;
Described supercharger is for balancing the inside and outside air pressure of described nacelle.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201610805098.7A CN106314796A (en) | 2016-09-01 | 2016-09-01 | Ejection device |
PCT/CN2017/100290 WO2018041255A1 (en) | 2016-09-01 | 2017-09-01 | Ejecting device |
PCT/CN2017/100287 WO2018041253A1 (en) | 2016-09-01 | 2017-09-01 | Black box control method and system |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201610805098.7A CN106314796A (en) | 2016-09-01 | 2016-09-01 | Ejection device |
Publications (1)
Publication Number | Publication Date |
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CN106314796A true CN106314796A (en) | 2017-01-11 |
Family
ID=57788116
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201610805098.7A Pending CN106314796A (en) | 2016-09-01 | 2016-09-01 | Ejection device |
Country Status (2)
Country | Link |
---|---|
CN (1) | CN106314796A (en) |
WO (1) | WO2018041255A1 (en) |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2018041253A1 (en) * | 2016-09-01 | 2018-03-08 | 梁泰然 | Black box control method and system |
WO2018041255A1 (en) * | 2016-09-01 | 2018-03-08 | 梁泰然 | Ejecting device |
CN108583891A (en) * | 2018-05-24 | 2018-09-28 | 安徽工程大学 | A kind of fire extinguisher bomb delivery device in multi-rotor unmanned aerial vehicle |
CN109552627A (en) * | 2018-10-24 | 2019-04-02 | 国网山东省电力公司龙口市供电公司 | A kind of unmanned plane delivery case |
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Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2497766A1 (en) * | 1981-01-09 | 1982-07-16 | Alkan R & Cie | Compressed-air powered device for firing buoys - contains sleeve which can be inverted to accommodate small or large charges |
US4474101A (en) * | 1981-03-24 | 1984-10-02 | Francois Boulard | Process and system for storing and releasing a cylindrical object from a vehicle |
CN201923321U (en) * | 2010-12-29 | 2011-08-10 | 西安四方航空科技有限公司 | Airborne dry powder dropping device |
CN203753393U (en) * | 2013-12-24 | 2014-08-06 | 西安理工大学 | Double-door release device of unmanned aerial vehicle |
CN204979246U (en) * | 2015-09-23 | 2016-01-20 | 王志红 | Automatic dry powder formula unmanned aerial vehicle that puts in of fire control |
CN206125434U (en) * | 2016-09-01 | 2017-04-26 | 肇庆高新区异星科技有限公司 | Catapulting device |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4080868A (en) * | 1977-02-25 | 1978-03-28 | Lockheed Corporation | Support and retention mechanism for missiles in launchers |
CN203623966U (en) * | 2013-12-23 | 2014-06-04 | 景德镇陶瓷学院 | Cargo delivery device for unmanned helicopter |
CN103895853B (en) * | 2014-04-11 | 2015-10-14 | 北京理工大学 | The method of designing that a kind of built-in type cabin is opened |
CN105270628A (en) * | 2014-07-14 | 2016-01-27 | 姜蕾 | Lifesaving lead ejection device for helicopter |
CN105599901A (en) * | 2016-03-03 | 2016-05-25 | 三翼航空科技南通有限公司 | Fire-extinguishing bullet firing device for unmanned aerial vehicle fire control |
CN106314796A (en) * | 2016-09-01 | 2017-01-11 | 肇庆高新区异星科技有限公司 | Ejection device |
-
2016
- 2016-09-01 CN CN201610805098.7A patent/CN106314796A/en active Pending
-
2017
- 2017-09-01 WO PCT/CN2017/100290 patent/WO2018041255A1/en active Application Filing
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2497766A1 (en) * | 1981-01-09 | 1982-07-16 | Alkan R & Cie | Compressed-air powered device for firing buoys - contains sleeve which can be inverted to accommodate small or large charges |
US4474101A (en) * | 1981-03-24 | 1984-10-02 | Francois Boulard | Process and system for storing and releasing a cylindrical object from a vehicle |
CN201923321U (en) * | 2010-12-29 | 2011-08-10 | 西安四方航空科技有限公司 | Airborne dry powder dropping device |
CN203753393U (en) * | 2013-12-24 | 2014-08-06 | 西安理工大学 | Double-door release device of unmanned aerial vehicle |
CN204979246U (en) * | 2015-09-23 | 2016-01-20 | 王志红 | Automatic dry powder formula unmanned aerial vehicle that puts in of fire control |
CN206125434U (en) * | 2016-09-01 | 2017-04-26 | 肇庆高新区异星科技有限公司 | Catapulting device |
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---|---|---|---|---|
WO2018041255A1 (en) * | 2016-09-01 | 2018-03-08 | 梁泰然 | Ejecting device |
WO2018041253A1 (en) * | 2016-09-01 | 2018-03-08 | 梁泰然 | Black box control method and system |
CN108583891A (en) * | 2018-05-24 | 2018-09-28 | 安徽工程大学 | A kind of fire extinguisher bomb delivery device in multi-rotor unmanned aerial vehicle |
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CN109808887B (en) * | 2019-01-29 | 2022-04-05 | 西北工业大学 | Throwing mechanism for small unmanned aerial vehicle |
CN109808887A (en) * | 2019-01-29 | 2019-05-28 | 西北工业大学 | A throwing mechanism for small unmanned aerial vehicles |
CN110576972A (en) * | 2019-08-30 | 2019-12-17 | 中国气象局气象探测中心 | multi-cylinder type lower-dropping sonde ejection device, dropping device and dropping method |
CN110576972B (en) * | 2019-08-30 | 2024-05-07 | 中国气象局气象探测中心 | Multi-cylinder type downward projecting sonde ejection device, projecting device and projecting method |
CN111907706A (en) * | 2020-06-15 | 2020-11-10 | 哈尔滨工业大学 | Electromagnetic drive's black box throws and puts separating mechanism |
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