CN109747806A - A kind of airplane catapult system - Google Patents
A kind of airplane catapult system Download PDFInfo
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- CN109747806A CN109747806A CN201811505061.8A CN201811505061A CN109747806A CN 109747806 A CN109747806 A CN 109747806A CN 201811505061 A CN201811505061 A CN 201811505061A CN 109747806 A CN109747806 A CN 109747806A
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- locking device
- cover
- ejection
- parachute
- fuselage
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Abstract
The present invention relates to vehicle technology fields, more particularly to a kind of airplane catapult system, the aircraft is made of fuselage and wing, the fuselage interior is keel structure, and the fuselage head is equipped with cockpit, main cabin is equipped in the middle part of aircraft characterized by comprising the main cabin is separable setting with the fuselage；Locking device is launched, the main cabin is attached with the fuselage by the ejection locking device；Parachute, the landing are connect with the main cabin；Controller, trigger of the controller respectively with the ejection locking device, the parachute are electrically connected.
Description
Technical field
The present invention relates to vehicle technology fields, and in particular to a kind of airplane catapult system.
Background technique
The existing general passenger capacity of passenger plane is larger, once accident occurs during high-altitude flight, often results in a large amount of people
Member's injures and deaths, and passenger can not survive in most cases.
Summary of the invention
The purpose of the present invention is to provide a kind of airplane catapult systems, are solved by the separate type main cabin with parachute
Deficiency certainly in the prior art.
To achieve the above object, the invention provides the following technical scheme: a kind of airplane catapult system, the aircraft is by fuselage
It is constituted with wing, the fuselage interior is keel structure, and the fuselage head is equipped with cockpit, is equipped with visitor in the middle part of aircraft
Cabin characterized by comprising the main cabin and the fuselage are arranged to be separable；Launch locking device, the main cabin with it is described
Fuselage is attached by the ejection locking device；Parachute, the landing are connect with the main cabin；Controller, the control
Trigger of the device processed respectively with the ejection locking device, the parachute is electrically connected.
Preferably, the multiple seperated hatch covers in the main cabin are constituted, and the cloth that each seperated hatch cover is symmetrical
It sets in the fuselage upper half；Each described seperated hatch cover is made of outer cover and floor；The floor upper surface, which is equipped with, to be multiplied
Visiting chair, the corresponding seperated hatch cover in left and right enclose manned cabin.
Preferably, two corners and floor two corners far from the outer cover of the outer cover far from the floor are set respectively
There is fixed anchor point；The parachute is multiple settings, and is connect respectively with each anchor point.
Preferably, the cockpit is connect by the ejection locking device with the fuselage；And the cockpit is set
There is anchor point, the parachute is connect with the anchor point.
Preferably, the controller includes master controller and from controller；The main control is arranged in the cockpit,
And the master controller is equipped with and starts switch and the first height sensor；It is described to be multiple settings from controller and divide one by one
She Zhi not be described to be electrically connected from controller and the master controller in each seperated hatch cover, and it is respectively equipped with second
Height sensor；It is described electrically to connect with corresponding parachute and the ejection locking device respectively from controller
It connects.
Preferably, the parachute includes the central air bladder and an exumbrella cover that coaxial inner conductor is arranged in；The center
Filling gas inside air bladder, and the center air bladder has a guidance part；An inflatable chamber is set inside the exumbrella cover, passes through institute
It states in central air bladder is coated on by inflatable chamber, and the guidance part position of exumbrella cover bottom adjacent central air bladder is equipped with one
Bottom surface, and the bottom surface and central air bladder connects and are equipped with multiple air inlets, the exumbrella cover appearance formation one on toward
Under tapered inclined-plane；The bottom surface is a plastotype ring body, and the plastotype ring body is around the multiple air inlets of setting；The center bubble
Body external rings set multiple flexible bodies and bottom ora terminalis is equipped with a guidance part, and the flexible body other end is then connected to exumbrella cover
One limitation rope of inside and guidance part bottom connection, the limitation rope other end are connect with the anchor point；The exumbrella cover
The axial symmetry angle on top sets a pressure relief opening and exumbrella cover bottom end is equipped with multiple drawstrings, and the multiple drawstring connects
Has ponderable main cabin；The plastotype ring body is rigid；The guidance part is curved surface；The drawstring is adjacent to the anchor point ring
Connect a connection ring.
Preferably, the lateral flip angle of the ejection locking device is between 30 degree to 60 degree of upward from horizontal.
Preferably, the ejection locking device includes the stack shell being vertically arranged, and the stack shell top is equipped with upper top cover, described
Ejection system is equipped in stack shell；The ejection system upper end is fixedly connected with stack shell inner cavity top, and the bottom end of ejection system is prolonged
It extends to outside the lower port of stack shell bottom, and ejection system and stack shell are coaxial；The ejection system includes energy storage equipment, locking dress
It sets, release device and limitation seat, the energy storage equipment includes spring, pressure plare and mandril, and one end of spring is free end, bullet
The other end of spring is contacted with pressure plare upper surface, and one end of pressure plare lower surface and mandril is detachably connected, the other end of mandril
It is detachably connected across limitation seat with locking device, limits seat and be also rotatably connected to release device, release device when spring-compressed
Locking device is limited with locking device clamping；The upper and lower end face shaft core position of the mandril is provided with upper groove, locking dress
The upper surface set is provided with the concentric column to match with upper groove, and wherein upper groove inner wall has internal screw thread, and the outer wall of concentric column has
External screw thread, the lower end of mandril and the upper end of locking device are detachably connected by the internal and external threads of upper groove and concentric column.
Preferably, the locking device includes at least concentric column and the circular deck positioned at locking device middle section,
Deck lower surface is plane；The release device includes at least the latch hook positioned at side, and the upper surface of latch hook is plane, spring
The upper surface of latch hook and the lower surface of deck are clamped when compression；The latch hook further includes the barrier being arranged with latch hook with side bottom
Piece and the frizzen being arranged in the bottom of the other side of latch hook；The lower section of the locking device is round table-like bracket, lock
The plane for determining device lower section stent outer wall and deck lower surface forms angle；The outer of the deck upper surface dips down
Tiltedly, the bottom center of bracket is provided with truncated cone-shaped slot；The limitation seat be by the enlarged diameter section of the reduced diameter section of upper section, lower section with
And linking reduced diameter section and enlarged diameter section between rotary table section, reduced diameter section, enlarged diameter section and rotary table section be structure as a whole and
With the through-lumen to match with mandril outer diameter, rectangular opening is wherein longitudinally provided on enlarged diameter section side wall, rectangular opening two sides are each
It is provided with a fixator, coaxial through hole is provided on two fixators；Release device is plate structure, the thickness of plate release device
Spacing between degree and two fixators matches, and the top of release device side is provided with round through hole, and pivot pin is fixed through two
The same axis through hole of device and the through hole of release device connect release device and limitation seat pin；The pressure plare is ring-type,
Round through hole is laid in matrix on anchor ring；The limitation seat and release device passes through pivot pin pin joint, pivot pin distance of shaft centers limit
Horizontal distance of the horizontal distance at seat center processed than deck outer away from locking device center is small；It further include pedestal, base upper surface
One end be provided with inertia rod, be provided with lower groove in the upper surface of inertia rod.
Beneficial effects of the present invention: the passenger plane equipped with airplane catapult system drives seating as conventional airplane, but works as
Aircraft is in senior middle school's in-flight burst accident, and controller, which will start ejection locking device, to be made to launch separation with the slave of main cabin, separation
Controller triggers Parachute Opening afterwards, to guarantee the passenger survival safety in main cabin.
The main cabin of separate structure mitigates the burden of parachute, while also passenger being dispersed in multiple regions, such as: by every 10
It arranges seat to be in a seperated hatch cover, when aircraft has 50 row's seat, it will constitute 10 seperated hatch covers, 5, left side fission
Hatch cover, the seperated hatch cover in 5, the right.
Seperated hatch cover is connect in the position of aforementioned four point setting anchor point with parachute respectively, therefore in parachute-opening descent
In, so that entire fission hatch cover uniform force, avoids shaking while also increasing decline resistance, guarantees the stabilization during decline
Property.The cockpit where pilot equally has ejection system simultaneously.
When aircraft meets with an accidet, pilot, which moved, starts switch triggering master controller, and master controller is sent to from controller
Signal, after being connected to signal from controller, triggering ejection locking device makes to launch separation with seperated hatch cover slave, when seperated hatch cover
It after being separated with fuselage, is disconnected from controller and master controller, the ejection locking mechanism of the cockpit of master controller triggering at this time,
And it launches cockpit with fuselage and separates.
In each seperated hatch cover and cockpit decline drop event, master controller and to pass through first respectively from controller high
Sensor and the second height sensor real-time monitoring present level are spent, when reaching the jumping altitude that the mankind are suitble to, main control
It device and is triggered respectively from controller and carries out parachute-opening deceleration with the parachute that respectively connect, to guarantee the life of pilot and passenger
Safety, it is various unfavorable caused by too early parachute-opening to avoid.
The central air bladder of parachute and the center of exumbrella cover are arranged on coaxial inner conductor, and because in central air bladder
Portion is filled with helium so as to generating a buoyancy, because the gas density of helium is much smaller than external atmospheric density, therefore central air bladder
Buoyancy caused by inside can enable central air bladder float up to an appropriate height, and work as and be connected to central air bladder and exumbrella
When the main cabin landing of cover lower section, the upward air-flow of external air must take advantage of a situation to be entered inside inflatable chamber by the air inlet of exumbrella cover and be formed
Another buoyancy makes to be in complete deployed condition because air-flow enters inside the inflatable chamber of exumbrella cover, at this time central air bladder and exumbrella
Covering connected limitation rope and drawstring related can up be straightened, wherein limitation rope can enable central air bladder float on after being straightened
An axisymmetric position of center line, which must be limited in, when aerial disorderly to shake, and buoyancy is more able to accurately in central air bladder accordingly
Inside center is formed, and it is accurately to act on position of center line that in other words the buoyancy inside central air bladder, which is cured, then is more avoided that
Central air bladder leads to knockdown because Impact direction is inconsistent.After central air bladder is floated up because of internal buoyancy, and
It enables parachute be landed down by high-altitude, and there is weight by the main cabin that limitation rope and drawstring are connected, therefore parachute is dropping
A phenomenon that freely falling body must be presented when falling, while the air-flow in multiple and different directions can be generated in atmosphere, at this time because of central bubble
The bottom ora terminalis design of body has the guidance part of curved surface, can guide the bottom surface that most air-flow is taken advantage of a situation by exumbrella cover by curved surface
Air inlet enters inside the inflatable chamber of exumbrella cover and forms buoyancy, and complete deployed condition is presented.Parachute of the invention simultaneously
Not needing certain height could use, and also not need the effect that complicated parachute-opening step can make exumbrella cover reach complete parachute-opening
Fruit, the drawstring that furthermore exumbrella cover bottom end is connected can be reached limitation purpose by connection ring, enable drawstring equably be softened and avoid
Mutually overlapping or wrapping phenomena.
The lateral flip angle of the ejection locking device is between 30 degree to 60 degree of upward from horizontal.
It is crushed in order to avoid fission covers on after ejection to generate to collide with wing, therefore in the flip angle of fission cover by counting
Setting is calculated, it and is transversely and horizontally between 30 degree to 60 degree with fuselage that flip angle range, which is separately stretched forward to fuselage two sides,.
Simultaneously in order to avoid the seperated hatch cover of phase the same side occurs mutually to collide in ejection process, therefore in ejection,
The seperated hatch cover of left and right is separated according to sequence sequence ejection from back to front.
The free end of spring is fixedly connected with the top in stack shell cavity, and the other end of spring is close to pressure plare, the pressure
Power plate and mandril are rigidly connected, and are limited below mandril by limitation seat；Mandril can move along a straight line along limitation seat and stack shell axle center, limitation
Seat is fixedly connected on the bottom of stack shell, and the top for limiting seat extends between empennage and mandril.Locking device is pressed when accumulation of energy vertically,
Locking device drives mandril and pressure plare to make spring-compressed, and after locking device enters limitation seat, locking device locks automatically, lock
It is fixed to complete；Amount of spring compression is maximum at this time, and accumulation of energy is completed.When ejection release, release device is pushed, release device deflects,
Latch-release, spring elongation release elastic potential energy, so that projectile motion is completed.
The cylindrical concentric column of locking device upper section is directly nested in mandril during installation, so that firmly installing, is locked
Determine the deck in device middle section with a thickness of 1 millimeter or so；The lower surface of the deck in the middle section of locking device and the upper side of bracket
Face forms angle, and making it is in not only to realize the function of hook locking, but also meet unlock, accumulation of energy release smoothly function.It limits on seat
Set fixator is used for fixed pivot pin, and pressure plare is set as cyclic annular, is laid with round through hole in matrix on anchor ring, is
In order to balance inner and outer air pressure；The axle center of pivot pin and apart 1 millimeter or so of the most outer of locking device, the distance of shaft centers central axes of pivot pin
Distance be shorter than the setting of distance of the most outer of locking device apart from axis so that locking and unlock are realized and are obtained easily
Good effect.In actual use, the frizzen of release device bottom setting, in accumulation of energy release, as long as touching triggering
Bar, latch hook break off relations, so that it may unlock and realize the release of accumulation of energy easily.The frizzen of release device bottom setting, is released in accumulation of energy
When putting, as long as touching frizzen, U-shaped latch hook breaks off relations, so that it may unlock and realize the release of accumulation of energy easily.Outside deck upper surface
Along tilting down, the outer of the deck upper surface in the middle section of locking device tilts down setting and locking device lower section stent outer
The plane of wall and deck lower surface forms angle, and accumulation of energy release can be made smooth, flat when stent outer wall and deck lower surface
Releasing effect is best when face forms 60 degree of angles.The bottom center of bracket is provided with truncated cone-shaped slot, not only meets cradling function, but also save material
Expect and mitigates own wt.When pivot pin distance of shaft centers limits water of the horizontal distance at seat center than deck outer away from locking device center
It puts down apart from hour, the effect of locking and unlocking is best.Pedestal is arranged on fuselage, and frizzen hits pedestal, and latch hook deflects
It breaks off relations and unlocks with locking device, spring elongation release elastic potential energy launches completion at this time.
Detailed description of the invention
Fig. 1 is application schematic diagram of the present invention；
Fig. 2 is cross section view of the present invention；
Fig. 3 is parachute schematic diagram of the present invention；
Fig. 4 is present invention ejection locking device schematic diagram.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention is described in detail.
Fig. 1, Fig. 2, Fig. 3, Fig. 4, a kind of airplane catapult system are please referred to, the aircraft is made of fuselage 1 and wing 2, institute
Stating is keel structure inside fuselage 1, and 1 head of the fuselage is equipped with cockpit 3, is equipped with main cabin 4 in the middle part of aircraft, feature exists
In, comprising: the main cabin 4 is separable setting with the fuselage 1；Locking device 5 is launched, the main cabin 4 and the fuselage 1 are logical
The ejection locking device 5 is crossed to be attached；Parachute 6, the parachute are connect with the main cabin 4；Controller, the control
Trigger of the device respectively with the ejection locking device 5, the parachute 6 is electrically connected.
By above-mentioned setting, the passenger plane equipped with airplane catapult system drives seating as conventional airplane, but works as aircraft
In senior middle school's in-flight burst accident, controller, which will start ejection locking device 5, makes main cabin 4 launch separation from fuselage 1, after separation
Controller triggers 6 parachute-opening of parachute, to guarantee the passenger survival safety in main cabin 4.
As a preferred embodiment, the seperated hatch cover in more than 4, the main cabin is constituted, and each seperated hatch cover is in left and right
It is arranged symmetrically on 1 upper half of fuselage；Each described seperated hatch cover is made of outer cover 9 and floor 10；The floor
10 upper surfaces are equipped with passenger seat, and the corresponding seperated hatch cover in left and right encloses manned cabin.
By above-mentioned setting, the main cabin 4 of separate structure mitigates the burden of parachute 6, while being also dispersed in passenger multiple
In region, such as: every 10 row seat being in a seperated hatch cover, when aircraft has 50 row's seat, it will constitute 10 fissions
Hatch cover, the seperated hatch cover in 5, the left side, the seperated hatch cover in 5, the right.
As a preferred embodiment, two corners and the floor 10 of the outer cover 9 far from the floor 10 are far from described outer
The two corners of cover 9 are respectively equipped with fixed anchor point 11；The parachute 6 is multiple settings, and is connected respectively with each anchor point 11
It connects.
Seperated hatch cover is connect in the position of aforementioned four point setting anchor point 11 with parachute 6 respectively, therefore is landed in parachute-opening
In the process, so that entire seperated hatch cover uniform force, avoids shaking while also increasing decline resistance, guarantee steady during declining
It is qualitative.
As a preferred embodiment, the cockpit 3 is connect by the ejection locking device 5 with the fuselage 1；And institute
Cockpit 3 is stated equipped with anchor point 11, the parachute 6 is connect with the anchor point 11.Therefore the cockpit 3 where pilot equally has
There is ejection system.
As a preferred embodiment, the controller includes master controller 12 and from controller 13；The main control setting exists
In the cockpit 3, and the master controller 12 is equipped with and starts switch and the first height sensor；It is described from controller 13
It is separately positioned in each seperated hatch cover for multiple settings and one by one, it is described electric from controller 13 and the master controller 12
Property connection, and be respectively equipped with the second height sensor；It is described from controller 13 respectively with corresponding parachute 6 and
The ejection locking device 5 is electrically connected.
By above-mentioned setting, when aircraft meets with an accidet, pilot, which moved, starts switch triggering master controller 12, main control
Device 12 sends signal to from controller 13, and after being connected to signal from controller 13, triggering ejection locking device 5 makes seperated hatch cover slave
Separation is launched on body 1, after seperated hatch cover is separated with fuselage 1, is disconnected from controller 13 and master controller 12, at this time master control
Device 12 processed triggers the ejection locking mechanism of cockpit 3, and launches cockpit 3 with fuselage 1 and separate.
Decline in drop event in each seperated hatch cover and cockpit 3, master controller 12 and passes through respectively from controller 13
First height sensor and the second height sensor real-time monitoring present level, when reaching the jumping altitude that the mankind are suitble to,
It master controller 12 and is triggered respectively from controller 13 and carries out parachute-opening deceleration with the parachute 6 that respectively connect, to guarantee pilot
With the life security of passenger, it is various unfavorable caused by too early parachute-opening to avoid.
As a preferred embodiment, the parachute 6 includes the central bubble 16 and an exumbrella cover that coaxial inner conductor is arranged in
21；The center 16 inside filling gas of bubble, and the center bubble 16 has a guidance part；One is set inside the exumbrella cover 21
Inflatable chamber, by the inflatable chamber central bubble 16 is coated in, and 21 bottom adjacent central bubble 16 of the exumbrella cover
Guidance part position is equipped with a bottom surface, and the bottom surface connect with central bubble 16 and is equipped with multiple air inlets 25, the exumbrella
It covers 21 appearances and forms an inclined-plane tapered from top to bottom；The bottom surface is a plastotype ring body, and the plastotype ring body is more around being arranged
A air inlet 25；Center 16 external rings of bubble set multiple flexible bodies 20 and bottom ora terminalis is equipped with a guidance part, and described
20 other end of flexible body is then connected to inside exumbrella cover 21 and one limitation rope 19 of guidance part bottom connection, the limitation
19 other ends of restricting are connect with the anchor point 11；The axial symmetry angle on 21 top of exumbrella cover sets a pressure relief opening 26 and described outer
21 bottom end of umbrella cover is equipped with multiple drawstrings 27, and the connection of the multiple drawstring 27 has ponderable main cabin 4；The plastotype ring body is
Rigid；The guidance part is curved surface；The drawstring 27 connects a connection ring 28 adjacent to 11 ring of anchor point.
The central bubble 16 of parachute 6 and the center of exumbrella cover 21 are arranged on coaxial inner conductor, and because of central bubble
Helium is filled with inside 16 so as to generating a buoyancy, because the gas density of helium is much smaller than external atmospheric density, therefore central bubble
Buoyancy caused by 16 inside can enable central bubble 16 float up to an appropriate height, and when being connected to central bubble 16 and outer
When the main cabin 4 of 21 lower section of umbrella cover is landed, the upward air-flow of external air, which must take advantage of a situation, enters inflation by the air inlet 25 of exumbrella cover 21
Intracavitary portion forms another buoyancy, makes to be in complete deployed condition because air-flow enters inside the inflatable chamber of exumbrella cover 21, central at this time
The limitation rope 19 and drawstring 27 that bubble 16 and exumbrella cover 21 are connected related can up be straightened, wherein limitation rope 19 is being straightened
After can enable central bubble 16 that must be limited in an axisymmetric position of center line when floating on aerial will not disorderly shaking, buoyancy is more accordingly
Accurately to be formed in central 16 inside center of bubble, it is in accurately acting on that in other words the buoyancy inside central bubble 16, which is cured,
Heart line position is then more avoided that central bubble 16 leads to knockdown because Impact direction is inconsistent.When central bubble 16 is because of inside
Buoyancy float up after, the main cabin that and parachute 6 is enabled to be landed down by high-altitude, and connected by limitation rope 19 and drawstring 27
The phenomenon that 4 have weight, therefore in landing a freely falling body must be presented in parachute 6, while can be generated in atmosphere multiple and different
The air-flow in direction can guide big portion by curved surface at this time because the bottom ora terminalis design of central bubble 16 has the guidance part of curved surface
Part air-flow, which is taken advantage of a situation, to be entered inside the inflatable chamber of exumbrella cover 21 by the air inlet 25 of the bottom surface of exumbrella cover 21 and forms buoyancy, and is presented
Complete deployed condition.Parachute 6 of the invention simultaneously, which does not need certain height, to be used, and does not also need complicated parachute-opening
Step can make exumbrella cover 21 achieve the effect that complete parachute-opening, and the drawstring 27 that furthermore 21 bottom end of exumbrella cover is connected can pass through connection
Ring 28 reaches limitation purpose, enables drawstring 27 equably be softened and avoids mutually overlapping or wrapping phenomena.
As a preferred embodiment, the lateral flip angle of the ejection locking device 5 is 30 degree to 60 of upward from horizontal
Between degree.
It is crushed in order to avoid fission covers on after ejection to generate to collide with wing 2, therefore passes through in the flip angle of fission cover
Calculate setting, flip angle range be separately stretch forward to 1 two sides of fuselage, and with fuselage 1 transversely and horizontally in 30 degree to 60 degree it
Between.
Simultaneously in order to avoid the seperated hatch cover of phase the same side occurs mutually to collide in ejection process, therefore in ejection,
The seperated hatch cover of left and right is separated according to sequence sequence ejection from back to front.
As a preferred embodiment, the ejection locking device 5 includes the stack shell 36 being vertically arranged, and 36 top of stack shell is set
There is upper top cover 35, is equipped with ejection system in the stack shell 36；The ejection system upper end and 36 inner cavity top of stack shell is fixed to be connected
It connects, the bottom end of ejection system extends to outside 36 bottom lower port of stack shell, and ejection system and stack shell 36 are coaxial；The ejection system
System includes energy storage equipment, locking device, release device and limitation seat 44, and the energy storage equipment includes spring 37, pressure plare 38
One end with mandril 39, spring 37 is free end, and the other end of spring 37 is contacted with 38 upper surface of pressure plare, 38 following table of pressure plare
Face and one end of mandril 39 are detachably connected, and the other end of mandril 39 passes through limitation seat 44 and is detachably connected with locking device, are limited
Seat 44 processed is also rotatably connected to release device, and release device and locking device, which are clamped, when spring 37 compresses limits locking device；
The upper and lower end face shaft core position of the mandril 39 is provided with upper groove 45, and the upper surface of locking device is provided with and upper groove 45
The concentric column 48 to match, wherein 45 inner wall of upper groove has internal screw thread, and the outer wall of concentric column 48 has external screw thread, the lower end of mandril 39
It is detachably connected with the upper end of locking device by the internal and external threads of upper groove 45 and concentric column 48.
By above-mentioned setting, the free end of spring 37 is fixedly connected with the top in 36 cavity of stack shell, spring 37 it is another
Pressure plare 38 is close at end, and the pressure plare 38 is rigidly connected with mandril 39, and 39 lower section of mandril is limited by limitation seat 44；Mandril 39 can
Along limitation seat 44 and 36 axle center of stack shell linear motion, limitation seat 44 is fixedly connected on the bottom of stack shell 36, limits the top of seat 44
It extends between empennage and mandril 39.Locking device is pressed when accumulation of energy vertically, locking device drives mandril 39 and pressure plare 38 to make bullet
Spring 37 compresses, and after locking device enters limitation seat 44, locking device locks automatically, and locking is completed；37 decrement of spring at this time
Maximum, accumulation of energy are completed.When ejection release, release device is pushed, release device deflects, latch-release, and the elongation of spring 37 is released
Elastic potential energy is put, so that projectile motion is completed.
As a preferred embodiment, the locking device includes at least concentric column 48 and the circle positioned at locking device middle section
Cyclic annular deck 49,49 lower surface of deck are plane；The release device includes at least the latch hook 41 positioned at side, latch hook 41
Upper surface is plane, and the upper surface of latch hook 41 and the lower surface of deck 49 are clamped when spring 37 compresses；The latch hook 41 also wraps
The frizzen 42 for including the barrier flaps 47 being arranged with latch hook 41 with side bottom and being arranged in the bottom of the other side of latch hook 41；It is described
Locking device lower section be round table-like bracket, locking device lower section stent outer wall and the plane of 49 lower surface of deck are formed
Angle；The outer of 49 upper surface of deck tilts down, and the bottom center of bracket is provided with truncated cone-shaped slot；The limitation seat
44 be by the reduced diameter section of upper section, the enlarged diameter section of lower section and linking reduced diameter section and enlarged diameter section between rotary table section, it is small
Diameter segment, enlarged diameter section and rotary table section are structure as a whole and have the through-lumen to match with 39 outer diameter of mandril, wherein greatly
Rectangular opening is longitudinally provided on diameter segment side wall, rectangular opening two sides are each provided with a fixator, and coaxial pass through is provided on two fixators
Through-hole；Release device is plate structure, and the spacing between the thickness of plate release device and two fixators matches, release device
The top of side is provided with round through hole, and pivot pin 43 will be released through the same axis through hole of two fixators and the through hole of release device
Put device and limitation 44 pin joint of seat；The pressure plare 38 is ring-type, is laid with round through hole in matrix on anchor ring；It is described
Limitation seat 44 and release device by 43 pin joint of pivot pin, 43 distance of shaft centers of pivot pin limits the horizontal distance at 44 center of seat than deck 49
Horizontal distance of the outer away from locking device center is small；It further include pedestal 40, one end of 40 upper surface of pedestal is provided with inertia rod,
The upper surface of inertia rod is provided with lower groove.
The cylindrical concentric column 48 of locking device upper section is directly nested in mandril 39 during installation, so that installation jail
Gu the deck 49 in locking device middle section with a thickness of 1 millimeter or so；The lower surface of the deck 49 in the middle section of locking device and bracket
Upper side form angle, making it is in not only to realize the function of hook locking, but also meet unlock, accumulation of energy release smoothly function.
It limits fixator set on seat 44 and is used for fixed pivot pin 43, pressure plare 38 is set as cyclic annular, lays on anchor ring in matrix
There is round through hole, is to balance inner and outer air pressure；The axle center of pivot pin 43 and apart 1 millimeter or so of the most outer of locking device,
The distance of the distance of shaft centers central axes of pivot pin 43 is shorter than the setting of distance of the most outer of locking device apart from axis, so that locking
And unlock is realized easily and achieves good effect.In actual use, the frizzen 42 of release device bottom setting, is storing
When can discharge, as long as touching frizzen 42, latch hook 41 breaks off relations, so that it may unlock and realize the release of accumulation of energy easily.Release device
The frizzen 42 of bottom setting, in accumulation of energy release, as long as touching frizzen 42, U-shaped latch hook 41 breaks off relations, so that it may unlock easily
And realize the release of accumulation of energy.The outer of 49 upper surface of deck tilts down, outside 49 upper surface of deck in the middle section of locking device
Angle is formed along the plane for tilting down setting and locking device lower section stent outer wall and 49 lower surface of deck, accumulation of energy can be made
Discharge smooth, when the plane of stent outer wall and 49 lower surface of deck forms 60 degree of angles, releasing effect is best.The bottom surface of bracket
Center is provided with truncated cone-shaped slot, not only meets cradling function, but also saves material and mitigate own wt.When 43 distance of shaft centers of pivot pin limits seat
Horizontal distance hour of the horizontal distance at 44 centers than 49 outer of deck away from locking device center, the effect of locking and unlocking is most
It is good.Pedestal 40 is arranged on the fuselage 1, and frizzen 42 hits pedestal 40, and latch hook 41 deflects to break off relations with locking device and unlock, bullet
The elongation release elastic potential energy of spring 37 launches completion at this time.
Finally, it should be noted that the foregoing is only a preferred embodiment of the present invention, it is not intended to restrict the invention,
Although the present invention is described in detail referring to the foregoing embodiments, for those skilled in the art, still may be used
To modify the technical solutions described in the foregoing embodiments or equivalent replacement of some of the technical features,
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (9)
1. a kind of airplane catapult system, the aircraft is made of fuselage (1) and wing (2), is keel knot inside the fuselage (1)
Structure, and the fuselage (1) head is equipped with cockpit (3), is equipped with main cabin (4) in the middle part of aircraft characterized by comprising
The main cabin (4) and the fuselage (1) are separable setting；
It launches locking device (5), the main cabin (4) is attached with the fuselage (1) by the ejection locking device (5)；
Parachute (6), the parachute (6) connect with the main cabin (4)；
Controller, trigger of the controller respectively with ejection locking device (5), the parachute (6) are electrically connected.
2. airplane catapult system according to claim 1, it is characterised in that: the multiple seperated hatch covers of the main cabin (4) are constituted,
And each seperated hatch cover it is symmetrical be arranged in the fuselage (1) upper half；Each described seperated hatch cover
It is made of outer cover (9) and floor (10)；Floor (10) upper surface is equipped with passenger seat, the corresponding seperated hatch cover in left and right
Enclose manned cabin.
3. airplane catapult system according to claim 2, it is characterised in that: the outer cover (9) is far from the floor (10)
Two corners and the floor (10) far from the two corners of the outer cover (9) be respectively equipped with fixed anchor point (11)；The parachute
(6) it is multiple settings, and is connect respectively with each anchor point (11).
4. airplane catapult system according to claim 3, it is characterised in that: the cockpit (3) is locked by the ejection
Determine device (5) to connect with the fuselage (1)；And the cockpit (3) be equipped with anchor point (11), the parachute (6) with it is described
Anchor point (11) connection.
5. airplane catapult system according to claim 4, it is characterised in that: the controller include master controller (12) and
From controller (13)；The main control setting is in the cockpit (3), and the master controller (12) is equipped with and starts switch
And first height sensor；It is described to be multiple settings from controller (13) and be separately positioned on each seperated hatch cover one by one
On, it is described to be electrically connected from controller (13) and the master controller (12), and it is respectively equipped with the second height sensor；It is described from
Controller (13) is electrically connected with corresponding parachute (6) and the ejection locking device (5) respectively.
6. airplane catapult system according to claim 1, it is characterised in that: the parachute (6) includes being arranged coaxial
The central bubble (16) of the one of heart line and an exumbrella cover (21)；The internal filling gas of center bubble (16), and the center bubble
(16) there is a guidance part；An inflatable chamber is set inside the exumbrella cover (21), is wrapped central bubble (16) by the inflatable chamber
In being overlying on, and the guidance part position of the exumbrella cover (21) bottom adjacent central bubble (16) is equipped with a bottom surface, and the bottom surface
It connect and is equipped with multiple air inlets (25) with central bubble (16), it is tapered from top to bottom that exumbrella cover (21) appearance forms one
Inclined-plane；The bottom surface is a plastotype ring body, and the plastotype ring body is around the multiple air inlets (25) of setting；The center bubble
(16) external rings set multiple flexible bodies (20) and bottom ora terminalis is equipped with a guidance part, and the flexible body (20) other end then connects
Be connected to that exumbrella cover (21) is internal and the one limitation rope (19) of guidance part bottom connection, limitation rope (19) other end and
Anchor point (11) connection；The axial symmetry angle on exumbrella cover (21) top sets a pressure relief opening (26) and the exumbrella cover
(21) bottom end is equipped with multiple drawstrings (27), and the multiple drawstring (27) connection has ponderable main cabin (4)；The plastotype ring
Body is rigid；The guidance part is curved surface；The neighbouring anchor point (11) ring of the drawstring (27) connects a connection ring (28).
7. airplane catapult system according to claim 1, it is characterised in that: the lateral bullet of ejection locking device (5)
Firing angle degree is between 30 degree to 60 degree of upward from horizontal.
8. airplane catapult system according to claim 1, it is characterised in that: the ejection locking device (5) includes vertical
The stack shell (36) of setting, stack shell (36) top are equipped with upper top cover (35), and ejection system is equipped in the stack shell (36)；It is described
Ejection system upper end be fixedly connected with stack shell (36) inner cavity top, the bottom end of ejection system extends to stack shell (36) bottom lower end
Outside mouthful, and ejection system and stack shell (36) are coaxial；The ejection system include energy storage equipment, locking device, release device and
It limits seat (44), the energy storage equipment includes spring (37), pressure plare (38) and mandril (39), and one end of spring (37) is certainly
By holding, the other end of spring (37) is contacted with pressure plare (38) upper surface, one end of pressure plare (38) lower surface and mandril (39)
It is detachably connected, the other end of mandril (39) passes through limitation seat (44) and is detachably connected with locking device, and limitation seat (44) also turns
Dynamic to be connected with release device, release device and locking device, which are clamped, when spring (37) compresses limits locking device；The top
The upper and lower end face shaft core position of bar (39) is provided with upper groove (45), and the upper surface of locking device is provided with and upper groove (45) phase
Matched concentric column (48), wherein upper groove (45) inner wall has internal screw thread, and the outer wall of concentric column (48) has external screw thread, mandril (39)
Lower end and the upper end of locking device be detachably connected by the internal and external threads of upper groove (45) and concentric column (48).
9. airplane catapult system according to claim 1, it is characterised in that: the locking device includes at least concentric column
(48) and the circular deck (49) positioned at locking device middle section, deck (49) lower surface are plane；The release device
Including at least the latch hook (41) for being located at side, the upper surface of latch hook (41) is plane, and latch hook (41) is upper when spring (37) compresses
The lower surface of surface and deck (49) is clamped；The latch hook (41) further includes the barrier flaps being arranged with latch hook (41) with side bottom
(47) and in the bottom of the other side of latch hook (41) frizzen (42) being arranged；The lower section of the locking device is round table-like
Bracket, the plane of locking device lower section stent outer wall and deck (49) lower surface forms angle；On the deck (49)
The outer on surface tilts down, and the bottom center of bracket is provided with truncated cone-shaped slot；The limitation seat (44) is by the small straight of upper section
Diameter section, lower section enlarged diameter section and linking reduced diameter section and enlarged diameter section between rotary table section, reduced diameter section, enlarged diameter section with
And rotary table section is structure as a whole and has the through-lumen to match with mandril (39) outer diameter, it is wherein longitudinal on enlarged diameter section side wall
It is provided with rectangular opening, rectangular opening two sides are each provided with a fixator, coaxial through hole is provided on two fixators；Release device is plate
Shape structure, the spacing between the thickness of plate release device and two fixators match, and the top of release device side is provided with circle
Shape through hole, pivot pin (43) by release device and limit seat through the same axis through hole of two fixators and the through hole of release device
(44) pin joint；The pressure plare (38) is ring-type, is laid with round through hole in matrix on anchor ring；The limitation seat
(44) with release device by pivot pin (43) pin joint, the horizontal distance at pivot pin (43) distance of shaft centers limitation seat (44) center compares deck
(49) horizontal distance of the outer away from locking device center is small；It further include pedestal (40), one end of pedestal (40) upper surface is provided with
Inertia rod is provided with lower groove in the upper surface of inertia rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811505061.8A CN109747806A (en) | 2018-12-10 | 2018-12-10 | A kind of airplane catapult system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811505061.8A CN109747806A (en) | 2018-12-10 | 2018-12-10 | A kind of airplane catapult system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109747806A true CN109747806A (en) | 2019-05-14 |
Family
ID=66403644
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811505061.8A Pending CN109747806A (en) | 2018-12-10 | 2018-12-10 | A kind of airplane catapult system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109747806A (en) |
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| CN111976948A (en) * | 2020-09-02 | 2020-11-24 | 南昌航空大学 | Pneumatic layout of flying wing type unmanned fighting bomber |
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