CN106516148A - Tubular launching device for aircraft launching and missile support mechanism of tubular launching device - Google Patents
Tubular launching device for aircraft launching and missile support mechanism of tubular launching device Download PDFInfo
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- CN106516148A CN106516148A CN201610991864.3A CN201610991864A CN106516148A CN 106516148 A CN106516148 A CN 106516148A CN 201610991864 A CN201610991864 A CN 201610991864A CN 106516148 A CN106516148 A CN 106516148A
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- aircraft
- bullet
- support mechanism
- bullet support
- spring
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- 230000007246 mechanism Effects 0.000 title claims abstract description 51
- 230000008878 coupling Effects 0.000 claims description 8
- 238000010168 coupling process Methods 0.000 claims description 8
- 238000005859 coupling reaction Methods 0.000 claims description 8
- 230000011664 signaling Effects 0.000 claims description 8
- 230000008901 benefit Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract description 3
- 230000008569 process Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 239000004677 Nylon Substances 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 210000003205 muscle Anatomy 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Details Of Connecting Devices For Male And Female Coupling (AREA)
Abstract
The invention provides a tubular launching device for aircraft launching and a missile support mechanism of the tubular launching device. The missile support mechanism is arranged in a launching barrel of the tubular aircraft launching device, and in the aircraft launching process, the missile support mechanism is used for supporting and fixing an aircraft in the launching barrel. The missile support mechanism comprises a connection seat, an electrical connector missile support, a fixing pin missile support and two spring pin missile supports, wherein the electrical connector missile support, the fixing pin missile support and the two spring pin missile supports are fixedly connected with the connection seat, the two spring pin missile supports are arranged oppositely, and the electrical connector missile support and the fixing pin missile support are arranged oppositely so that the aircraft can be supported and fixed from four positions on the periphery of the tailcone of the aircraft. Compared with the prior art, the missile support mechanism has the advantages that the structure is simple and compact, the missile support mechanism is suitable for aircrafts of a large number of types, and the missile supports have complete functions.
Description
Technical field
The present invention relates to the technical field of vehicle launch equipment, is specifically related to a kind of cartridge type for vehicle launch
Discharger and its bullet support mechanism.
Background technology
Vehicle launch equipment commonly used in the prior art has ejection type transmitting equipment and towed transmitting equipment etc..
The main formula of ejection type transmitting equipment tightens up rubber band by motor, discharges rubber band in transmitting, thus by rubber
The potential energy of muscle is the kinetic energy of aircraft, makes aircraft reach takeoff speed.But the technical scheme is suitable for the wing of aircraft
Limited types, and accessible flight speed is relevant with rubber band energy storage and energy rate of release, therefore limit aircraft institute
The maximum takeoff speed that can be reached, general takeoff speed can only achieve 20m/s-30m/s, limit the scope of application of aircraft.
Launching cradle energy storage is too high to be susceptible to danger, and in energy release process can produce overload to launching cradle some, affects
The service life of launching cradle.After the ejection of certain number of times, periodically need to be safeguarded, maintenance cost is higher.One for launching every time
Cause property is not very good, and each ejection status is otherwise varied；Standby fleet-footed runner person is more, and launching cradle is heavier, needs multiple personnel to carry out
Carry, and after carrying, need related personnel to install launching cradle, should be noted in installation process between each movable part not
Collide, general standby fleet-footed runner person needs more than 5.
Aircraft is generally connected with pulling equipment (generally automobile) by towed launching technique by support, by vapour
The speed of car gives aircraft one initial velocity, after aircraft obtains initial velocity, aircraft is separated with support, realizes flight
The transmitting of device.This kind of mode equally exists the technical problem of complex operation (need pulling equipment and need multi-user collaborative operation).
The content of the invention
The embodiment of the present invention provides a kind of cartridge type discharger for vehicle launch and its plays support mechanism, existing to solve
There are complex structure and unhandy technical problem present in the vehicle launch equipment of technology.
To solve the above problems, a kind of bullet support machine for aircraft cartridge type discharger is embodiments provided
Structure, the bullet support mechanism are located in the launching tube of cartridge type launch craft device, during vehicle launch, the bullet support machine
Structure is for being supported to aircraft and fix in launching tube；The bullet support mechanism includes a connecting seat, an electric interfaces bullet
Support, a steady pin bullet support and two spring catch bullet supports；Wherein, the electric interfaces bullet support, the steady pin bullet support and institute
State two spring catch bullet supports to be fixedly connected with the connecting seat respectively, described two spring catch bullet supports are oppositely arranged, it is described electric
Interface bullet support and the steady pin bullet support are oppositely arranged, and aircraft are supported with four positions from aircraft tail cone ring week
And fixation.
According to one preferred embodiment of the present invention, the electric interfaces bullet support includes electric interfaces seat, the electric interfaces seat
Bottom be fixedly connected with the connecting seat, top is provided with the first supporting surface and electric interfaces supporting walls, and described first supports
Face is used for the tail cone bottom surface for supporting aircraft, inlays and be provided with adapter on the electric interfaces supporting walls, and the adapter is used for
The signal of telecommunication connects aircraft and launching tube.
According to one preferred embodiment of the present invention, the adapter includes linking together and be embedded at respectively and described electrically connects
The aircraft connector and transmitting coupling sleeve of mouthful supporting walls both sides, the aircraft connector for carry-on letter
The connection of number interface, the transmitting coupling sleeve is for being connected with the signaling interface on launching tube.
According to one preferred embodiment of the present invention, the electric interfaces supporting walls are also set in the side for inlaying aircraft connector
Have a boss, the boss for aircraft tail cone on groove fit positioning, to ensure the aircraft connector with flight
Signaling interface para-position on device is accurate.
According to one preferred embodiment of the present invention, the spring catch bullet support includes spring key seat, the bottom of the spring key seat
It is fixedly connected with the connecting seat, top is provided with the second supporting surface and spring catch supporting walls, second supporting surface is used to prop up
The tail cone bottom surface of support aircraft, the spring catch supporting walls are provided with T-shaped hole on parallel to the second supporting surface direction, described
The small end in T-shaped hole is provided with spring catch spring and spring catch, the spring catch towards second supporting surface in the T-shaped hole
Circumferential profile for T-shaped, its small end stretches out in the small end in the T-shaped hole, and inserts in the corresponding fixing hole of aircraft tail cone, with
Constraint is fixed to aircraft tail cone, the big end of the spring catch is held in the inwall of launching tube；The spring catch spring
One end holds the stepped locations in the T-shaped hole, and the other end holds the spring catch, and the spring catch spring is in compressive state；
The spring catch spring is for when playing support mechanism and skidding off launching tube, ejecting the T-shaped hole by the spring catch, so that aircraft
With spring catch bullet support constraint relief.
According to one preferred embodiment of the present invention, the spring key seat is provided with the direction of vertical second supporting surface and pushes away
Bullet pin, the bullet pin that pushes away in the presence of bullet pin spring is pushed away, when the spring catch constraint relief, push away bullet pin and will push away elastic force applying
In aircraft tail cone bottom surface, to accelerate aircraft with the disengaging for playing support mechanism.
According to one preferred embodiment of the present invention, the steady pin bullet support includes fixing key seat, the bottom of the fixing key seat
It is fixedly connected with the connecting seat, top is provided with the 3rd supporting surface and steady pin supporting walls, the 3rd supporting surface is used to prop up
The tail cone bottom surface of support aircraft, the steady pin supporting walls are provided with pin-and-hole on parallel to the 3rd supporting surface direction, described
Pin-and-hole is realized playing the fixation of support mechanism and launching tube for coordinating with the steady pin on launching tube.
According to one preferred embodiment of the present invention, the spring catch supporting walls are oblique in the side near second supporting surface
Face structure, the ramp structure is for adaptable with the lateral profile of aircraft tail cone side, it is ensured that abuts with aircraft tail cone and props up
Support.
According to one preferred embodiment of the present invention, the shape contour of first supporting surface and the 3rd supporting surface and flight
The shape contour of device tail cone bottom surface is adapted so that aircraft tail cone bottom surface it is reliable and stable with first supporting surface and described
The contact of 3rd supporting surface is supported.
To solve above-mentioned technical problem, the present invention also provides a kind of cartridge type discharger for vehicle launch, described
Discharger includes launching tube and the bullet support mechanism any one of the above-described embodiment inside the launching tube.
Relative to prior art, cartridge type discharger provided by the present invention for vehicle launch and its support mechanism is played,
The bullet support mechanism is capable of achieving following functions by coordinating with aircraft tail cone section：Fixed aircraft；There is provided aircraft to connect with outside
The electric interfaces for connecing；Sufficiently large supporting surface is given in transmitting, with the case where sufficiently large thrust is provided as aircraft
Reduce local stress；Keep the fixation of bullet support and cylinder；Bullet support can be released bullet support in time and be constrained with aircraft after ejecting cylinder, and
Accelerate to depart from, it is ensured that unmanned drive end unit oar reliably can be opened, while electric interfaces disconnect；Between bullet support, space is sufficiently large, fits
Paddle structure is folded for various aircraft.The advantage of the cartridge type discharger is：Simple and compact for structure, Fit Models are more, bullet
Support is realized multiple functional.
Description of the drawings
For the technical scheme being illustrated more clearly that in the embodiment of the present invention, below will be to making needed for embodiment description
Accompanying drawing is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the present invention, for
For those of ordinary skill in the art, on the premise of not paying creative work, can be obtaining other according to these accompanying drawings
Accompanying drawing.
Fig. 1 is structural representation of the present invention for bullet one preferred embodiment of support mechanism of aircraft cartridge type discharger；
Fig. 2 is that Fig. 1 embodiments are hit by a bullet the polycrystalline substance schematic diagram of support mechanism；
Fig. 3 is the structural representation that play support mechanism and aircraft tail cone cooperation of the present invention for aircraft cartridge type discharger
Figure；
Fig. 4 is the positive structure schematic of electric interfaces bullet support in Fig. 1 embodiments；
Fig. 5 is the structure schematic diagram of electric interfaces bullet support in Fig. 1 embodiments；
Fig. 6 is the sectional view of electric interfaces bullet support in Fig. 1 embodiments；
Fig. 7 is the overall structure diagram of spring catch bullet support in Fig. 1 embodiments；
Fig. 8 is the structure sectional view of spring catch bullet support in Fig. 1 embodiments；And
Fig. 9 is the overall structure diagram of steady pin bullet support in Fig. 1 embodiments.
Specific embodiment
With reference to the accompanying drawings and examples, the present invention is described in further detail.It is emphasized that following implement
Example is merely to illustrate the present invention, but the scope of the present invention is not defined.Likewise, following examples are only the portion of the present invention
Point embodiment and not all embodiments, the institute obtained under the premise of creative work is not made by those of ordinary skill in the art
There are other embodiments, belong to the scope of protection of the invention.
It is that the present invention is preferred for the bullet support mechanism one of aircraft cartridge type discharger to see also Fig. 1 and Fig. 2, Fig. 1
The structural representation of embodiment, Fig. 2 are that Fig. 1 embodiments are hit by a bullet the polycrystalline substance schematic diagram of support mechanism.The bullet support mechanism is located at cylinder
In the launching tube (not shown) of formula launch craft device, during vehicle launch, support mechanism is played in launching tube
It is interior aircraft to be supported and is fixed, the main flight equipment such as including unmanned plane of described aircraft in the present invention.
The bullet support mechanism includes a connecting seat 410, an electric interfaces bullet support 420, a steady pin bullet support 430 and two bullets
Spring pin bullet support 440.
Specifically, electric interfaces bullet support 420, steady pin bullet support 430 and two spring catch bullet supports 440 respectively be connected
Seat 410 is fixedly connected, and specific type of attachment can be to be fastenedly connected by screw.As connecting seat 410 is that main power is held
Section, its effect is that the power of the generation such as electromotor or combustor or propeller is delivered on unmanned plane, is that unmanned plane is carried
For active force, it is ensured that unmanned plane can reach and enough go out launching tube speed, i.e. initial velocity；Therefore connecting seat 410 is preferably adopted
Scleroid and heat-resisting, wear-resisting alloy material is made, and specific material those skilled in the art can be according to design requirement
Voluntarily choose, will not enumerate herein.
Wherein, two spring catch bullet supports 440 are oppositely arranged, that is, be arranged on the relative both sides of aircraft tail cone 500, Ke Yibao
Card has the effect for preferably resisting corresponding deflection torque after connecting and fixing.Electric interfaces bullet support 420 and steady pin bullet support
430 are oppositely arranged, so that electric interfaces bullet support 420, steady pin bullet support 430 and two spring catch bullet supports 440 are from aircraft tail
Four positions for boring 500 rings week are supported to aircraft and fix.Fig. 3 is seen also, Fig. 3 is the present invention for aircraft
The structural representation for playing support mechanism and the cooperation of aircraft tail cone of cartridge type discharger.Wherein, the bottom of aircraft tail cone 500 is used
In motor (not shown) is installed, motor is used to drive the tail-rotor of unmanned plane to rotate.Space between four bullet supports is that tail-rotor is pre-
The space stayed, unmanned plane tail cone underlying space are motor headspace.
See also Fig. 4-Fig. 6, Fig. 4 is the positive structure schematic of electric interfaces bullet support in Fig. 1 embodiments, Fig. 5 is
The structure schematic diagram of electric interfaces bullet support in Fig. 1 embodiments, Fig. 6 are the sectional views of electric interfaces bullet support in Fig. 1 embodiments.
The electric interfaces bullet support 420 includes electric interfaces seat 421, and bottom and the connecting seat 410 of the electric interfaces seat 421 lead to
Cross screw to be fixedly connected, top is provided with the first supporting surface 422 and electric interfaces supporting walls 423, first supporting surface 422 is used for
The bottom surface of aircraft tail cone 500 is supported, wherein, the shape of 422 shape contour of the first supporting surface and 500 bottom surface of aircraft tail cone
Profile be adapted so that the bottom surface of aircraft tail cone 500 it is reliable and stable contact support with first supporting surface 422, specifically,
Step side 4221 can be set in the edge placement of the first supporting surface 422, the step side 4221 is used to limit aircraft tail
Bore the position of 500 bottom surfaces.
Inlay on the electric interfaces supporting walls 423 and be provided with adapter 424, adapter 424 is used for the signal of telecommunication and connects aircraft
With launching tube.Specifically, the adapter 424 includes linking together and being embedded at respectively 423 both sides of electric interfaces supporting walls
Aircraft connector 4241 and transmitting coupling sleeve 4242, the aircraft connector 4241 is for connecing with carry-on signal
Mouth connection, launches coupling sleeve 4242 for being connected with the signaling interface on launching tube.
Wherein, adapter 424 can be the version of contact and golden finger, can both stablize transmission signal, again can be with
Electrical connection easily release after support mechanism goes out launching tube being played.Further, the adapter 424 and electric interfaces supporting walls 423
Between be additionally provided with nylon cushion block 425, for ensureing that circuit board reserves certain distance with adapter 424, it may also be used for cabling and be
Pcb board components and parts reserved location.
Connection is provided with electric interfaces supporting walls 423 between aircraft connector 4241 and transmitting coupling sleeve 4242 logical
Hole 426, the connection through hole 426 is for through the connecting wire aircraft connector 4241 and transmitting coupling sleeve 4242
(not shown).
Electric interfaces bullet support 420 provides the electric interfaces of same aircraft, it is ensured that reliably can transmit under different operating modes
Signal, and in transmitting (going out launching tube) rapid ring off signal transmission afterwards, and there is no the series winding of signalling contact.
It is further preferred that electric interfaces supporting walls 423 are additionally provided with boss in the side for inlaying aircraft connector 4241
427, the boss 427 for aircraft tail cone 500 on groove (not indicating in figure) coordinate positioning, with ensure aircraft connect
Device 4241 is accurate with carry-on signaling interface para-position.
See also Fig. 7 and Fig. 8, Fig. 7 be spring catch bullet support in Fig. 1 embodiments overall structure diagram, Fig. 8 is figure
The structure sectional view of spring catch bullet support in 1 embodiment, the spring catch bullet support 440 include spring key seat 441, the bottom of spring key seat
It is fixedly connected with connecting seat 410, top is provided with the second supporting surface 442 and spring catch supporting walls 443, second supporting surface 442
For supporting the bottom surface of aircraft tail cone 500.
Preferably, the spring catch supporting walls 443 are being ramp structure 4431 near the side of the second supporting surface 442, and this is oblique
For being adapted with the lateral profile of 500 side of aircraft tail cone, specifically, the ramp structure 4431 can be face structure 4431
The radiused ramp being adapted with 500 side of aircraft tail cone, for ensureing with aircraft tail cone 500 against support.
The spring catch supporting walls 443 are provided with T-shaped hole, the small end direction in T-shaped hole on parallel to 442 direction of the second supporting surface
Second supporting surface 442, is provided with spring catch spring 444 and spring catch 445 in T-shaped hole, the circumferential profile of spring catch 445 is also T
Type, its small end stretch out in the small end in T-shaped hole, and for inserting in the corresponding fixing hole of aircraft tail cone 500, with to aircraft tail
Cone 500 is fixed constraint.
The big end of spring catch 445 is held in the inwall of launching tube；One end of spring catch spring 444 holds the step in T-shaped hole
Position, the shoulder of other end top supporting spring pin 445, spring catch spring 444 are in compressive state；The spring catch spring 444 is used for
When bullet support mechanism skids off launching tube, spring catch 445 is ejected into T-shaped hole, so that aircraft is released about with spring catch bullet support 440
Beam.
Further, the spring key seat 441 is additionally provided with the direction of vertical second supporting surface 442 and pushes away bullet pin 446, and this pushes away
Bullet pin 446 when 445 constraint relief of spring catch, pushes away bullet pin 446 and will push away elastic force being applied in the presence of bullet pin spring 447 is pushed away
The bottom surface of aircraft tail cone 500, to accelerate aircraft with the disengaging for playing support mechanism.
Refer to Fig. 9, Fig. 9 is the overall structure diagram of steady pin bullet support in Fig. 1 embodiments, the steady pin bullet support 430
Including fixing key seat 431, the bottom of the fixing key seat 431 is fixedly connected by screw with connecting seat 410, and top is provided with the 3rd
Support face 432 and steady pin supporting walls 433, the 3rd supporting surface 432 are used for the bottom surface for supporting aircraft tail cone 500, wherein, this
Three supporting surfaces, 432 shape contour is adapted with the shape contour of 500 bottom surface of aircraft tail cone, so that the bottom of aircraft tail cone 500
What face was reliable and stable contacts support with the 3rd supporting surface 432, specifically, can set in the edge placement of the 3rd supporting surface 432
Step side 4321 is put, the step side 4321 is used for the position for limiting 500 bottom surface of aircraft tail cone.
The steady pin supporting walls 433 are provided with pin-and-hole 434 on parallel to 432 direction of the 3rd supporting surface, and the pin-and-hole 434 is used for
Coordinate with the steady pin on launching tube, realize playing the fixation of support mechanism and launching tube.Launching tube can be released about when to be launched
Beam, in battery.
Further, the embodiment of the present invention also provides a kind of cartridge type discharger for vehicle launch, and the transmitting is filled
Put including but not limited to launching tube and play support mechanism inside the launching tube, with regard to play support mechanism detail technical features and
With the fit form of launching tube, the specific descriptions in above-described embodiment are referred to, here is omitted.
Relative to prior art, cartridge type discharger provided by the present invention for vehicle launch and its support mechanism is played,
The bullet support mechanism is capable of achieving following functions by coordinating with aircraft tail cone section：Fixed aircraft；There is provided aircraft to connect with outside
The electric interfaces for connecing；Sufficiently large supporting surface is given in transmitting, with the case where sufficiently large thrust is provided as aircraft
Reduce local stress；Keep the fixation of bullet support and cylinder；Bullet support can be released bullet support in time and be constrained with aircraft after ejecting cylinder, and
Accelerate to depart from, it is ensured that unmanned drive end unit oar reliably can be opened, while electric interfaces disconnect；Between bullet support, space is sufficiently large, fits
Paddle structure is folded for various aircraft.The advantage of the cartridge type discharger is：Simple and compact for structure, Fit Models are more, bullet
Support is realized multiple functional.
The section Example of the present invention is the foregoing is only, is not thereby limited the scope of the invention, every utilization
Equivalent device or equivalent flow conversion that description of the invention and accompanying drawing content are made, or directly or indirectly it is used in other correlations
Technical field, be included within the scope of the present invention.
Claims (10)
1. a kind of bullet support mechanism for aircraft cartridge type discharger, it is characterised in that the bullet support mechanism is sent out located at cartridge type
Penetrate in the launching tube of aircraft device, during vehicle launch, it is described bullet support mechanism in launching tube to aircraft
It is supported and fixes；The bullet support mechanism includes a connecting seat, an electric interfaces bullet support, a steady pin bullet support and two bullets
Spring pin bullet support；Wherein, the electric interfaces bullet support, the steady pin bullet support and described two spring catch bullet supports respectively with it is described
Connecting seat is fixedly connected, and described two spring catch bullet supports are oppositely arranged, the electric interfaces bullet support and the steady pin bullet support phase
To arranging, aircraft is supported and is fixed with four positions from aircraft tail cone ring week.
2. bullet support mechanism according to claim 1, it is characterised in that the electric interfaces bullet support includes electric interfaces seat,
The bottom of the electric interfaces seat is fixedly connected with the connecting seat, and top is provided with the first supporting surface and electric interfaces are supported
Wall, first supporting surface are used for the tail cone bottom surface for supporting aircraft, inlay and be provided with adapter on the electric interfaces supporting walls,
The adapter is used for the signal of telecommunication and connects aircraft and launching tube.
3. bullet support mechanism according to claim 2, it is characterised in that the adapter includes linking together and difference is embedding
Located at the aircraft connector and transmitting coupling sleeve of the electric interfaces supporting walls both sides, the aircraft connector is used for
It is connected with carry-on signaling interface, the coupling sleeve of launching is for being connected with the signaling interface on launching tube.
4. bullet support mechanism according to claim 3, it is characterised in that the electric interfaces supporting walls are inlaying aircraft company
The side for connecing device is additionally provided with boss, the boss for aircraft tail cone on groove fit positioning, to ensure the flight
Device adapter is accurate with carry-on signaling interface para-position.
5. bullet support mechanism according to claim 1, it is characterised in that the spring catch bullet support includes spring key seat, described
The bottom of spring key seat is fixedly connected with the connecting seat, and top is provided with the second supporting surface and spring catch supporting walls, and described
Two supporting surfaces are used for the tail cone bottom surface for supporting aircraft, and the spring catch supporting walls are on parallel to the second supporting surface direction
T-shaped hole is provided with, the small end in the T-shaped hole is provided with spring catch spring and spring in the T-shaped hole towards second supporting surface
Pin, the circumferential profile of the spring catch is T-shaped, and its small end stretches out in the small end in the T-shaped hole, and inserts the phase of aircraft tail cone
Answer in fixing hole, so that constraint is fixed to aircraft tail cone, the big end of the spring catch is held in the inwall of launching tube；It is described
One end of spring catch spring holds the stepped locations in the T-shaped hole, and the other end holds the spring catch, at the spring catch spring
In compressive state；The spring catch spring for play support mechanism skid off launching tube when, will the spring catch eject it is described T-shaped
Hole, so that aircraft and spring catch bullet support constraint relief.
6. bullet support mechanism according to claim 5, it is characterised in that the spring key seat is in vertical second supporting surface
Direction be provided with and push away bullet pin, the bullet pin that pushes away when the spring catch constraint relief, pushes away bullet in the presence of bullet pin spring is pushed away
Pin will push away elastic force and be applied to aircraft tail cone bottom surface, to accelerate aircraft with the disengaging for playing support mechanism.
7. bullet support mechanism according to claim 1, it is characterised in that the steady pin bullet support includes fixing key seat, described
The bottom of fixing key seat is fixedly connected with the connecting seat, and top is provided with the 3rd supporting surface and steady pin supporting walls, and described
Three supporting surfaces are used for the tail cone bottom surface for supporting aircraft, and the steady pin supporting walls are on parallel to the 3rd supporting surface direction
Pin-and-hole is provided with, the pin-and-hole is realized playing the fixation of support mechanism and launching tube for coordinating with the steady pin on launching tube.
8. bullet support mechanism according to claim 5, it is characterised in that the spring catch supporting walls are near described second
The side in support face be ramp structure, the ramp structure for the lateral profile of aircraft tail cone side be adapted, it is ensured that with fly
Row device tail cone is against support.
9. the bullet support mechanism according to claim 2 or 7, it is characterised in that first supporting surface and the described 3rd is supported
The shape contour in face and the shape contour of aircraft tail cone bottom surface are adapted so that aircraft tail cone bottom surface it is reliable and stable with institute
State the first supporting surface and the 3rd supporting surface contact is supported.
10. a kind of cartridge type discharger for vehicle launch, it is characterised in that the discharger include launching tube and
The bullet support mechanism described in any one of claim 1-9 inside the launching tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610991864.3A CN106516148B (en) | 2016-11-10 | 2016-11-10 | Cartridge type emitter and its bullet support mechanism for vehicle launch |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610991864.3A CN106516148B (en) | 2016-11-10 | 2016-11-10 | Cartridge type emitter and its bullet support mechanism for vehicle launch |
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| Publication Number | Publication Date |
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| CN106516148A true CN106516148A (en) | 2017-03-22 |
| CN106516148B CN106516148B (en) | 2019-01-11 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111661332A (en) * | 2020-07-08 | 2020-09-15 | 中国计量大学 | Butt joint device and method for unmanned aerial vehicle suspension type load unmanned trolley |
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| CN106039731A (en) * | 2016-07-06 | 2016-10-26 | 安徽大学 | Vertical launching platform system |
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| CN111661332A (en) * | 2020-07-08 | 2020-09-15 | 中国计量大学 | Butt joint device and method for unmanned aerial vehicle suspension type load unmanned trolley |
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