CN206984420U - Unmanned plane high-pressure pneumatic catapult launcher - Google Patents
Unmanned plane high-pressure pneumatic catapult launcher Download PDFInfo
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- CN206984420U CN206984420U CN201720595221.7U CN201720595221U CN206984420U CN 206984420 U CN206984420 U CN 206984420U CN 201720595221 U CN201720595221 U CN 201720595221U CN 206984420 U CN206984420 U CN 206984420U
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- unmanned plane
- launcher
- support body
- pneumatic
- pressure
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- 229910000831 Steel Inorganic materials 0.000 claims abstract description 19
- 239000010959 steel Substances 0.000 claims abstract description 19
- 239000000872 buffer Substances 0.000 claims description 27
- 229910000838 Al alloy Inorganic materials 0.000 claims description 8
- 239000000956 alloy Substances 0.000 claims description 3
- 230000003139 buffering effect Effects 0.000 claims description 3
- 238000013016 damping Methods 0.000 claims description 3
- 230000001914 calming effect Effects 0.000 claims 1
- 238000010276 construction Methods 0.000 abstract description 6
- 239000007789 gas Substances 0.000 description 22
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000032683 aging Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
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Abstract
The utility model provides a kind of unmanned plane high-pressure pneumatic catapult launcher.The unmanned plane high-pressure pneumatic catapult launcher includes launcher support body, Pneumatic assembly and unmanned plane release device, the Pneumatic assembly and the unmanned plane release device are respectively arranged on the launcher support body both ends, the unmanned plane release device includes steel wire rope, described steel wire rope one end connects the unmanned plane release device, and the steel wire rope other end connects the Pneumatic assembly.A kind of unmanned plane high-pressure pneumatic catapult launcher provided by the utility model is applied in Mini-Unmanned Aerial Vehicles launch, overcome the shortcomings of existing catapult-launching gear, realize small volume, in light weight, floor space is small, it is simple in construction, deploy and to remove receipts rapid, and the unmanned plane of big load can be launched.
Description
Technical field
The utility model belongs to field of aviation machinery, more particularly to a kind of unmanned plane high-pressure pneumatic catapult launcher.
Background technology
With the continuous development of unmanned plane aerial remote sens ing technique, the application of unmanned plane is also more and more extensive, and unmanned plane occurs
Accident mainly occurred in the takeoff and landing stage, carries out taking off for unmanned plane by support launcher, can be very good
Improve the launching success rate of unmanned plane.Therefore design a kind of catapult-launching gear for adapting to a variety of places has turned into unmanned plane transmitting
Trend.It is domestic also fewer relative to such catapult-launching gear, be using more at present《The ejection of taking off of small-sized pilotless aircraft
Frame》Application number/the patent No.：200920107578.
The take-off launch frame of existing small-sized pilotless aircraft includes support body, launching trajectory, angular adjustment apparatus, triggering dress
Put, take-up and pay-off device and power elastic.The program uses aluminum alloy plate materials as main body, and elastic force elastic is power source, retractable cable
Device is electric capstan, and complicated integral structure, handling are complicated, weight is larger (typically in more than 100kg), and launch power is weaker,
Elastic force elastic has aging phenomenon, and rear elastic elastic force, which is used for multiple times, to be reduced, it is necessary to change elastic force elastic.
Utility model content
To solve the technical problem of existing catapult-launching gear, the utility model offer is a kind of to use gases at high pressure as power source
Catapult-launching gear, existing catapult-launching gear can be overcome the shortcomings of, realize small volume, in light weight, floor space is small, simple in construction, exhibition
It is rapid to open and remove receipts, and the unmanned plane high-pressure pneumatic catapult launcher of big load can be launched.
Unmanned plane high-pressure pneumatic catapult launcher provided by the utility model includes launcher support body, Pneumatic assembly and nothing
Man-machine release device, the Pneumatic assembly and the unmanned plane release device are respectively arranged on the launcher support body both ends, described
Unmanned plane release device includes steel wire rope, and described steel wire rope one end connects the unmanned plane release device, and the steel wire rope is another
End connects the Pneumatic assembly.
In a kind of preferred embodiment of unmanned plane high-pressure pneumatic catapult launcher provided by the utility model, it is described nobody
Machine release device includes shot trolley, unmanned plane grasping mechanism and relieving mechanism, the unmanned plane grasping mechanism and the release
In the shot trolley, the shot trolley includes small pulley sheave for mechanism, the small pulley sheave quantity be it is multiple, it is multiple
The small pulley sheave is respectively arranged on the shot trolley both sides, and can be in the launcher support body with respect to upper and lower surface scrolls fortune
It is dynamic.
In a kind of preferred embodiment of unmanned plane high-pressure pneumatic catapult launcher provided by the utility model, the transmitting
Frame support body includes support body body and support arm, and the support arm quantity is two, and two support arms are respectively arranged on the frame
Body body both ends.
In a kind of preferred embodiment of unmanned plane high-pressure pneumatic catapult launcher provided by the utility model, the support body
Body includes support body and quick connector, and the support body quantity is multiple, passes through the quick connection between multiple support bodys
Device connects.
In a kind of preferred embodiment of unmanned plane high-pressure pneumatic catapult launcher provided by the utility model, it is described nobody
Machine high-pressure pneumatic catapult launcher also includes buffer unit, and the buffer unit is located at the hair side by side with the Pneumatic assembly
Penetrate frame support body one end.
In a kind of preferred embodiment of unmanned plane high-pressure pneumatic catapult launcher provided by the utility model, the buffering
Device includes buffer fixed seat and buffer, and the buffer is located at the buffer fixed seat, and the buffer is air pressure
Damping buffering.
In a kind of preferred embodiment of unmanned plane high-pressure pneumatic catapult launcher provided by the utility model, the transmitting
Frame support body is aluminum alloy material.
It is described pneumatic in a kind of preferred embodiment of unmanned plane high-pressure pneumatic catapult launcher provided by the utility model
Component includes ejection cylinder, actuating plunger, high pressure gas valve and assembly pulley, the assembly pulley and is located at the launching cradle support body,
The high pressure gas valve is connected with the ejection cylinder, and the actuating plunger is described located at the ejection cylinder relative interior
Actuating plunger is connected by the assembly pulley with the steel wire rope.
Unmanned plane high-pressure pneumatic catapult launcher of the present utility model has the advantages that：
Apply in Mini-Unmanned Aerial Vehicles launch, overcome the shortcomings of existing catapult-launching gear, realize small volume, weight
Gently, floor space it is small, it is simple in construction, deploy and to remove receipts rapid, and the unmanned plane that can launch big load uses aluminum alloy plate materials
For main body, gases at high pressure are as power source, new release device, dismountable mounting means, such a launching cradle floor space
Small, expansion removes receipts rapidly, greatly reduces size compared to common launching cradle, facilitates the use of Mini-Unmanned Aerial Vehicles, has weight
Amount is light, small volume, it is simple in construction, easy to carry the features such as.Pressurization gas storage is carried out to caisson by a source of the gas first, stored up
Device of air mesohigh gas promotes the actuating plunger in pressurized strut, piston passes through steel wire rope and cunning by the control of operated pneumatic valve
Wheel group is connected in the release device of fixed unmanned plane, unmanned plane has been accelerated in short distance by the promotion of gases at high pressure
Rapidly degree, catapult-assisted take-off.The use of high pressure gas is that power source can reduce the weight of whole trigger mechanism, and realizes power
Maximum transmitted.During work, gases at high pressure enter in ejection cylinder, and promote actuating plunger to move backward, the steel wire being connected with piston
Rope pulls shot trolley, drives no human footmarks to accelerate to takeoff speed, and winged from erecting, and shot trolley is hit in moving end to be buffered
Device, buffer unit make shot trolley slowly slow down and stop at support body end, complete whole unmanned plane launch process.
Using dismountable some section (such as 3~4 section) support bodys and support meanss, can not be limited by place, structure letter
Single, assembling rapidly, deploys and removes receipts fast；Using pressure-air as power source, it is only necessary to change gas pressure and can reach
Launch unmanned plane of the load in 10~20kg scopes.Launch support body using aluminum alloy square tube making, overall weight can 100kg with
It is interior.
Brief description of the drawings
, below will be to needed for embodiment description in order to illustrate more clearly of the technical scheme in the embodiment of the utility model
The accompanying drawing to be used is briefly described, it should be apparent that, drawings in the following description are only some realities of the present utility model
Example is applied, for those of ordinary skill in the art, on the premise of not paying creative work, can also be according to these accompanying drawings
Other accompanying drawings are obtained, wherein：
Fig. 1 is the structural representation of the preferred embodiment of unmanned plane high-pressure pneumatic catapult launcher one provided by the utility model
Figure；
Fig. 2 is the structure of the preferred embodiment of Pneumatic assembly one of the unmanned plane high-pressure pneumatic catapult launcher shown in Fig. 1
Schematic diagram；
Fig. 3 is the structure of the preferred embodiment of buffer unit one of the unmanned plane high-pressure pneumatic catapult launcher shown in Fig. 1
Schematic diagram.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the embodiment of the utility model is carried out
Clearly and completely describing, it is clear that described embodiment is only part of the embodiment of the present utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The all other embodiment obtained, belong to the scope of the utility model protection.
Also referring to Fig. 1 to Fig. 3, wherein Fig. 1 is unmanned plane high-pressure pneumatic catapult-assisted take-off dress provided by the utility model
Put the structural representation of a preferred embodiment；Fig. 2 is the Pneumatic assembly of the unmanned plane high-pressure pneumatic catapult launcher shown in Fig. 1
The structural representation of one preferred embodiment；Fig. 3 is the buffer unit one of the unmanned plane high-pressure pneumatic catapult launcher shown in Fig. 1
The structural representation of preferred embodiment.
The unmanned plane high-pressure pneumatic catapult launcher 1 includes launcher support body 11, Pneumatic assembly 12, unmanned plane release
Device 13 and buffer unit 14.The Pneumatic assembly 12 and the unmanned plane release device 13 are respectively arranged on the launcher support body
11 both ends, the buffer unit 14 are located at described one end of launcher support body 11 side by side with the Pneumatic assembly 12.
The unmanned plane release device 13 includes steel wire rope 131, shot trolley 132, unmanned plane grasping mechanism 133 and release
Mechanism 134.Described one end of steel wire rope 131 connects the unmanned plane release device 13, described in the other end of steel wire rope 131 connection
Pneumatic assembly 12.The unmanned plane grasping mechanism 133 and the relieving mechanism 134 are in the shot trolley 132.It is described
Shot trolley 132 includes small pulley sheave 1321.The quantity of small pulley sheave 1321 is multiple, and multiple small pulley sheaves 1321 divide
Not She Yu the both sides of shot trolley 132, and can be in the launcher support body 11 with respect to the motion of upper and lower surface scrolls.
The launcher support body 11 includes support body body 111 and support arm 112.The quantity of support arm 112 be two, two
The individual support arm 112 is respectively arranged on the both ends of support body body 111.The launcher support body 11 is aluminum alloy material.
The support body body 111 includes support body 1111 and quick connector 1112.The quantity of support body 1111 is more to be multiple
Connected between the individual support body 1111 by the quick connector 1112.
The buffer unit 14 includes buffer fixed seat 141 and buffer 142.The buffer 142 is located at described slow
Device fixed seat 141 is rushed, the buffer 142 buffers for air-pressure damping.
The Pneumatic assembly 12 includes ejection cylinder 121, actuating plunger 122, high pressure gas valve 123 and assembly pulley 124.
The assembly pulley 124 is located at the launching cradle support body 11, and the high pressure gas valve 123 is connected with the ejection cylinder 121, institute
State actuating plunger 122 and pass through the assembly pulley 124 and institute located at the ejection relative interior of cylinder 121, the actuating plunger 122
Steel wire rope 131 is stated to connect.
Unmanned plane high-pressure pneumatic catapult launcher 1 of the present utility model has the advantages that：
Apply in Mini-Unmanned Aerial Vehicles launch, overcome the shortcomings of existing catapult-launching gear, realize small volume, weight
Gently, floor space it is small, it is simple in construction, deploy and to remove receipts rapid, and the unmanned plane of big load can be launched.Using aluminum alloy plate materials
For main body, gases at high pressure are as power source, new release device, dismountable mounting means, such a launching cradle floor space
Small, expansion removes receipts rapidly, greatly reduces size compared to common launching cradle, facilitates the use of Mini-Unmanned Aerial Vehicles, has weight
Amount is light, small volume, it is simple in construction, easy to carry the features such as.Pressurization gas storage is carried out to caisson by a source of the gas first, stored up
Device of air mesohigh gas promotes the actuating plunger 122 in pressurized strut, actuating plunger by the control of high pressure gas valve 123
122 are connected in fixed unmanned plane release device 13 by steel wire rope 131 and assembly pulley 124, are made by the promotion of gases at high pressure
Unmanned plane accelerates to takeoff speed, catapult-assisted take-off in short distance.The use of high pressure gas is that power source can reduce whole emitter
The weight of structure, and realize the maximum transmitted of power.During work, gases at high pressure enter in ejection cylinder 121, and promote start
Piston 122 moves backward, and the steel wire rope 131 being connected with actuating plunger 122 pulls shot trolley 132, drives no human footmarks to accelerate to
Takeoff speed, and it is winged from erecting, and shot trolley 132 makes shot trolley in moving end impact attenuation device 14, buffer unit 14
132 slowly slow down and stop at support body end, complete whole unmanned plane launch process.
Using dismountable some section (such as 3~4 section) support bodys and support meanss, can not be limited by place, structure letter
Single, assembling rapidly, deploys and removes receipts fast；Using pressure-air as power source, it is only necessary to change gas pressure and can reach
Launch unmanned plane of the load in 10~20kg scopes.Launch support body using aluminum alloy square tube making, overall weight can 100kg with
It is interior.
Embodiment of the present utility model is the foregoing is only, not thereby limits the scope of the claims of the present utility model, it is every
The equivalent structure or equivalent flow conversion made using the utility model specification and accompanying drawing content, or be directly or indirectly used in
Other related technical fields, are similarly included in scope of patent protection of the present utility model.
Claims (8)
- A kind of 1. unmanned plane high-pressure pneumatic catapult launcher, it is characterised in that including launcher support body, Pneumatic assembly and nobody Machine release device, the Pneumatic assembly and the unmanned plane release device are respectively arranged on the launcher support body both ends, the nothing Man-machine release device includes steel wire rope, and described steel wire rope one end connects the unmanned plane release device, the steel wire rope other end Connect the Pneumatic assembly.
- 2. according to the unmanned plane high-pressure pneumatic catapult launcher described in claim 1, it is characterised in that the unmanned plane is released Putting device includes shot trolley, unmanned plane grasping mechanism and relieving mechanism, the unmanned plane grasping mechanism and the relieving mechanism In the shot trolley, the shot trolley includes small pulley sheave, the small pulley sheave quantity be it is multiple, it is multiple described in Small pulley sheave is respectively arranged on the shot trolley both sides, and can be in the launcher support body with respect to the motion of upper and lower surface scrolls.
- 3. according to the unmanned plane high-pressure pneumatic catapult launcher described in claim 1, it is characterised in that the launcher frame Body includes support body body and support arm, and the support arm quantity is two, and two support arms are respectively arranged on the support body sheet Body both ends.
- 4. according to the unmanned plane high-pressure pneumatic catapult launcher described in claim 3, it is characterised in that the support body body Including support body and quick connector, the support body quantity is multiple, is connected between multiple support bodys by the quick connector Connect.
- 5. according to the unmanned plane high-pressure pneumatic catapult launcher described in claim 1, it is characterised in that the unmanned plane is high Dynamic catapult launcher of calming the anger also includes buffer unit, and the buffer unit is located at the launcher side by side with the Pneumatic assembly Support body one end.
- 6. according to the unmanned plane high-pressure pneumatic catapult launcher described in claim 5, it is characterised in that the buffer unit Including buffer fixed seat and buffer, the buffer is located at the buffer fixed seat, and the buffer is air-pressure damping Buffering.
- 7. according to the unmanned plane high-pressure pneumatic catapult launcher described in claim 1, it is characterised in that the launcher frame Body is aluminum alloy material.
- 8. according to the unmanned plane high-pressure pneumatic catapult launcher described in claim 1, it is characterised in that the Pneumatic assembly Including ejection cylinder, actuating plunger, high pressure gas valve and assembly pulley, the assembly pulley is located at the launching cradle support body, described High pressure gas valve is connected with the ejection cylinder, and the actuating plunger is located at the ejection cylinder relative interior, the start Piston is connected by the assembly pulley with the steel wire rope.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720595221.7U CN206984420U (en) | 2017-05-25 | 2017-05-25 | Unmanned plane high-pressure pneumatic catapult launcher |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720595221.7U CN206984420U (en) | 2017-05-25 | 2017-05-25 | Unmanned plane high-pressure pneumatic catapult launcher |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206984420U true CN206984420U (en) | 2018-02-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720595221.7U Expired - Fee Related CN206984420U (en) | 2017-05-25 | 2017-05-25 | Unmanned plane high-pressure pneumatic catapult launcher |
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| Country | Link |
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| CN (1) | CN206984420U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110027720A (en) * | 2019-05-13 | 2019-07-19 | 南京航空航天大学 | A kind of portable pneumatic fixed-wing unmanned aerial vehicle ejecting system and working method |
| RU2822927C1 (en) * | 2024-01-09 | 2024-07-16 | Общество С Ограниченной Ответственностью "Завод Сигнал" | Portable folding unit for ejection of small-size unmanned aerial vehicle |
-
2017
- 2017-05-25 CN CN201720595221.7U patent/CN206984420U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110027720A (en) * | 2019-05-13 | 2019-07-19 | 南京航空航天大学 | A kind of portable pneumatic fixed-wing unmanned aerial vehicle ejecting system and working method |
| CN110027720B (en) * | 2019-05-13 | 2023-09-26 | 南京航空航天大学 | Portable pneumatic fixed wing unmanned aerial vehicle ejection system and working method |
| RU2822927C1 (en) * | 2024-01-09 | 2024-07-16 | Общество С Ограниченной Ответственностью "Завод Сигнал" | Portable folding unit for ejection of small-size unmanned aerial vehicle |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180209 |
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| CF01 | Termination of patent right due to non-payment of annual fee |