CN203222116U - High pressure water powered ejecting apparatus - Google Patents
High pressure water powered ejecting apparatus Download PDFInfo
- Publication number
- CN203222116U CN203222116U CN 201320025733 CN201320025733U CN203222116U CN 203222116 U CN203222116 U CN 203222116U CN 201320025733 CN201320025733 CN 201320025733 CN 201320025733 U CN201320025733 U CN 201320025733U CN 203222116 U CN203222116 U CN 203222116U
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- CN
- China
- Prior art keywords
- high pressure
- catapult
- launcher
- bottle
- storage bottle
- Prior art date
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 29
- 238000003860 storage Methods 0.000 claims abstract description 31
- 229910000838 Al alloy Inorganic materials 0.000 claims description 2
- 239000000956 alloy Substances 0.000 claims description 2
- 239000007788 liquid Substances 0.000 claims description 2
- 229910052751 metal Inorganic materials 0.000 claims description 2
- 239000002184 metal Substances 0.000 claims description 2
- 238000005516 engineering process Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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- Fluid-Pressure Circuits (AREA)
Abstract
The utility model discloses a high pressure water powered ejecting apparatus comprising a power source adding device, a launcher rack, an assistor and a controller. The launcher rack comprises a launcher base and a launcher track; the assistor comprises a storage bottle and an assistor nozzle, wherein the storage bottle is fixedly connected with the assistor nozzle; and the controller comprises a mechanical clamp and a hand brake. The ejecting apparatus further comprises a cylinder port which is fixedly connected with base; the assistor is arranged on the base of the launcher rack via the cylinder port; a lower end of the cylinder port is connected with the power source adding device; and the hand brake controls a clamping and release of the assistor via the mechanical clamp. By the above technical scheme, ejecting track length is shortened; ejecting energy is increased; ejecting technological difficulty is overcome; cost is reduced; and no pollution is caused, thereby protecting environment.
Description
Technical field
The utility model belongs to model airplane aircraft, small-sized unmanned plane technical field, relates in particular to a kind of high pressure water power catapult-launching gear.
Background technology
At present, unmanned plane is the aircraft that a kind of miniature self-service is driven, and it mainly relies on modes such as wireless remote control device, autopilot facility to fly.Because unmanned vehicle low cost of manufacture, simple to operate, safe, good concealment also can be carried plurality of devices, unmanned plane has become the favourable assistant of a plurality of industry fields.Use in army, launch military unmanned machine, since the convenient performance of launcher, reliability, and safety can be used for individual combat; On civilian, be widely used in launching of civilian unmanned plane and recreational aeromodelling airplane.
At present, the ejector of unmanned plane mainly leans on elastic power, motor power, hydraulic pressure cold air, spring powered and rocket-powered cataplane rely on elastic power, motor power, it is very long that these power of spring powered cause occurring the ejection orbit needs, and launch energy and be restricted, rocket-powered because technical sophistication, reason such as cost is high, be difficult to be widely used, simultaneously also since technical matters also be difficult to apply on small-sized unmanned aerial vehicle ejecting takes off.
Summary of the invention
Technical problem to be solved in the utility model is, provides a kind of high pressure water power catapult-launching gear to launch energy to shorten ejection orbit length, to increase, and reduces catapult technique, and cost-cutting is simultaneously environment friendly and pollution-free.
For solving the problems of the technologies described above, the technical solution adopted in the utility model is:
A kind of high pressure water active flight device catapult-launching gear comprises propulsion source adder device, launcher frame, booster device and control device; Described launcher frame comprises launcher base and launcher track; Described propulsion source adder device comprises pressure bottle 7, the conduit 13 that liquid water is housed; Described booster device comprises: storage bottle 1, booster nozzle 11, track slide block 2, and track slide block 2 is installed in the both sides of storage bottle 1, and storage bottle 1 is captiveed joint with booster nozzle 11; It is characterized in that: described catapult-launching gear also comprises hollow cylinder interface 4, and described hollow cylinder interface 4 is captiveed joint with base 5, and the booster device is positioned on the base 5 of emission frame by hollow cylinder interface 4; Described conduit 13 input ends are communicated with the mouth of pressure bottle 7, and the mouth of conduit 13 is communicated with storage bottle 1; Described control device comprises machinery folder 9, the rim brake 3 for locking or release booster nozzle 11, machinery folder 9 is connected with rim brake 3, described machinery folder 9 is installed on the base 5 of emission frame, and rim brake 3 comes clamping and releasing of short range control storage bottle 1 by machinery folder 9.
Described conduit 13 mouths link to each other by the lower end with hollow cylinder interface 4, thereby are communicated with storage bottle 1.
Described propulsion source adder device also comprises air pump 8, and described air pump 8 mouths are connected with the input end of pressure bottle 7.
Described catapult-launching gear has also comprised radio singlechip controller 10, and described radio singlechip controller 10 is installed on the launcher base 5, and the clamping that is used for Long-distance Control machinery folder 9 discharges, the switch of control air pump 8.
Described catapult-launching gear comprises the aircraft hook, and described flight hook is installed in the storage bottle outside, is used for connecting aircraft.
Described holding bottle 1 is high pressure resistant plastic bottle or high pressure resistant gold urn, and described transmitter framework and controller box are that aluminum alloy materials is made.
Compared with prior art, adopt the effect of technique scheme to be: the utility model adopts the high pressure water power catapult technique of innovation, will be through compressing water and air in the propulsion source adder device, be injected in the storage bottle of propelling unit, catapult-launching gear is opened the propelling unit jet pipe by controller, water sprays from the propelling unit jet pipe under the high-pressure gas pressure effect, and then produce than big momentum, according to conservation of momentum principle, aircraft obtains to take off more greatly initial velocity, thereby shortened ejection orbit length, increased and launched energy; Simple because of technology again, thus cost-cutting; As propulsion source, environment friendly and pollution-free with water and gas.And the setting up of rim brake that self-locking mechanism is arranged in the controller makes the machinery folder can carry out clamping and releasing of short range control storage bottle more convenient, effectively.
As a kind of preferred version of the present utility model, described conduit 13 mouths link to each other by the lower end with hollow cylinder interface 4, thereby are communicated with storage bottle 1.Make structure compacter like this, reduce perforate in storage bottle 1, the performance safety and reliability.
Propulsion source adder device has increased air pump 8, has increased and has launched energy, and technology is simple simultaneously, configuration easily, and cost reduces.
Setting up of radio singlechip controller 10, can Long-distance Control storage bottle 1 clamp and release can be controlled the switch of air pump 8 simultaneously, safety and reliability.The micro controller system executive command is to carry out control by special-purpose control software on the control software of the special use on the computer or the mobile device, and micro controller system and computer or mobile device carry out communication by radio equipment.Electric air pump provides compressed air gas source for ejector, to be assemblied on the launcher base, the closed manners of electric air pump switch is controlled by singlechip controller, and the radio singlechip controller also is used for replacing rim brake control simultaneously, i.e. radio singlechip controller control machinery clamps and releases.
The preferred hollow circular cylinder of cylinder interface in the catapult-launching gear, the preferred high pressure resistant conduit of conduit, air pump is preferably electric air pump or inflator, and material disposes easily, and cost is low, and is simple in structure, the safety performance height.
The material of storage bottle is high pressure resistant plastic bottle or high pressure resistant metal bottle, advance one and improve safety performance less, but the utility model is not limited to this two kinds of materials.
Description of drawings
Fig. 1 is high pressure water power catapult-launching gear assembly drawing.
Fig. 2 is booster device in the high pressure water power catapult-launching gear.
Fig. 3 is high pressure water power catapult-launching gear medium power source adder device.
Fig. 4 is high pressure water power catapult-launching gear middle controller device.
Fig. 5 is transmitter framework in the high pressure water power catapult-launching gear.
Fig. 6 is cataplane design sketch in the high pressure water power catapult-launching gear.
In Fig. 1: 1, storage bottle, 2, the track slide block, 3, rim brake, 4, the cylinder interface, 5, the launcher base, 6, the aircraft hook, 7, pressure bottle, 8, electric air pump, 9, the machinery folder, 10, micro controller system
Among Fig. 2: 11, booster nozzle.
Among Fig. 3: 12, aqueous water, 13, high pressure resistant conduit.
Among Fig. 4: 14, steel wire line.
Among Fig. 5: 15, launcher track.
The specific embodiment
Below in conjunction with accompanying drawing and present embodiment, the utility model is elaborated:
Embodiment of the present utility model as shown in Figure 1, high pressure water power catapult-launching gear comprises: launcher base 5, launcher track 15, storage bottle 1, cylinder interface 4, booster nozzle 11, storage bottle 1 adopts the screw thread assembling with booster nozzle 11, with unsintered tape and silica gel sealing, guaranteed that in the leak tightness of launching under the pressure booster nozzle 11 is by being installed in the locking of machinery folder and the release of launcher base; Cylinder interface 4 is captiveed joint with launcher base 5 by screw thread, the sealing of interface O type circle; Storage bottle 1 is positioned on the base 5 of emission frame by hollow circular cylinder interface 4, and this cylindrical interface provides pressurized air and aqueous water for storage bottle.Storage bottle 1 outside midway location arranges flight hook 6, is used for connecting aircraft; Attachment rail slide block 2 on the launcher track 15 of the both sides of storage bottle 1; Electric air pump 8 is installed on the launcher base 5, can conveniently provide source of the gas like this; Air and the aqueous water 12 of compression are housed in the pressure bottle 7, and the mouth of pressure bottle 7 is communicated with high pressure resistant conduit 13 input ends, and the mouth of high pressure resistant conduit 13 links to each other by the lower end with hollow circular cylinder interface 4, thereby is communicated with storage bottle; Control device comprises machinery folder 9, the rim brake 3 of self-locking mechanism is arranged, machinery folder 9 is connected by steel rope 14 with the rim brake 3 that self-locking mechanism is arranged, machinery folder 9 is installed on the base 5 of emission frame, has the rim brake of self-locking mechanism to come clamping and releasing of short range control booster nozzle 11 by machinery folder 9.Radio singlechip controller 10 is installed on the launcher base 5, and the switch of electric air pump 8 is controlled in can Long-distance Control storage bottle 1 clamp and release simultaneously.
Claims (7)
1. a high pressure water power catapult-launching gear comprises propulsion source adder device, launcher frame, booster device and control device; Described launcher frame comprises launcher base and launcher track; Described propulsion source adder device comprises pressure bottle (7), the conduit (13) that liquid water is housed; Described booster device comprises: storage bottle (1), booster nozzle (11), track slide block (2), and track slide block (2) is installed in the both sides of storage bottle (1), and storage bottle 1 is captiveed joint with booster nozzle 11; It is characterized in that: described catapult-launching gear also comprises hollow cylinder interface (4), and described hollow cylinder interface (4) is captiveed joint with base (5), and the booster device is positioned on the base (5) of emission frame by hollow cylinder interface (4); Described conduit (13) input end is communicated with the mouth of pressure bottle (7), and the mouth of conduit (13) is communicated with storage bottle (1); Described control device comprises machinery folder (9), the rim brake (3) for locking or release booster nozzle (11), machinery folder (9) is connected with rim brake (3), described machinery folder (9) is installed on the base (5) of emission frame, and rim brake (3) comes clamping and releasing of short range control storage bottle (1) by machinery folder (9).
2. according to the described high pressure water power of claim 1 catapult-launching gear, it is characterized in that: described conduit (13) mouth links to each other by the lower end with hollow cylinder interface (4), thereby is communicated with storage bottle (1).
3. according to claim 1 or 2 described high pressure water power catapult-launching gears, it is characterized in that: described propulsion source adder device also comprises air pump (8), and described air pump (8) mouth is connected with the input end of pressure bottle (7).
4. according to the described high pressure water power of claim 3 catapult-launching gear, it is characterized in that: described catapult-launching gear has also comprised radio singlechip controller (10), described radio singlechip controller (10) is installed on the launcher base (5), and the clamping that is used for Long-distance Control machinery folder (9) discharges, the switch of control air pump (8).
5. according to the described high pressure water power of claim 4 catapult-launching gear, it is characterized in that: described catapult-launching gear has comprised aircraft hook (6), and described flight hook (6) is installed in storage bottle (1) outside.
6. according to the described high pressure water power of claim 5 catapult-launching gear, it is characterized in that: described hollow cylinder interface (4) is hollow circular cylinder, and described conduit (13) is high pressure resistant conduit, and described air pump (8) is electric air pump or inflator.
7. according to the described high pressure water power of claim 6 catapult-launching gear, it is characterized in that: described holding bottle (1) is high pressure resistant plastic bottle or high pressure resistant metal bottle, and described transmitter framework and controller box are that aluminum alloy materials is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320025733 CN203222116U (en) | 2013-01-18 | 2013-01-18 | High pressure water powered ejecting apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320025733 CN203222116U (en) | 2013-01-18 | 2013-01-18 | High pressure water powered ejecting apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203222116U true CN203222116U (en) | 2013-10-02 |
Family
ID=49249129
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320025733 Expired - Fee Related CN203222116U (en) | 2013-01-18 | 2013-01-18 | High pressure water powered ejecting apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203222116U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103723281A (en) * | 2013-12-31 | 2014-04-16 | 北京中宇新泰科技发展有限公司 | Folding wing unmanned aerial vehicle pneumatic launcher |
| CN108128478A (en) * | 2017-11-27 | 2018-06-08 | 北京特种机械研究所 | A kind of accumulator tank for hydrodynamic force ejection |
| CN108657459A (en) * | 2018-05-07 | 2018-10-16 | 北京特种机械研究所 | A kind of hydrodynamic force catapult-launching gear of ship-board aircraft |
-
2013
- 2013-01-18 CN CN 201320025733 patent/CN203222116U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103723281A (en) * | 2013-12-31 | 2014-04-16 | 北京中宇新泰科技发展有限公司 | Folding wing unmanned aerial vehicle pneumatic launcher |
| CN103723281B (en) * | 2013-12-31 | 2016-02-24 | 北京中宇新泰科技发展有限公司 | A kind of folding wings unmanned plane Pneumatic catapult |
| CN108128478A (en) * | 2017-11-27 | 2018-06-08 | 北京特种机械研究所 | A kind of accumulator tank for hydrodynamic force ejection |
| CN108657459A (en) * | 2018-05-07 | 2018-10-16 | 北京特种机械研究所 | A kind of hydrodynamic force catapult-launching gear of ship-board aircraft |
| CN108657459B (en) * | 2018-05-07 | 2019-09-10 | 北京特种机械研究所 | A kind of hydrodynamic force catapult-launching gear of ship-board aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20131002 Termination date: 20150118 |
|
| EXPY | Termination of patent right or utility model |