CN106005435A - Pneumatic parachute opening system for parachute of unmanned aerial vehicle - Google Patents
Pneumatic parachute opening system for parachute of unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106005435A CN106005435A CN201610464631.8A CN201610464631A CN106005435A CN 106005435 A CN106005435 A CN 106005435A CN 201610464631 A CN201610464631 A CN 201610464631A CN 106005435 A CN106005435 A CN 106005435A
- Authority
- CN
- China
- Prior art keywords
- parachute
- cylinder
- unmanned plane
- deployment system
- pneumatic
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/62—Deployment
- B64D17/72—Deployment by explosive or inflatable means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/62—Deployment
- B64D17/70—Deployment by springs
Abstract
The invention discloses a pneumatic parachute opening system for a parachute of an unmanned aerial vehicle. The pneumatic parachute opening system comprises a parachute cylinder, a control valve and an air guide pipe, wherein a top plug is mounted in the parachute cylinder and divides the inside of the parachute cylinder into an ejection capsule and a parachute capsule; an ejection capsule air inlet is formed in the rear part of the ejection capsule; a high-pressure cylinder is mounted outside the parachute cylinder, a high-pressure air chamber is formed in the high-pressure cylinder, an inflation port and an air outlet are formed in the rear part of the high-pressure cylinder, and the air outlet is connected with the ejection capsule air inlet through the air guide pipe; the control valve is mounted in the middle of the air guide pipe; a capsule door is mounted at the right end of the parachute cylinder and is matched with and mounted on the parachute capsule through a hinge pin; an air pressure detection meter and an air one-way valve are arranged at the inflation port. The pneumatic parachute opening system has a high success rate and is safer and more reliable.
Description
[technical field]
The present invention relates to the technical field in aeronautical engineering, particularly a kind of unmanned plane parachute pneumatic parachute-opening system
The technical field of system.
[background technology]
After the unmanned plane end of job, owing to being limited by reasons such as places, typically can use and release a parachute
The mode implementing parachuting reclaims.A kind of comparatively safe, reliable and the most ripe method.The most universal
During the method used, parachute is folded according to certain method, be then placed in cabin, also to put in cabin
Entering extractor parachute, extractor parachute is connected with main chute, equipped with spring on hatch door, blocks hatch door by servomotor,
When needing parachute-opening, bayonet lock extracted by servomotor, and hatch door automatically opens up, and creates in a flash necessarily open
Vacuum, relatively light due to extractor parachute again, can blow out out of my cabin along with air-flow, at this time need to allow aircraft add again
Speed once, utilizes the resistance pull-out main chute of extractor parachute, last until main chute is fully deployed could close electromotor,
Enter parachuting process, the most not only can waste the energy, and structure is unreliable, there is bigger mortality,
And affected bigger by weather.
[summary of the invention]
The purpose of the present invention solves the problems of the prior art exactly, proposes that a kind of unmanned plane parachute is pneumatic opens
Umbrella system, it is possible to ensure that parachute is unlocked smoothly, add the reliability of system, it is not necessary to what volume was adds
Speed process, saves the energy, is not affected by the weather simultaneously, fills parachute and be more prone in parachute compartment.
For achieving the above object, the present invention proposes a kind of pneumatic deployment system of unmanned plane parachute, including fall
Fall umbrella cylinder, control valve and airway, and described parachute cylinder is internally installed top plug, and described top plug is by parachute
Cylinder is internal is divided into elastic force cabin and parachute compartment, and rear portion, elastic force cabin is provided with elastic force cabin air inlet, parachute cylinder
Outside high pressure cylinder is installed, described high pressure cylinder is internally provided with plenum chamber, and the rear portion of high pressure cylinder is provided with
Inflation inlet and gas outlet, described gas outlet is connected by airway with elastic force cabin air inlet, in described airway
Between control valve is installed, the right-hand member of parachute cylinder is provided with hatch door, and described hatch door and parachute compartment are by hinged
Pin coordinates to be installed, and described inflation inlet is provided with air pressure detection table and air check valve.
As preferably, described parachute cylinder being provided with electromagnetic valve and snap seats, described snap seats is internally installed
Buckle, described buckle is had to coordinate installation with hook.
As preferably, described electromagnetic valve being provided with pull bar, described pull bar coordinates installation with snap seats.
As preferably, described control valve both sides are respectively arranged with high pressure outlet air mouth and high pressure admission mouth, control valve
Inside is respectively arranged with admission line, outlet pipe, and control valve is internally installed cock plug, described cock plug
It is connected with motor by motor shaft, sealing ring is installed between cock plug and motor.
As preferably, described cock plug being provided with cock plug passage, cock plug turns under the drive of motor
Dynamic, admission line can be connected with outlet pipe by cock plug passage.
As preferably, described air check valve is internally provided with guide rod seat, described guide rod seat is provided with some
Cross air filter hole, guide rod seat is provided with boss.
As preferably, described guide rod seat being provided with guide rod, one end of described guide rod is installed with unidirectional
Gas lid, is provided with secondary spring between unidirectional inducing QI lid and guide rod seat.
As preferably, described air check valve is internally provided with sealing gasket, described sealing gasket and unidirectional inducing QI lid
Contact.
As preferably, in described elastic force cabin, power assistant spring is installed.
Beneficial effects of the present invention: the present invention, by increasing high pressure cylinder around parachute compartment, makes parachute
Startup can rely on the gases at high pressure substituted the bad for the good in advance to be ejected by parachute as power, pacifies in elastic force cabin simultaneously
Equipped with power assistant spring, the elastic force of spring is less, and its effect is that top plug is ejected by auxiliary, increases success rate,
It is provided with electromagnetic valve at parachute cover, makes hatch door fix relatively reliable, open rapider simultaneously.
Inventive feature and advantage will combine accompanying drawing by embodiment and be described in detail.
[accompanying drawing explanation]
Fig. 1 is the main pseudosection of the present invention a kind of unmanned plane pneumatic deployment system of parachute；
Fig. 2 is the main pseudosection of control valve；
Fig. 3 is the main pseudosection of air check valve.
In figure: 1-airway, 2-height pressure cylinder, 21-plenum chamber, 22-inflation inlet, 23-gas outlet, 24-
Air check valve, 241-guide rod seat, 242-cross air filter hole, 243-guide rod, 244-unidirectional inducing QI lid, 245-
Secondary spring, 246-sealing gasket, 25-air pressure detection table, 3-electromagnetic valve, 31-pull bar, 32-snap seats, 33-
Buckle, 4-parachute cylinder, 41-hatch door hook, 42-hatch door, 43-swivel pin, 44-parachute compartment, 45-help
Power spring, 46-top plug, 47-elastic force cabin air inlet, 48-elastic force cabin, 5-control valve, 51-high pressure outlet air mouth,
52-cock plug, 53-cock plug passage, 54-motor, 55-motor shaft, 56-sealing ring, 57-height are pressed into
QI KOU, 58-admission line, 59-outlet pipe.
[detailed description of the invention]
Refering to Fig. 1, Fig. 2 and Fig. 3, the one pneumatic deployment system of unmanned plane parachute of the present invention, including landing
Umbrella cylinder 4, control valve 5 and airway 1, described parachute cylinder 4 is internally installed top plug 46, described top plug
46 are divided into elastic force cabin 48 and parachute compartment 44 by internal for parachute cylinder 4, and rear portion, elastic force cabin 48 is provided with bullet
Power cabin air inlet 47, the outside of parachute cylinder 4 is provided with high pressure cylinder 2, and described high pressure cylinder 2 is internally provided with
Plenum chamber 21, the rear portion of high pressure cylinder 2 is provided with inflation inlet 22 and gas outlet 23, described gas outlet 23 with
Elastic force cabin air inlet 47 is connected by airway 1, is provided with control valve 5 in the middle of described airway 1, landing
The right-hand member of umbrella cylinder 4 is provided with hatch door 42, and described hatch door 42 coordinates peace with parachute compartment 44 by swivel pin 43
Dress, described inflation inlet 22 is provided with air pressure detection table 25 and air check valve 24.Described parachute cylinder 4
On electromagnetic valve 3 and snap seats 32 are installed, described snap seats 32 is internally installed buckle 33, described buckle
33 coordinate installation with hook.Pull bar 31, described pull bar 31 and snap seats 32 are installed on described electromagnetic valve 3
Coordinate and install.Described control valve 5 both sides are respectively arranged with high pressure outlet air mouth 51 and high pressure admission mouth 57, control
Valve 5 is internal is respectively arranged with admission line 58, outlet pipe 59, and control valve 5 is internally installed cock plug 52,
Described cock plug 52 is connected with motor 54 by motor shaft 55, is provided with between cock plug 52 and motor 54
Sealing ring 56.Described air check valve 24 is internally provided with guide rod seat 241, and described guide rod seat 241 is arranged
There are some air filter holes 242 excessively, guide rod seat 241 is provided with boss.It is provided with guide rod on described guide rod seat 241
243, one end of described guide rod 243 is installed with unidirectional inducing QI lid 244, unidirectional inducing QI lid 244 and guide rod
It is provided with secondary spring 245 between seat 241.Described air check valve 24 is internally provided with sealing gasket 246,
Described sealing gasket 246 contacts with unidirectional inducing QI lid 244.It is provided with cock plug passage on described cock plug 52
53, cock plug 52 rotates under the drive of motor 54, can be by admission line by cock plug passage 53
58 connect with outlet pipe 59.In described elastic force cabin 48, power assistant spring 45 is installed.
Work process of the present invention:
The one pneumatic deployment system of unmanned plane parachute of the present invention in the course of the work, when aircraft is to be landed
Wait, start electromagnetic valve 3 and control valve 5 simultaneously, owing to aircraft has higher speed, so hatch door 42 mouthfuls
Can form bigger negative pressure, hatch door 42 is opened by negative pressure, and parachute can be pulled outward by the active force of negative pressure simultaneously,
Under the common effect of power assistant spring 45 and gases at high pressure, parachute can be pushed out parachute compartment 44, and next time makes
Used time needs the gas by being filled with requirement to high pressure cylinder 2 by inflation inlet 22, and parachute is encased in landing
In umbrella.
The one pneumatic deployment system of unmanned plane parachute of the present invention, this equipment fills parachute more in parachute
Easy, need not the accelerator that volume is during aircraft landing, save the energy, simultaneously not by weather
Impact, good reliability, success rate is high.
Above-described embodiment is the description of the invention, is not limitation of the invention, any simple to the present invention
Scheme after conversion belongs to protection scope of the present invention.
Claims (9)
1. the pneumatic deployment system of unmanned plane parachute, it is characterised in that: include parachute cylinder (4), control valve
(5) and airway (1), described parachute cylinder (4) is internally installed top plug (46), described top plug (46)
It is divided into elastic force cabin (48) and parachute compartment (44), after elastic force cabin (48) by internal for parachute cylinder (4)
Portion is provided with elastic force cabin air inlet (47), and the outside of parachute cylinder (4) is provided with high pressure cylinder (2),
Described high pressure cylinder (2) is internally provided with plenum chamber (21), and the rear portion of high pressure cylinder (2) is provided with inflation
Mouth (22) and gas outlet (23), inducing QI is passed through in described gas outlet (23) and elastic force cabin air inlet (47)
Pipe (1) connects, and is provided with control valve (5), the right side of parachute cylinder (4) in the middle of described airway (1)
End is provided with hatch door (42), and described hatch door (42) is joined by swivel pin (43) with parachute compartment (44)
Close and install, described inflation inlet (22) is provided with air pressure detection table (25) and air check valve (24).
2. a kind of pneumatic deployment system of unmanned plane parachute as claimed in claim 1, it is characterised in that: described fall
Fall and electromagnetic valve (3) and snap seats (32) are installed on umbrella cylinder (4), the internal peace of described snap seats (32)
Equipped with buckle (33), described buckle (33) coordinates installation with hook.
3. a kind of pneumatic deployment system of unmanned plane parachute as claimed in claim 2, it is characterised in that: described electricity
Being provided with pull bar (31) on magnet valve (3), described pull bar (31) coordinates installation with snap seats (32).
4. a kind of pneumatic deployment system of unmanned plane parachute as claimed in claim 1, it is characterised in that: described control
Valve processed (5) both sides are respectively arranged with high pressure outlet air mouth (51) and high pressure admission mouth (57), control valve (5)
Inside is respectively arranged with admission line (58), outlet pipe (59), and control valve (5) is internally installed to be had out
Guan Sai (52), described cock plug (52) is connected with motor (54) by motor shaft (55), cock plug
And sealing ring (56) is installed between motor (54) (52).
5. a kind of pneumatic deployment system of unmanned plane parachute as claimed in claim 4, it is characterised in that open described in:
Cock plug passage (53), the cock plug (52) drive in motor (54) it is provided with on Guan Sai (52)
Lower rotation, can be by admission line (58) and outlet pipe (59) by cock plug passage (53)
Connection.
6. a kind of pneumatic deployment system of unmanned plane parachute as claimed in claim 1, it is characterised in that: described sky
Gas check valve (24) is internally provided with guide rod seat (241), described guide rod seat (241) is provided with some
Crossing air filter hole (242), guide rod seat is provided with boss on (241).
7. a kind of pneumatic deployment system of unmanned plane parachute as claimed in claim 1, it is characterised in that lead described in:
Being provided with guide rod (243) on pole socket (241), one end of described guide rod (243) is installed with unidirectional
Inducing QI lid (244), is provided with secondary spring (245) between unidirectional inducing QI lid (244) and guide rod seat (241).
8. a kind of pneumatic deployment system of unmanned plane parachute as claimed in claim 7, it is characterised in that: described sky
Gas check valve (24) is internally provided with sealing gasket (246), described sealing gasket (246) and unidirectional inducing QI lid
(244) contact.
9. a kind of pneumatic deployment system of unmanned plane parachute as according to any one of claim 1 to 8, its feature
It is: in described elastic force cabin (48), power assistant spring (45) is installed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610464631.8A CN106005435A (en) | 2016-06-22 | 2016-06-22 | Pneumatic parachute opening system for parachute of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610464631.8A CN106005435A (en) | 2016-06-22 | 2016-06-22 | Pneumatic parachute opening system for parachute of unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106005435A true CN106005435A (en) | 2016-10-12 |
Family
ID=57087332
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610464631.8A Pending CN106005435A (en) | 2016-06-22 | 2016-06-22 | Pneumatic parachute opening system for parachute of unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106005435A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109272600A (en) * | 2018-08-30 | 2019-01-25 | 芜湖翼讯飞行智能装备有限公司 | A kind of unmanned plane cloud black box subsystem and its auxiliary device based on big data |
| CN109774955A (en) * | 2019-03-06 | 2019-05-21 | 成都飞机工业（集团）有限责任公司 | Drag parachute housing structure is buried in one kind is two-door |
| CN112340031A (en) * | 2020-10-26 | 2021-02-09 | 北京洛必德科技有限公司 | All direction movement supervisory-controlled robot device |
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| CN201176266Y (en) * | 2008-01-18 | 2009-01-07 | 王剑刚 | Auto opening parachute in condition of weightlessness |
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2016
- 2016-06-22 CN CN201610464631.8A patent/CN106005435A/en active Pending
Patent Citations (7)
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109272600A (en) * | 2018-08-30 | 2019-01-25 | 芜湖翼讯飞行智能装备有限公司 | A kind of unmanned plane cloud black box subsystem and its auxiliary device based on big data |
| CN109774955A (en) * | 2019-03-06 | 2019-05-21 | 成都飞机工业（集团）有限责任公司 | Drag parachute housing structure is buried in one kind is two-door |
| CN109774955B (en) * | 2019-03-06 | 2022-01-25 | 成都飞机工业（集团）有限责任公司 | Double-door embedded resistance umbrella cabin structure |
| CN112340031A (en) * | 2020-10-26 | 2021-02-09 | 北京洛必德科技有限公司 | All direction movement supervisory-controlled robot device |
| CN112340031B (en) * | 2020-10-26 | 2022-06-14 | 北京洛必德科技有限公司 | All direction movement supervisory-controlled robot device |
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| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161012 |
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| RJ01 | Rejection of invention patent application after publication |