CN101214856A - Safety self-saving device for vertically taking off and landing flyer - Google Patents
Safety self-saving device for vertically taking off and landing flyer Download PDFInfo
- Publication number
- CN101214856A CN101214856A CNA2008100325559A CN200810032555A CN101214856A CN 101214856 A CN101214856 A CN 101214856A CN A2008100325559 A CNA2008100325559 A CN A2008100325559A CN 200810032555 A CN200810032555 A CN 200810032555A CN 101214856 A CN101214856 A CN 101214856A
- Authority
- CN
- China
- Prior art keywords
- umbrella
- storehouse
- unilateral bearing
- umbrella storehouse
- cang gai
- 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
Links
Images
Landscapes
- Walking Sticks, Umbrellas, And Fans (AREA)
Abstract
The present invention relates to the technical field of vertical aircraft equipment and concretely provides a safe self rescue device of a vertical rising and landing aircraft. The outer bottom middle part of a parachute chamber is provided with a groove. A disk at the top of a parachute chamber fixing base is embedded into the groove. The coaxial core sleeve of a cylinder type sleeve at the bottom of the parachute chamber fixing base is arranged at the upper part of the guide pipe. The outside of the guide pipe under the parachute chamber fixing base is mounted with a principal transmission shaft which is connected with a principal propeller clamp by middle linkage. A unilateral bearing lining is mounted under the principal transmission shaft and the underside of the unilateral bearing lining is fixed at the principal transmission shaft. A unilateral bearing is embedded at the unilateral bearing lining. The unilateral bearing lining supports the lower end of the unilateral bearing. A main gear lining is covered at the outside of the unilateral bearing. The outer middle part of the main gear lining is protrudent to form an upper part and a lower part, the upper part covers a main gear and the lower part covers a spinning landing group. Compared with the prior art, the present invention has simple structure and convenient installation, solves the problem of safe landing when an unmanned helicopter has the fault and reduces the loss rate when an airplane has the fault.
Description
[technical field]
The present invention relates to vertical flight device equipment technology field, a kind of specifically safety self-saving device for vertically taking off and landing flyer.
[background technology]
Pilotless helicopter mainly comprises fuel engines by power unit; Chargeable battery; Transfer unit comprises various gears and movable parts, body skeleton, rotor, empennage; Flight control system comprises gyroscope, servomechanism, global position system GPS, infrared gyroscope, laser rangefinder, pick up camera, sensor, control microcomputer; Radio frequency sending set, receiver, remote controller; Compositions such as auto-control software, the transmission of power that aircraft produces by driving engine produces lift to rotor flies aircraft aloft, by adjusting rotor and the rotating speed of empennage and the control that aircraft flight attitude is realized in the drift angle.
Unmanned vehicle is the not manned craft of controlling by radio robot or airborne computer stored program controlled, the unmanned vehicle use cost is low, not only can finish the task that manned aircraft is carried out, more be applicable to the task that people's aircraft should not be carried out, scouting as the hazardous location, air rescue commander and remote sensing monitoring, the technical advantage of pilotless helicopter is can spot takeoff, landing, conditional request to landing site is not high, its flight also is by radio telecommand or realizes program control by airborne computer, and the structure of pilotless helicopter more complicated comparatively speaking, it is also bigger to control difficulty, has embodied the integrated application on the modern high technology.
Air remote sensing equipment in light weight, that volume is little, performance is high, and the fast development of unmanned plane technology, it is integrated that unmanned plane and later-model remote sensing equipment are carried out, and becomes the emerging technological means in the air remote sensing.
At present, unmanned plane expands to civil use industry from initial military domain, and its application is constantly expansion, as flood control, sea and atmospheric surveillance, safe early warning, environmental protection and soil dynamic monitoring or the like.
Though depopulated helicopter is safer because of driverless operation, when practical application, in case unmanned aerial vehicle break down and can cause air crash and cause heavy losses, if air crash is have that the people assembles local even can cause casualties.
[summary of the invention]
The objective of the invention is in order to overcome the deficiencies in the prior art, by on existing vertically taking off and landing flyer, a safe falling device being installed, the loss rate during with minimizing personnel and aircraft et out of order.
For achieving the above object, design a kind of safety self-saving device for vertically taking off and landing flyer, it is characterized in that: establish groove in the middle of the outer bottom of umbrella storehouse (8), the disk of umbrella storehouse permanent seat (7) upper end embeds in the groove, the cylinder type sleeve pipe concentric of umbrella storehouse permanent seat (7) lower end is enclosed within guide pipe (2) upper end, cylinder type sleeve pipe at umbrella storehouse permanent seat (7) adopts screw (15) to captive joint with guide pipe (2), a sheathed main driving axle (1) outside the guide pipe (2) of umbrella storehouse permanent seat (7) below, connection (5) connected main oar folder (6) during adopted at position, the outside top of main driving axle (1), the sheathed unilateral bearing lining (10) of main driving axle (1) lower portion, unilateral bearing lining (10) below adopts screw (14) to be fixed on the main driving axle (1), unilateral bearing (11) is nested on the unilateral bearing lining (10), unilateral bearing liner (13) is supported on unilateral bearing (11) lower end, main gear lining (12) is enclosed within outside the unilateral bearing (11), be two parts about convexing to form in the middle of main gear lining (12) is outside, the first half overcoat main gear (4), the latter half overcoat spin landing group (9).The shell in described umbrella storehouse (8) is an arc, umbrella storehouse (8) cover top portion is that (26 umbrella Cang Gai (26) left ends adopt hinge (28) to be connected with umbrella storehouse (8) shell one abutted seam place to umbrella Cang Gai, the both wings of hinge (28) adopt screw (27) to be individually fixed in umbrella storehouse shell one end and umbrella Cang Gai (26) left end, umbrella Cang Gai (26) right-hand member is fixed a umbrella Cang Gai hook (24) that is the knuckle shape with screw (25), umbrella Cang Gai hook (24) band hook one end fits in umbrella storehouse shell surface, umbrella Cang Gai hook (24) other end is vertical configuration, in the groove that the seam of insertion umbrella Cang Gai (26) right-hand member and the umbrella storehouse shell other end is established, it is interior umbrella storehouse (21) that inside, umbrella storehouse (8) is provided with a chamber, the shape in interior umbrella storehouse (21), the shape of position and umbrella Cang Gai (26), the position correspondence, interior umbrella storehouse (21) left outer wall is with an interior umbrella of screw retention storehouse hook (20), the inboard right wall in interior umbrella storehouse (21) is installed umbrella storehouse lid steering wheel (22), two walls are respectively established two ropes that a self-locking link hole (30) tangles the parachute bottom respectively before and after in the interior umbrella storehouse (21), a steering wheel rocking arm of screw retention (23) is adopted at lid steering wheel (22) top, umbrella storehouse, steering wheel rocking arm (23) touches with the vertical end of umbrella Cang Gai hook (24) is crossing, the umbrella storehouse was linked up with on (20) in rubber band (29) one ends hung over, establish a hole on the umbrella storehouse shell of left side hinge (28) below, rubber band (28) other end passes this aperture and hangs on the umbrella Cang Gai hook (24).Between described main driving axle (1) and the guide pipe (2) gap from top to bottom rectangular distribution be provided with center bearing pilot bearing (3), the number of center bearing pilot bearing (3) is at least 2.Described parachute bottom is main chute (32), and main chute (32) top is provided with pilot-parachute (31).
The present invention compares with prior art, simple in structure, easy for installation, safe falling problem when having solved depopulated helicopter and breaking down, avoided the loss of air crash effectively and to ground staff's injury, the loss rate in the time of can reducing personnel and aircraft et out of order simultaneously.
[description of drawings]
Fig. 1 is a structural representation of the present invention.
Fig. 2 is appearance figure of the present invention.
Fig. 3 a is the birds-eye view in umbrella storehouse among the present invention.
Fig. 3 b is the A-A section-drawing in umbrella storehouse among the present invention.
Fig. 3 c is the B-B section-drawing in umbrella storehouse among the present invention.
Fig. 4 a is the scheme drawing behind the parachute ejection umbrella storehouse among the present invention.
Fig. 4 b is the scheme drawing after open in the umbrella storehouse among the present invention.
Referring to Fig. 1, Fig. 3, Fig. 4,1 is main driving axle; 2 is guide pipe; 3 is center bearing pilot bearing; 4 is main gear; 5 is middle; 6 is main oar folder; 7 is umbrella storehouse permanent seat; 8 is the umbrella storehouse; 9 are spin landing group; 10 is the unilateral bearing lining; 11 is unilateral bearing; 12 is the main gear lining; 13 is the unilateral bearing liner; 14 is screw; 15 is screw; 20 is interior umbrella storehouse hook; 21 is interior umbrella storehouse; 22 are umbrella storehouse lid steering wheel; 23 is the steering wheel rocking arm; 24 are umbrella Cang Gai hook; 25 is screw; 26 is umbrella Cang Gai; 27 is screw; 28 is hinge; 29 is rubber band; 30 are self-locking link hole; 31 is pilot-parachute; 32 is main chute.
Appointment Fig. 1 is a Figure of abstract.
[specific embodiment]
The invention will be further described below in conjunction with accompanying drawing, the present invention concerning those skilled in the art still clearly.
Referring to accompanying drawing 1, a kind of safety self-saving device that can on helicopter, install, specifically comprise: one, aircraft rotor main driving axle unit, comprise main driving axle 1, guide pipe 2, center bearing pilot bearing 3, wherein, main driving axle 1 is a hollow cylinder, includes guide pipe 2, the two is a concentric, and the gap between main driving axle 1 and the guide pipe 2 is provided with center bearing pilot bearing 3.
Two, the main gear unit, comprise main gear 4, spin landing group 9, unilateral bearing lining 10, unilateral bearing 11, main gear lining 12, be also referred to as main gear individual event gear, unilateral bearing liner 13 and screw, unilateral bearing lining 10 concentrics are enclosed within on the main driving axle 1, and it is fixing with screw 14, unilateral bearing 11 is nested on the unilateral bearing lining 10, be supported on unilateral bearing 11 lower ends with unilateral bearing liner 13, then main gear lining 12 is enclosed within on the unilateral bearing 11, the main gear lining is a projection in the middle of 12 outsides, form two parts up and down, the first half overcoat main gear 4, the latter half is overcoat spin landing group 9 then, the radical function of spin landing group 9 is when helicopter aloft flies, driving engine breaks down and runs out of steam or when flame-out suddenly, utilize helicopter own wt and acceleration due to gravity principle, with change lifting airscrew pitch, promptly strengthen negative pitch, helicopter is when descending fast, main rotor can be rotated automatically, and remain on the flight attitude that certain speed is controlled helicopter, it can farthest be reduced the loss.
Three, main oar folder unit comprises main oar folder 6 and middle 5, and main oar folder 6 and middle 5 is nested in the outer tops of main driving axle 1, and main oar folder 6 is used to connect the main rotor of aircraft.
Four, umbrella warehouse receipt unit, comprise umbrella storehouse 8 and umbrella storehouse permanent seat 7, wherein, establish groove in the middle of 8 outer bottoms of umbrella storehouse, the disk position of permanent seat 7 upper ends, umbrella storehouse embeds in this groove, the cylinder type sleeve pipe concentric of permanent seat 7 lower ends, umbrella storehouse is enclosed within the top of guide pipe 2, makes umbrella storehouse 8 be fixed in guide pipe 2 tops, adopts screw 15 that umbrella storehouse permanent seat 7 is captiveed joint with guide pipe 2.
The main shaft of guide pipe in the safety self-saving device for vertically taking off and landing flyer 2 with the vertically taking off and landing flyer top linked to each other, when aircraft is worked, the driving engine of aircraft reaches main gear 4 with kinetic energy, main gear 4 is rotated, main gear 4 then drives main driving axle 1 and rotates, at this moment, and along with the raising of engine speed, make bonded assembly aircraft main rotor high speed revolution and change pitch obtain lift by main oar folder 6, make aircraft takeoff and flight.
Umbrella storehouse 8 is positioned at guide pipe 2 tops, when the aircraft normal flight, can not influence the normal flight of aircraft, when emergency appears in aircraft, at first the power transmission with driving engine breaks away from by spin landing group 9 and main driving axle 1, aircraft rotor is because of running out of steam like this, with the former rotatory inertia speed that slows down gradually, when aircraft runs out of steam when down falling, the parachute that is positioned at umbrella storehouse, guide pipe 2 top 8 ejects automatically and opens by difference beat control system, and aircraft is slowly landed, and has both guaranteed the safety of aircraft, guarantee the safety of ground staff and property again, made loss reduce to minimum.Wherein difference beat control system is used for the ejection of parachute and opens, and can be installed near the helicopter center of gravity, and most cases is at the close main shaft place of fuselage side plate.
Referring to accompanying drawing 3a-c, after being sent to the umbrella storehouse lid steering wheel 22 that is positioned at umbrella storehouse 8 when signal, by difference beat control system, make steering wheel rocking arm 23 horizontally rotate the 90-120 degree left, the hook 6 of umbrella Cang Gai is thrown off with it, under the tension of umbrella Cang Gai because of rubber band 29 umbrella Cang Gai is opened, have hinge 9 to link to each other between umbrella Cang Gai and the umbrella storehouse, can rotate along the hinge axle umbrella Cang Gai is opened.
Referring to accompanying drawing 4a-b, the introductory note pilot chute 31 that thereupon is positioned at umbrella storehouse 8 is at first dished out from umbrella storehouse 3 under the application force of air and is opened, pilot-parachute drives the main parachute 32 that is positioned at umbrella storehouse 21 again and also ejects umbrella storehouse 8 and open, aircraft has slowed down the speed that descends under the effect of main parachute 32 lift like this, thereby reached the purpose of safe falling, guarantee the safety of aircraft, reduced loss.
Claims (4)
1. safety self-saving device for vertically taking off and landing flyer, it is characterized in that: establish groove in the middle of the outer bottom of umbrella storehouse (8), the disk of umbrella storehouse permanent seat (7) upper end embeds in the groove, the cylinder type sleeve pipe concentric of umbrella storehouse permanent seat (7) lower end is enclosed within guide pipe (2) upper end, cylinder type sleeve pipe at umbrella storehouse permanent seat (7) adopts screw (15) to captive joint with guide pipe (2), a sheathed main driving axle (1) outside the guide pipe (2) of umbrella storehouse permanent seat (7) below, connection (5) connected main oar folder (6) during adopted at position, the outside top of main driving axle (1), the sheathed unilateral bearing lining (10) of main driving axle (1) lower portion, unilateral bearing lining (10) below adopts screw (14) to be fixed on the main driving axle (1), unilateral bearing (11) is nested on the unilateral bearing lining (10), unilateral bearing liner (13) is supported on unilateral bearing (11) lower end, main gear lining (12) is enclosed within outside the unilateral bearing (11), be two parts about convexing to form in the middle of main gear lining (12) is outside, the first half overcoat main gear (4), the latter half overcoat spin landing group (9).
2. a kind of safety self-saving device for vertically taking off and landing flyer as claimed in claim 1, it is characterized in that: the shell in described umbrella storehouse (8) is an arc, umbrella storehouse (8) cover top portion is umbrella Cang Gai (26), umbrella Cang Gai (26) left end adopts hinge (28) to be connected with umbrella storehouse (8) shell one abutted seam place, the both wings of hinge (28) adopt screw (27) to be individually fixed in umbrella storehouse shell one end and umbrella Cang Gai (26) left end, umbrella Cang Gai (26) right-hand member is fixed a umbrella Cang Gai hook (24) that is the knuckle shape with screw (25), umbrella Cang Gai hook (24) band hook one end fits in umbrella storehouse shell surface, umbrella Cang Gai hook (24) other end is vertical configuration, in the groove that the seam of insertion umbrella Cang Gai (26) right-hand member and the umbrella storehouse shell other end is established, it is interior umbrella storehouse (21) that inside, umbrella storehouse (8) is provided with a chamber, the shape in interior umbrella storehouse (21), the shape of position and umbrella Cang Gai (26), the position correspondence, interior umbrella storehouse (21) left outer wall is with an interior umbrella of screw retention storehouse hook (20), the inboard right wall in interior umbrella storehouse (21) is installed umbrella storehouse lid steering wheel (22), two walls are respectively established two ropes that a self-locking link hole (30) tangles the parachute bottom respectively before and after in the interior umbrella storehouse (21), a steering wheel rocking arm of screw retention (23) is adopted at lid steering wheel (22) top, umbrella storehouse, steering wheel rocking arm (23) touches with the vertical end of umbrella Cang Gai hook (24) is crossing, the umbrella storehouse was linked up with on (20) in rubber band (29) one ends hung over, establish a hole on the umbrella storehouse shell of left side hinge (28) below, rubber band (28) other end passes this aperture and hangs on the umbrella Cang Gai hook (24).
3. a kind of safety self-saving device for vertically taking off and landing flyer as claimed in claim 1, it is characterized in that: between described main driving axle (1) and the guide pipe (2) gap from top to bottom rectangular distribution be provided with center bearing pilot bearing (3), the number of center bearing pilot bearing (3) is at least 2.
4. a kind of safety self-saving device for vertically taking off and landing flyer as claimed in claim 2 is characterized in that: described parachute bottom is main chute (32), and main chute (32) top is provided with pilot-parachute (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008100325559A CN101214856A (en) | 2008-01-11 | 2008-01-11 | Safety self-saving device for vertically taking off and landing flyer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008100325559A CN101214856A (en) | 2008-01-11 | 2008-01-11 | Safety self-saving device for vertically taking off and landing flyer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101214856A true CN101214856A (en) | 2008-07-09 |
Family
ID=39621384
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2008100325559A Pending CN101214856A (en) | 2008-01-11 | 2008-01-11 | Safety self-saving device for vertically taking off and landing flyer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101214856A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103111024A (en) * | 2013-01-27 | 2013-05-22 | 李建青 | Multi-purpose high-rise fire fighting lifesaver |
| CN103129738A (en) * | 2011-12-02 | 2013-06-05 | 武汉孙言明太阳能科技有限公司 | Automatic propeller landing flight life saving device |
| CN104118565A (en) * | 2014-08-04 | 2014-10-29 | 陈世文 | Airplane parachute |
| CN104627371A (en) * | 2013-11-13 | 2015-05-20 | 银川上河图新技术研发有限公司 | Safe landing device used when helicopter breaks down and shuts down at high altitude |
| CN105217043A (en) * | 2015-11-11 | 2016-01-06 | 陆克勇 | A kind of multifunctional helicopter |
| CN109279006A (en) * | 2018-11-16 | 2019-01-29 | 苏州神龙航空科技有限公司 | A kind of gyroplane of variable power |
-
2008
- 2008-01-11 CN CNA2008100325559A patent/CN101214856A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103129738A (en) * | 2011-12-02 | 2013-06-05 | 武汉孙言明太阳能科技有限公司 | Automatic propeller landing flight life saving device |
| CN103111024A (en) * | 2013-01-27 | 2013-05-22 | 李建青 | Multi-purpose high-rise fire fighting lifesaver |
| CN103111024B (en) * | 2013-01-27 | 2015-03-25 | 李建青 | Multi-purpose high-rise fire fighting lifesaver |
| CN104627371A (en) * | 2013-11-13 | 2015-05-20 | 银川上河图新技术研发有限公司 | Safe landing device used when helicopter breaks down and shuts down at high altitude |
| CN104118565A (en) * | 2014-08-04 | 2014-10-29 | 陈世文 | Airplane parachute |
| CN105217043A (en) * | 2015-11-11 | 2016-01-06 | 陆克勇 | A kind of multifunctional helicopter |
| CN109279006A (en) * | 2018-11-16 | 2019-01-29 | 苏州神龙航空科技有限公司 | A kind of gyroplane of variable power |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11912404B2 (en) | Vertical takeoff and landing aircraft | |
| US5289994A (en) | Equipment carrying remote controlled aircraft | |
| CN202071985U (en) | Novel plane symmetrical layout type multi-rotor unmanned air vehicle | |
| US20200148387A1 (en) | Recovery System for UAV | |
| CN105966612B (en) | Become posture VTOL unmanned plane | |
| US20050109874A1 (en) | Vertical lift flying craft | |
| CN103552686B (en) | A kind of compound type duct aerial reconnaissance machine people | |
| CN106005400A (en) | Vertical-takeoff auxiliary system for fixed-wing aircraft | |
| CN201362362Y (en) | Composite power multipurpose unmanned aerial vehicle | |
| US6142414A (en) | Rotor--aerostat composite aircraft | |
| CN102874408A (en) | Double ducted-propeller electric manned aircraft capable of taking off and landing vertically | |
| CN101214856A (en) | Safety self-saving device for vertically taking off and landing flyer | |
| CN201710952U (en) | Suspension cable type low-altitude flight system | |
| CN105818971A (en) | Unmanned gyroplane | |
| RU127039U1 (en) | AEROBIKE | |
| JP4279194B2 (en) | Aircraft and method of switching modes | |
| CN101973395A (en) | Electric anti-collision safety unmanned helicopter | |
| CN108583868B (en) | Ground effect type ducted fan aircraft | |
| CN101525049B (en) | High-speed rotator type helicopter | |
| CN115258146B (en) | Fixed-wing aircraft with electric rotor wing capable of vertically taking off and landing and flying forwards under power drive of fuel oil | |
| CA2315524A1 (en) | Personal hoverplane having four tiltmotors | |
| CN205524948U (en) | Unmanned autogyro | |
| CN208393628U (en) | Imitate formula ducted fan aircraft in ground | |
| RU2403182C1 (en) | Unmanned aerial system | |
| CN201670359U (en) | Single-thrust-propeller disc-shaped unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Open date: 20080709 |