CN111661340A - Small-sized airplane fault landing device - Google Patents
Small-sized airplane fault landing device Download PDFInfo
- Publication number
- CN111661340A CN111661340A CN202010466059.5A CN202010466059A CN111661340A CN 111661340 A CN111661340 A CN 111661340A CN 202010466059 A CN202010466059 A CN 202010466059A CN 111661340 A CN111661340 A CN 111661340A
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- CN
- China
- Prior art keywords
- shaped clamping
- parachute
- landing gear
- traction
- small aircraft
- 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
- 238000007789 sealing Methods 0.000 claims description 21
- 238000004804 winding Methods 0.000 claims description 9
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 8
- 239000004917 carbon fiber Substances 0.000 claims description 8
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 8
- 230000006835 compression Effects 0.000 claims description 7
- 238000007906 compression Methods 0.000 claims description 7
- 230000008054 signal transmission Effects 0.000 claims description 7
- 239000004593 Epoxy Substances 0.000 claims description 6
- 230000008602 contraction Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 description 3
- 230000002349 favourable effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 238000006748 scratching Methods 0.000 description 1
- 230000002393 scratching effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/40—Packs
- B64D17/52—Opening, e.g. manual
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/62—Deployment
- B64D17/70—Deployment by springs
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Emergency Lowering Means (AREA)
Abstract
The invention discloses a small airplane fault landing device, which comprises a containing groove arranged on a machine body, wherein a parachute and an ejecting device are arranged in the containing groove, a pair of fixing points of parachute traction belts are arranged on the left side and the right side of the front part and the rear part of the machine body, a cover plate is arranged on the containing groove, and a locking device is arranged on the cover plate; the invention can reduce the damage of the airplane as much as possible and can effectively improve the safety coefficient of property and life.
Description
Technical Field
The invention relates to a small airplane fault landing device, and belongs to the field of airplane landing tools.
Background
Along with the development of the aerospace industry, the use of following small aircraft can be more and more extensive, including unmanned aerial vehicle application, private aircraft application, when small aircraft's use, because the relation of volume, various safety guarantee devices on it are inevitable not as complete as big passenger aircraft class, consequently, factor of safety is lower, in case the condition such as the organism malfunction takes place, not only the aircraft itself has the risk of crashing, personnel on it also have life risk.
Therefore, a small airplane fault landing device is needed, which can reduce the damage of the airplane as much as possible and effectively improve the safety coefficient of property and life.
Disclosure of Invention
The invention aims to solve the technical problem of providing a small airplane fault landing device which can reduce the damage of the airplane as much as possible and effectively improve the safety coefficient of property and life; the defects of the prior art can be overcome.
The technical scheme of the invention is as follows: a fault landing device for small airplane is composed of a storage slot on the main body, a parachute and a spring unit in said storage slot, a pair of fixing points for the parachute drawing belt, a cover plate on said storage slot, and a locking unit on said cover plate.
The pop-up device comprises a guide groove arranged on the inner wall of the accommodating groove, a lifting plate arranged on the guide groove, a spring I in a compression state is arranged between the lifting plate and the bottom of the accommodating groove, and the parachute is arranged on the lifting plate.
Foretell accomodate the groove and be located aircraft fuselage rear portion upside, two fixed points lie in the control room and the tail between be connected the baffle behind the parachute traction area, and two preceding fixed points lie in the baffle of control room front end, are equipped with the reservation groove at the outer wall of control room both sides, the parachute traction area of being connected with two preceding fixed points lies in the reservation groove, is equipped with carbon fiber layer and epoxy layer at the reservation notch.
The cover plate consists of left and right closed sealing doors, one side of each sealing door is hinged to the inner wall of the accommodating groove, and the locking device is arranged between the sealing doors.
The locking device comprises L-shaped plates arranged on the lower surfaces of the two sealing doors, bayonets are formed between the L-shaped plates and the sealing doors, accommodating holes are formed in the side walls of the accommodating grooves, U-shaped clamping pieces matched with the bayonets are arranged in the accommodating holes, openings of the U-shaped clamping pieces are downward, the two L-shaped plates in the locking state are located in the openings of the U-shaped clamping pieces, springs II in the compression state are arranged between the inner ends of the U-shaped clamping pieces and the inner walls of the accommodating holes, and traction devices for controlling the contraction of the U-shaped clamping pieces are arranged on the U-shaped clamping pieces.
The traction device comprises a traction rope connected with the inner end of the U-shaped clamping piece, the other end of the traction rope is connected with a winding wheel, a rotating shaft of the winding wheel is connected with a motor shaft, an independent power supply of a motor is arranged in a control chamber, and the motor is connected with a control device for controlling the motor to rotate forwards and backwards.
The control device comprises a manual button connected with a motor.
The control device comprises a signal transmission device, and the signal transmission device is connected with a control center on the ground.
A chamfer is arranged between the free end surface and the lower end surface of the U-shaped clamping piece.
Compared with the prior art, the small airplane fault landing device comprises a containing groove arranged on a machine body, a parachute and an ejecting device are arranged in the containing groove, a pair of fixing points of parachute traction belts are arranged on the left side and the right side of the front portion and the rear portion of the machine body, a cover plate is arranged on the containing groove, and a locking device is arranged on the cover plate.
Pop out the device and include the guide slot that is equipped with at the groove inner wall of accomodating, the lifter plate that is equipped with on the guide slot is equipped with spring I under the compression state between lifter plate and storage tank bottom, the parachute arrange such structure on the lifter plate in, through spring I under the compression state, when having the air crash risk, can pop out the parachute.
Accomodate the groove and be located aircraft fuselage rear portion upside, two fixed points lie in the baffle of being connected between control room and the tail behind the parachute traction area, two preceding fixed points lie in the baffle of control room front end, are equipped with the preformed groove at control room both sides outer wall, the parachute traction area of being connected with two preceding fixed points lies in the preformed groove, is equipped with carbon fiber layer and epoxy layer at the preformed groove mouth, can be favorable to hiding the parachute traction area through preformed groove and carbon fiber layer and epoxy layer like this, is favorable to improving the security performance.
The cover plate consists of sealing doors which are closed left and right, one side of each sealing door is hinged on the inner wall of the accommodating groove, and the locking device is arranged between the sealing doors; the locking device comprises L-shaped plates arranged on the lower surfaces of the two sealing doors, bayonets are formed between the L-shaped plates and the sealing doors, accommodating holes are formed in the side walls of the accommodating grooves, U-shaped clamping pieces matched with the bayonets are arranged in the accommodating holes, openings of the U-shaped clamping pieces are downward, the two L-shaped plates in a locking state are located in the openings of the U-shaped clamping pieces, springs II in a compression state are arranged between the inner ends of the U-shaped clamping pieces and the inner walls of the accommodating holes, and traction devices for controlling the U-shaped clamping pieces to shrink are arranged on the U-shaped clamping pieces.
The traction device comprises a traction rope connected with the inner end of the U-shaped clamping piece, the other end of the traction rope is connected with a winding wheel, a rotating shaft of the winding wheel is connected with a motor shaft, an independent power supply of a motor is arranged in a control chamber, the motor is connected with a control device for controlling the motor to rotate forwards and backwards, and the independent power supply can be used for preventing the parachute from being popped up under the condition that a circuit fault occurs to a machine body; the control device comprises a manual button connected with the motor, so that the parachute can be conveniently popped out under the manual control of personnel in the machine room; the control device comprises a signal transmission device, the signal transmission device is connected with a control center on the ground, and the structure is suitable for a small unmanned transporter and improves the safety factor in the transportation process; a chamfer is arranged between the free end surface and the lower end surface of the U-shaped clamping piece, so that the U-shaped clamping piece can be favorably prevented from scratching or clamping a main parachute in the process of popping the parachute.
Drawings
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail with reference to the accompanying drawings, in which:
fig. 1 is a schematic view of the connection structure of the present invention.
Fig. 2 is a schematic perspective view of the present invention.
Fig. 3 is a schematic structural view of the parachute of the present invention in an opened state.
Fig. 4 is a schematic structural view of the cross section of the machine body of the invention.
Fig. 5 is a partially enlarged schematic view of a portion a in fig. 4.
Fig. 6 is a schematic view showing a structure in which the receiving groove of the present invention is installed on a connection partition between the control room and the rear.
Fig. 7 is a schematic view of the connection structure in the uncovered state according to the present invention.
Fig. 8 is a half sectional view of fig. 6.
Fig. 9 is a schematic view of the connection structure at another angle of fig. 8.
Wherein, the fuselage 1; a storage tank 2; a parachute 3; an ejection device 4; a guide groove 401; a lifter plate 402; a spring I403; a cover plate 5; sealing a door 501; a locking device 6; an "L" shaped plate 601; a receiving hole 602; a U-shaped fastener 603; a spring II 604; parachute towing bridles 7; a preformed groove 8; a carbon fiber layer 9; a pull rope 10; a winding wheel 11; an electric motor 12.
Detailed Description
Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be understood that the preferred embodiments are illustrative of the invention only and are not limiting upon the scope of the invention.
Embodiment 1. as shown in fig. 1, a small airplane crash landing apparatus for protecting an airplane in an airplane failure state, characterized in that: the parachute collecting device comprises a containing groove 2 arranged on a machine body 1, a parachute 3 and an ejecting device 4 are arranged in the containing groove 2, a pair of fixing points of a parachute traction belt 7 are arranged on the left side and the right side of the front portion and the rear portion of the machine body 1, a cover plate 5 is arranged on the containing groove 2, the cover plate 5 is composed of left and right closed sealing doors 501, one side of each sealing door 501 is hinged to the inner wall of the containing groove 2, and a locking device 6 is arranged between the sealing doors 501; the cover plate 5 is provided with a locking device 6.
The ejecting device 4 comprises a guide groove 401 arranged on the inner wall of the accommodating groove 2, a lifting plate 402 arranged on the guide groove 401, a spring I403 in a compressed state arranged between the lifting plate 402 and the bottom of the accommodating groove 2, and the parachute 3 is arranged on the lifting plate 402.
Accomodate groove 2 be located 1 rear portion upside of aircraft fuselage, two fixed points lie in the baffle of being connected between control room and the tail behind 7 back parachute traction area, two preceding fixed points lie in the baffle of control room front end, are equipped with reserve tank 8 at control room both sides outer wall, parachute traction area 7 with two preceding fixed point connections is located reserve tank 8, is equipped with carbon fiber layer 9 and epoxy layer at reserve tank 8 mouth, carbon fiber layer 9 and epoxy layer's gross thickness is 0.2-0.8 cm.
The locking device 6 comprises L-shaped plates 601 arranged on the lower surfaces of the two sealing doors 501, a bayonet is formed between the L-shaped plates 601 and the sealing doors 501, a containing hole 602 is arranged on the side wall of the containing groove 2, a U-shaped clamping piece 603 matched with the bayonet is arranged in the containing hole 602, and a chamfer is arranged between the free end surface and the lower end surface of the U-shaped clamping piece 603; the U-shaped clamping piece 603 is provided with a downward opening, two L-shaped plates 601 are positioned in the opening of the U-shaped clamping piece 603 in a locking state, a spring II 604 in a compressed state is arranged between the inner end of the U-shaped clamping piece 603 and the inner wall of the accommodating hole 602, and a traction device for controlling the U-shaped clamping piece 603 to contract is arranged on the U-shaped clamping piece 603; the traction device comprises a traction rope 10 connected with the inner end of the U-shaped clamping piece 603, the other end of the traction rope 10 is connected with a winding wheel 11, a rotating shaft of the winding wheel 11 is connected with a motor shaft, an independent power supply of a motor 12 is arranged in a control chamber, and the motor 12 is connected with a control device for controlling the forward rotation and the reverse rotation of the motor; the control means comprise a manual button connected to the motor 12 or a signal transmission means connected to a control centre on the ground.
When the parachute opening device is used, if an airplane breaks down and a risk of crash exists, the motor 12 is controlled by the control device to retract the traction rope 10, the U-shaped clamping piece 603 is separated from the bayonet on the L-shaped plate 601, the parachute 3 is upwards popped out and opened under the action of the popping device 4, the parachute 3 pulls the parachute traction belt 7 connected with the front two fixed points in the opening process, and the carbon fiber layer 9 and the epoxy resin layer on the outer side of the parachute traction belt 7 are torn under the stress condition, so that the parachute 3 is completely opened, and the airplane is pulled to slowly fall; the falling speed of the airplane is reduced, so that the airplane crash damage is reduced.
Finally, the above embodiments are only intended to illustrate the technical solutions of the present invention and not to limit the present invention, and although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions, and all of them should be covered by the claims of the present invention.
Claims (9)
1. The utility model provides a small aircraft trouble landing gear, it is used for aircraft failure state to protect the aircraft which characterized in that: the parachute storage device comprises a storage groove (2) formed in a machine body (1), parachutes (3) and ejection devices (4) are arranged in the storage groove (2), fixing points of a pair of parachute traction belts (7) are arranged on the left side and the right side of the front portion and the rear portion of the machine body (1), a cover plate (5) is arranged on the storage groove (2), and a locking device (6) is arranged on the cover plate (5).
2. A small aircraft landing gear, according to claim 1, wherein: pop-up device (4) including guide slot (401) that are equipped with at holding groove (2) inner wall, lifter plate (402) that are equipped with on guide slot (401), be equipped with spring I (403) under compression state between lifter plate (402) and holding groove (2) bottom, parachute (3) arrange in on lifter plate (402).
3. A small aircraft landing gear, according to claim 2, wherein: accomodate groove (2) be located aircraft fuselage (1) rear portion upside, two fixed points are located the baffle of being connected between control room and the tail behind parachute traction area (7), two preceding fixed points are located the baffle of control room front end, are equipped with reserve tank (8) at control room both sides outer wall, parachute traction area (7) of being connected with two preceding fixed points are located reserve tank (8), are equipped with carbon fiber layer (9) and epoxy layer at reserve tank (8) mouth.
4. A small aircraft landing gear, according to claim 3, wherein: the cover plate (5) is composed of left and right closed sealing doors (501), one side of each sealing door (501) is hinged to the inner wall of the accommodating groove (2), and the locking device (6) is arranged between the sealing doors (501).
5. A small aircraft landing gear, according to claim 4, wherein: the locking device (6) comprises L-shaped plates (601) arranged on the lower surfaces of two sealing doors (501), bayonets are formed between the L-shaped plates (601) and the sealing doors (501), accommodating holes (602) are formed in the side walls of the accommodating grooves (2), U-shaped clamping pieces (603) matched with the bayonets are arranged in the accommodating holes (602), the openings of the U-shaped clamping pieces (603) are downward, the two L-shaped plates (601) are located in the openings of the U-shaped clamping pieces (603) in a locking state, springs II (604) in a compression state are arranged between the inner ends of the U-shaped clamping pieces (603) and the inner walls of the accommodating holes (602), and a traction device for controlling the contraction of the U-shaped clamping pieces (603) is arranged on the U-shaped clamping pieces.
6. A small aircraft landing gear, according to claim 5, wherein: the traction device comprises a traction rope (10) connected with the inner end of the U-shaped clamping piece (603), the other end of the traction rope (10) is connected with a winding wheel (11), a rotating shaft of the winding wheel (11) is connected with a motor shaft, an independent power supply of a motor (12) is arranged in a control chamber, and the motor (12) is connected with a control device for controlling the forward rotation and the reverse rotation of the motor.
7. A small aircraft landing gear, according to claim 6, wherein: the control device comprises a manual button connected with the motor (12).
8. A small aircraft landing gear, according to claim 6, wherein: the control device comprises a signal transmission device, and the signal transmission device is connected with a control center on the ground.
9. A small aircraft landing gear according to any one of claims 1 to 8, wherein: a chamfer is arranged between the free end surface and the lower end surface of the U-shaped clamping piece (603).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010466059.5A CN111661340A (en) | 2020-05-28 | 2020-05-28 | Small-sized airplane fault landing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010466059.5A CN111661340A (en) | 2020-05-28 | 2020-05-28 | Small-sized airplane fault landing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111661340A true CN111661340A (en) | 2020-09-15 |
Family
ID=72384882
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010466059.5A Pending CN111661340A (en) | 2020-05-28 | 2020-05-28 | Small-sized airplane fault landing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111661340A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113104200A (en) * | 2021-05-11 | 2021-07-13 | 南京信息职业技术学院 | Anti-falling unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203946278U (en) * | 2014-06-11 | 2014-11-19 | 江苏数字鹰科技发展有限公司 | The parachuting umbrella cabin of unmanned plane |
| CN205168922U (en) * | 2015-11-11 | 2016-04-20 | 杭州深空实业股份有限公司 | Unmanned helicopter safety parachuting system |
| US20170225792A1 (en) * | 2014-08-13 | 2017-08-10 | Dronetech Studio, Llc | Parachute deployment system for an unmanned aerial vehicle |
| CN109850164A (en) * | 2019-03-27 | 2019-06-07 | 河南机电职业学院 | A kind of parachute landing recovery device for unmanned aerial vehicle and its recovery method |
| CN212473924U (en) * | 2020-05-28 | 2021-02-05 | 贵州通用航空有限责任公司 | Small-sized airplane fault landing device |
-
2020
- 2020-05-28 CN CN202010466059.5A patent/CN111661340A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203946278U (en) * | 2014-06-11 | 2014-11-19 | 江苏数字鹰科技发展有限公司 | The parachuting umbrella cabin of unmanned plane |
| US20170225792A1 (en) * | 2014-08-13 | 2017-08-10 | Dronetech Studio, Llc | Parachute deployment system for an unmanned aerial vehicle |
| CN205168922U (en) * | 2015-11-11 | 2016-04-20 | 杭州深空实业股份有限公司 | Unmanned helicopter safety parachuting system |
| CN109850164A (en) * | 2019-03-27 | 2019-06-07 | 河南机电职业学院 | A kind of parachute landing recovery device for unmanned aerial vehicle and its recovery method |
| CN212473924U (en) * | 2020-05-28 | 2021-02-05 | 贵州通用航空有限责任公司 | Small-sized airplane fault landing device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113104200A (en) * | 2021-05-11 | 2021-07-13 | 南京信息职业技术学院 | Anti-falling unmanned aerial vehicle |
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