CN2474470Y - Airplane forced landing device - Google Patents
Airplane forced landing device Download PDFInfo
- Publication number
- CN2474470Y CN2474470Y CN 01209947 CN01209947U CN2474470Y CN 2474470 Y CN2474470 Y CN 2474470Y CN 01209947 CN01209947 CN 01209947 CN 01209947 U CN01209947 U CN 01209947U CN 2474470 Y CN2474470 Y CN 2474470Y
- Authority
- CN
- China
- Prior art keywords
- chassis
- actuating cylinder
- hydraulic actuating
- hydraulic cylinder
- hydraulic
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Tires In General (AREA)
Abstract
The utility model relates to an aircraft forced landing device, which comprises soft landing units which are longitudinally and transversely connected, each soft landing unit comprises a chassis, a hydraulic cylinder square matrix and a rubber wheel, wherein the hydraulic cylinder square matrix is arranged on the chassis, and the rubber wheel is arranged on the top of each hydraulic cylinder piston rod. Each column of the piston rods are connected with one connecting bar through a pin bearing, wheel shafts of each line of the rubber wheels are connected into one body, a torsion spring or a diagonal brace hydraulic cylinder is arranged on the lower end of a support bar of each hydraulic cylinder, connection journal stirrups are arranged on the four side surfaces of the chassis, and a road wheel is arranged on the lower of the chassis. The utility model has the advantages of simple structure, low cost, safety and reliability, and is capable of reducing the flight accidents.
Description
The utility model relates to a kind of forced landing device.Be applicable to that working as undercarriage can't put down, the forced landing under the abominable situations such as (as hurricane, storms) of vigour.
At present, the method that solves forced landing in the world is the interim plastic foam that sprays on airstrip, rely on the friction between fuselage and the foam to realize forced landing by force, but the safety reliability of this kind method is not high enough, line of travel during forced landing is difficult for grasping, cause accidents such as fuselage fracture, wing fracture easily.
The purpose of this utility model provides and a kind ofly can reduce aircraft accident, forced landing device that can safe landing when needs force-land.
The purpose of this utility model is achieved in that a kind of forced landing device, it by mutually in length and breadth bonded assembly soft landing unit form, each soft landing unit is by the chassis, be installed in the hydraulic actuating cylinder square formation on the chassis, the rubber wheel that is installed in each hydraulic cylinder piston rod top is formed, each hydraulic actuating cylinder is by same HYDRAULIC CONTROL SYSTEM, every row piston rod of hydraulic actuating cylinder square formation links together by bearing pin and same connecting rod, the wheel shaft of the rubber wheel on the every capable piston rod top of hydraulic actuating cylinder square formation is connected as a single entity, in the strut bar lower end of each hydraulic actuating cylinder torsion spring or diagonal brace hydraulic actuating cylinder are housed, on four sides on chassis, be provided with the connection journal stirrup, road wheel is housed below the chassis.
The columns of the hydraulic pressure square formation of each soft landing unit is more than 3 row, and its line number is more than 5 row.
Principle of work of the present utility model is as follows:
Utilize the elastic deformation of rubber wheel, and the motion of hydraulic actuating cylinder, aircraft landing to the forced landing device on after, form a kind of completely inelastic collision, impact when reducing aircraft landing, reduce the kinetic energy of aircraft, and forced landing device proper such as same flexible, soft runway, when forced landing, the gear up of aircraft, airframe slides on the device in forced landing, and rubber wheel rolls, make fly slip become relative rolling movement.Allow aircraft " soft landing ", loaded onto " wheel " again in other words aircraft.
The utility model is connected to form a larger area soft landing runway in length and breadth by the soft landing unit, can produce bigger bearing force, and the pressure that produces during aircraft landing, make the hydraulic actuating cylinder drive rubber wheel of part in compression move downward, the hydraulic actuating cylinder of the right and left because of pressurized not then relative position than part in compression height, just look like to have formed a recessed channel like this, not only increased friction fuselage, and the line of travel of easier assurance aircraft.
Torsion spring or diagonal brace hydraulic actuating cylinder are equipped with in each hydraulic actuating cylinder strut bar lower end simultaneously, after being subjected to aircraft impulse force forward, can bear bigger impact.
Below in conjunction with drawings and Examples the utility model is further described:
Fig. 1 is the structural representation of soft landing of the present utility model unit.
Fig. 2 is the birds-eye view of Fig. 1.
Fig. 3 is the left view of Fig. 1.
By the embodiment shown in Fig. 1-3 as can be known, the utility model by mutually in length and breadth bonded assembly soft landing unit form, each soft landing unit is by chassis 6, be installed in the hydraulic actuating cylinder square formation on the chassis, the rubber wheel 1 that is installed in each hydraulic cylinder piston rod top is formed, each hydraulic actuating cylinder is by same HYDRAULIC CONTROL SYSTEM, every row piston rod of hydraulic actuating cylinder square formation links together by bearing pin and same connecting rod 2, the wheel shaft of the rubber wheel 1 on the every capable piston rod top of hydraulic actuating cylinder square formation is connected as a single entity, torsion spring 9 or diagonal brace hydraulic actuating cylinder are equipped with in strut bar 5 lower ends at each hydraulic actuating cylinder, on four sides on chassis 6, be provided with connection journal stirrup 7, road wheel 8 is housed below chassis 6.
The columns of the hydraulic pressure square formation of the soft landing unit of present embodiment is 3 row, and its line number is 5 row.
In Fig. 1,3 is by pass valve.
The accuracy of the aircraft landing point that can control from the oad of aircraft and performance perameter and aviator is analyzed the reliability that this forced landing device is realized safe landing below:
With the Boeing is example: oad and the performance perameter of Boeing 777-200A are as follows: length of aircraft: 63.73 meters, aircraft altitude: 18.44 meters, 6.20 meters of fuselage widths, 60.93 meters of the spanes, 229520 kilograms of maximum take-off weights, 2072 meters of landing heads (being about), velocity of approach (being about 270 kilometers/hour).
The accuracy of the aircraft landing point that common aviator can control is: the front and back error is about 3 meters, and left and right sides error is about 2 meters.
Therefore, to realize that for the aircraft of needs forced landings safe landing adopts this device then can realize fully.
The utility model has the advantages that simple in structurely, cost is lower, and is safe and reliable, adopts this device can reduce the generation of aircraft accident.
Claims (2)
1, a kind of forced landing device, it is characterized in that it by mutually in length and breadth bonded assembly soft landing unit form, each soft landing unit is by chassis (6), be installed in the hydraulic actuating cylinder square formation on the chassis, the rubber wheel (1) that is installed in each hydraulic cylinder piston rod top is formed, each hydraulic actuating cylinder is by same HYDRAULIC CONTROL SYSTEM, every row piston rod of hydraulic actuating cylinder square formation links together by bearing pin and same connecting rod (2), the wheel shaft of the rubber wheel (1) on the every capable piston rod top of hydraulic actuating cylinder square formation is connected as a single entity, torsion spring (9) or diagonal brace hydraulic actuating cylinder are equipped with in strut bar (5) lower end at each hydraulic actuating cylinder, be provided with connection journal stirrup (7) on four sides of chassis (6), road wheel (8) is equipped with in (6) below on the chassis.
2, forced landing device according to claim 1, the columns that it is characterized in that the hydraulic pressure square formation of each soft landing unit are more than 3 row, and its line number is more than 5 row.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01209947 CN2474470Y (en) | 2001-03-02 | 2001-03-02 | Airplane forced landing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01209947 CN2474470Y (en) | 2001-03-02 | 2001-03-02 | Airplane forced landing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2474470Y true CN2474470Y (en) | 2002-01-30 |
Family
ID=33629599
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 01209947 Expired - Fee Related CN2474470Y (en) | 2001-03-02 | 2001-03-02 | Airplane forced landing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2474470Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2007124673A1 (en) * | 2006-04-19 | 2007-11-08 | Yuen Liu | A secure system for aircraft emergency landing |
| CN108750133A (en) * | 2018-06-19 | 2018-11-06 | 内蒙古丹枫园林绿化工程服务有限公司 | A kind of automatic auxiliary landing system of aircraft |
-
2001
- 2001-03-02 CN CN 01209947 patent/CN2474470Y/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2007124673A1 (en) * | 2006-04-19 | 2007-11-08 | Yuen Liu | A secure system for aircraft emergency landing |
| CN108750133A (en) * | 2018-06-19 | 2018-11-06 | 内蒙古丹枫园林绿化工程服务有限公司 | A kind of automatic auxiliary landing system of aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101304919B (en) | Aircraft and method for enabling braked pivoted turning on ground | |
| EP2748063B1 (en) | Aircraft landing gear | |
| CN106628125A (en) | Quick-disassembling energy absorption undercarriage for multi-rotor unmanned aerial vehicle | |
| EP2282938A2 (en) | Ground-bound device for take off, landing and taxiing of aircrafts | |
| Young | Aircraft landing gears—the past, present and future | |
| WO2006094145A9 (en) | Landing gear with articulated length extension mechanism | |
| CN111470036A (en) | Anti single leg buffer structure and leg formula undercarriage that hit that weigh down | |
| US9033275B2 (en) | Aircraft undercarriage | |
| WO2007001714A1 (en) | Process for landing a tailless aircraft | |
| CN201086822Y (en) | Rear kneeing type damping device for undercarriage of pilotless plane | |
| CN2474470Y (en) | Airplane forced landing device | |
| CN2140880Y (en) | Seat specially adapted for civil passenger plane | |
| CN112069712B (en) | Method for rapidly analyzing landing load of support arm type undercarriage | |
| CN109183662A (en) | A kind of banister convenient for adjusting height | |
| Nuti et al. | Design of a fuselage-mounted main landing gear of a medium-size civil transport aircraft | |
| CN105292512A (en) | Airplane lander and landing system thereof | |
| CN107512388A (en) | A kind of the aircraft takeoffs and landings control system and method for the separation of Flight main body and undercarriage | |
| US20130146706A1 (en) | Method and a rotary wing aircraft optimized for minimizing the consequences of a running off-specification emergency landing | |
| CN109835472A (en) | A kind of small drone column support type spring nose-gear | |
| Jenkins | Landing gear design and development | |
| CN2581330Y (en) | Land spare device for aircraft landing gear | |
| CN102530257A (en) | Forced landing device for civil aircrafts | |
| EP0174876B1 (en) | Shock absorbing strut for aircraft undercarriage | |
| CN202541844U (en) | Emergency landing device used for civil airplane | |
| CN213705819U (en) | Ground receiving and delivering machine vehicle capable of replacing aircraft landing gear |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |