CN202054141U - Extending parallel buffer-rocker arm type undercarriage - Google Patents
Extending parallel buffer-rocker arm type undercarriage Download PDFInfo
- Publication number
- CN202054141U CN202054141U CN2011201181523U CN201120118152U CN202054141U CN 202054141 U CN202054141 U CN 202054141U CN 2011201181523 U CN2011201181523 U CN 2011201181523U CN 201120118152 U CN201120118152 U CN 201120118152U CN 202054141 U CN202054141 U CN 202054141U
- Authority
- CN
- China
- Prior art keywords
- rocker arm
- wheel
- energy disperser
- airplane
- buffer
- 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
- 238000009434 installation Methods 0.000 claims description 3
- 230000003139 buffering effect Effects 0.000 abstract description 3
- 239000000872 buffer Substances 0.000 abstract 6
- 238000012856 packing Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- YGANSGVIUGARFR-UHFFFAOYSA-N dipotassium dioxosilane oxo(oxoalumanyloxy)alumane oxygen(2-) Chemical compound [O--].[K+].[K+].O=[Si]=O.O=[Al]O[Al]=O YGANSGVIUGARFR-UHFFFAOYSA-N 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 229910052627 muscovite Inorganic materials 0.000 description 1
Images
Landscapes
- Tires In General (AREA)
Abstract
The utility model discloses an extending parallel buffer-rocker arm type undercarriage, comprising an upper load-bearing supporting rod, a lower load-bearing supporting rod, a strut buffer, a rocker arm and an airplane wheel assembly which are sequentially connected. The upper load-bearing supporting rod, the lower load-bearing supporting rod, the strut buffer and the rocker arm are connected in a hinged manner, simultaneously, the strut buffer is respectively connected with extending ends of an upper retractable rod and a lower retractable rod, a rocker arm type buffer is connected between the strut buffer and an arm body of the rocker arm, the airplane wheel assembly comprises an airplane wheel axle and a pair of airplane wheels mounted at two ends of the airplane wheel axel in parallel, and the airplane wheel axle is connected with the rocker arm. Accordingly, the double airplane wheels and the two buffers which form a certain included angle are respectively mounted on the rocker arm of the extending rocker arm type undercarriage, so that the undercarriage not only meets requirements of airworthiness to the sideward heeling angle of an airplane, but also reduces requirements of the airplane wheels to floatability of a runway, and further, the buffering landing property of a main undercarriage can be improved.
Description
Technical field
The utility model relates to a kind of overhanging articulated landing gear, belongs to airplane spare parts, is applied to adopt the large-scale amphibious aircraft of airscrew engine.
Background technology
Amphibious aircraft has the characteristics that are better than vehicle and boats and ships on landing on the land and the water surface, speed.So in today of 21 century, along with the World Airways industrial expansion, countries in the world just progressively start the development climax of hydroairplane, amphibious aircraft and ground (sea) face effect aircraft of a new round.So, carry out the research of amphibious aircraft Landing Gear System aspect at present, the meaning of " work is in the contemporary generation, profit is in the future thousands of years " is arranged for the development that promotes China's modernization national defense construction and General Aviation cause.
Develop one of important references type of large-scale amphibious aircraft as China, what Muscovite not-200 aircrafts adopted is two jet engines, and China does not also grasp this technology at present, still adopts airscrew engine.
Amphibious aircraft alighting gear general design, key issue is the design of main landing gear, its essence is whether the determined aircraft rollover of the folding and unfolding form angle of main landing gear satisfies the problem of airworthiness requirement.
Canada CL-215 aircraft maximum take-off weight is 19890 kilograms, and the maximum take-off weight of U.S. PBY-5A aircraft is 16066 kilograms, is the tricycle landing gear layout, and the wheel number on each root main unit of landing gear is one; 45000 kilograms of maximum take-off weights of this and SH-5 are far apart.
The utility model content
The utility model is at the deficiencies in the prior art, a kind of overhanging and column buffer-articulated landing gear is provided, it is according to the fuselage characteristics of amphibious aircraft, two energy dispersers of two-wheel arranged side by side being installed respectively on the rocking arm of overhanging articulated landing gear and being formed an angle, make alighting gear described in the utility model both satisfy the requirement of air worthiness regulation to aircraft rollover angle, the requirement of wheel can be reduced again, the buffering landing data of main landing gear can also be improved the runway floatability.
For realizing above technical purpose, the utility model will be taked following technical scheme:
A kind of overhanging and column buffer-articulated landing gear, comprise the last load strut bar that is linked in sequence, following load strut bar, pillar energy disperser, rocking arm and wheel assembly, and the annexation that goes up between load strut bar, following load strut bar, pillar energy disperser and the rocking arm is hinged; The pillar energy disperser is connected with the overhanging end of last folding and unfolding bar and following folding and unfolding bar respectively simultaneously; Be connected the rocker-arm energy disperser between the arm body of described pillar energy disperser and rocking arm; The a pair of wheel that the wheel assembly comprises the wheel wheel shaft and is installed in wheel wheel shaft two ends side by side; The wheel wheel shaft is connected with rocking arm.
Angle between described pillar energy disperser and the rocker-arm energy disperser is 30 °.
Described down load strut bar and last folding and unfolding bar coaxially location and installation on the pillar energy disperser.
According to above technical scheme, can realize following beneficial effect:
(a), main landing gear of the present utility model at first adopts rocker-arm, and is and then articulated landing gear is overhanging, satisfied the requirement of civilian air worthiness regulation to aircraft rollover angle; After making that alighting gear is packed up fully, wheel does not interfere with the following folding and unfolding bar of jack yet;
(b), main landing gear wheel of the present utility model adopts dicycly arranged side by side, compares with the PBY-5A aircraft with the CL-215 aircraft, reduced the requirement to runway road face floatability.
(c), arranged side by side, angled two energy dispersers are installed on rocking arm, the energy disperser of more existing articulated landing gear, buffering efficient is higher, has better landing data.
(d), since the utility model mainly be the large-scale amphibious aircraft that is applied to adopt airscrew engine, it belongs to dopey.After main landing gear is packed up, place the fuselage both sides to be higher than the position of waterline, both realized the free folding and unfolding of main landing gear, do not take the fuselage interior space again, also can not produce significantly influence flying speed.
Description of drawings
Fig. 1 is the structural representation of overhanging and column buffer-articulated landing gear described in the utility model;
Fig. 2 is the structure diagram of the described overhanging and column buffer-articulated landing gear of Fig. 1 when putting down fully;
Fig. 3 is the structure diagram of the described overhanging and column buffer-articulated landing gear of Fig. 1 when packing up fully;
Wherein: go up load strut bar 1; Following load strut bar 2; Rocker-arm energy disperser 3; Pillar energy disperser 4; Wheel 5; Rocking arm 6; Following folding and unfolding bar 7; Folding and unfolding pressurized strut 8; Last folding and unfolding bar 9.
The specific embodiment
Accompanying drawing discloses the structural representation of the related preferred embodiment of the utility model without limitation, explains the technical solution of the utility model below with reference to accompanying drawing.
Research according to the application's utility model people, when designing large-scale amphibious aircraft, can consider alighting gear, require to redesign, thereby finish the design effort of Chinese large-sized amphibious aircraft according to the alighting gear of amphibious aircraft with " water Hong-5(SH-5) " hydroairplane.Then, on this basis,, update upgrading, crack the international market according to domestic and international client's demand.
Now consider to adopt alighting gear distribution form, the SH-5 aircraft is improved upgrading, make it to become real amphibious aircraft as CL-215 aircraft and PBY-5A aircraft.
As shown in Figures 1 to 3, overhanging and column buffer-articulated landing gear described in the utility model, comprise the last load strut bar 1 that is linked in sequence, following load strut bar 2, pillar energy disperser 4, rocking arm 6 and wheel 5 assemblies, and the annexation that goes up between load strut bar 1, following load strut bar 2, pillar energy disperser 4 and the rocking arm 6 is hinged; Pillar energy disperser 4 is connected with the overhanging end of last folding and unfolding bar 9 and following folding and unfolding bar 7 respectively simultaneously; Be connected rocking arm 6 formula energy dispersers 3 between the arm body of described pillar energy disperser 4 and rocking arm 6; Wheel 5 assemblies comprise wheel 5 wheel shafts and a pair of wheel 5 that is installed in wheel 5 wheel shaft two ends side by side; Wheel 5 wheel shafts are connected with rocking arm 6.Angle between described pillar energy disperser 4 and the rocking arm 6 formula energy dispersers 3 is 30 °.Described down load strut bar 2 and last folding and unfolding bar 9 coaxially location and installation on pillar energy disperser 4.
Hence one can see that: as shown in Figure 1 that main landing gear (going up folding and unfolding bar 9, following folding and unfolding bar 7, rocking arm 6 and pillar energy disperser 4 etc.) is overhanging, and make aircraft when ground taxi, satisfy the requirement of air worthiness regulation to aircraft rollover angle; In conjunction with Fig. 1 and Fig. 2, can know clearly the folding and unfolding principle of this overhanging formula alighting gear simultaneously, promptly be a plane four link work mechanisms.
Main landing gear described in the utility model adopts rocking arm 6 formulas, makes wheel 5 in the process of packing up and after packing up fully, does not all interfere with following folding and unfolding bar 7.
As shown in Figure 3, wheel 5 makes two-wheel into by single-wheel, can reduce the requirement of aircraft to runway road face floatability; Rocking arm 6 energy dispersers and pillar energy disperser 4 are installed on the rocking arm 6 with forming an angle, and this angle should make wheel 5 in the process of packing up and after packing up fully, and be all under the precondition that does not interfere with following folding and unfolding bar 7, as far as possible littler; The moment of flexure that rocking arm 6 energy dispersers are subjected at work is as far as possible littler.
Claims (3)
1. overhanging and column buffer-articulated landing gear, comprise the last load strut bar that is linked in sequence, following load strut bar, pillar energy disperser, rocking arm and wheel assembly, and the annexation that goes up between load strut bar, following load strut bar, pillar energy disperser and the rocking arm is hinged; The pillar energy disperser is connected with the overhanging end of last folding and unfolding bar and following folding and unfolding bar respectively simultaneously; It is characterized in that: be connected the rocker-arm energy disperser between the arm body of described pillar energy disperser and rocking arm; The a pair of wheel that the wheel assembly comprises the wheel wheel shaft and is installed in wheel wheel shaft two ends side by side; The wheel wheel shaft is connected with rocking arm.
2. according to the described overhanging and column buffer-articulated landing gear of claim 1, it is characterized in that: the angle between described pillar energy disperser and the rocker-arm energy disperser is 30 °.
3. according to the described overhanging and column buffer-articulated landing gear of claim 1, it is characterized in that: described down load strut bar and last folding and unfolding bar coaxially location and installation on the pillar energy disperser.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201181523U CN202054141U (en) | 2011-04-21 | 2011-04-21 | Extending parallel buffer-rocker arm type undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201181523U CN202054141U (en) | 2011-04-21 | 2011-04-21 | Extending parallel buffer-rocker arm type undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202054141U true CN202054141U (en) | 2011-11-30 |
Family
ID=45014123
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011201181523U Expired - Fee Related CN202054141U (en) | 2011-04-21 | 2011-04-21 | Extending parallel buffer-rocker arm type undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202054141U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103523210A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Friction shimmy damping device of nose landing gear |
| CN105197228A (en) * | 2015-10-30 | 2015-12-30 | 深圳市大疆创新科技有限公司 | Undercarriage and unmanned aerial vehicle |
| CN105752879A (en) * | 2016-04-12 | 2016-07-13 | 浙江中力机械有限公司 | Two-stage lifting mechanism |
| CN110126300A (en) * | 2019-05-05 | 2019-08-16 | 宜兴市新立织造有限公司 | A kind of composite material undercarriage and preparation method thereof using 3 D weaving |
| JP2021084622A (en) * | 2019-11-29 | 2021-06-03 | キム, モン リョンKIM, Mong Ryong | Landing device for motorcycle including vertical alignment auxiliary wheel |
-
2011
- 2011-04-21 CN CN2011201181523U patent/CN202054141U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103523210A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Friction shimmy damping device of nose landing gear |
| CN105197228A (en) * | 2015-10-30 | 2015-12-30 | 深圳市大疆创新科技有限公司 | Undercarriage and unmanned aerial vehicle |
| CN105752879A (en) * | 2016-04-12 | 2016-07-13 | 浙江中力机械有限公司 | Two-stage lifting mechanism |
| CN105752879B (en) * | 2016-04-12 | 2018-07-03 | 浙江中力机械有限公司 | two-stage lifting mechanism |
| CN110126300A (en) * | 2019-05-05 | 2019-08-16 | 宜兴市新立织造有限公司 | A kind of composite material undercarriage and preparation method thereof using 3 D weaving |
| JP2021084622A (en) * | 2019-11-29 | 2021-06-03 | キム, モン リョンKIM, Mong Ryong | Landing device for motorcycle including vertical alignment auxiliary wheel |
| JP7037212B2 (en) | 2019-11-29 | 2022-03-16 | リョン キム，モン | Landing device for motorcycles with vertical alignment auxiliary wheels |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN202054141U (en) | Extending parallel buffer-rocker arm type undercarriage | |
| CN102020014B (en) | Airplane landing gear with deflected airplane wheel retraction jack | |
| WO2010076776A9 (en) | Method for comprehensively increasing aerodynamic and transport characteristics, a wing-in-ground-effect craft for carrying out said method (variants) and a method for realizing flight | |
| CN207809790U (en) | A kind of unmanned logistics transportation machine of binary | |
| CN101693468A (en) | Amphibious large aircraft without air-stairs | |
| CN202783777U (en) | Unmanned aerial vehicle undercarriage | |
| CN108216621A (en) | A kind of wing tip connection composite lights aircraft in parallel | |
| WO2012134701A3 (en) | Method of reducing fuel carried by an aircraft in flight | |
| CN102963521B (en) | Central wing of horizontal tail of civil airplane | |
| CN105270620A (en) | Integrated general-purpose vertical take-off and landing aircraft based on lifting and floating force | |
| CN107697269B (en) | Propeller airplane | |
| CN201525255U (en) | Gyroplane landing ship capable of driving on land and water | |
| CN104943850A (en) | Main wing retractable type fixed wing airplane | |
| CN205554569U (en) | Aerospace's undercarriage is exclusively used in | |
| CN204895853U (en) | Compound aircraft that stationary vane and deformable electronic many rotors are constituteed | |
| CN209209028U (en) | One kind is verted three rotor VTOL all-wing aircraft of type | |
| CN103231804A (en) | Wing framework of imitation pterosaur flapping-wing aircraft | |
| CN108058830A (en) | A kind of unmanned logistics transportation machine of binary | |
| CN205524948U (en) | Unmanned autogyro | |
| CN210284611U (en) | Flying wing layout solar unmanned aerial vehicle | |
| CN203255355U (en) | Wing skeleton of pterosaur simulated ornithopter | |
| CN204822053U (en) | Nearly spacecraft with dirigible and solar powered aircraft | |
| CN219257735U (en) | Tandem wing vertical take-off and landing aircraft | |
| CN203528806U (en) | Fixed wing type unmanned aerial vehicle | |
| CN205554570U (en) | Space shuttle intelligence shock attenuation wheel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20111130 Termination date: 20130421 |