CN107985562A - A kind of lightweight compact formula undercarriage - Google Patents
A kind of lightweight compact formula undercarriage Download PDFInfo
- Publication number
- CN107985562A CN107985562A CN201711288312.7A CN201711288312A CN107985562A CN 107985562 A CN107985562 A CN 107985562A CN 201711288312 A CN201711288312 A CN 201711288312A CN 107985562 A CN107985562 A CN 107985562A
- Authority
- CN
- China
- Prior art keywords
- brace
- hinged
- locking rod
- undercarriage
- main carrier
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/26—Control or locking systems therefor
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
A kind of lightweight compact formula undercarriage, it includes drive system, vibration insulating system, brace and locking rod；Vibration insulating system contains main carrier bar, sprung shock-strut and aero tyre；The top of main carrier bar is hinged with fuselage, and in working status, main carrier bar is perpendicular to horizontal plane；Brace includes upper brace and lower brace, and upper brace one end is hinged with fuselage, and the other end is hinged with lower brace one end and locking rod one end respectively；The lower brace other end is hinged with main carrier bar；The locking rod other end is hinged with drive system；Brace and lower brace are in dead-centre position in working status, that is, are located along the same line, and the straight line is exactly perpendicular to locking rod.During recycling state, locking rod is almost conllinear with upper brace, effectively reduces undercarriage the space occupied；The present invention carries out locking only with a driver and a locking rod, not only reduces the weight of undercarriage, and mechanism is simple, and rational and compact, improves landing gear reliability.
Description
Technical field
The present invention relates to a kind of undercarriage, belongs to airplane design technical field.
Background technology
Landing gear is the important safety feature for having load and maneuverability concurrently of aircraft, in aircraft safety landing
Extremely important mission is responsible in journey.Undercarriage is always that domestic and international researcher endeavours one of improved key member, its
The quality of performance is directly related to the security performance of aircraft.Meanwhile modern aircraft is higher and higher to the Capability Requirement of long cruise,
Oil consumption to aircraft is more and more sensitive, this just proposes aircraft light-weight design urgent demand.
The content of the invention
The object of the present invention is to provide a kind of lightweight compact formula undercarriage, before undercarriage strength and stiffness are ensured
Put, optimize landing gear structure, make every effort to simple and reliable, and be preferably minimized its construction weight.
Technical solution of the present invention is as follows：A kind of lightweight compact formula undercarriage, including drive system and vibration insulating system, subtract
Vibrating system includes main carrier bar, torque arm, sprung shock-strut and aero tyre, it is characterised in that：The undercarriage further includes brace
And locking rod；The other end of the main carrier bar is hinged by the first hold-down support with fuselage, the main carrier bar in working status
Perpendicular to horizontal plane；The brace includes upper brace and lower brace；Branch is fixed in described upper brace one end by second
Seat is hinged with fuselage, and the other end is hinged with lower brace one end and locking rod one end at the same time；The lower brace other end and main carrying
Bar is hinged；The locking rod other end is hinged with drive system, in working status on brace and lower brace be in dead-centre position,
It is located along the same line, and the straight line is exactly perpendicular to locking rod.
In above-mentioned technical proposal, the drive system uses linear motor or fluid pressure drive device.
The present invention has the following advantages and the technique effect of high-lighting：1. in the operating condition, locking rod of the invention hangs down
Directly in the position that upper brace and lower brace, the restraining force that locking rod provides at this time may occur with upper brace, lower brace
Conllinear, arrangement energy secure ratcs just is moved, brace and lower brace are on same straight line in guarantee；In recycling shape
Under state, locking rod is almost conllinear with upper brace, at this time upper brace, lower brace, locking rod, main carrier bar and vibration insulating system
Structure is extremely compact, reduces undercarriage the space occupied；2. the locking rod of the present invention belongs to zero-g bar in the operating condition,
Do not stress under theoretical case, can effectively protect driver；3. the present invention is locked only with a driver and a locking rod
Only, mechanism is simple and reliable, improves landing gear reliability, and reduces the weight of undercarriage.
Brief description of the drawings
Fig. 1 is axonometric drawing of the present invention in takeoff and landing under undercarriage working status (when putting down completely).
Fig. 2 is structure diagram of the present invention in takeoff and landing under undercarriage working status (when putting down completely).
Fig. 3 is front view of the present invention under undercarriage recycling state after taking off (when packing up completely).
In figure：1- aero tyres；2- sprung shock-struts；3- torque arms；4- primary load bearing bars；Brace under 5-；The upper braces of 6-；
7- locking rods；8- linear actuators；The first hold-down supports of 9-；The second hold-down supports of 10-.
Embodiment
In order to illustrate more clearly of technical scheme, below in conjunction with concrete structure of the attached drawing to the present invention, original
Reason and embodiment, which are done, to be further described in detail.
Referring to Fig. 1, Fig. 2, a kind of lightweight compact formula undercarriage provided by the invention, it includes drive system, vibration damping
System, brace and locking rod 7；The vibration insulating system includes main carrier bar 4, torque arm 3, sprung shock-strut 2 and aero tyre 1.
The sprung shock-strut 2 is arranged in the lower part of main carrier bar 4, and aero tyre 1 is installed on 2 lower part of sprung shock-strut, and torque arm 3 passes through hinge
Chain link sprung shock-strut 2 and aero tyre 1.The other end of the main carrier bar 4 is hinged by the first hold-down support 9 with fuselage,
In working status, main carrier bar is perpendicular to horizontal plane.The driving of 6 available hydraulic of drive system or linear motor driving.
Brace of the present invention includes upper brace 6 and lower brace 5；Described 6 one end of upper brace is solid by second
Determine bearing 10 to be hinged with fuselage, the other end is hinged with lower 5 one end of brace and 7 one end of locking rod at the same time；Lower 5 other end of brace
It is hinged with main carrier bar 4；7 other end of locking rod is hinged with drive system 8；In working status, upper brace 6 and lower brace
5 are in dead-centre position, it is ensured that are located along the same line, and the straight line is exactly perpendicular to locking rod 7.The arrangement causes locking
The constraint force direction that bar 7 provides is just consistent with the direction that upper brace 6 and lower brace 5 may be subjected to displacement, and can effectively protect
Demonstrate,prove secure ratcs.
In the state of recycling (referring to Fig. 3), upper brace 6, locking rod 7, main carrier bar 4 and the vibration insulating system are in several
The position overlapped, effectively reduces the space occupied, i.e., the arrangement of mechanism is extremely compact.
In terms of the reliability of undercarriage provided by the invention in the operating condition is based on following four：1) brace on
6 and lower brace 5 be in dead-centre position；2) locking rod 7 is perpendicular to upper brace 6 and lower brace 5；3) locking rod 7 is in theory
For zero-g bar, drive system can be effectively protected；4) using as far as possible few driver, driver malfunction probability is reduced.Meanwhile this skill
Art mechanisms simple and compact, reduces space shared when weight and the recycling of undercarriage.
In conclusion technical scheme can effectively improve the landing security of undercarriage, it is ensured that undercarriage
Functional reliability, and the undercarriage possesses the advantage of compact lightweight, is with a wide range of applications and huge city
Field value.
Claims (2)
1. a kind of lightweight compact formula undercarriage, including drive system and vibration insulating system, vibration insulating system includes main carrier bar
(4), torque arm (3), sprung shock-strut (2) and aero tyre (1), it is characterised in that the undercarriage further includes brace (6) and lock
Only bar (7)；The top of the main carrier bar (4) is hinged by the first hold-down support (9) with fuselage, the main carrying in working status
Bar (4) is perpendicular to horizontal plane；
The brace includes upper brace (6) and lower brace (5)；Branch is fixed in described upper brace (6) one end by second
Seat (10) is hinged with fuselage, and the other end is hinged with lower brace (5) one end and locking rod (7) one end respectively；Lower brace (5) is another
One end is hinged with main carrier bar (4)；Locking rod (7) other end is hinged with drive system, in working status on brace (6) and
Lower brace (5) is in dead-centre position, that is, is located along the same line, and the straight line is exactly perpendicular to locking rod (7).
A kind of 2. lightweight compact formula undercarriage as claimed in claim 1, it is characterised in that：The drive system is using straight
Line motor or fluid pressure drive device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711288312.7A CN107985562A (en) | 2017-12-07 | 2017-12-07 | A kind of lightweight compact formula undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711288312.7A CN107985562A (en) | 2017-12-07 | 2017-12-07 | A kind of lightweight compact formula undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107985562A true CN107985562A (en) | 2018-05-04 |
Family
ID=62036461
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711288312.7A Pending CN107985562A (en) | 2017-12-07 | 2017-12-07 | A kind of lightweight compact formula undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107985562A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844124A (en) * | 2019-11-11 | 2020-02-28 | 中国运载火箭技术研究院 | Reusable carrier landing gear control system and control method |
| CN114671011B (en) * | 2022-03-18 | 2023-10-03 | 成都飞机工业（集团）有限责任公司 | Symmetrical multi-connecting-rod electric drive aircraft landing gear structure |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB397964A (en) * | 1932-04-27 | 1933-09-07 | Airspeed Ltd | Improvements in or relating to aeroplanes |
| US2116395A (en) * | 1936-04-25 | 1938-05-03 | United Aircraft Corp | Retractile landing gear |
| JP2012528759A (en) * | 2009-06-05 | 2012-11-15 | メシエ−ブガッティ−ドウティ | Method for operating a landing gear with folding struts |
| CN102803068A (en) * | 2010-03-31 | 2012-11-28 | 梅西耶-布加蒂-道提公司 | Method of protecting an aircraft landing gear while the aircraft is being towed, and pin for coupling a towing bar to an orientable lower part of a landing gear |
| CN103895858A (en) * | 2014-03-24 | 2014-07-02 | 清华大学 | Novel undercarriage with high strength and high reliability |
| CN105056543A (en) * | 2015-08-03 | 2015-11-18 | 金剑 | Five-link nose landing gear |
| CN106516087A (en) * | 2016-10-21 | 2017-03-22 | 清华大学 | Novel high-strength high-compactness lightweight aircraft landing gear |
| CN106660630A (en) * | 2014-04-17 | 2017-05-10 | 赛峰电子与防务公司 | Landing gear for an aircraft, comprising an obstacle detector |
| CN206691357U (en) * | 2017-04-06 | 2017-12-01 | 天津飞悦航空零部件制造有限公司 | Durable type undercarriage |
-
2017
- 2017-12-07 CN CN201711288312.7A patent/CN107985562A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB397964A (en) * | 1932-04-27 | 1933-09-07 | Airspeed Ltd | Improvements in or relating to aeroplanes |
| US2116395A (en) * | 1936-04-25 | 1938-05-03 | United Aircraft Corp | Retractile landing gear |
| JP2012528759A (en) * | 2009-06-05 | 2012-11-15 | メシエ−ブガッティ−ドウティ | Method for operating a landing gear with folding struts |
| CN102803068A (en) * | 2010-03-31 | 2012-11-28 | 梅西耶-布加蒂-道提公司 | Method of protecting an aircraft landing gear while the aircraft is being towed, and pin for coupling a towing bar to an orientable lower part of a landing gear |
| CN103895858A (en) * | 2014-03-24 | 2014-07-02 | 清华大学 | Novel undercarriage with high strength and high reliability |
| CN106660630A (en) * | 2014-04-17 | 2017-05-10 | 赛峰电子与防务公司 | Landing gear for an aircraft, comprising an obstacle detector |
| CN105056543A (en) * | 2015-08-03 | 2015-11-18 | 金剑 | Five-link nose landing gear |
| CN106516087A (en) * | 2016-10-21 | 2017-03-22 | 清华大学 | Novel high-strength high-compactness lightweight aircraft landing gear |
| CN206691357U (en) * | 2017-04-06 | 2017-12-01 | 天津飞悦航空零部件制造有限公司 | Durable type undercarriage |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844124A (en) * | 2019-11-11 | 2020-02-28 | 中国运载火箭技术研究院 | Reusable carrier landing gear control system and control method |
| CN110844124B (en) * | 2019-11-11 | 2021-09-03 | 中国运载火箭技术研究院 | Reusable carrier landing gear control system and control method |
| CN114671011B (en) * | 2022-03-18 | 2023-10-03 | 成都飞机工业（集团）有限责任公司 | Symmetrical multi-connecting-rod electric drive aircraft landing gear structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR100790530B1 (en) | An auxiliary nose undercarriage, a force-transmission structure, and a rotary wing aircraft | |
| RU2662588C2 (en) | Device for retaining tank in aircraft | |
| CN102015449B (en) | For power supply being bearing in bearing set on the framing member of aircraft and there is the aircraft of bearing set | |
| EP3628592B1 (en) | Aircraft landing gear assembly | |
| CN107985562A (en) | A kind of lightweight compact formula undercarriage | |
| JP2013233927A (en) | Aircraft landing device | |
| JP2011116186A (en) | Engine mount for airplane and airplane | |
| CN202863759U (en) | Stay bar structure of retractable nose landing gear | |
| CN106516087A (en) | Novel high-strength high-compactness lightweight aircraft landing gear | |
| US9957032B2 (en) | Fibre composite component, winglet and aircraft with a fibre composite component | |
| CN105000169A (en) | Novel folding wing and driving and deadlocking mechanism | |
| US11319082B2 (en) | Aircraft assembly comprising a mounting pylon, a wing and two fixing systems fixing the mounting pylon to the wing | |
| CN111003147A (en) | Airplane wing folding control method | |
| CN104875878B (en) | Aircraft with the main landing gear being placed in nacelle | |
| US8439304B2 (en) | Energy absorber system for an undercarriage, and an aircraft provided with said energy absorber system | |
| CN103318425A (en) | Tie rod type connecting and unlocking device | |
| CN109421915A (en) | Energy absorption floor lower body | |
| CN103303483B (en) | A kind of aero-engine installation and maintenance rotating mechanism | |
| JP6356848B2 (en) | Storage / extension of landing gear in aircraft | |
| US10940956B2 (en) | Suspension system for an aircraft auxiliary power unit | |
| CN203581386U (en) | Rotating mechanism for mounting and maintaining aero-engine | |
| CN213705805U (en) | Electric aircraft battery pack's installation device and electric aircraft | |
| US20120085881A1 (en) | Assembly for an aircraft, the assembly including at least one vibration damper | |
| Abeysinghe et al. | Qtd 2 (quiet technology demonstrator 2) main landing gear noise reduction fairing design and analysis | |
| CN109229338B (en) | Self-limiting mechanism for helicopter tail fairing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180504 |
|
| WD01 | Invention patent application deemed withdrawn after publication |