RU1808767C - Retractable aircraft landing gear - Google Patents
Retractable aircraft landing gearInfo
- Publication number
- RU1808767C RU1808767C SU894770026A SU4770026A RU1808767C RU 1808767 C RU1808767 C RU 1808767C SU 894770026 A SU894770026 A SU 894770026A SU 4770026 A SU4770026 A SU 4770026A RU 1808767 C RU1808767 C RU 1808767C
- Authority
- RU
- Russia
- Prior art keywords
- landing gear
- shock absorber
- wheel suspension
- retracted position
- retractable
- Prior art date
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Fluid-Damping Devices (AREA)
- Axle Suspensions And Sidecars For Cycles (AREA)
Abstract
Изобретение относитс к авиационной технике, а именно к убирающимс шасси летательных аппаратов. Целью изобретени вл етс уменьшение массы. Убирающеес шасси летательного аппарата содержит гидроцилиндр 1, шарнирно соединенный со звеном 2, упор 3, рычаг А подвески колеса, ось 5, амортизатор 6, вилку 7 креплени амортизатора, складывающийс подкос и гидроцилиндр складывающегос подкоса, серьгу убранного положени 10 и замок убранного положени 11. 2 ил.FIELD OF THE INVENTION This invention relates to aeronautical engineering, in particular to retractable aircraft landing gear. The aim of the invention is to reduce weight. The aircraft retractable landing gear comprises a hydraulic cylinder 1 pivotally connected to link 2, a stop 3, a wheel suspension arm A, an axle 5, a shock absorber 6, a shock absorber attachment fork 7, a folding brace and a folding brace strut, an earring of a retracted position 10 and a lock of a retracted position 11. 2 ill.
Description
Изобретение относитс к авиационной технике, а именно к убирающимс шасси летательных аппаратов.FIELD OF THE INVENTION This invention relates to aeronautical engineering, in particular to retractable aircraft landing gear.
Цель изобретени - уменьшение массы.The purpose of the invention is weight reduction.
На фиг.1 изображен общий вид шасси; на фиг,2 - вид сверху на шасси,Figure 1 shows a General view of the chassis; in Fig.2 is a top view of the chassis,
Устройство содержит гидроцилиндр 1, шарнирно соединенный со звеном 2,.упор 3, рычаг 4 подвески колеса, ось 5, амортизатор 6, вилку 7 креплени амортизатора, склады- вающийс подкос 8 и гидроцилмндр 9 складывающегос подкоса, серьгу убранного положени 10 и замок убранного положени The device comprises a hydraulic cylinder 1, pivotally connected to a link 2, an abutment 3, a lever 4 of a wheel suspension, an axle 5, a shock absorber 6, a fork 7 for attaching a shock absorber, a folding brace 8 and a hydraulic cylinder 9 of a folding brace, an earring of a retracted position 10 and a lock of a retracted position
11,eleven,
Устройство работает следующим обра- зом.The device operates as follows.
При уборке гидроцилиндр 9 складывает подкос 8. Открываетс замок-фиксатор звена 2 рычага 4. Гидроцилиндр 1 отводит звено 2 с соединенным с ним амортизатором 6 When cleaning, the hydraulic cylinder 9 folds the strut 8. The locking lock of the link 2 of the lever 4 opens. The hydraulic cylinder 1 retracts the link 2 with the shock absorber 6 connected to it
от рычага 4 подвески колеса, При этом осуществл етс подъем стойки путем увеличени размера кинематической св зи рычаг 4 + звено 2 при посто нной длине амо ртизатора 6.from the lever 4 of the wheel suspension. In this case, the rack is lifted by increasing the size of the kinematic connection, the lever 4 + link 2 with a constant length of the shock absorber 6.
Выпуск шасси осуществл етс в обратном пор дке.The landing gear is reversed.
Claims (1)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU894770026A RU1808767C (en) | 1989-11-01 | 1989-11-01 | Retractable aircraft landing gear |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU894770026A RU1808767C (en) | 1989-11-01 | 1989-11-01 | Retractable aircraft landing gear |
Publications (1)
Publication Number | Publication Date |
---|---|
RU1808767C true RU1808767C (en) | 1993-04-15 |
Family
ID=21485103
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SU894770026A RU1808767C (en) | 1989-11-01 | 1989-11-01 | Retractable aircraft landing gear |
Country Status (1)
Country | Link |
---|---|
RU (1) | RU1808767C (en) |
-
1989
- 1989-11-01 RU SU894770026A patent/RU1808767C/en active
Non-Patent Citations (1)
Title |
---|
Патент US № 3807667, кл. 244-102, 1974. * |
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