| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | Track-type machine having undercarriage system with sweeping track shoe | US12967674 | 2010-12-14 | US08764128B2 | 2014-07-01 | Kenneth Nebergall; Stephen Garnett; Britta A. Jost |
| A ground engaging track for a track-type machine includes a set of identical standard track shoes each having a relatively narrow shoe footprint, and a sweeping track shoe having a relatively wide shoe footprint. The sweeping track shoe is connectable via track links with the standard track shoes in an endless chain configuration such that the sweeping track shoe juts outwardly of the standard track shoes, for sweeping debris from a clearance between the track and a main frame of the track-type machine. The sweeping track shoe includes bolting apertures formed therein and communicating between an upper shoe surface and a ground contacting shoe surface, the bolting apertures being arranged in a directional link bolting pattern. The directional link bolting pattern defines a minor shoe axis and a major shoe axis, and the sweeping shoe body may be configured such that an inboard sweeping edge is spaced further than an outboard edge from the minor shoe axis. | ||||||
| 142 | Independent suspension undercarriage module for a low floor vehicle | US10021128 | 2001-12-12 | US20030111834A1 | 2003-06-19 | Ragnar Ledesma; Lawrence Brill; Steven E. Hunter; Malcolm Green; Duy Lam; Michael Edward Schuster; Tomaz Dopico Varela |
| An independent suspension undercarriage module includes a first subframe segment and a second subframe segment. The subframe is manufactured of a composite material to provide a truss-like structural unibody which is mounted as a unit to the underside of a low floor vehicle through a plurality of resilient dampers. Passengers are thereby provided with a secondary vibration isolation structure separate from the suspension systems which filter out high frequency content generated by the suspension systems. | ||||||
| 143 | Low load angle step deck trailer having shiftable undercarriage | US354637 | 1989-05-19 | US5013056A | 1991-05-07 | Donald R. Landoll; Kelly Williams; Ted Peck |
| A trailer having a tiltable main deck and a shiftable undercarriage includes an undercarriage assembly having a deck support structure mounted thereon for supporting the deck. The deck support structure includes lifting arms for lifting the elongated deck assembly relative to the undercarriage independently of the undercarriage shifting mechanism so that the deck may be lifted relative to the undercarriage without simultaneouly shifting the undercarriage along the deck. The trailer may include a hitch assembly that permits the trailer to be pivotally connected to a towing vehicle to permit the forward deck to be tilted away from the main deck to increase the angle between the main deck and the forward deck when the trailer is in the unloading position. Further, a deck angle adjustment assembly is disclosed for adjusting the relative positions of the decks. | ||||||
| 144 | Independent suspension undercarriage module for a low floor vehicle | US10021128 | 2001-12-12 | US06893046B2 | 2005-05-17 | Ragnar Ledesma; Lawrence Brill; Steven E. Hunter; Malcolm Green; Duy Lam; Mike Schuster; Tomaz Dopico Varela |
| An independent suspension undercarriage module includes a first subframe segment and a second subframe segment. The subframe is manufactured of a composite material to provide a truss-like structural unibody which is mounted as a unit to the underside of a low floor vehicle through a plurality of resilient dampers. Passengers are thereby provided with a secondary vibration isolation structure separate from the suspension systems which filter out high frequency content generated by the suspension systems. | ||||||
| 145 | Gripping and locking arrangement for aircraft flap doors or undercarriages | US484498 | 1990-02-23 | US5040747A | 1991-08-20 | Brian Kane; Jurgen Laude |
| A gripping and locking arrangement for an aircraft movable component such as a flap door or undercarriage comprises a piston and a piston rod operative as a means for sensing a closing movement of the flap door or undercarriage, and also operative automatically actively to pull same by means of a closing hook into a position in which it is to be locked. The arrangement includes a locking member displaceable within the piston to move lock elements into a locking position and to hold them in the locking position until the arrangement receives a hydraulic pressure signal for causing lowering of the flap door or undercarriage, and the locking member is then displaced whereby the lock elements move into a release position. The hydraulic oil pressure can then act on the piston to produce displacement thereof into a position in which the closing hook releases the flap door or undercarriage component. | ||||||
| 146 | Cover panel for an aircraft, more particularly a landing gear cover panel for a cargo plane | US12457076 | 2009-06-01 | US08740146B2 | 2014-06-03 | Hermann Benthien; Björn Bertram; Sandra Kuckuck; Frank Gustävel |
| The invention relates to a cover panel for a landing gear for an aircraft with at least one pivotal closable flap 6, 7. According to the invention the at least one flap 6, 7 is attached for swivel movement to the fuselage cell 2 of the aircraft by means of at least one multi-articulated joint 8, 9, 13 wherein the multi-articulated joint 8, 9, 13 is constructed with a number of individual joints seated on a shaft 17, similar to a piano hinge, and a mechanical play increases preferably uniformly starting from a middle individual joint 14 towards the outer individual joints 15, 16. As a result of the mechanical play which increases within the multi-articulated joint 8, 9, 13 from the middle individual joint 14 to the two outer individual joints 15, 16 in the direction of the x-axis or aircraft longitudinal axis, a substantial mechanical isolation of the cover panel from any possible fuselage cell movements is provided. The flap 7 has at least in the area of one side edge an anti-lift security mechanism 26 in order to prevent aerodynamically conditioned flapping and lifting movements of the flap 7 in the direction of the aircraft vertical axis or z-axis. | ||||||
| 147 | Cover panel for an aircraft, more particularly a landing gear cover panel for a cargo plane | US12457076 | 2009-06-01 | US20090308976A1 | 2009-12-17 | Hermann Benthien; Bjorn Bertram; Sandra Kuckuck; Frank Gustavel |
| The invention relates to a cover panel for a landing gear for an aircraft with at least one pivotal closable flap 6, 7. According to the invention the at least one flap 6, 7 is attached for swivel movement to the fuselage cell 2 of the aircraft by means of at least one multi-articulated joint 8, 9, 13 wherein the multi-articulated joint 8, 9, 13 is constructed with a number of individual joints seated on a shaft 17, similar to a piano hinge, and a mechanical play increases preferably uniformly starting from a middle individual joint 14 towards the outer individual joints 15, 16. As a result of the mechanical play which increases within the multi-articulated joint 8, 9, 13 from the middle individual joint 14 to the two outer individual joints 15, 16 in the direction of the x-axis or aircraft longitudinal axis, a substantial mechanical isolation of the cover panel from any possible fuselage cell movements is provided. The flap 7 has at least in the area of one side edge an anti-lift security mechanism 26 in order to prevent aerodynamically conditioned flapping and lifting movements of the flap 7 in the direction of the aircraft vertical axis or z-axis. | ||||||
| 148 | Dispositif d'augmentation de la stabilité des hélicoptères embarqués et posés, à train d'atterrissage tricycle, et hélicoptère équipé d'un tel dispositif | EP89400076.9 | 1989-01-10 | EP0324683A1 | 1989-07-19 | Bernard, Louis Arthur; Thomassin, René |
L'invention concerne un dispositif d'augmentation de la stabilité, en particulier latérale, d'un hélicoptère embarqué (1) à train d'atterrissage tricycle (2, 6), lorsqu'il est posé sur une plate-forme mouvante. Le dispositif comprend deux stabilisateurs latéraux (13) munis chacun d'une roue (16) d'appui sur la plate-forme et relié à la structure de l'hélicoptère par un support essentiellement rigide comprenant une jambe (17), autour de l'axe de laquelle la roue (16) peut tourillonner, la jambe (17) étant elle-même reliée à la structure par un organe rigide et transversale pouvant être un axe de pivot si la jambe est relevable, ou un bras d'emmanchement si le stabilisateur (13) est additionnel. Les stabilisateurs peuvent aussi être intégrés à un chariot de remorquage. Application à l'équipement des hélicoptères embarqués à train d'atterrissage tricycle. |
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| 149 | Method and device for an optimal management of the slats, the flaps and the landing gear of an aircraft | US13557381 | 2012-07-25 | US08864081B2 | 2014-10-21 | Florian Constans; Mickaël Lefebvre |
| A method is described for optimized energy management of an aircraft upon a flight along a trajectory. The method allows the aircraft to join a given point of the trajectory in a given energy state, with a given position of the slats and flaps, and with a given position of the landing gear. The method includes determining current parameter values of the aircraft. The method also includes determining optimized command orders based on the current parameter values by performing a sequence of operations in an iterative way. The method further includes applying the optimized command orders to an automatic slats and flaps command device and an automatic landing gear command device for automatic control of the slats and flaps and the landing gear, respectively. | ||||||
| 150 | METHOD FOR INFLIGHT DEICING OF LANDING GEAR AND WHEEL BAYS IN AIRCRAFT WITH ONBOARD DRIVE MEANS | US13779724 | 2013-02-27 | US20150210399A1 | 2015-07-30 | Isaiah W. Cox |
| A method is provided for removing ice, snow, slush, and frozen contaminants from landing gear, wheel wells, and associated structures while an aircraft is in flight and preventing the accumulation of frozen contaminants during flight in an aircraft equipped with onboard drive means powered to drive at least one landing gear wheel and selectively controllable to move the aircraft on the ground during taxi in winter and other weather conditions. | ||||||
| 151 | Method And Device For An Optimal Management Of The Slats, The Flaps And The Landing Gear Of An Aircraft | US13557381 | 2012-07-25 | US20130026299A1 | 2013-01-31 | Florian Constans; Mickaël Lefebvre |
| Method and device for an optimal management of the slats, the flaps and the landing gear of an aircraft.The device (1) includes means (5) for determining, in an iterative manner, according to a predicted energy state, optimal commands of means (10, 11) for controlling the slats, the flaps and the landing gear of the aircraft, which allow the aircraft to reach a given point of a trajectory in a given energy state with a given aerodynamic configuration and a given position of the landing gear. | ||||||
| 152 | 高可靠性无人机起落架收放系统 | CN201710866169.9 | 2017-09-22 | CN107719647B | 2019-11-29 | 付竟成; 黄俊; 宋磊; 郑浩 |
| 本发明公开了一种高可靠性无人机起落架收放系统，属于无人机设计技术领域。所述的收放系统包括一套起落架收放机构和一套起落架收放锁止机构。所述的起落架收放机构包括起落架侧板及边框结构、起落架支柱及机轮总成、起落架支柱收放摇臂、起落架支柱收放作动气缸、起落架撑杆万向节、起落架上撑杆和起落架下撑杆；所述的起落架收放锁止机构包括起落架下位锁气缸、起落架下位锁三角、起落架下位锁锁舌、起落架上位锁外壳、起落架上位锁气缸、起落架上位锁锁舌和起落架上位锁锁钩。该起落架收放系统具有结构紧凑、受力形式合理、非作动状态下无需驱动力保持、无气压放下可自行锁定等优点。 | ||||||
| 153 | 高可靠性无人机起落架收放系统 | CN201710866169.9 | 2017-09-22 | CN107719647A | 2018-02-23 | 付竟成; 黄俊; 宋磊; 郑浩 |
| 本发明公开了一种高可靠性无人机起落架收放系统，属于无人机设计技术领域。所述的收放系统包括一套起落架收放机构和一套起落架收放锁止机构。所述的起落架收放机构包括起落架侧板及边框结构、起落架支柱及机轮总成、起落架支柱收放摇臂、起落架支柱收放作动气缸、起落架撑杆万向节、起落架上撑杆和起落架下撑杆；所述的起落架收放锁止机构包括起落架下位锁气缸、起落架下位锁三角、起落架下位锁锁舌、起落架上位锁外壳、起落架上位锁气缸、起落架上位锁锁舌和起落架上位锁锁钩。该起落架收放系统具有结构紧凑、受力形式合理、非作动状态下无需驱动力保持、无气压放下可自行锁定等优点。 | ||||||
| 154 | 一种无人飞行器 | PCT/CN2019/128059 | 2019-12-24 | WO2020135448A1 | 2020-07-02 | 梁智颖 |
一种无人飞行器（100），包括机身（10）和安装于机身的起落架组件（40），起落架组件包括安装板，起落架（42）和压紧结构（43）。安装板与机身相连，起落架安装于安装板，起落架可相对于安装板绕中心线转动，安装板和起落架中的一个设置有锁孔（114），另一个设置有锁销（425），所述锁孔绕中心线呈圆周分布，压紧结构连接安装板和起落架，用于提供使安装板和起落架沿中心线相互靠近的压紧力。所述无人飞行器配置有起落架组件，并且所述起落架组件中的起落架可相对于所述机身展开或者折叠，可实现所述无人飞行器便于携带。 |
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| 155 | 一种无人机起落架连接结构 | CN202011392262.9 | 2020-12-02 | CN112478140B | 2023-09-22 | 许阳阳; 苏亚东; 陈召斌; 金凤新; 赵博; 王德刚; 李宪开; 唐雪松; 季宝峰; 王志勇; 刘含洋; 刘志军; 霍贵臣 |
| 本申请涉及一种无人机起落架连接结构，包括：起落架占位环框；传载梁，侧壁连接在起落架占位环框一侧；扣板，边缘与起落架占位环框连接，包覆传载梁；起落架接头，与扣板连接。上述无人机起落架连接结构中，起落架占位环框可在无人机机身上设置，起落架接头与无人机起落架连接，以实现无人机起落架与机身的连接，在无人机起落过程中，起落架承受的冲击载荷，经起落架接头、扣板、传载梁传递至起落架占位环框，在传递过程中被分解，避免了起落架直接向起落架占位环框传递集中载荷，从而能够避免在起落架占位环框产生较大的局部应力，使起落架占位环框遭受破坏。 | ||||||
| 156 | 一种无人机起落架连接结构 | CN202011392262.9 | 2020-12-02 | CN112478140A | 2021-03-12 | 许阳阳; 苏亚东; 陈召斌; 金凤新; 赵博; 王德刚; 李宪开; 唐雪松; 季宝峰; 王志勇; 刘含洋; 刘志军; 霍贵臣 |
| 本申请涉及一种无人机起落架连接结构，包括：起落架占位环框；传载梁，侧壁连接在起落架占位环框一侧；扣板，边缘与起落架占位环框连接，包覆传载梁；起落架接头，与扣板连接。上述无人机起落架连接结构中，起落架占位环框可在无人机机身上设置，起落架接头与无人机起落架连接，以实现无人机起落架与机身的连接，在无人机起落过程中，起落架承受的冲击载荷，经起落架接头、扣板、传载梁传递至起落架占位环框，在传递过程中被分解，避免了起落架直接向起落架占位环框传递集中载荷，从而能够避免在起落架占位环框产生较大的局部应力，使起落架占位环框遭受破坏。 | ||||||
| 157 | 一种基于打水漂原理辅助飞行器水陆滑行的机构 | CN201910988137.5 | 2019-10-17 | CN110682751B | 2022-07-15 | 王革; 王英男; 李冬冬; 唐春辉; 邹志辉; 李君婷; 孟伶智; 黄果成; 苏成志; 周凌 |
| 本发明涉及飞行器水陆两栖滑行机构领域，具体涉及一种基于打水漂原理辅助飞行器水陆滑行的机构。包括前滑行机构部分和后滑行机构部分；前滑行机构部分安装于前起落架处，包括前起落架乘板，前起落架机身支承，前起落架机轮支承，前起落架机轮，前起落架乘板固定支架，前起落架液压缓冲作动筒，前起落架螺栓和连接段液压缓冲器；后滑行机构部分安装于后起落架处，包括后起落架机身支承，后起落架乘板，后起落架尾舵，后起落架液压缓冲作动筒，后起落架机轮支承，后起落架机轮和后起落架螺栓。本发明可使飞行器在地面滑行起飞，提高飞行高度，拓宽探测范围，减少水面阻力，无需发动机提供过多动力。 | ||||||
| 158 | 一种基于打水漂原理辅助飞行器水陆滑行的机构 | CN201910988137.5 | 2019-10-17 | CN110682751A | 2020-01-14 | 王革; 王英男; 李冬冬; 唐春辉; 邹志辉; 李君婷; 孟伶智; 黄果成; 苏成志; 周凌 |
| 本发明涉及飞行器水陆两栖滑行机构领域，具体涉及一种基于打水漂原理辅助飞行器水陆滑行的机构。包括前滑行机构部分和后滑行机构部分；前滑行机构部分安装于前起落架处，包括前起落架乘板，前起落架机身支承，前起落架机轮支承，前起落架机轮，前起落架乘板固定支架，前起落架液压缓冲作动筒，前起落架螺栓和连接段液压缓冲器；后滑行机构部分安装于后起落架处，包括后起落架机身支承，后起落架乘板，后起落架尾舵，后起落架液压缓冲作动筒，后起落架机轮支承，后起落架机轮和后起落架螺栓。本发明可使飞行器在地面滑行起飞，提高飞行高度，拓宽探测范围，减少水面阻力，无需发动机提供过多动力。 | ||||||
| 159 | 仿真飞机起落架模拟装置 | CN201510632393.2 | 2015-09-29 | CN105160961B | 2017-12-26 | 陈笑慰 |
| 一种仿真飞机起落架模拟装置，包括：左固定板及右固定板，设有起落架三档位位置槽及起落架限位装置槽；起落架操纵杆，通过支撑轴固定在左固定板与右固定板之间；多个起落架档位感应开关，靠近起落架三档位位置槽及起落架三档位位置槽的档位设置于左固定板或右固定板上；起落架收放限位杆，固定在设置起落架操纵杆上，与起落架三档位位置槽及起落架三档位位置槽相配合；电磁铁，固定在左固定板与右固定板之间；限位装置，在电磁铁的作用下撑起或者落下；限位轴，固定在起落架操纵杆的末端，可沿起落架限位装置槽及起落架限位装置槽滑动；服务器，接收起落架档位感应开关传输的位置数据，根据位置数据控制限位装置的撑起或者落下。 | ||||||
| 160 | 仿真飞机起落架模拟装置 | CN201510632393.2 | 2015-09-29 | CN105160961A | 2015-12-16 | 陈笑慰 |
| 一种仿真飞机起落架模拟装置，包括：左固定板及右固定板，设有起落架三档位位置槽及起落架限位装置槽；起落架操纵杆，通过支撑轴固定在左固定板与右固定板之间；多个起落架档位感应开关，靠近起落架三档位位置槽及起落架三档位位置槽的档位设置于左固定板或右固定板上；起落架收放限位杆，固定在设置起落架操纵杆上，与起落架三档位位置槽及起落架三档位位置槽相配合；电磁铁，固定在左固定板与右固定板之间；限位装置，在电磁铁的作用下撑起或者落下；限位轴，固定在起落架操纵杆的末端，可沿起落架限位装置槽及起落架限位装置槽滑动；服务器，接收起落架档位感应开关传输的位置数据，根据位置数据控制限位装置的撑起或者落下。 | ||||||
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