公开(公告)号：US20040267413A1

公开(公告)日：2004-12-30

申请号：US10490676

申请日：2004-03-24

发明人： Werner Keber

IPC分类号： B64C001/00 ,  G01S001/00

CPC分类号： G08G5/006 ,  B64D45/0031

摘要： The invention concerns a method for preventing airplanes from impermissibly approaching defendable ground objects, with the momentary flight position being recorded in a satellite-based way and used for the purposes of manual and automatic flight corrections. According to the invention, this method suggests that a defendable ground object is assigned a virtual prohibited zone spatially surrounding it, with the outer boundary of such zone being provided with a sufficient horizontal minimum distance from the ground object and a vertical minimum distance determining a given minimum crossing altitude, that the prohibited zone is assigned a virtual correction zone laterally surrounding it whose outer boundary has a horizontal minimum distance from the outer boundary of the prohibited zone in any case sufficient for any forced deviation corrections and an altitude equal to that of the prohibited zone; that the correction zone is assigned a virtual alarm zone spatially surrounding it whose outer boundary has a horizontal and vertical minimum distance from the outer boundary of the correction zone in any case sufficient for manual deviation corrections; that the geographical data of the outer boundaries of at least the alarm and the correction zone are recorded and digitally stored together with the vertical minimum distance or the minimum crossing altitude and stored with access protection provided in every airplane and displayed in the cockpit; that the momentary flight position is recorded in a satellite-based way and the momentary flight altitude established and these instantaneous data compared with the geographical data of the outer boundaries of the alarm and the correction zone; that in the event of an airplane's penetration into the alarm zone detected by such position data comparison, a warning signal is transmitted until the airplane leaves that zone, and at the same time the airplane is allowed to be manually steered for the purposes of leaving the alarm zone; that in the event of an airplane's lateral penetration into the correction zone detected by such position data comparison, the airplane's manual steerability is temporarily inhibited and replaced by autopilot control to the right or left forcing the airplane to leave the correction zone at least until the airplane again reaches the alarm zone, and that in the event of an approach in descent to the vertical minimum distance determining the given minimum crossing altitude above the prohibited zone and the correction zone, the airplane's descent is limited to at minimum the minimum crossing altitude by force.

公开(公告)号：US20040249519A1

公开(公告)日：2004-12-09

申请号：US10727447

申请日：2003-12-03

发明人： Bentley D. Frink

IPC分类号： B64C001/00 ,  G06F017/00

CPC分类号： G05D1/0061 ,  B64D45/0015 ,  B64D2045/0055 ,  H04B7/18506

摘要： The present invention is an aircraft having a memory loaded with geolocation data corresponding to restricted airspace boundaries and an autonomous means for rerouting the aircraft outside of the restricted airspace boundaries as the aircraft approaches to within a predetermined distance of the restricted airspace.

摘要翻译： 本发明是具有装载有对应于受限制的空域边界的地理定位数据的存储器的飞行器，以及用于在飞行器接近限制空域的预定距离内的情况下将飞机重新路由在受限空域边界之外的自主装置。

公开(公告)号：US20040200923A1

公开(公告)日：2004-10-14

申请号：US10410364

申请日：2003-04-10

发明人： John Randy Lee

IPC分类号： B64C001/00

CPC分类号： B64D43/00

摘要： An instrumentation panel has a panel display surface and an opposed surface, with an interconnected web of raised material lands arranged across the display surface of the panel and which display surface is otherwise generally characterized by interstitial depressions, and wherein the display surface lands are adapted to receive at least one instrumentation housing in fixed-supported relation there through. In one embodiment, the opposed surface also comprises a plurality of raised complementary lands, preferably arranged in a transverse intersecting pattern relative to the pattern of the raised lands of the display surface. In another embodiment, the lands form a pattern that provides visual cues that aid the viewer in rapidly centering the instrumentation within the visual field and preferably, the lands and the depressions on the display surface receive respective but mutually visually contrasting surface treatments.

摘要翻译： 仪表板具有面板显示表面和相对表面，其中横跨面板的显示表面布置有互相连接的凸起材料的腹板，并且该显示表面通常以间隙凹陷为特征，并且其中显示表面平台适于 至少在一个固定支持的关系中收到一个仪表住房。 在一个实施例中，相对表面还包括多个凸起的互补平台，优选地相对于显示表面的凸起凸起的图案以横向相交图案布置。 在另一个实施例中，脊台形成提供视觉提示的图案，其帮助观看者快速地将仪器对准在视野内，并且优选地，显示表面上的平台和凹陷接收相应但相互视觉上对比的表面处理。

公开(公告)号：US20040187409A1

公开(公告)日：2004-09-30

申请号：US10806229

申请日：2004-03-23

申请人： KOBELCO CONSTRUCTION MACHINERY CO., LTD.

发明人： Kenta Kojima ,  Tadashi Shirogami

IPC分类号： B64C001/00

CPC分类号： E02F9/16

摘要： A method of assembling a floor structure of a construction machine is based upon the machine with a stepwise part that is located at a lower level on the outside is formed on the end edge of a floor plate as a floor structure. In case of a cabin specification with a cabin mounted, a device for opening and closing a door is housed in the stepwise part with the stepwise part filled in, and a first floor mat having a substantially constant thickness is mounted on the floor plate. In case of a canopy specification having a canopy, a second floor mat having on its end edge a protrusion which is fitted into the stepwise part instead of the device to fill the part is mounted on the floor plate. Accordingly, the same floor plate can be employed in both cabin and canopy specifications, regardless of the specification, thereby reducing the number of parts constituting the floor structure.

摘要翻译： 一种组装施工机械的地板结构的方法是基于具有位于外侧下层的阶梯部分的机器形成在地板板的端部边缘上作为地板结构。 在安装有机舱的舱室规格的情况下，用于打开和关闭门的装置被容纳在逐步部分被填充的阶梯部分中，并且具有基本上恒定厚度的第一层地垫被安装在地板上。 在具有冠层的罩盖规格的情况下，在其端部边缘具有装配到阶梯部分中的突起部分而不是用于填充部件的装置的二层垫子被安装在地板上。 因此，无论规格如何，都可以在舱室和舱盖规格中使用相同的地板，从而减少构成地板结构的部件的数量。

公开(公告)号：US20040182966A1

公开(公告)日：2004-09-23

申请号：US10479409

申请日：2003-12-03

发明人： Catherine Schneider ,  Dominique Morin

IPC分类号： B64C001/00

CPC分类号： G08G5/0052 ,  B64D39/00

摘要： The in-flight refuelling of a squadron (1) of aircraft by a tanker (2) by means of the same refuelling hose requires the formation of a queue and the determination of the number of passes, one or possibly two, by each aircraft to the refuelling hose, which constitutes a refuelling sequence. Although the order in the queue is simple to establish, since it often corresponds to a classification by decreasing quantities of fuel demanded, the same does not apply to the number of passes to the refuelling hose, which must be minimized while still respecting the endurances of the aircraft to be refuelled before their actual refuelling starts. The method described, which may be implemented by a computer, automates the search for a refuelling sequence that satisfies the endurance requirements of the various aircraft to be refuelled, while still having the minimum number of passes to the refuelling hose by the aircraft in the squadron.

摘要翻译： 油轮（2）通过相同的加油软管在飞机上加油的飞行员（1）需要形成一个排队队伍，并确定每架飞机的通行证数目（一个或两个）到 加油软管，构成加油顺序。 虽然队列中的顺序很容易建立，但由于通常通过减少所需燃料的数量来对应于分类，所以同样不适用于加油软管的通行次数，这一点必须最小化，同时仍然遵守 在实际加油开始之前要加油的飞机。 可以由计算机实现的描述的方法自动搜索满足要加油的各种飞机的耐久性要求的加油顺序，同时仍然具有由中队中的飞机到加油软管的最小次数 。

公开(公告)号：US20040148068A1

公开(公告)日：2004-07-29

申请号：US10360020

申请日：2003-02-07

发明人： Richard A. Fowell ,  Salma I. Saeed ,  Rongsheng Li ,  Yeong-Wei Wu

IPC分类号： B64C001/00

CPC分类号： B64G1/361 ,  B64G1/288 ,  B64G1/36 ,  B64G1/363 ,  B64G1/365

摘要： A method, apparatus, article of manufacture, and a memory structure for compensating for optical sensor data corrupted by angular acceleration is disclosed. The method comprises the steps of determining an angular acceleration of the optical sensor and modifying the optical sensor data according to the determined angular acceleration of the optical sensor. The apparatus comprises a sensor for determining an angular acceleration of the optical sensor and a navigation system for modifying the optical sensor data according to the determined angular acceleration of the optical sensor.

摘要翻译： 公开了一种用于补偿由角加速度损坏的光学传感器数据的方法，装置，制品和存储结构。 该方法包括以下步骤：根据确定的光学传感器的角加速度确定光学传感器的角加速度并修改光学传感器数据。 该装置包括用于确定光学传感器的角加速度的传感器和用于根据确定的光学传感器的角加速度来修改光学传感器数据的导航系统。

公开(公告)号：US20040124310A1

公开(公告)日：2004-07-01

申请号：US10619623

申请日：2003-07-16

发明人： Daiya Yamashita ,  Fumihiko Shikano ,  Hiroshi Kato ,  Akira Kaneko ,  Takumi Shibata

IPC分类号： B64C001/00 ,  B64C003/00 ,  B64C005/00

CPC分类号： B23H9/00 ,  B23H7/02 ,  B23H9/10 ,  B64C27/473

摘要： It is an object to provide a blade member for an airplane which is simple in structure, and moreover is excellent with respects to weight, aerodynamic performance, cost, strength and durability. A vane of a double-slotted flap includes: an outer skin area surrounded by a first outer skin, a second outer skin, a leading edge and a trailing edge each having a predetermined wall thickness. Front and rear reinforcing areas are provided that extend in a span direction within the outer skin area and are connected to the first outer skin and the second outer skin. The outer skin area and the reinforcing areas are integrally formed by wire electrical discharge-machining. The first outer skin and the second outer skin respectively have thickened portions thicker than the other portions, and the trailing edge is formed to have a thickness which is approximately zero. This blade member can be simplified in structure, leading to reductions in the number of parts, number of assembling steps and weight. Moreover, no step nor seam is generated on a surface of the blade member, and hence it is possible to prevent an increase in drag and the generation of corrosion.

摘要翻译： 本发明的目的是提供一种结构简单的用于飞机的叶片构件，并且在重量，空气动力学性能，成本，强度和耐久性方面都是优异的。 双开口翼片的叶片包括：由第一外皮，第二外皮，前缘和后缘围绕的外皮区域，每个具有预定的壁厚。 提供前后加强区域，其在外皮肤区域内沿跨度方向延伸并连接到第一外皮和第二外皮。 外皮区域和加强区域通过电线放电加工一体形成。 第一外皮和第二外皮分别具有比其他部分更厚的加厚部分，并且后缘形成为具有近似为零的厚度。 该叶片构件可以简化结构，从而减少零件数量，组装步骤数量和重量。 此外，在叶片构件的表面上不产生台阶或接缝，因此可以防止阻力的增加和腐蚀的产生。

公开(公告)号：US20040122568A1

公开(公告)日：2004-06-24

申请号：US10687585

申请日：2003-10-20

申请人： ALCATEL

发明人： Eric Montfort ,  Cedric Salenc ,  Xavier Roser ,  Loic Gaudic

IPC分类号： G05D001/00 ,  B64C001/00 ,  G05D003/00 ,  G06F007/00 ,  G06F017/00

CPC分类号： B64G1/244

摘要： An attitude control system is disclosed for geostationary satellites including elongate members such as solar generators and/or antennas, in particular deployable members. The system includes gyroscopic actuators for supplying the torque necessary for maintaining the attitude of the satellite when subjected to disturbing forces or torques. The gyroscopic actuators preferably maintain a setpoint attitude during orbit correction phases.

摘要翻译： 公开了一种用于对地静止卫星的姿态控制系统，包括诸如太阳能发电机和/或天线的细长构件，特别是可部署的构件。 该系统包括用于在受到扰动力或扭矩时提供用于维持卫星的姿态所必需的扭矩的陀螺仪致动器。 陀螺式致动器优选地在轨道校正阶段保持设定点姿态。

公开(公告)号：US20040118978A1

公开(公告)日：2004-06-24

申请号：US10326995

申请日：2002-12-24

发明人： Bruce D. Anning

IPC分类号： B64C001/00 ,  B64C003/00 ,  B64C005/00

CPC分类号： B64C11/205 ,  B64C27/473

摘要： An aerofoil, particularly a helicopter main rotor blade has a leading edge protector comprising a strip of resilient polymer, preferably polyurethane, adhered to the leading edge of the blade.

摘要翻译： 机翼，特别是直升机主转子叶片具有前缘保护器，其包括粘附到叶片的前缘上的弹性聚合物条，优选聚氨酯。

公开(公告)号：US20040118977A1

公开(公告)日：2004-06-24

申请号：US10712041

申请日：2003-11-14

申请人： Toyota Motor Sales, U.S.A., Inc.

发明人： Alan H. Anderson ,  Kathlene K. Bowman ,  Paul D. Teufel

IPC分类号： B64C001/00

CPC分类号： B64C1/064 ,  B29C33/505 ,  B29C70/342 ,  B29C70/446 ,  B29L2031/3082 ,  B64C1/061 ,  B64C2001/0072 ,  B64C2211/00 ,  B64D2011/0046 ,  Y02T50/43

摘要： The present invention relates to a one-piece closed-shape structure and a method for manufacturing a one-piece closed-shape structure. In particular, the present invention relates to a one-piece fuselage and a method for manufacturing a one-piece fuselage. One embodiment of the method of the invention involves the use of molding technology, tooling technology, the integration of the molding and tooling technology, and fiber placement to manufacture a one-piece closed shape structure.

摘要翻译： 本发明涉及一体封闭形状结构和一体式封闭形结构的制造方法。 特别地，本发明涉及一体式机身和一体式机身的制造方法。 本发明方法的一个实施例涉及使用成型技术，模具技术，成型和模具技术的集成以及纤维布置以制造一体式闭合形状结构。