公开(公告)号：US20160101875A1

公开(公告)日：2016-04-14

申请号：US14510020

申请日：2014-10-08

Applicant: Cessna Aircraft Company

Inventor： David Wayne Davis ,  Todd Thisius ,  Chris Trask ,  Chris Pinkerton

IPC: B64F5/00 ,  G09B25/00

CPC classification number: B64F5/10 ,  G09B25/02

Abstract: A system and method for simulating a structure is disclosed. An adjustable interior mockup for simulating a structure has a base with a first elongated side and a second elongated side, the first elongated side being nonadjacent the second elongated side; and an adjustable frame secured to the base. The adjustable frame includes a plurality of girder members secured along the first and second elongated sides to form an arc; a plurality of brackets; a plurality of arms having a latch attached to one end; and a sheet of fabric. The girders are securely fastened along the first elongated side of the base at predetermined intervals; the brackets are secured to the girders; the arms are received by the brackets and adjustably anchored to the girders via a fastener; and the latches engage the sheet of fabric, thus pulling the fabric into a shape that resembles the structure.

Abstract translation: 公开了一种用于模拟结构的系统和方法。 用于模拟结构的可调节内部模型具有具有第一细长侧和第二细长侧的基部，第一细长侧不在第二细长侧; 以及固定到基座的可调节框架。 可调节框架包括沿着第一和第二细长侧固定以形成弧的多个梁构件; 多个括号; 多个臂，其具有附接到一端的闩锁; 和一张面料。 大梁以预定间隔沿着基座的第一细长侧牢固地固定; 支架固定在桁架上; 支架被支架接收并通过紧固件可调节地锚固到桁材上; 并且闩锁接合织物片，从而将织物拉到类似于结构的形状。

公开(公告)号：US20160001871A1

公开(公告)日：2016-01-07

申请号：US14789330

申请日：2015-07-01

Applicant: Cessna Aircraft Company

Inventor： Billy M. Martin ,  Timothy E. Harrison ,  Zai Lo ,  Brandon L. Parks

IPC: B64C3/34 ,  B64C1/14

CPC classification number: B64C3/34 ,  B64C1/1446 ,  B64D37/32 ,  B64D45/02 ,  Y02T50/44

Abstract: Aircraft fuel tank access door systems and methods incorporating one or more of an outer fuel tank access door completely encapsulated by a dielectric material and an inner fuel tank access door comprising at least one drainage feature are disclosed. These systems and methods reduce or prevent (i) fuel pooling on the inner fuel tank access door, (ii) moisture pooling between the inner and outer fuel tank access doors, and (iii) p-static build up and lightning attachment to the outer fuel tank access door to increase safety, reduce the likelihood of corrosion and ease installation of the fuel tank access door system.

Abstract translation: 公开了包括完全由电介质材料包封的外部燃料箱检修门的一个或多个和包括至少一个排水特征的内部燃料箱检修门的飞机燃料箱检修门系统和方法。 这些系统和方法减少或防止（i）内燃料箱检修门上的燃料积聚，（ii）内部和外部燃料箱检修门之间的水分聚集，以及（iii）静电积聚和闪电附着到外部 燃油箱检修门增加安全性，减少腐蚀和容易安装燃油箱门禁系统的可能性。

公开(公告)号：US20150288466A1

公开(公告)日：2015-10-08

申请号：US14244618

申请日：2014-04-03

Applicant: CESSNA AIRCRAFT COMPANY

Inventor： Joseph Charles Norman ,  Adam Blake Wolfe ,  Mark Christopher Hansen

IPC: H04B17/20 ,  H04B1/00

CPC classification number: H04B1/0057 ,  H04B1/406

Abstract: An apparatus for testing for the susceptibility of an aircraft system to radio frequencies comprises a wireless module for generating radio signals that sweep each of the 2.4 GHz frequency band and the 5 GHz frequency band. A first amplifier is configured for amplifying signals in the 2.4 GHz band, and a second amplifier is configured for amplifying signals in the 5 GHz band. The apparatus comprises at least one dual band antenna for transmitting the signals in each of the 2.4 GHz and the 5 GHz bands.

Abstract translation: 用于测试飞行器系统对无线电频率的敏感性的装置包括用于产生扫描2.4GHz频带和5GHz频带中的每一个的无线电信号的无线模块。 第一放大器被配置用于放大2.4GHz频带中的信号，并且第二放大器被配置用于放大5GHz频带中的信号。 该装置包括用于在2.4GHz和5GHz频带中的每一个传输信号的至少一个双频带天线。

公开(公告)号：US20150262545A1

公开(公告)日：2015-09-17

申请号：US14642032

申请日：2015-03-09

Applicant: Cessna Aircraft Company

Inventor： Jeremy Joseph Kneuper ,  Isaac Wayne Stanfield ,  Jason Michael Decker ,  John Robert Lanier ,  Christopher Adair Pinkerton

IPC: G09G5/00

CPC classification number: B64D43/00 ,  G01C23/00 ,  G06F3/0488 ,  G06F2203/04804 ,  G09G5/14 ,  G09G2340/10 ,  G09G2340/12 ,  G09G2380/12

Abstract: A system and method for displaying standby instrument information is disclosed. The touch-screen instrument panel system for a vehicle has a touch-screen information panel display configured to display vehicle operation information received from a computing system and a standby instrument display that is secured to an area located behind the information panel display. The standby instrument display is hidden from view when the information panel display is in a powered state but is in full view when the information panel display is in an unpowered state.

Abstract translation: 公开了一种用于显示备用仪器信息的系统和方法。 用于车辆的触摸屏仪表板系统具有触摸屏信息面板显示器，其被配置为显示从计算系统接收的车辆操作信息和固定到位于信息面板显示器后面的区域的待机仪器显示器。 当信息面板显示器处于供电状态时，备用仪器显示屏被隐藏，当信息面板显示屏处于无动力状态时，显示屏处于完整视图。

公开(公告)号：US20150108114A1

公开(公告)日：2015-04-23

申请号：US14517206

申请日：2014-10-17

Applicant: Cessna Aircraft Company

Inventor： Charles Bernard Beuning ,  Vernon Weng-Yew Chang

IPC: H01M10/633 ,  H01M10/623 ,  H01M10/615 ,  H01M10/625 ,  H02J7/00 ,  H01M10/44

CPC classification number: H01M10/443 ,  H01M10/615 ,  H01M10/633 ,  H01M10/657 ,  H01M2220/20 ,  H01M2220/30

Abstract: A battery heater system for a battery used in cold weather operations and methods for using the battery heater system are described. Embodiments of the battery heater system may incorporate a heater switch with an indicator, a timer circuit, a controller, a voltage meter, a temperature transducer, and a heating element. In some methods of using the device, the battery powers the heating element for a fixed cycle time based on the time to discharge the battery at a cold-soaked temperature. In other methods of using the device, the battery powers the heating element for a varying cycle time as necessary to discharge the battery to a discharge cut-off voltage value. In other methods of using the device, the heating element is operated using a duty cycle that is varied based on the battery temperature.

Abstract translation: 描述了用于寒冷天气操作的电池的电池加热器系统和用于使用电池加热器系统的方法。 电池加热器系统的实施例可以包括具有指示器的加热器开关，定时器电路，控制器，电压计，温度传感器和加热元件。 在使用该装置的一些方法中，电池基于在冷浸温度下放电电池的时间，为加热元件供电固定循环时间。 在使用该装置的其它方法中，根据需要，电池为加热元件供电以改变周期时间，以将电池放电至放电截止电压值。 在使用该装置的其它方法中，使用基于电池温度而改变的占空比操作加热元件。

公开(公告)号：US20150048210A1

公开(公告)日：2015-02-19

申请号：US13966738

申请日：2013-08-14

Applicant: Cessna Aircraft Company

Inventor： Michael Scott Montgomery

IPC: B64D37/32 ,  B64D37/04

CPC classification number: B64D37/32 ,  B64D37/04

Abstract: Disclosed is a method for controlling the flammability of fuel vapors in an aircraft main fuel tank that is located in whole or in part in the fuselage contour. The method comprises a fuel system architecture and fuel consumption sequencing maintaining liquid fuel in said main tanks during all normal operations. Ceasing the withdrawal of fuel from the main tank when the fuel reaches a predetermined level thereby limiting the volume and flammability exposure time of the fuel vapor ullage. Once the predetermined level is met the fuel is supplied from wing tanks throughout the remainder of the mission. The predetermined main tank fuel level at which wing tank fuel begins to be consumed is determined by the aircraft flight reserves fuel volume stored in the main tank as well as the amount necessary to continuously submerge the main tank fuel pumps during the entire mission.

Abstract translation: 公开了一种控制整个或部分位于机身轮廓中的飞行器主燃料箱中的燃料蒸汽的可燃性的方法。 该方法包括在所有正常操作期间在所述主油箱中保持液体燃料的燃料系统结构和燃料消耗顺序。 当燃料达到预定水平时，停止燃油从主油箱的撤出，从而限制燃油蒸汽消耗的体积和可燃性暴露时间。 一旦满足预定水平，燃油就从任务的其余部分的翼舱提供。 机舱油箱燃料开始消耗的预定主油箱燃料油位由存储在主油箱中的飞机储备燃料量以及整个任务期间连续淹没主油箱燃油泵所需的量决定。

公开(公告)号：USD198346S

公开(公告)日：1964-06-02

Applicant: The Cessna Aircraft Company

Designer： Donald J. Ahrens

公开(公告)号：US20170284856A1

公开(公告)日：2017-10-05

申请号：US15407903

申请日：2017-01-17

Applicant: Cessna Aircraft Company

Inventor： Steven G. Hagerott ,  Russell Peters

IPC: G01G19/07 ,  G01P15/00 ,  B64F5/60 ,  G01P13/02

CPC classification number: G01G19/07 ,  B64F5/60 ,  G01P5/16 ,  G01P13/025 ,  G01P15/00

Abstract: In an embodiment, a method for aircraft weight estimation is provided that includes determining a weight signal based on a dynamic pressure signal, a calibrated angle of attack signal, a lift coefficient signal, a load factor signal, and a wing surface area. In another embodiment, a method to estimate aircraft weight is provided that includes determining a weight based on historical flight data relating horizontal control surface position to dynamic pressure. In another embodiment, a system for continuously estimating aircraft weight during flight is provided that includes a pitot-static subsystem, an angle of attack indicator, an accelerometer, a controller configured to provide a weight signal, and a signal filter for filtering the weight signal to determine a stable aircraft weight.

公开(公告)号：US09672745B2

公开(公告)日：2017-06-06

申请号：US14643571

申请日：2015-03-10

Applicant: Cessna Aircraft Company

Inventor： Jeremy Joseph Kneuper ,  Isaac Wayne Stanfield ,  Jason Michael Decker

IPC: G08B23/00 ,  G08G5/00 ,  B64D43/00 ,  G01C23/00 ,  G06F3/0481 ,  G06F3/0484

CPC classification number: G08G5/0021 ,  B64D43/00 ,  G01C23/00 ,  G01C23/005 ,  G06F3/0481 ,  G06F3/04817 ,  G06F3/04847 ,  G08G5/0052

Abstract: Systems, methods and computer-storage media are provided for enhancing awareness in an aircraft using a touch-screen instrument panel. In one aspect, a warning is displayed peripherally in the panel in a way that attracts attention without interfering with the use of the panel for other purposes. In another aspect, a crew member is directed by highlighting through menus to a screen that enables the problem causing the warning to be corrected. In another aspect, parameters (e.g., temperatures, pressures) are displayed along with oriented graphical representations of system components. In yet another aspect, aircraft parameters are displayed in a historical context so that the user has a time-line context for a value at issue.

公开(公告)号：US09340275B2

公开(公告)日：2016-05-17

申请号：US14189692

申请日：2014-02-25

Applicant: Cessna Aircraft Company

Inventor： Daniel Jonathan Lyon ,  Joe Garland Skerbetz

IPC: B64C1/14

CPC classification number: B64C1/1492 ,  B64C1/1484

Abstract: A system and method for installing a window panel onto an aircraft including providing a retaining device having an outside edge that is sealed against an inboard surface of the aircraft. A biasing member mounted to an inside edge of the retaining device includes spring clips that press against the window panel. The spring clips push the window panel outward against the outside edge of the retaining device to maintain a seal around the edge of the window panel.

Abstract translation: 一种用于将窗板安装到飞机上的系统和方法，包括提供具有与飞机的内侧表面密封的外边缘的保持装置。 安装到保持装置的内边缘的偏置构件包括抵靠窗面板的弹簧夹。 弹簧夹将窗板向外压靠在保持装置的外边缘上，以保持围绕窗板边缘的密封。