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    • 5. 发明授权
    • Method for determining a currently obtainable climb gradient of an aircraft
    • 用于确定目前可获得的飞机爬升梯度的方法
    • US06691004B2
    • 2004-02-10
    • US09888705
    • 2001-06-25
    • Steven C. JohnsonHoward Glover
    • Steven C. JohnsonHoward Glover
    • G06F700
    • G08G5/0086G01C5/005G01C23/00G05D1/0676G08G5/045
    • A method for determining a currently obtainable climb gradient of an aircraft by determining an estimated aircraft weight as a function of phase of flight, determining the current aircraft weight as a function of the current dynamic pressure, the unaccelerated lift of the aircraft, and the wing surface area of the aircraft during steady-state flight, updating said estimated aircraft weight as a function of the current aircraft weight, determining the current lift and drag coefficients of the aircraft, determining currently available aircraft thrust, and estimating a currently obtainable maximum climb gradient as a function of said thrust, current weight, current lift and drag coefficients.
    • 一种用于通过确定作为飞行阶段的函数的估计的飞行器重量来确定当前可获得的飞行器爬升梯度的方法,根据当前动态压力确定当前飞机重量,飞行器的未加速升力和翼 在稳态飞行期间飞行器的表面积,作为当前飞机重量的函数更新所估计的飞机重量,确定当前飞行器的升力和阻力系数,确定当前可用的飞机推力,以及估计当前可获得的最大爬升梯度 作为所述推力,当前重量,当前升力和阻力系数的函数。
    • 6. 发明授权
    • Archery bow sight
    • US06634110B2
    • 2003-10-21
    • US09747482
    • 2000-12-20
    • Steven C. Johnson
    • Steven C. Johnson
    • F41G100
    • F41G1/467
    • A bow sight provides horizontal, vertical and at least one rotational adjustment mechanism which provides continuous movement of the sight ring without having to release a locking mechanism and still not allow unintentional movement of the sight ring. The sight has a plurality of sight pins having illuminated tips located at spaced-apart locations along a vertical sight line which extends across the sight ring. First adjustment mechanisms allow the sight pins to be rotated in order to set the location of the tips along the sight line and second adjustment mechanisms allow the sight pins to be moved along their longitudinal axes to align them with the sight line after they have been rotated. The sight also includes particular horizontal and vertical micro adjustment mechanisms which allow very small movements of the sight ring in the horizontal and vertical directions without having to release a locking mechanism.
    • 7. 发明授权
    • Ground proximity warning system, method and computer program product for controllably altering the base width of an alert envelope
    • 地面接近警告系统,方法和计算机程序产品,用于可控地改变警报信封的基座宽度
    • US06484071B1
    • 2002-11-19
    • US09496297
    • 2000-02-01
    • Kevin J ConnerSteven C. Johnson
    • Kevin J ConnerSteven C. Johnson
    • G08G504
    • G01C5/005
    • A ground proximity warning system, method and computer program product are provided that controllably alter the base width of the alert envelope in order to accommodate uncertainties associated with the current position of the aircraft. In one embodiment, the ground proximity warning system, method and computer program product controllably alter the base width of the alert envelope depending upon an error value, i.e., an uncertainty, associated with the current position of the aircraft. Since the error value associated with the current position of the aircraft is largely dependent upon the type of navigation equipment onboard the aircraft, the ground proximity warning system, method and computer program product of another embodiment controllably alter the base width of the alert envelope depending upon the type of navigation equipment that provides the current position of the aircraft.
    • 提供地面接近警报系统,方法和计算机程序产品,其可控制地改变警报信封的基本宽度,以便适应与飞行器的当前位置相关联的不确定性。 在一个实施例中,地面接近警告系统,方法和计算机程序产品根据与飞行器的当前位置相关联的误差值(即不确定性)可控地改变警报信封的基本宽度。 由于与飞机的当前位置相关联的误差值在很大程度上取决于飞机上的导航设备的类型,所以另一实施例的接地警报系统,方法和计算机程序产品可以根据情况可控地改变警报信封的基本宽度 提供飞机当前位置的导航设备的类型。
    • 8. 发明授权
    • Apparatus, methods, computer program products for generating a runway field clearance floor envelope about a selected runway
    • 装置,方法,计算机程序产品,用于产生关于所选跑道的跑道现场清除地面信封
    • US06445310B1
    • 2002-09-03
    • US09496298
    • 2000-02-01
    • C. Don BatemanSteven C. JohnsonScott GremmertYasuo Ishihara
    • C. Don BatemanSteven C. JohnsonScott GremmertYasuo Ishihara
    • G08B2300
    • G08G5/025G01C5/005G08G5/0078
    • The present invention provides apparatus, methods, and computer program products that monitor the altitude of an aircraft with respect to a selected runway. If the attitude of the aircraft is below a minimum glideslope with respect to the selected runway, the apparatus, methods, and computer program products of the present invention alert the flight crew, such that the altitude of the aircraft can be increased. This, in turn, increases time for reaction to abrupt changes in elevation near the selected runway. Specifically, the apparatus, methods, and computer program products of the present invention define a runway field clearance floor envelope about the selected runway that represents different preselected altitudes above the selected runway at respective distances from the selected runway. The apparatus, method, and computer program products of the present invention compare the altitude of the aircraft with respect to the selected runway to the runway field clearance floor envelope. If the altitude of the aircraft is less than the minimum altitude indicated for the aircraft at the given distance , the apparatus, method, and computer program products of the present invention provide an indication to the flight crew. Since the runway field clearance floor envelope is constructed relative to the runway by defining minimum altitude values that should be maintained relative to the elevation of the runway, the indications generated to the flight crew should provide a desired reaction time for the flight crew to adjust the aircraft to abrupt changes in elevation at or near a selected runway.
    • 本发明提供了相对于所选跑道监测飞机高度的装置,方法和计算机程序产品。 如果飞机的姿态相对于所选择的跑道低于最小滑坡,则本发明的装置,方法和计算机程序产品警告飞行机组人员,从而可以增加飞行器的高度。 这反过来又增加了在所选跑道附近的突然突然变化反应的时间。 具体来说,本发明的装置,方法和计算机程序产品在所选择的跑道的相应距离处定义围绕所选择的跑道的跑道野外距离地面信号,其表示选定跑道上方不同的预选高度。 本发明的装置,方法和计算机程序产品将飞机相对于所选跑道的高度与跑道野外间隙地面信封进行比较。 如果飞行器的高度小于在给定距离处为飞机指示的最小高度,则本发明的装置,方法和计算机程序产品向飞行机组提供指示。 由于通过定义相对于跑道高程应保持的最小高度值,相对于跑道构建跑道野外间隙地面信封,因此向飞行机组人员生成的指示应为飞行机组人员提供所需的反应时间 飞机在选定的跑道处或附近突然发生高度变化。
    • 10. 发明授权
    • Apparatus, methods, and computer program products for monitoring the attitude of an aircraft
    • 用于监控飞机姿态的装置,方法和计算机程序产品
    • US06341248B1
    • 2002-01-22
    • US09602611
    • 2000-06-22
    • Steven C. Johnson
    • Steven C. Johnson
    • G06G778
    • G05D1/0833
    • An apparatus, methods, and computer program products are provided for monitoring the attitude of an aircraft. The apparatus of the present invention includes a navigation system, such as a GPS, that provide values representing the velocity vector of the aircraft. Additionally, the apparatus includes two gyroscopes positioned with respect to the aircraft to sense the roll and pitch of the aircraft. A generator is connected to the navigation system and generates a calculated flight path and roll angle based on the velocity vector of the aircraft. Further, the apparatus of the present invention includes a combiner connected to both the generator and the gyroscopes. The combiner combines the calculated flight path angle to the sensed pitch angle and the calculated roll angle to the sensed roll angle and generates composite flight path and roll angles. The composite flight path and roll angles represent the attitude of the aircraft. In some embodiments, the apparatus combines either the composite flight angle or the composite roll angle with either the pitch or roll values generated by the aircraft's attitude indicator. If the difference between these corresponding values exceed a threshold, the apparatus provides an indication to the pilot that the aircraft's attitude indicator is malfunctioning. In another embodiment, the apparatus may compare the composite flight path and roll angle values to corresponding threshold values. If the composite path and roll angle values exceed these thresholds, the apparatus provides an indication to the pilot that the aircraft is at an unsafe attitude.
    • 提供了一种用于监视飞机姿态的装置,方法和计算机程序产品。 本发明的装置包括诸如GPS的导航系统,其提供表示飞行器的速度矢量的值。 此外,该装置包括相对于飞行器定位的两个陀螺仪,以感测飞行器的滚动和俯仰。 发电机连接到导航系统,并根据飞行器的速度矢量生成计算出的飞行路径和滚转角度。 此外,本发明的装置包括连接到发电机和陀螺仪两者的组合器。 组合器将计算的飞行路径角度与感测到的俯仰角和计算的滚动角度相结合,使其与感测到的滚动角度相结合,并产生复合飞行路线和滚动角度。 复合飞行路线和滚转角度代表飞机的姿态。 在一些实施例中,该装置将复合飞行角度或复合滚转角度与由飞行器姿态指示器产生的俯仰或滚动值组合。 如果这些对应值之间的差异超过阈值,则该装置向飞行员提供飞机姿态指示器发生故障的指示。 在另一个实施例中,装置可将复合飞行路径和侧倾角值与相应的阈值进行比较。 如果复合路径和侧倾角值超过这些阈值,则该装置向飞行员提供飞行员处于不安全姿态的指示。