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    • 5. 发明申请
    • METHOD FOR FIXED PATTERN NOISE (FPN) CORRECTION
    • 固定模式噪声(FPN)校正方法
    • WO2009137037A1
    • 2009-11-12
    • PCT/US2009/002773
    • 2009-05-05
    • ALTASENS, INC.RICHARDSON, John
    • RICHARDSON, John
    • H04N5/217
    • H04N5/361H04N5/335H04N5/3658
    • A method for correcting column Fixed Pattern Noise (FPN) in an image sensor offers a compromise between speed and precision for calculating column FPN offsets The present correction technique is digital, and is applied after the pixel signal voltages have been digitized by an ADC. A first Optical Black (OB) pixel is sampled and compared to a target level. An offset is stored, and an appropriate push-size is determined. Additional OB pixels are sampled and the offset is applied. The pushsize is increased or decreased depending upon whether the pixel signal with the applied offset is above or below a target value. This new offset value is written to memory, and the push-size is reduced, and the process is repeated until the last OB pixel has been processed. The resulting offset is applied to the signal pixels in a column.
    • 用于校正图像传感器中的列固定模式噪声(FPN)的方法提供用于计算列FPN偏移的速度和精度之间的折衷。本校正技术是数字的,并且在像素信号电压被ADC数字化之后被应用。 对第一个光学黑(OB)像素进行采样并与目标电平进行比较。 存储偏移量,并确定适当的推送尺寸。 对其他OB像素进行采样,并应用偏移。 根据所施加的偏移的像素信号是否高于或低于目标值,推送尺寸被增加或减小。 这个新的偏移值被写入存储器,并且推式尺寸减小,并且重复该过程,直到最后一个OB像素被处理。 所产生的偏移量应用于列中的信号像素。
    • 7. 发明申请
    • SYSTEM AND METHOD FOR COOLING AN AIRCRAFT WING
    • 用于冷却飞机的系统和方法
    • WO2013079100A1
    • 2013-06-06
    • PCT/EP2011/071318
    • 2011-11-29
    • SHORT BROTHERS PLCRICHARDSON, John
    • RICHARDSON, John
    • B64D13/06B64D27/26B64D29/02B64D33/00
    • B64D13/006B64C7/02B64D15/04B64D29/02B64D2033/0233
    • An aircraft comprises a turbine engine (104) suspended from a wing (102) by means of a pylon (105). Compressed hot air is bled off from the turbine engine (104). A bleed air duct (209) in the wing (102) conveys the compressed hot air towards a fuselage. In order to prevent overheating of aircraft parts that are relatively close to the bleed air duct (209), the following solution is proposed. The pylon (105) comprises an opening (302) with a covering structure (303) projecting into a bypass exhaust flow (213) from the turbine engine (104). The covering structure (303) leaves a slit (304) facing away from the bypass exhaust flow (213). An airflow path (305) extends from openings (211) in the wing (102) to the slit (304) left by the covering structure (303).
    • 飞机包括借助于塔架(105)从翼(102)悬挂的涡轮发动机(104)。 压缩的热空气从涡轮发动机(104)排出。 机翼(102)中的排气导管(209)将压缩的热空气传送到机身。 为了防止比较靠近排气管道(209)的飞机部件过热,提出了以下解决方案。 塔架(105)包括具有从涡轮发动机(104)突出到旁路排气流(213)中的覆盖结构(303)的开口(302)。 覆盖结构(303)离开面向旁路排气流(213)的狭缝(304)。 气流路径(305)从机翼(102)中的开口(211)延伸到由覆盖结构(303)留下的狭缝(304)。