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    • 7. 发明授权
    • Adaptive notch filter for FM interference cancellation
    • 用于FM干扰消除的自适应陷波滤波器
    • US5307517A
    • 1994-04-26
    • US778501
    • 1991-10-17
    • David A. Rich
    • David A. Rich
    • H04B1/10H04B1/12
    • H04B1/1036H04B1/123H04B2001/1063
    • An improved adaptive notch filter for removing undesired cochannel FM interference includes in-phase and quadrature signal processing paths in which the undesired FM signal is translated to zero frequency, i.e. to DC. In each of the in-phase and quadrature phase signal paths, a first multiplier translates the input frequency spectrum in a dynamic manner so that the frequency of the undesired FM signal is always centered on DC. The undesired signal, now at DC, is filtered out by a high pass filter with a sharp rolloff. The output of the high pass filter is remultiplied in a second multiplier to translate the desired FM signal back to the original position in the frequency spectrum. In order to eliminate an unwanted difference frequency remodulation signal at the output of the second multiplier, the quadrature phase signal path performs a parallel operation on the same input signal, but with a quadrature phase (90 degree phase shift) control signal. The output the in-phase and quadrature signal processing circuits are combined in an adder circuit to cancel the unwanted difference frequency remodulation signal.
    • 用于去除不期望的同频道FM干扰的改进的自适应陷波滤波器包括同步和正交信号处理路径,其中不期望的FM信号被转换为零频率,即到DC。 在每个同相和正交相位信号路径中,第一乘法器以动态方式转换输入频谱,使得不期望的FM信号的频率始终以DC为中心。 现在处于DC状态的不需要的信号通过高通滤波器被过滤掉,具有清晰的滚降。 高通滤波器的输出在第二乘法器中重新乘法,以将期望的FM信号转换回到频谱中的原始位置。 为了消除第二乘法器的输出端的不希望的差分再生信号,正交相位信号路径对相同的输入信号进行并行运算,但是以正交相位(90度相移)控制信号。 将同相和正交信号处理电路的输出组合在加法器电路中以消除不想要的差分再生信号。
    • 9. 发明专利
    • Improvements in and relating to Gas Turbine Engines
    • GB1151177A
    • 1969-05-07
    • GB3048667
    • 1967-07-03
    • RICH DAVID
    • RICH DAVID
    • F02C7/18F02K3/077
    • 1,151,177. Cooling gas turbine engines. D. RICH. July 3, 1967 [July 5, 1966; Jan. 3, 1967], No.30486/67. Headings F1G, F1J and F1T. In a gas turbine engine a by-pass duct 28 for cooling air is provided downstream of the lowpressure axial-flow compressor 18 and inward of the high-pressure axial-flow compressor 46, the combustion chamber 26 and the turbine 56. The compressor and turbine blades are secured to the housing 20 mounted on the axial engine shaft 21 rotatable in the nose cap 16 and the tail bullet 62. A by-pass duct 22 may be provided outward of the high-pressure compressor, the combustion chamber and turbine. Turbine cooling air is supplied by the high-pressure compressor 46 through a duct 24a inward of the combustion chamber 26. A turbine cooling duct (33, Fig.6, not shown), may be provided outward of the combustion chamber. Air-flow through the turbine cooling ducts may be controlled to provide little or no flow at reduced engine power. The axial engine shaft (21', Figs.4 and 8, not shown), may extend forward of the nose cap (16') for attachment to a power take-off device, e.g. a propeller.