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    • 3. 发明专利
    • LOOP PHASE CONJUGATE MIRROR FOR UNPOLARIZED BEAM
    • JPH10232417A
    • 1998-09-02
    • JP29871397
    • 1997-10-30
    • HUGHES AIRCRAFT CO
    • BETIN ALEXANDER AMANGIR METIN S
    • G02F1/35H01S3/083H01S3/10H01S3/108
    • PROBLEM TO BE SOLVED: To use a unpolarized beam of signal by providing a polarization splitting device for splitting a beam of signal into orthogonal polarization components and a polarization mixer for mixing energy from the orthogonally polarized light components. SOLUTION: Polarized light splitting device 10 splits a beam of signal ε1 into two orthogonally polarized light components ε11 and ε12 and guides them to a nonlinear medium 12. Relay optical systems 14, 16 guide loop beam components ε21 , ε22 appearing from a nonlinear medium 12 so as to return them to the nonlinear medium 12, and these optically interfere the signal beam components ε11 , ε12 in the nonlinear medium 12 for forming a refractive index grating 18. A polarized light mixer 19 mixes energy from the orthogonally polarized light loop components ε21 , ε22 . An oscillation beam ε3 with orthogonally polarized light components ε31 , ε32 is grown up from optical noises of resonance/loop, and oscillates in an opposite direction to the propagation of the loop beam components ε21 , ε22 due to irreversible losses introduced by an optical diode 20.
    • 7. 发明专利
    • SATELLITE POSITION ESTIMATION PROCESS DETERMINATION SYSTEM USING GAS TRACKING TECHNIQUE
    • JPH1073651A
    • 1998-03-17
    • JP12600097
    • 1997-05-15
    • HUGHES AIRCRAFT CO
    • MALLA RAJENDRA P
    • G01C15/00G01S1/00G01S19/48G01S5/14G01S5/02
    • PROBLEM TO BE SOLVED: To determine the position estimation process of a middle and high orbit satellite exactly, in real time and autonomically by sending information of position estimation process concerning the earth and time with a plurality of arranged transmitters by means of communication processing through the satellite. SOLUTION: A geostationary earth orbit(GEO) satellite 12 loading a GPS flying receiver receives GPS signals leaked from the edge of the earth with GPS satellites 14 and 16. It also receives GPS-like signals from pseudosatellites 18, 20, 22 and 24 tactically arranged on the earth surface 30. Each pseudosatellite is on the coordinate position recognized with high accuracy for reference to frame of the earth, and even in the case this exact coordinate is useful for the correction of exact orbit of the GEO satellite 12 even in the case that a deciphering module can not be used. Therefore, owing to the tactical arrangement of each pseudosatellite, the GEO satellite 12 can perform autonomic flight orbit determination and the like with high accuracy. In this manner, by using one or more GPS pseudosatellites and GPS satellite transmitters, the position estimation process of middle and high altitude orbit satellite can be determined exactly, in real time and autonomically.