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Efficient CRT-based residue-to-binary converter for the arbitrary moduli set

Science China(Information Sciences) 2011年第1期54卷 70-78页

作者： CHEN JianWen & YAO RuoHe School of Electronic and Information Engineering,South China University of Technology, Guangzhou 510640,China School of Electronic and Information Engineering South China University of Technology Guangzhou China

The conversion from residue to weighted binary representation plays an important role in the residue number *** on Chinese Remainder Theorem,a new residue-to-binary converter using arbitrary moduli set is *** new converter uses the difference-correction algorithm for the conversion output and eliminates the modulo M operation,where M is the dynamic range of the residue number *** sizes of the multipliers and modular multipliers in the new converter are small,thereby reducing the area and delay of the proposed *** and synthesis results indicate that the new converter is more area-time effcient than the published converters based on Chinese Remainder Theorem.

关键词： RNS Chinese Remainder Theorem difference correction modular arithmetic residue-to-binary arbitrary moduli set

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The Orbit Maneuvers for Spacecraft reentry with Full Parameters

The Orbit Maneuvers for Spacecraft reentry with Full Paramet...

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第37届中国控制会议

作者： Gefei Li Chuanling Ma Jun Song Hua Yan Beijing Aerospace Control Centre

In order to send the spacecraft to return to the schedule d placement accurately in accordance with the nomina l trajectory, three orbital maneuvers can control the spacecraft to the nomina l reentry point w ith fully-parametric pos ition and veloc ity including six reentry-point parameters of height, longitude, latitude, ve loc ity va lue, ve loc ity inc lination, ve loc ity azimuth to meet requireme nts. Three orbit maneuvers are non-redundant accurate reentry trajectory controls to achie ve the reentry point with fully-parametric pos ition and ve loc ity. Affected with orbit perturbation model error, orbit determination error, orbit control error, etc. the reentry-point status will deviate from the theory status after a longer flight. Moreover, w ith the imple mentation of orbit maneuvers one by one, orbit maneuver progra mming variables decrease. Under the conditions of the various errors a nd the orbit maneuver variables reducing, to solve the technica l proble ms of the spacecraft landing at the predetermine d placement with the multi-parameter optimization reentry point, the fully-parametric reentry trajectory contro l strategy need to be adjuste d dynamica lly. This paper designs three orbital maneuvers control mode ls and a lgorithms to achie ve spacecraft accurate reentry point with fully-parametric pos ition and ve loc ity. For the reentry point of fully-parametric pos ition and ve loc ity objective requirements, the re lationships of the maneuver programming varia bles in match w ith the objective reentry point parameters are establis hed, and the orbit mane uve r initia l values are solved for the reentry pos ition vector and veloc ity vector independe ntly. A gradua l orbit ma neuver progra mming strategy is establis hed w ith the ma in constra int to the veloc ity vector, the supplement constra int to the pos ition vector. The performance indicators are des igned to solve globa l optimization and local optimization solution, and differentia l correcti

关键词： Orbit maneuver Ful-parametric reentry difference correction Land point Reentry point

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