公开(公告)号：WO1996026108A1

公开(公告)日：1996-08-29

申请号：PCT/FR1996000278

申请日：1996-02-21

申请人： CENTRE NATIONAL D'ETUDES SPATIALES ,  DELEPIERRE-MASSUE, Olivier ,  FEVRIER, Claude ,  SALOME, Roland ,  LE TORRIVELLEC, Pierre

发明人： CENTRE NATIONAL D'ETUDES SPATIALES

IPC分类号： B64G01/42

CPC分类号： G01F22/02 ,  B64G1/007 ,  B64G1/26 ,  B64G1/402 ,  G01F23/14

摘要： A device for pressurising a unified two-liquid propulsion subsystem for geostationary satellites, including a high-pressure helium storage assembly (10) comprising at least one helium storage tank, a control assembly (11) and an assembly for pressurising propellant tanks (17, 18) interconnected through a pressurising circuit. The control assembly is an electronic control assembly including at least one solenoid valve (51) arranged at one point in the pressurising circuit and controlled by a processing and control circuit (54) receiving data from pressure sensors (43, 47, 48) for the various tanks. Said processing and control circuit enables the propellant tanks (17, 18) to be pressurised at a constant pressure during the satellite transition and position-fixing process, while enabling the amount of residual propellants to be measured during the orbital operating time of the satellite.

摘要翻译： 一种用于加压用于对地静止卫星的统一的双液体推进子系统的装置，包括包括至少一个氦储存罐的高压氦存储组件（10），控制组件（11）和用于对推进剂罐（17， 18）通过加压电路互连。 控制组件是电子控制组件，其包括布置在加压电路中的一个点处的至少一个电磁阀（51），并由加工和控制电路（54）控制，该处理和控制电路从压力传感器（43,47,48）接收数据， 各种坦克 所述处理和控制电路使得能够在卫星转换和定位过程期间以恒定压力对推进剂罐（17,18）进行加压，同时能够在卫星的轨道运行时间期间测量剩余推进剂的量。

公开(公告)号：WO1994015834A1

公开(公告)日：1994-07-21

申请号：PCT/US1993011758

申请日：1993-12-03

申请人： HUGHES AIRCRAFT COMPANY

发明人： HUGHES AIRCRAFT COMPANY ,  AHRENS, Allan, F. ,  ROSEN, Harold, A.

IPC分类号： B64G01/42

CPC分类号： B64G1/443 ,  B64G1/428 ,  H02J7/35 ,  Y10S136/292 ,  Y10S136/293 ,  Y10S320/33 ,  Y10S323/906

摘要： A spacecraft power bus regulation method and apparatus for a spacecraft. The spacecraft has solar arrays (10) and a battery (30) coupled to the spacecraft power bus (32) to drive electrical loads (34). A bus voltage limiter (38) controls the flow of current from the solar arrays while a bidirectional battery controller (36) controls power flow into and out of the battery. A processor (46) monitors current flow and battery condition using sensors (40, 42, 44, 48) and controls the bus voltage limiter accordingly. Auxiliary control is provided by the solar array drive (24) which controls the orientation of the solar arrays with respect to the sun.

摘要翻译： 航天器电力总线调节方法和装置。 航天器具有太阳能阵列（10）和耦合到航天器电力总线（32）以驱动电力负载（34）的电池（30）。 当双向电池控制器（36）控制电流进出电池时，总线限制器（38）控制来自太阳能电池阵列的电流流动。 处理器（46）使用传感器（40,42,44,48）监视电流和电池状况，并且相应地控制总线电压限制器。 辅助控制由太阳能阵列驱动器（24）提供，太阳能阵列驱动器控制太阳能阵列相对于太阳的取向。