Correction of uncommanded mode changes in a spacecraft subsystem

• US 5,822,515 A
• Filed: 02/10/1997
• Issued: 10/13/1998
• Est. Priority Date: 02/10/1997
• Status: Expired due to Term

• Current Assignee: Space Systems/Loral Incorporated (Loral Space and Communications Incorporated)
• Original Assignee: Space Systems/Loral Incorporated (Loral Space and Communications Incorporated)
• Inventors: Baylocq, Michel B.
• Primary Examiner(s): Beausoliel, Jr., Robert W.
• Assistant Examiner(s): VALES, PHILLIP
• Application Number:
  US08/797,878
• Time in Patent Office: 610 Days
• Field of Search: 395/185.08, 395/185.09, 371/61, 371/62, 371/69.1, 342/354, 342/355, 244/164, 244/165, 244/166, 244/167, 244/168, 244/169, 244/170, 244/171, 701/3, 701/4, 701/5, 701/6, 701/7, 701/8, 701/9, 701/10, 701/11, 701/12, 701/13
• US Class Current: 714/56
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: B64G 1/365 using horizon or Earth sensors
• CPC Class Codes: B64G 1/546 shielding electronic equipment
• CPC Class Codes: G01S 3/7868 using horizon sensors

Abstract

In a spacecraft having devices which are operative in plural modes, particularly an earth sensor operative in a north hemispherical inhibit mode, a south hemispherical inhibit mode, and a normal mode, a watchdog circuit* is employed to detect the presence of a mode command issued to the device. The command may be issued by a station on the earth, and communicated via a telemetry link to the spacecraft. The watchdog circuit may be part of a central processing unit (CPU) with a computer on board the spacecraft, the computer serving to perform various data processing operations for the mission of the spacecraft. The watchdog circuit stores the mode command and then repeats the command during a succession of repetitions. Thereby, in the event that the device, particularly the earth sensor, is momentarily disabled by an electrostatic discharge (ESD) event, wherein digital control circuitry of the earth sensor may shift the sensor to a different mode of operation, the next repetition of the mode command from the watchdog circuit reinstates the desired mode of operation. The watchdog circuit and the CPU are radiation hardened and may be enclosed by a Faraday shield to render them substantially impervious to the radiation.

Claims

1. In a spacecraft having a central processing unit (CPU) and a device, the CPU being hardened against radiation encountered by the spacecraft during a traveling of the spacecraft in space, the device being operative in any one of a plurality of modes, the device being subject to disruption from electrostatic discharge (ESD) of the radiation, the disruption being manifested by a switching from one of said modes of operation to a second of said modes of operation, a system for operating the device comprising:

means for communicating a signal having a mode command to said device;

means coupled to said communicating means for storing said mode command; and

means coupled to said storing means for repetitively applying said mode command to said device for reestablishing a desired operating mode in the event of an occurrence of the disruption.

2. A system according to claim 1 wherein said spacecraft has a Faraday shield enclosing said CPU, said device is a sensor disposed outside of said Faraday shield, said communicating means includes telemetry means for transmitting the mode command signal from a location distant from the spacecraft to the spacecraft, and said means for repetitively applying the mode command is located on the spacecraft within said Faraday shield.

3. A system according to claim 2 wherein said device is an earth sensor having a mode of inhibited north hemispherical scanning and a mode of inhibited south hemispherical scanning and a mode of concurrent scanning in both the north and the south hemispherical scannings, and said location distant from the spacecraft is on the earth.

4. A system according to claim 3 wherein said means for repetitively applying the mode command includes a watchdog circuit, said watchdog circuit having means for detecting a presence of the mode command signal among a plurality of other signals transmitted by said telemetry means.

6. A method according to claim 1 wherein said device is on board a spacecraft, said source of command is located remote from the spacecraft, said monitor comprises electrical detection circuitry, and said determining step is performed electrically by detection of a presence of a mode command.

7. A method according to claim 6 wherein said device includes electrical circuitry for establishing a mode of operation in said device, said disruption is a radiation or electrostatic discharge event, and said employing step is accomplished by electrically storing a sample of said command in a radiation hardened memory, and repetitively reading out the command sample from the memory.

5. A method for correcting a selection of operating mode of a device for which mode selection has been interrupted by a disruption, comprising the steps of:

determining by a monitor located relatively close to the device that an operating mode for the device has been selected by command from a source of command located relatively distant from the device; and

employing the monitor to reissue repetitively the command to the device for continual operation of the device within a selected mode of operation over an interval of time including a possible occurrence of the disruption.