Earth oriented satellite and process for controlling the position, nutation and spin

• US 5,957,410 A
• Filed: 06/05/1996
• Issued: 09/28/1999
• Est. Priority Date: 06/09/1995
• Status: Expired due to Fees

• Current Assignee: Daimler-Benz Aerospace AG (Mercedes-Benz Group AG)
• Original Assignee: Daimler-Benz Aerospace AG (Mercedes-Benz Group AG)
• Inventors: Fichter, Walter, Bruederle, Ernst, Surauer, Michael
• Primary Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/658,264
• Time in Patent Office: 1,210 Days
• Field of Search: 244/164, 244/166, 244/170, 244/168, 244/173
• US Class Current: 244/166
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/281 Spin-stabilised spacecraft
• CPC Class Codes: B64G 1/32 using earth's magnetic field
• CPC Class Codes: B64G 1/365 using horizon or Earth sensors

Abstract

A low earth orbiting satellite control arrangement according to the invention has an earth sensor for measuring roll and pitch of the satellite relative to an earth oriented moving reference system, a spin wheel mounted along an axis perpendicular to the orbital plane of the satellite for measuring spin of the satellite, and two magnet coils for generating control. A first of the two magnet coils is aligned substantially in parallel to a roll axis of the satellite, and the second is aligned substantially parallel to the yaw axis. Alternative control algorithms are disclosed for controlling attitude, nutation and spin of the satellite based on information from the earth sensor, spin wheel and an observer which is also mounted on the satellite.

Claims

1. Process for controlling attitude, nutation and momentum of a satellite orbiting in a low earth orbit, with a medium inclination in an earth oriented alignment, said satellite being of the type having an earth sensor for measuring in two axes;

a spin wheel having an axis of rotation oriented in parallel to a pitch axis of the satellite and two magnet coils for generating control moments, a first one of the two magnet coils being aligned substantially in parallel to a roll axis of the satellite and a second one of the two magnet coils being aligned substantially in parallel to a yaw axis of the satellite, said process comprising at least one of the steps of;

controlling attitude and nutation of said satellite by activating said magnet coils based on a linear control algorithm which in the case of attitude control is a function of a roll angle measured by the earth sensor and of a yaw angle estimated by means of an observer or measured by an additional sensor on said satellite and, in the case of nutation control, a function of a roll angle chance determined by earth sensor measurements and a yaw angle chance estimated by the observer or measured by an additional sensor; and

controlling wheel spin by activation of at least said first magnet coil, as a function of a deviation from a desired value for spin, and of a yaw component of th earth'"'"'s magnetic field based on PI feedback control;

wherein said linear control algorithm for attitude control is given by ##EQU31## m_x.sup.(h), m.sup.(h) being the magnetic moments to be generated by the roll and yaw axis magnet coils;

h_0x, h_0z being the roll and yaw components of the satellite spin vector, respectively, related to the yaw and roll angles, φ and

Φ

respectively, by the equations h_0x =φ

h_w and h_0z =-φ

h_w, h_w being the magnitude of the wheel spin vector; and

K_ij.sup.(h) being amplification parameters.

2. Process for controlling attitude, nutation and momentum of a satellite orbiting in a low earth orbit, with a medium inclination in an earth oriented alignment, said satellite being of the type having an earth sensor for measuring in two axes;

a spin wheel having an axis of rotation oriented in parallel to a pitch axis of the satellite and two magnet coils for generating control moments, a first one of the two magnet coils being aligned substantially in parallel to a roll axis of the satellite and a second one of the two magnet coils being aligned substantially in parallel to a yaw axis of the satellite, said process comprising at least one of the steps of;

controlling attitude and nutation of said satellite by activating said magnet coils based on a linear control algorithm which in the case of attitude control is a function of a roll angle measured by the earth sensor and of a yaw angle estimated by means of an observer or measured by an additional sensor on said satellite and, in the case of nutation control, a function of a roll angle change determined by earth sensor measurements and a yaw angle change estimated by the observer or measured by an additional sensor; and

controlling wheel spin by activation of at least said first magnet coil, as a function of a deviation from a desired value for spin, and of a yaw component of the earth'"'"'s magnetic field based on PI feedback control;

wherein said linear control algorithm for nutation control is given by ##EQU32## m_x.sup.(w), m_x.sup.(w) being the magnetic moments to be generated by the roll and yaw axis magnet coils;

w_x and w_z being the roll and yaw components of the satellite'"'"'s inertial roting speed vector; and

K_ij.sup.(w) being amplification parameters.

3. Process for controlling attitude, nutation and momentum of a satellite which orbits in a low earth orbit, with a median inclination, said satellite being of the type having an earth sensor for measuring in two axes, a spin wheel having an axis of rotation oriented in parallel to a pitch axis of the satellite, and two magnet coils which are aligned substantially in parallel to the rolling and pitching axis respectively, said process comprising at least one of the steps of:

controlling attitude and momentum of said satellite by activating both of said magnet coils based on a combined linear control algorithm which is a function of a rolling angle of the satellite measured by the earth sensor, a yaw angle estimated by an observer on said satellite and a deviation of the spin from a desired value, the latter being acted upon by a PI-element; and

controlling nutation of the satellite by activating at least one of said magnet coils which is aligned in parallel to the pitch axis using a linear control algorithm which is a function of a change of a roll angle of the satellite determined on the basis of earth sensor measurements, and of a yaw angle change estimated by said observer.