METHOD OF ORIENTING SPACECRAFT PURPOSE-DESIGNED HARDWARE AND DEVICE TO THIS END Russian patent published in 2011 - IPC B64G1/24 B64G1/22 

FIELD: transport.

SUBSTANCE: invention relates to orientation of spacecraft and its purpose-designed hardware. Both proposed method and device rules out inertial masses (rotors, flywheels) traditionally used in inertial actuators and incorporate them with structural components of spacecraft with maintenance systems. Note here that purpose-designed hardware is suspended to spacecraft structural components. Drives of said actuators and angle transducers are arranged on axes of suspension to move there along. Structural components are moved from the centre of mass of spacecraft and from the centre of purpose-designed hardware suspension. Then both said centres are aligned. Thus, maximum moments of inertia of said structural components are created and spacecraft lengthwise axis is located in position of stable equilibrium (along local vertical). Accumulated kinetic moment is defined from parametres of angular motion of purpose-designed hardware and spacecraft structural elements. Control signals are generated for inertial mass drives and kinetic moment reset system to allow required variation of aforesaid parametres of angular motion. Proposed device, for example, strapdown inertial control system comprises kinetic moment reset system. Computer and angular speed transducers connected thereto. There are also the drive of spacecraft structural elements with aforesaid suspension accommodating purpose-designed hardware moving relative to said structural elements, angle transducers and drives of inertial actuators.

EFFECT: reduced weight and power consumption, higher accuracy and speed of orientation.

2 cl, 2 dwg