Disclosed is a flywheel controlled sun capturing and sun orientation method by using star sensor information. The method comprises the following steps that 1, measured information qbi of a start sensor and direction qsi of sun in an inertial system are used to calculate sun vector coordinate system quaternion qsd conveted from a vector coordinate system d in a satellite star body; 2, characteristics of the sun vector coordinate system quaternion qsd conveted from the vector coordinate system d, maximum angular velocity Omega max of the attitude maneuver and flywheel output torque Mm are used to calculate parameter Phi, and an attitude maneuver path is planned according to the parameter Phi; and 3, a control law is designed according to the attitude maneuver path planned in the step 2, andthe control quantity is allocated to a flywheel group to control a satellite to realize sun orientation of a vector d. The flywheel controlled sun capturing and sun orientation method is a supplementorientation mean of sun orientation by using a sun sensor, a system is simple and reliable, the sun orientation function in a shadow area can be implemented, and the defect that the sun sensor cannotbe continuously oriented is remedied.

Flywheel controlled sun capturing and sun orientation method by using star sensor information

The invention relates to an automatic sunshine avoiding method for a space to ground observation apparatus, belongs to the space weather monitoring technology field and solves problems of complexity and poor timeliness existing in a ground intervention sunshine avoiding method in the prior art The method comprises steps that a sun vector of a track coordinate system is converted to a sun vector S2 of an apparatus coordinate system through a conversion matrix T1 from the track coordinate system to a satellite coordinate system and a calibration conversion matrix T2 from the satellite coordinate system to the apparatus coordinate system, an included angle alpha=asin(s2x) of the sun vector S2 and a YcZc surface of the apparatus coordinate system is calculated, an included angle of the YcZc surface and an apparatus optical axis is made to be beta, an included angle of sunlight and the apparatus optical axis on an XcZc surface is gamma=alpha-beta(south pole) or gamma=beta-alpha(north pole), according to sunshine avoiding determination conditions, whether sunshine avoiding is needed is determined, if yes, an apparatus is controlled for rotation in an opposite direction, if not, the apparatus rotates in an original direction The sunshine avoiding method is advantaged in that system safety is effectively improved, automatic in-orbit measurement is carried out, and the method further has properties of strong timeliness, low cost and easy realization

Automatic sunshine avoiding method for space to ground observation apparatus

The invention discloses a satellite steady sun-facing orientation method taking earth pointing deviation as constraint, and belongs to the technical field of spacecraft attitude control. The stable sun-facing orientation method comprises the following two steps: establishing an expected attitude of a satellite by two steps: firstly, establishing an intermediate attitude of the satellite on the basis of a satellite-geocentric connecting line direction, a satellite orbital plane normal direction and a satellite advancing direction; and then rotating the middle attitude around an Euler axis for acertain angle to reduce the sun pointing deviation of the satellite and ensure that the included angle between the expected earth axis and the earth center direction is not greater than the constraint angle. The expected attitude of the satellite obtained according to the strategy can keep stable change, the singular phenomenon that the expected attitude of the satellite violently changes in a short time under the sun-earth-satellite collinear condition caused by a traditional strategy is avoided, and therefore peak energy consumption in the sun-oriented process of the satellite is greatly reduced.

Satellite steady sun-facing orientation method taking earth pointing deviation as constraint

The invention discloses an all-attitude top-free geosynchronous communication link establishment method of a Mars surrounder. The method comprises the steps that the surrounder captures the sun and the Mars to obtain a surrounder-sun vector and a surrounder-Mars vector; the surrounder determines a current attitude of the surrounder according to the surrounder-sun vector and a surrounder-Mars vector and performs maneuvering control, so that the surrounder makes the installing direction of a geosynchronous-communication directive antenna point to the earth and establishes a geosynchronous communication link. The sun is captured by simulating a sun angle meter, the Mars is captured by simulating an infrared navigation sensor, the surrounder-sun vector and the surrounder-Mars vector are obtained, and attitude control is performed to establish a geosynchronous communication link. The all-attitude top-free geosynchronous communication link establishment method of the Mars surrounder breaks through the working mode that the Mars surrounder still depends on a top after attitude abnormity, so that the all-attitude geosynchronous direction reliability of the Mars surrounder is improved.

Mars surrounder and all-attitude top-free geosynchronous communication link establishment method of Mars surrounder

The invention discloses a coordinate transformation method based on flattening angle compensation The coordinate transformation method comprises the following steps: assuming that the position and velocity of a current earth-rectangular coordinate of an aircraft are determined, acquiring the geological longitude and latitude of the current position of the aircraft through an iterative method for transforming the earth-rectangular coordinate into a geodetic coordinate system, then calculating a transformation relationship between a local geocentric latitude A and a local geographical latitude B', and calculating an earth flattening angle C; judging a current latitude area zdg(i), and determining a compensation rule according to the latitude area; comprehensively judging a threshold restraining way according to the trends of an iteration latitude B'(i) and C(i); lastly, implementing non-orthogonal vector transformation by using a quaternion relationship According to the coordinate transformation method based on the flattening angle compensation, accurate coordinate transformation can be realized by using pneumatic attitude information in the absence of tracking information and local horizontal information in an aircraft flight, and the antenna communication orientation accuracy is increased

Coordinate transformation method based on flattening angle compensation

The invention discloses a three-axis sun-oriented control method of a satellite for a guaranteeing satellite-earth link. The three-axis sun-oriented control method comprises the following steps: solving a projection of a sun vector under a satellite orbit coordinate system according to the sun vector calculated according to a satellite orbit; establishing a sun-oriented reference coordinate system according to the satellite orbit and the definition of the satellite polarity, and calculating an attitude quaternion of the sun-oriented reference coordinate system relative to the satellite orbit coordinate system; calculating an error quaternion between an attitude quaternion of a star relative to the satellite orbit coordinate system and the attitude quaternion of the sun-oriented reference coordinate system relative to the satellite orbit coordinate system; carrying out attitude reference tracking according to a symbol of the error quaternion; and when continuously meeting that the error quaternion is smaller than a preset threshold value, establishing a star sensor sun-oriented sign, carrying out three-axis stabilization sun-oriented control by virtue of a star sensor, and otherwise, continuing to carry out two-axis sun-oriented control based on sun sensor. By virtue of the three-axis sun-oriented control method, the smoothness of the satellite-earth link after the sun orientation of a sailboard can be guaranteed, and a near-optimal maneuvering path is guaranteed when a sun-oriented maneuvering manner is changed into a ground-oriented maneuvering manner.

Three-axis sun-oriented control method of satellite for guaranteeing satellite-earth link

The invention discloses a method for improving the operation multiple of an all-digital satellite attitude and orbit control software operation platform. A read operation step includes: outputting a target reading address to an address line, and reading a signal setting; after it is detected that the read signal is set, completing address decoding immediately, and outputting a chip selection signal; after the read signal is detected, completing address line latching, and sending data in the target address to the data line; informing the CPU of taking the data after the fixed time. The write operation step comprises the steps of outputting a target write-in address to an address line, outputting target write-in data to a data line, and meanwhile, setting a write signal; after it is detectedthat the write signal is set, completing address decoding immediately, and outputting a chip selection signal; after a writing signal is detected, completing latching of the address line and the dataline, and completing writing operation according to data of the data line and the address line; and informing the CPU of writing data after the fixed time. The method ensures high efficiency and accuracy of system operation, and has the capability of further improving the operation efficiency of the all-digital platform.

Method for improving operation multiple of all-digital satellite attitude and orbit control software operation platform

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Three-axis sun-oriented control method of satellite for guaranteeing satellite-earth link

Method for improving operation multiple of all-digital satellite attitude and orbit control software operation platform