Настройки

Укажите год
-

Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

Подробнее
-

Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

Подробнее

Форма поиска

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Укажите год
Укажите год
Применить Всего найдено 12. Отображено 12.
10-04-2013 дата публикации

Control method for hierarchical saturation PID (Proportion Integration Differentiation) controller based on integral separation

Номер: CN103034121A
Автор: Sun Zhaowei, Yang Yungang, Wang Feng, Cao Xibin, Pan Xiaotong, Li Dongbai, Pang Bo, Li Taiping, Ning Mingfeng, Yue Chengfei
Принадлежит:

A control method for a hierarchical saturation PID (Proportion Integration Differentiation) controller based on integral separation relates to a control method for a hierarchical saturation PID controller, and solves the problem of larger system overshoot and even system oscillation caused by calculated control quantity far more than limit control quantity which corresponds to the maximal output capacity of an execution mechanism due to the integral accumulation of PID operation, wherein the integral accumulation of the PID operation is caused by the hierarchical saturation PID controller added in an integral item. The method comprises the following steps: a deviation vector e is calculated according to a real-time online quaternion Q and a target quaternion Qc; an angular velocity restraint coefficient Li is calculated according to the maximal star control acceleration ai, the maximal rotating angular velocity |Omega i|max and the deviation vector e obtained in the step 1, and an integral ...

Подробнее
Номер записи: 1
08-05-2013 дата публикации

Spacecraft high-accuracy speediness attitude maneuver method based on single gimbal control moment gyro (SGCMG) and reaction wheel (RW)

Номер: CN103092208A
Автор: Sun Zhaowei, Yang Yungang, Wang Feng, Cao Xibin, Pan Xiaotong, Li Dongbai, Pang Bo, Li Taiping, Ning Mingfeng, Yue Chengfei, Yuan Qin
Принадлежит:

The invention discloses a spacecraft high-accuracy speediness attitude maneuver method based on a single gimbal control moment gyro (SGCMG) and a reaction wheel (RW) and relates to a spacecraft high-accuracy speediness attitude maneuver method which is used for achieving spacecraft high-accuracy speediness attitude maneuver. According to the method, a control moment gyro (CMG) and the RW are used as a combination executing mechanism to achieve the spacecraft high-accuracy speediness attitude maneuver. Angular speed of winding around an Euler main shaft is divided into three sections. Needed controlling torque is generated through the CMG in an accelerating section and a braking section. After a constant speed section and the braking section are finished, a compensate torque generated by the RW is adopted to guarantee that the angular speed is kept near a steady state value so that the spacecraft high-accuracy speediness attitude maneuver is achieved. The method is suitable for the attitude ...

Подробнее
Номер записи: 2
19-10-2011 дата публикации

Normal cloud model-based moonlet cost optimization design method

Номер: CN102222266A
Автор: Sun Zhaowei, Chen Changchun, Ye Dong, Zhong Weichao, Deng Hong, Xing Lei, Wang Feng, Chen Xueqin
Принадлежит:

The invention discloses a normal cloud model-based moonlet cost optimization design method, and relates to a moonlet cost optimization method for solving the problems of high continuity requirements for functions, low convergence, un-guaranteed stability and low calculation efficiency of the conventional satellite cost optimization method which adopts a gradient information-based optimization algorithm. The method comprises the following steps of: 1, establishing a moonlet cost C optimization model; 2, setting optimization design variables of the moonlet cost C; 3, initially assigning values for the seven optimization design variable in the step 1; 4, providing the optimization algorithm has finished the k-th step (k is not less than 1), calculating the speed of the k+1 step of each particle; 5, calculating the position of the k+1 step of each particle by using the speed of the k+1 step of the particle and the position at the k-th step; 6, calculating the optimized position of each particle ...

Подробнее
Номер записи: 3
03-10-2012 дата публикации

Two-freedom nonlinear vibration absorption device

Номер: CN102705430A
Автор: Kong Xianren, Cao Xibin, Sun Zhaowei, Ye Shuichi, Zhang Yechi
Принадлежит:

The invention relates to a vibration absorption device, in particular to a two-freedom nonlinear vibration absorption device, aiming at solving the problem that the traditional linear rigidity vibration absorber is only effective at the part with natural frequency, and can not effectively absorb the vibration which is not at the part with natural frequency. The two-freedom nonlinear vibration absorption device comprises two first support frames which are arranged in parallel from top to bottom; the two ends of a first elastic string are respectively connected with the two first support frames; the middle part of the first elastic string is fixedly connected with one end of a first mass block; two second support frames are arranged on the end surface of the other end of the first mass block in parallel from top to bottom; the two ends of a second elastic string are respectively connected with the two second support frames; the end surface of one end of a second mass block is connected with ...

Подробнее
Номер записи: 4
09-10-2013 дата публикации

Single-shaft batch counteractive flywheel moment optimal distribution method based on angular momentum margin

Номер: CN103345275A
Автор: Sun Zhaowei, Zhang Zhongzheng
Принадлежит:

The invention discloses a single-shaft batch counteractive flywheel moment optimal distribution method based on an angular momentum margin, and belongs to the field of control distribution. The multi-objective optimization distribution method based on the angular momentum margin is designed for solving the problem that due to the fact that a traditional moment distribution method takes no account of self angular momentum of flywheels, the flywheels are saturated and cannot complete tasks. A weight coefficient optimization method is used, system energy consumption and output margins of the flywheels are integrally considered, a suitable weight coefficient is given to each item according to energy consumption and the output margin of each flywheel, the weight coefficients are adjusted in the process of moment distribution, therefore, energy consumption is reduced, and saturation of the flywheels is avoided. The single-shaft batch counteractive flywheel moment optimal distribution method based ...

Подробнее
Номер записи: 5
24-04-2013 дата публикации

Autonomous interpreting and processing device and method of satellite closed-loop testing system data

Номер: CN103064300A
Автор: Sun Zhaowei, Zhang Jian, Li Huayi, Wang Feng, Li Dongbai, Cao Xibin, Xu Guodong, Pan Xiaotong, Guo Jinsheng
Принадлежит:

The invention discloses an autonomous interpreting and processing device and method of satellite closed-loop testing system data, relates to the autonomous interpreting and processing device and method of data and solves the problem that incorrect interpretation can be caused because testing data possibly exceed an established interpretation standard because of error accumulation in a system in the traditional method for interpreting the testing data. The control voltage data output end of a satellite closed-loop testing unit is connected with the control voltage data input end of a testing data simulating unit; the flywheel rotating speed data output end of the satellite closed-loop testing unit is connected with the flywheel rotating speed data input end of the testing data simulating unit; the testing end threshold interpreting data input end of a threshold interpreter is connected with the testing end threshold interpreting data output end of the satellite closed-loop testing unit; ...

Подробнее
Номер записи: 6
19-06-2013 дата публикации

Batch MEMS gyro information fusion method

Номер: CN103162678A
Автор: Sun Zhaowei, Pang Bo, Li Dongbai, Wang Feng, Cao Xibin, Yang Yungang, Pan Xiaotong, Cheng Yu, Zhang Zhongzheng
Принадлежит:

The invention discloses a batch MEMS gyro information fusion method and belongs to the technical field of MEMS gyro information fusion. The batch MEMS gyro information fusion method solves the problem that in multi-sensor information fusion, the existing single gyro information processing method has large operation quantity and a low output result precision. The batch MEMS gyro information fusion method comprises the following steps of 1, dividing equally batch MEMS gyros into N groups of gyro arrays, 2, through a primary fusion module, carrying out primary fusion of data acquired by all the MEMS gyros in each group of the gyro arrays based on a support degree to obtain fusion data of each group of the gyro arrays, and 3, acquiring a corresponding state space equation by a time-sequence model, 4, carrying out multistage sequenced filtering to obtain an N-grade fusion state estimated value, and carrying out extraction to obtain angular velocity of the batch MEMS gyros at k time after fusion ...

Подробнее
Номер записи: 7
25-09-2013 дата публикации

Satellite-borne data transmission system and task scheduling and optimizing method thereof

Номер: CN103324251A
Автор: Liu Yuan, Yang Jing, Sun Zhaowei, Cao Jiaming, Xing Lei, Ye Dong, Wang Feng
Принадлежит:

The invention discloses a satellite-borne data transmission system and a task scheduling and optimizing method thereof, and solves the problems that a system of an existing task scheduling method is low in work efficiency and limited in data processing size. The task scheduling and optimizing method thereof includes that an image output end of a high-resolution CCD (charge coupled device) camera is connected with an image input end of a large-capacity solid-state storage in the satellite-borne data transmission system, an image output end of the large-capacity solid-state storage is connected with an image data input end of a reconfigurable coprocessor, an image data output end of the reconfigurable coprocessor is connected with an image data input end of a modem, and the modem transmits image data to a ground receiving station through data transmission antennas. By the task scheduling and optimizing method, reconstruction time of FPGA (field programmable gate array) is reduced, work efficiency ...

Подробнее
Номер записи: 8
25-09-2013 дата публикации

Information path optimizing method based on quick response satellite

Номер: CN103324088A
Автор: Sun Zhaowei, Yang Jing, Liu Yuan, Cao Jiaming, Song Shounan
Принадлежит:

An information path optimizing method based on a quick response satellite relates to the field of spaceflight. The information path optimizing method is used for improving reliability of information path optimization of mutual communication of all modules in a plug and play technique of the quick response satellite. The information path optimizing method comprises the steps of utilizing a satellite-bone computer or a ground computer to initialize a connection method T of route modules, utilizing the satellite-bone computer or the ground computer to calculate a reliability value r of the connection method T, utilizing particle swarm optimization to optimize the connection method T, obtaining the reliability value r of the optimized connecting method T, and transmitting the reliability value r to a central wireless module. The connecting method T comprises the positions of the route modules and the speeds of the route modules. The central wireless module can send the optimized connecting ...

Подробнее
Номер записи: 9
10-07-2013 дата публикации

Batch MEMS (micro-electromechanical system) sensor based inertial measurement unit and gesture-position information acquisition method

Номер: CN103196447A
Автор: Sun Zhaowei, Cheng Yu, Yu Wu, Li Dongbai, Pang Bo
Принадлежит:

The invention discloses a batch MEMS (micro-electromechanical system) sensor based inertial measurement unit and a gesture-position information acquisition method, which belong to the technical field of inertial navigation. The invention is designed for solving the problem that traditional satellites only can be equipped with a small amount of gyroscopes and accelerometers, thereby reducing the redundancy and fault tolerance of an IMU system. The inertial measurement unit disclosed by the invention comprises m MEMS sensors, a CS (chip selection) decoder, a single-chip microcomputer and a power supply module; and the gesture-position information acquisition method comprises the following steps of: 1, initializing alignment; 2, carrying out data acquisition on the m MEMS sensors one by one by using an SPI bus through a time-sharing operation method, and feeding acquired data to the single-chip microcomputer; 3, after a fault is found, ignoring the outputs of the MEMS sensors, and restarting ...

Подробнее
Номер записи: 10
22-05-2013 дата публикации

Cluster module spacecraft system and control method thereof

Номер: CN103116325A
Автор: Cao Xibin, Zhang Jinxiu, Hua Jin, Lan Shengchang, Sun Zhaowei, Xing Lei, Wang Feng, Zhang Zhigang, Hou Zhendong, Chen Qing
Принадлежит:

The invention discloses a cluster module spacecraft system and a control method of the cluster module spacecraft system and relates to the field of spacecraft systems. The cluster module spacecraft system and the control method of the cluster module spacecraft system aim to solve the problems that once the existing spacecraft system breaks down or service life is due, the existing spacecraft system can not normally work, the whole spacecraft system is scrapped, and loss is large. The cluster module spacecraft system comprises service module spacecrafts and mission module spacecrafts. The number of the service module spacecrafts is M, and the number of the mission module spacecrafts is N. The service module spacecrafts comprise power supplying module spacecrafts, data processing module spacecrafts, remote monitoring and data transmission module spacecrafts and cluster control module spacecrafts. The number of the power supplying module spacecrafts is m, the number of the data processing ...

Подробнее
Номер записи: 11
22-07-2015 дата публикации

Global optimal double-pulse orbit transfer method under time free conditions

Номер: CN104794311A
Автор: Zhang Gang, Xie Chengqing, Cao Xibin, Sun Zhaowei
Принадлежит:

The invention provides a global optimal double-pulse orbit transfer method under time free conditions and relates to a global optimal double-pulse orbit transfer method. The invention provides the global optimal double-pulse orbit transfer method under the time free conditions so as to solve the problem in the prior art that for the Lambert problem, which orbit is the orbit with lowest energy consumption is not given out. The global optimal double-pulse orbit transfer method provided by the invention is realized by the following steps: determining true anomalies, namely f1 and f2 respectively; 2. defining energy consumed by an optimal double-pulse transfer orbit; 3. calculating to obtain wc and wp; 4. determining constants according to the wc and the wp; 5. decomposing a velocity pulse; 6. obtaining an eight-order polynomial about the wc; 7. rooting the eight-order polynomial to obtain wcop; 8. determining the optimal double-pulse transfer orbit under the time free conditions; 9. determining ...

Подробнее
Номер записи: 12