5results about How to "Simple model" patented technology

This invention provides a spacecraft escort control method based on zero-sum differential games, belonging to the field of aerospace technology. The control method includes the following steps: obtaining spacecraft escort problem parameters for both the pursuing and defending satellites; establishing a spacecraft escort model based on zero-sum differential games and inputting initial parameters into the model; transforming the spacecraft escort model into a two-point boundary value problem model; using a genetic algorithm to solve the two-point boundary value problem model to obtain the state trajectory within the game time, thus completing the spacecraft escort control. This spacecraft escort control method can effectively solve the spacecraft escort problem under continuous thrust, and is an effective extension of existing continuous thrust escort problem models and methods. The model employs a differential game method described by a zero-sum cost function, thus simplifying the solution of the difficult-to-solve weighted performance index escort problem and improving the solution efficiency of the spacecraft escort game problem.

The invention discloses a modal shape and frequency identification method for a motor stator system with an inner gear ring, and the method comprises the steps: building a shell unit and beam unit mixed analysis model of the motor stator system provided with the inner gear ring, and obtaining a total stiffness matrix and a total mass matrix under a local rectangular coordinate system through a matrix displacement method, obtaining a structural stiffness matrix and a structural mass matrix under the overall cylindrical coordinate system by using coordinate transformation; and establishing a discrete free vibration model, inputting the structural stiffness matrix and the structural mass matrix into the model, and outputting modal shapes of different orders and corresponding inherent frequencies of the motor stator system, thereby completing identification. The method comprehensively considers the influence of the stator teeth and the tooth part of the inner gear ring, helps to rapidly identify the modal shape and inherent frequency of the stator system, provides guidance for subsequent vibration acquisition and optimization, and has the advantages of simple modeling, rapid identification and high precision.

The application discloses an INS / GNSS rod arm error online estimation method based on dimension reduction filtering. The method splits the INS / GNSS rod arm error and other error variables, constructs multiple low-dimensional filters, reduces the coupling between the error variables, has clear mechanism, simplifies the model, reduces the requirements of the combined navigation algorithm on the chip main frequency and the storage space, improves the calculation speed and the filtering estimation precision, and can improve the positioning performance of the vehicle-mounted combined navigation system after the INS / GNSS rod arm error online estimation and compensation, and has high engineering application value.

This invention relates to the field of aero-engine technology and discloses a Simpack-based method for analyzing the misalignment vibration of aero-engine blades with bosses. While ensuring analytical accuracy, it improves computational efficiency by simplifying the modeling process and establishes a clear mapping relationship between parameters and responses, thus providing reliable technical support for vibration control of aero-engine bladed disk systems. The method includes the following steps: establishing finite element modal analysis models of all boss blades and disks, and performing free modal calculations; using Simpack modal condensation to establish blade-disk reduced flexible body models of all boss blades and disks, and then assembling them to form a complete blade-disk coupled dynamic analysis model of the aero-engine; subsequently, simulating the frictional vibration reduction effect between boss blades by establishing pre-compressed spring damping units or custom nonlinear spring units between the bosses of adjacent boss blades; and simulating the interference fit relationship between bosses by using the spring pre-compression amount.

The present application belongs to the field of aerospace space orbit game and space safety, and relates to a kind of orbit pursuit and evasion interception game strategy design method based on optimization theory, specifically comprising the following processes: determining orbit game scene parameters;Based on the relative motion equation of spacecraft, a round mode pursuit and evasion interception orbit game model is established;The pursuit strategy of the pursuer is designed, the interception strategy of the interceptor is designed, and the escape strategy of the evader is designed;Based on the orbit game scene parameters and the round mode pursuit and evasion interception orbit game model, the game indexes of the three are optimized, and the optimal values of the game indexes of the three are obtained respectively. The application of the method can provide an effective solution for the pursuit and evasion interception cooperation problem of spacecraft using impulse thrust, thereby laying a theoretical foundation for the realization of space failed spacecraft takeover, space failed spacecraft removal and other engineering applications.