44results about How to "Engineering feasibility" patented technology

The invention provides a non-destructive fault injection method for supporting fault tolerance verification of an on-board redundancy computer. A main program of a channel of the on-board redundancy computer is taken as the target object for injecting a fault. The non-destructive fault injection method includes the steps that a fault injection interaction terminal edits fault content and sends a fault injection command to a fault injection interrupt handling routine; the fault injection interaction terminal sends a fault injection interrupt request and enables the fault injection interrupt handling routine through interrupt interlock control; and the fault injection interrupt handling routine is executed. The non-destructive fault injection method enables the on-board redundancy computer to have the capability of supporting fault tolerance verification and can realize non-destructive fault injection in a fault simulation experiment on the basis of not causing any physical damage and not destructing the reliability and the safe performance characteristic of a product.

The invention provides a rendezvous approach method with the minimum speed increment. The method comprises the steps that the position and speed of a mooring track and a target track are acquired according to the parameters of a maneuvering satellite and a target satellite; the intersection vector of the mooring track and the target track and related parameters are solved; the intersection point of a maneuvering satellite and a target satellite is calculated; the optimal track control point is determined according to single-pulse track design under perturbation; phase is controlled and adjusted by closing the tracks; and the maneuvering satellite and the target satellite eventually intersect and approach at the intersection point.

The present invention relates to a satellite optical burst switching conflict resolution scheduling implementation system and method, according to the network topology of the space-based broadband transmission backbone network and the status of each switching node, through the scheduling mode of pre-allocation of network resources, in the space-based broadband transmission backbone network The boundary controls the data that will enter the space-based broadband transmission backbone network for transmission and exchange, pre-plans the exchange time and forwarding path of each optical burst data entering the space-based broadband transmission backbone network, and realizes the optical burst data exchange of the space-based broadband transmission backbone network conflict resolution scheduling. The optical burst data of the space-based broadband transmission backbone network is generated by the electrical domain. After the electrical-optical conversion is completed at the edge node of the backbone network, it enters the backbone network for optical burst exchange. After reaching the destination edge node, the optical-electrical conversion is completed, and then the data is sent to the processing terminal. , to complete the data routing exchange process. The system utilizes network resources to resolve conflicts in satellite optical burst switching through pre-planning and scheduling.

The invention provides a helicopter target recognition method used under a radar LPRF working condition. The helicopter target recognition method comprises the following steps that a time-frequency two-dimensional distribution diagram of an echo of a radar under the LPRF working condition is constructed, distribution characteristics of a helicopter main rotor echo in the frequency dimension are obtained, a helicopter body echo is removed, a main rotor echo is reserved, training is performed by adopting actually measured main rotor echo data to form a frequency domain template, an Euclidean matching measurement technology is adopted, the frequency domain template and the radar echo time-frequency two-dimensional distribution diagram are matched to form a two-dimensional output matrix, a minimum Euclidean distance region is found in the two-dimensional output matrix to be used as an optimal matching region, the optimal matching region is mapped to the original radar echo time-frequency two-dimensional distribution diagram, and distance and speed information of a helicopter target is obtained. According to the helicopter target recognition method, the recognition probability of the radar on the helicopter target can be effectively improved, the method is particularly suitable for detection and recognition of a radar system on the helicopter target in a complex electromagnetic environment, and the accuracy of detecting and recognizing low-altitude, low-speed and weak-small targets by the current radar can be improved.

The invention discloses a method for determining the lift aircraft reentry guidance resistance accelerated speed change rate. The method includes the steps that a mapping relation between the flight speed and a preset attack angle command is determined according to a task requirement; according to a pneumatic parameter model, fitting is carried out to obtain a fitting relational expression between a pneumatic resistance parameter and an attack angle, and an estimation value of the pneumatic resistance parameter is obtained according to the fitting relational expression; according to the estimation value of the pneumatic resistance parameter and the mapping relation between the flight speed and the preset attack angle command, the pneumatic resistance coefficient change rate is obtained through calculation; the height change rate and the speed change rate are calculated according to a navigation parameter and an approximation formula; according to the height change rate, the speed change rate and the pneumatic resistance coefficient change rate, a resistance accelerated speed change rate is obtained through calculation. By means of the method, influences of sampling noise on the reentry guidance control accuracy can be effectively avoided, and the tracking control accuracy of the resistance accelerated speed is improved.