3results about How to "Go online" patented technology

This application discloses an automatic data management function generation system and device, applied in the database field. The device is equipped with the system. The system includes: a data source design module for generating table metadata in response to user input commands in a graphical design interface; an automatic form generation module for generating front-end code for forms by recognizing the table metadata; a business layer data encapsulation module for encapsulating the front-end form data, enabling the encapsulated form data to interface with back-end business logic; and a historical data management module for storing historical versions of form data. This reduces workload while avoiding code oversights and errors caused by human error.

The embodiment of the invention provides display equipment and a system function configuration method. A system function configuration template is defined through metadata to form a new data structure related to parameter items, and then decoupling of the parameter items and scene dimensions is achieved. Based on decoupling of the parameter item and the scene dimension, the stability of system updating can be effectively improved in a system updating scene.

The invention discloses a reusable rocket landing section fuel optimal thrust adjusting method and device and a storage medium, and the method mainly comprises the steps: constructing a one-machine section energy upper limit index as a three-machine section thrust adjusting criterion; continuously iteratively calculating and adjusting the three-machine-section engine thrust virtual throttling ratio, so that the one-machine-section energy upper limit index meets a preset threshold value requirement and is as small as possible; based on the optimized virtual throttling ratio obtained through iteration, three-machine-section thrust vector space synthesis is conducted in combination with the current attitude angle of the rocket; and after three machines are converted into one machine, one-machine-section thrust vector calculation and throttling ratio amplitude limiting are carried out through iteration. According to the method, on the basis of the form of combining energy analysis and analysis iteration, by adjusting the virtual throttling ratio of engine thrust online in real time and combining thrust closed-loop control, fuel optimal thrust control in the rocket landing process can be effectively completed, and safe and accurate landing of a rocket is ensured.