6results about How to "Satisfy constraints" patented technology

The invention discloses a space-time four-dimensional coordinated guidance method for a dive section of an unpowered high-speed aircraft. The space-time four-dimensional coordinated guidance method comprises the specific steps that S1, a guidance model for dive terminal time and angle control of the aircraft is constructed; s2, diving optimal guidance meeting angle and position constraints; s3, two-stage diving space-time coordination guidance meeting the time constraint is carried out; and S4, carrying out online robustness compensation on the environment and ontology deviation. According to the method, the contradiction between time and space control in a traditional method is solved; the robustness is enhanced by means of a kinetic equation reverse solution technology, and real-time deviation estimation and compensation are achieved; meanwhile, the time control precision is improved by utilizing a two-stage switching logic and numerical integration optimization method based on terminal time prediction; according to the method, the flexibility and adaptability of guidance are improved, the robustness of the system is enhanced, and the strike precision and the overall performance of the aircraft when the aircraft executes complex tasks are remarkably improved.

The application relates to the technical field of semiconductor integrated circuit manufacturing, and particularly discloses an OPC processing method for solving the MRC limitation of metal layer patterns, which comprises the following steps: S1, screening out metal layer line ends with hole layers as to-be-optimized line ends from a metal layer layout; S2, identifying 'L' type line ends from the to-be-optimized line ends, and the patterns opposite to the 'L' type line ends are 'I' type line ends; S3, screening out short side 'L' type line ends from the 'L' type line ends, and the length of the short side of the short side 'L' type line end is less than 0.5 times of a design standard of a hole to a target; and S4, identifying adjacent sides of the short side, and generating line end marks according to the adjacent sides. The OPC processing method for solving the MRC limitation of metal layer patterns can ensure that the 'I' type line ends obtain sufficient compensation by preferentially controlling and setting edge placement errors of the contours to the connected adjacent sides, and solves the problem of contour retreat of the 'I' type line ends.

The present disclosure relates to a method, device and computer-readable storage medium for storing goods in a warehouse, and relates to the field of automated warehousing technology. The method disclosed in the present disclosure includes: obtaining the available volume and capacity interval of each storage area, as well as the inventory volume and average outbound quantity in unit measurement of each classification of goods in a preset historical time period; the capacity interval is the average outbound quantity interval in unit measurement of the storage area; for each storage area, determining the classification of goods stored in the storage area from the corresponding set of candidate goods according to constraint conditions; wherein the constraint conditions include: the sum of the inventory volume of goods stored in the storage area does not exceed the available volume of the storage area, and the sum of the average outbound quantity in unit measurement is within the capacity interval of the storage area; according to the determined classification of goods stored in each storage area, storing each classification of goods in the corresponding storage area.

The invention discloses a six-degree-of-freedom finite time space intersection control method under multiple constraints, and belongs to the technical field of space. According to the implementation method, a six-degree-of-freedom kinetic model is established based on a Lie group SE (3) framework, so that the spacecraft rendezvous process can meet position end constraints and attitude end constraints, the attitude-orbit coupling problem caused by thruster installation errors in actual engineering is fully considered, the spacecraft rendezvous precision is improved, and the spacecraft rendezvous performance is improved. And the unwinding problem caused by a traditional six-degree-of-freedom dual quaternion representation method is avoided. A finite time sliding mode control strategy is designed, so that the rendezvous process can meet task time window constraints, and the error convergence speed is increased. In order to solve potential collision risks in the rendezvous process and meet safety constraints of rendezvous tasks, an artificial potential function is introduced, collision avoidance in the rendezvous process is achieved, and safety of the spacecraft rendezvous process is improved. The rendezvous time can be shortened, the space rendezvous precision of the spacecraft is improved, and the safety of the rendezvous process of the spacecraft is improved.

Methods, systems, and apparatus for jointly determining neural network architecture and hardware accelerator architecture, including computer programs encoded on a computer storage medium. In one aspect, a method includes: generating a batch of one or more output sequences using a controller policy, each output sequence in the batch defining a corresponding architecture of a sub-neural network and a corresponding architecture of a hardware accelerator; for each output sequence in the batch: training a corresponding instance of the sub-neural network having the architecture defined by the output sequence; evaluating the network performance of the trained instance of the sub-neural network; and evaluating the accelerator performance of a corresponding instance of the hardware accelerator having the architecture defined by the output sequence to determine an accelerator performance metric for the instance of the hardware accelerator; and adjusting the controller policy using the network performance metric and the accelerator performance metric.

The present invention proposes a database management and security analysis method, which includes: defining objectives and constraints, wherein the objective is to minimize the comprehensive security risk of all data storage units in the database system, and the constraints include storage capacity constraints and performance overhead constraints; performing sensitivity analysis on key parameters in the database architecture to evaluate the degree of influence of changes in key parameters on the objectives and constraints; optimizing and adjusting the key parameters of the database architecture based on the sensitivity analysis results to achieve the minimum security risk while satisfying the actual constraints. The database management and security analysis method proposed in the present invention optimizes the key parameters of the database architecture through systematic optimization steps and precise calculations, thereby achieving the minimum security risk while satisfying the constraints of storage capacity and performance overhead.