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To solve the problem regarding the impact angle of the missile, this paper proposes a novel guidance law, which can control the missile to hit the target at the desired angle. The key of the guidance law is selecting a moving point on the collision line as the virtual target, and the tactical requirements can be fulfilled by the missile directly pu...
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Citations
... A two-stage guidance law combining sliding 64 mode control and PNG was introduced in [12], where 65 a virtual target is used to adjust the impact time and 66 angle. Hou [13] also utilized the virtual target technique 67 to realize the impact angle control against moving targets. 68 Kim[14] used polynomial to construct the ITACG. ...
The Impact-Time-Angle-Control guidance (ITACG) law can control the impact time and angle in a wide range of applications. The previous ITACG research generally suffer from the accuracy under the time-varying velocity condition, or the axial acceleration is required under 3-D conditions. This paper develops a four-stage guidance technique based on the Bezier curve, and it is effective in both 2-D and 3-D scenarios. First, we proved a proposition that the length of the two-stage Bezier trajectory increases monotonically with the initial flight path angle. Based on this, the four-stage guidance strategy is studied. The first stage is to adjust the impact angle in the line-of-sight coordinate system. The second stage is to change the heading angle to match the Bezier trajectory with the distance-to-go. The third stage tracks the Bezier trajectory generated in the second stage. The fourth stage uses the proportional navigation guidance law to realize the end-game guidance. The proposed strategy was extended to 3-D scenarios, where the algorithm performed well even under the influence of gravity and aerodynamic drag, achieving accurate impact angle and time with high robustness. Finally, the effectiveness of the proposed algorithm is verified through four sets of simulation experiments.
... In addition to the optimal control theory, sliding mode control method also can be used to deal with impact angle control problem [7][8][9][10][11]. The authors in [12] utilized the virtual target technique to achieve IACG on moving targets. As one of the most widely used guidance laws, the proportional navigation guidance (PNG) has produced a lot of impact angle control guidance. ...
... If upper t is less than the desired impact time, the impact time error can be eliminated before the target is destroyed. Combining (12) and (14), one can have Since D is nonzero when is not equal to d , the commanded acceleration does not encounter singularity problems during the curved flight stage. Once the missile flies along a straight path, the commanded acceleration will remain zero. ...
... Rockets based on Archimedes' spiral [3] are often used against airborne targets because of their stable rotation and accurate range prediction [4]. This is because the spatial location of air targets is relatively fixed relative to moving nodes and can be accurately engaged using prediction and tracking methods [5]. However, ground targets require more intelligent and efficient control methods as their location can change with the environment, terrain and other factors [6]. ...
Existing mobility models in the military domain focus on reconnaissance, siege and tracking, with fewer node movement scenarios for high-altitude precision military strikes.This paper combines the motion characteristics of Archimedean spiral and the idea of cluster mobility model to cluster nodes within the cluster and use the cluster head node to control nodes within the cluster to achieve intelligent node control. And our model is compared with the classic PSO and RPGM models. Experiments show that our proposed mobile model has excellent network performance and movement capability compared to the POS and RPGM models, and has broad application prospects.
