Most existing impact angle control guidance (IACG) laws that consider the reduced seeker field-of-view (FOV) focus only on a stationary or a nonmaneuvering moving target. In actual warfare, however, a number of targets are capable of maneuvering with lateral acceleration, which prohibits the existing FOV-constrained IACG laws from guaranteeing the reliable performance. In this article, we develop a guidance law that ensures the accurate IACG with obeying the FOV constraint against a maneuvering target. The proposed guidance law is based on the engagement kinematics against a maneuvering target and structured as a sliding mode controller to cope with unknown disturbance such as the normal acceleration of the target. The introduced sliding surface structure includes a sigmoid function of which output is limited in magnitude in order to restrict the missile look angle within the preset limits. In consequence, the proposed law has the capability to fulfill IACG without violating the FOV constraint against a maneuvering moving target. Numerical simulations that support the effectiveness of the proposed guidance law are also included in this article.

中文翻译：

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具有冲击角控制的机动目标视场约束制导律

大多数考虑减少导引头视野 (FOV) 的现有撞击角控制制导 (IACG) 法则仅关注静止或非机动移动目标。然而，在实际战争中，许多目标能够以横向加速度进行机动，这使得现有的受视场约束的IACG规则无法保证可靠的性能。在本文中，我们开发了一个制导律，以确保准确的 IACG，同时遵守针对机动目标的 FOV 约束。所提出的制导律基于对机动目标的交战运动学，并构造为滑模控制器，以应对未知干扰，例如目标的法向加速度。引入的滑动面结构包括一个 sigmoid 函数，其输出的幅度受到限制，以将导弹的视角限制在预设范围内。因此，拟议的法律有能力在不违反针对机动移动目标的 FOV 约束的情况下实现 IACG。支持所提议的制导法则有效性的数值模拟也包含在本文中。