发表机构
University of Arizona（亚利桑那大学）
机构由 AI 辅助整理，请以论文原文为准。AI 中文总结
本文针对航天器精密光学载荷的亚开尔文级温度稳定需求，提出非线性热模型与模型预测控制方法，结合无迹卡尔曼滤波实现闭环调节，并验证其优于传统PID控制。
AI 中文摘要
对于搭载精密光学仪器的航天器而言，维持稳定的热环境至关重要，因为温度梯度和热膨胀会改变光学元件的几何对准，影响波前传感，并降低图像质量，即使主动热系统提供实时控制也是如此。特别是，光学载荷的温度必须控制在期望设定点附近的亚开尔文容差范围内，这一要求通常难以通过传统的反应式控制方法实现。为此，本文为航天器光学系统开发了一种新颖的非线性热模型，考虑了传导、辐射以及由航天器轨道引起的辐射环境变化。利用该模型，我们提出了一种模型预测控制（MPC）方法，能够在真实轨道条件下实现对光学舱的闭环热调节。由于仅有部分受噪声污染的测量温度可用，我们采用无迹卡尔曼滤波器来估计完整的热状态，从而通过递归在线优化得到确定性等价MPC控制器。该热模型针对高保真热模拟器进行了验证，并将所提出的方法与传统的PID控制（目前在轨热调节的主流方法）进行了比较。
英文摘要
Maintaining a stable thermal environment is critical for spacecraft carrying precision optics, as temperature gradients and thermal expansion can alter the geometric alignment of optical components, compromise wavefront sensing, and degrade image quality even when active thermal systems provide real-time control. In particular, the temperature of the optical payload must be controlled to sub-Kelvin tolerances about the desired setpoint, a requirement that is often difficult to achieve with conventional reactive control methods. To this end, this paper develops a novel nonlinear thermal model for the optical system of a spacecraft, accounting for conduction, radiation, and the changing radiative environment induced by the spacecraft's orbit. Using this model, we develop a model predictive control (MPC) methodology that enables closed-loop thermal regulation of the optical compartment under realistic orbital conditions. Since only partial, noise-corrupted temperature measurements are available, an Unscented Kalman Filter is employed to estimate the full thermal state, yielding a certainty-equivalence MPC controller obtained via recursive online optimization. The thermal model is validated against a high-fidelity thermal simulator, and the proposed approach is compared against conventional PID control, the prevailing method for on-orbit thermal regulation.
