We present the general concept of a telescope with optics and detectors mounted on two separate spacecrafts, in orbit around the telescope’s target (scopocentric or target-centric orbit), and using propulsion to maintain the Target-Optics-Detector alignment and Optics-Detector distance. Specifically, we study the case of such a telescope with the Sun as the target, orbiting at \(\sim \)1 AU. We present a simple differential acceleration budget for maintaining Target-Optics-Detector alignment and Optics-Detector distance, backed by simulations of the orbital dynamics, including solar radiation pressure and influence of the planets. Of prime interest are heliocentric orbits (such as Earth-trailing/leading orbits or Distant Retrograde Orbits), where thrust requirement to maintain formation is primarily in a single direction (either sunward or anti-sunward), can be quite minuscule (a few m/s/year), and preferably met by constant-thrust engines such as solar electric propulsion or even by solar sailing via simple extendable and/or orientable flaps or rudders.

我们介绍了一种望远镜的一般概念，该望远镜的光学元件和检测器安装在两个独立的航天器上，围绕着望远镜的目标（近心或目标中​​心轨道）在轨道上运行，并使用推进力保持目标-光学-检测器对准和光学-检测器距离。具体来说，我们研究了以太阳为目标，以\（\ sim \）绕行的这种望远镜的情况1 AU。我们提供了一个简单的差分加速度预算，用于维持目标-光学-检测器对准和光学-检测器距离，并辅以对轨道动力学的仿真，包括太阳辐射压力和行星的影响。最感兴趣的是日心轨道（例如地球追踪/超前轨道或遥远的逆行轨道），其中维持编队的推力要求主要在一个方向（向阳或逆向），可能非常小（几米（/ s /年），最好通过恒定推力的发动机（例如太阳能推进器）或什至通过简单的可扩展和/或定向的襟翼或方向舵通过太阳航行来满足。