Ascent, transition, entry, and abort guidance algorithm design for the X-33 vehicle

Abstract

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Advanced guidance and control project for reusable launch vehicles

“…This case tests the ability of the guidance to return from a different orbit without modificatioa Fly both with the entry profile from the fourth case above and one tailored to this case. • Same [2] as the fourth case above but large crossrange. Dispersion cases included.…”

Entry guidance with real-time planning of reference based on analytical solutions

“…The desired terminal conditions of the entry phase are the heading error jDw TAEM j 6 5 deg, the speed relative to the rotating Earth V TAEM ¼ 2000 m=s, the altitude H TAEM ¼ 25 km and the bank angle jr TAEM j 6 30 deg. Note that the subscript "TAEM" is widely used to represent the requirements of the interface of the Terminal Area Energy Management phase for a Reusable Launch Vehicle (RLV) (Hanson et al, 1998), so we also use it here. Different from the RLV, the accuracy requirement of the CAV on H TAEM is relatively loose because the CAV attacks the ground target from a near-vertical orientation, rather than lands horizontally.…”

“…To eliminate the crossrange error, the sign of the bank angle changes when the heading error exceeds a pre-defined threshold. Hanson et al (1998) applied shuttle entry guidance to the X-33 program. Mease et al (2002) proposed a fast drag-profile planning method that predicts the final states by integrating a reduced-order system and then corrects the reference profile.…”

Progress in Guidance and Control Research for Space Access and Hypersonic Vehicles

“…The advanced methods were evaluated against the performance of the X-33 baseline guidance and control system in order to ascertain the benefits of the new technologies. A number of entry guidance techniques were tested including Drag-Energy 3D (EAGLE) [17,18] and Quasi-Equilibrium Glide [19,20,21], which tied for the best scores, as well as a Linear Quadratic Regulator [22], Predictor-Corrector [23], and Shuttle-like entry [24] guidance method. A number of advanced control methods were developed and tested under this project, as well including a dynamic inversion based adaptive/reconfigurable control law with linear programming based control allocation [25], robust PI servomechanism and quadratic programming-based control allocation [26], a direct adaptive neural network based controller [27], trajectory linearization [28,29], and sliding mode control [30].…”