Mission Analysis of a Reusable Launch Vehicle Technology Demonstrator (RLV-TD)

Brinda, V.; Arora, Rajesh; Janardhana, E.

doi:10.2514/6.2005-3291

Cited by 13 publications

(8 citation statements)

References 1 publication

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“…To meet the objective, the states r, V , γ , φ, θ , ψ are considered, with their dynamics given by Eqs. (1)- (6) and with α as a control variable.…”

Section: Problem Objectivesmentioning

confidence: 99%

“…The scenario of the reentry segment in descent phase can be seen in [6]. However in this work, motion of the vehicle is restricted with longitudinal profiles, which implies that the angle of attack is the only control variable available.…”

Section: Problem Objectivesmentioning

confidence: 99%

“…(3) Guidance command constraint: The physical constraint on the angle of attack is due to the restricted ability of the vehicle to control. The vehicle should fly within its prescribed upper and lower bounds as follows [6]:…”

Section: Problem Objectivesmentioning

confidence: 99%

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Suboptimal reentry guidance of a reusable launch vehicle using pitch plane maneuver

Chawla

Sarmah

Padhi

2010

Aerospace Science and Technology

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“…To meet the objective, the states r, V , γ , φ, θ , ψ are considered, with their dynamics given by Eqs. (1)- (6) and with α as a control variable.…”

Section: Problem Objectivesmentioning

confidence: 99%

Section: Problem Objectivesmentioning

confidence: 99%

See 1 more Smart Citation

Suboptimal reentry guidance of a reusable launch vehicle using pitch plane maneuver

Chawla

Sarmah

Padhi

2010

Aerospace Science and Technology

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“…The TAEM phase starts from the point with a height of 30km and a velocity of 2.5Ma, and ends at the point with a height of 4km and a velocity of 0.5Ma. In the TAEM phase, the task is to dissipate surplus energy and adjust the heading direction towards the runway, so the RLV will land safely with a suitable velocity and height [4], which makes this phase a vital phase of the reentry flight. However, a large variation range of dynamic pressure and velocity, significant changes of aerodynamic characteristics along with the uncertain states of the RLV after initial entry phase also make the task of the TAEM phase a highly difficult work.…”

Section: Introductionmentioning

confidence: 99%

Trajectory tracking for RLV terminal area energy management phase based on LQR

Zheng

Liang

et al. 2014

Proceedings of 2014 IEEE Chinese Guidance, Navigation and Control Conference

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A new longitudinal trajectory tracking law for the Terminal Area Energy Management (TAEM) phase of the Reusable Launch Vehicle (RLV) is presented in this paper. The conventional PID method controls the height and the velocity by the angle of attack and the angle of airbrake respectively, and no coupling is considered. To improve the tracking precision, the new tracking law is designed based on the linear quadratic regulator (LQR) theory where the coupling is taken into account. Finally, the trajectory tracking law based on the LQR is simulated and compared with the conventional method. Simulation results indicate the effectiveness and the robustness of the new tracking law.

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“…Moreover, note that the TAEM and automatic landing is not a must in all missions. In simpler missions, the vehicle is rather required to reach close to a specified final coordinates with sufficiently reduced velocity from where it can glide to the sea, possibly with the help of a parachute [3]. Such missions are typically common in initial flight trials to demonstrate the soundness of vehicle design and reentry technology and/or if the land mass for constructing a runway is not available at a feasible location after the mission of the launch vehicle is over.…”

mentioning

confidence: 99%

Robust Reentry Guidance of a Reusable Launch Vehicle Using Model Predictive Static Programming

Halbe

Raja

Padhi

2014

Journal of Guidance, Control, and Dynamics

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A robust suboptimal reentry guidance scheme is presented for a reusable launch vehicle using the recently-developed computationally efficient model predictive static programming. The formulation uses the nonlinear vehicle dynamics with spherical and rotating earth, hard constraints for desired terminal conditions and an innovative cost function having several components with associated weighting factors that can account for path and control constraints in a soft constraint manner, thereby leading to smooth solutions of the guidance parameters. The proposed guidance essentially shapes the trajectory of the vehicle by computing the necessary angle of attack and bank angle that the vehicle should execute. The path constraints are the structural load constraint, thermal load constraint, bounds on the angle of attack and bounds on the bank angle. In addition, the terminal constraints are the threedimensional position and velocity vector components at the end of the reentry. Where as the angle of attack command is generated directly, the bank angle command is generated by first generating the required heading angle history and then using it in a dynamic inversion loop considering the heading angle dynamics. Such a two-loop synthesis of bank angle leads to better management of the vehicle trajectory and avoids mathematical complexity as well. Moreover, all bank angle maneuvers have been confined to the middle of the trajectory and the vehicle ends the reentry segment with near zero bank angle, which is quite desirable. It has also been demonstrated that the proposed guidance has sufficient robustness for state perturbations as well as parametric uncertainties in the model.

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Mission Analysis of a Reusable Launch Vehicle Technology Demonstrator (RLV-TD)

Cited by 13 publications

References 1 publication

Suboptimal reentry guidance of a reusable launch vehicle using pitch plane maneuver

Suboptimal reentry guidance of a reusable launch vehicle using pitch plane maneuver

Trajectory tracking for RLV terminal area energy management phase based on LQR

Robust Reentry Guidance of a Reusable Launch Vehicle Using Model Predictive Static Programming

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