Robust neighboring extremal guidance for the advanced launch system

Bain, John; Speyer, Jason L.

doi:10.2514/6.1993-3750

Cited by 3 publications

(5 citation statements)

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“…Traditionally, neighboring optimal (or extremal) control [3] has played an important role in aerospace applications and control of nonlinear systems which are subject to perturbations in, for example, initial state or terminal constraints. For the applications of neighboring optimal control in hypersonic applications, one can refer to, for instance, [4], [5].…”

Section: Introductionmentioning

confidence: 99%

Feedback Strategies for Hypersonic Pursuit of a Ground Evader

Lee¹,

Bakolas²,

Akella³

2021

Preprint

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In this paper, we present a game-theoretic feedback terminal guidance law for an autonomous, unpowered hypersonic pursuit vehicle that seeks to intercept an evading ground target whose motion is constrained along an axis. We formulate this problem as a pursuit-evasion game whose saddle point solution is in general difficult to compute onboard the hypersonic vehicle due to its highly nonlinear dynamics. To overcome this difficulty, we linearize the nonlinear hypersonic dynamics around a reference trajectory and subsequently utilize feedback control design techniques from Linear Quadratic Differential Games (LQDGs). In our proposed guidance algorithm, the hypersonic vehicle computes its open-loop optimal state and input trajectories off-line and prior to the commencement of the game. These trajectories are then used to linearize the nonlinear equations of hypersonic motion. Subsequently, using this linearized system model, we formulate an auxiliary twoplayer zero-sum LQDG which is effective in the neighborhood of the given reference trajectory and derive its feedback saddle point strategy that allows the hypersonic vehicle to modify its trajectory online in accordance with the changes/dispersion to the target's position due to its evasive maneuvers. We provide numerical simulations to verify the performance of our proposed guidance law.

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Section: Introductionmentioning

confidence: 99%

Feedback Strategies for Hypersonic Pursuit of a Ground Evader

Lee¹,

Bakolas²,

Akella³

2021

Preprint

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“…The diagnostic algorithms developed in this paper are demonstrated through a simulation study of the ascent of the Shuttleclass vehicle depicted in Figure 1 [2]. We simulate the vehicle dynamics, kinematics, guidance, navigation & control (GN&C), propulsion, and consider some representative system faults.…”

Section: Rocket Ascent Simulationmentioning

confidence: 99%

“…This is a simplified model of a Space Shuttle class vehicle that is based on data published in the open literature [2]. The detailed engineering simulation used by NASA for the Space Shuttle has in excess of 100 states and thousands of parameters.…”

Section: Rocket Ascent Simulationmentioning

confidence: 99%

“…The modeling includes variation of mass, center of gravity, and moment of inertia with the propellant expenditure. The aerodynamic model is borrowed from an asymmetric vehicle (the first stage drag minimum is at small positive angle of attack) [2]. The model assumes a non-rotating spherical Earth and uses an inverse square gravitational field and an exponential atmosphere.…”

Section: Rocket Ascent Simulationmentioning

confidence: 99%

“…We assume full-state measurements for the navigation model. Neighboring Extremal (NE) closed-loop guidance uses a point mass simulation to calculate the minimum fuel trajectory [2]. NE guidance is implemented as full-state proportional feedback, which does not steer back to the original optimal trajectory.…”

Section: Rocket Ascent Simulationmentioning

confidence: 99%

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Integrated diagnostics of rocket flight control

Gorinevsky

Samar²,

Bain³

et al. 2005

2005 IEEE Aerospace Conference

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Abstract-This paper describes an integrated approach to parametric diagnostics demonstrated in a flight control simulation of a space launch vehicle. The proposed diagnostic approach is able to detect incipient faults despite the natural masking properties of feedback in the guidance and control loops. Estimation of time varying fault parameters uses parametric vehicle-level data and detailed dynamical models. The algorithms explicitly utilize the knowledge of fault monotonicity (damage can only increase, never improve with time) where available. The developed algorithms can be applied to health management of next generation space systems. We present a simulation case study of rocket ascent application to illustrate and validate the proposed approach.

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