Entry guidance with smooth drag planning and non-linear tracking

Gifty, R.; Rajeev, U P; Lalithambika, V.R.; Dhekane, M.V.

doi:10.1016/j.conengprac.2017.03.014

Cited by 9 publications

(6 citation statements)

References 17 publications

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“…This hypersonic vehicle utilizes an offset of mass center to create a constant angle of attack, which can generate sufficient lift during peak heating and peak deceleration. 8,34 Neglecting centripetal acceleration from the Earth rotation, the hypersonic vehicle can be regarded as a point mass and the standard simplified equations of motion are 12,34 = V r cos sin cos ,…”

Section: Entry Problemmentioning

confidence: 99%

“…ΔC D , ΔC L , and Δ are bounded parameter uncertainties. Therefore, the error dynamic model (12) can be rewritten as…”

Section: Problem Formulationmentioning

confidence: 99%

“…This hypersonic vehicle utilizes an offset of mass center to create a constant angle of attack, which can generate sufficient lift during peak heating and peak deceleration . Neglecting centripetal acceleration from the Earth rotation, the hypersonic vehicle can be regarded as a point mass and the standard simplified equations of motion are

\overset{θ}{true} = \frac{V}{r} \frac{\cos γ \sin ψ}{\cos ϕ},

\overset{ϕ}{true} = \frac{V}{r} \cos γ \cos ψ,

\overset{r}{true} = V \sin γ,

\overset{V}{true} = - D - sans-serifg \sin γ,

\overset{γ}{true} = \frac{1}{V} ([], L \cos σ - ((), sans-serifg - \frac{V^{2}}{r}) \cos γ),

\overset{ψ}{true} = \frac{1}{V \cos γ} ([], L \sin σ + \frac{V^{2}}{r} \cos^{2} γ \sin ψ \tan ϕ),

\overset{X}{true} = V \cos γ

with

D = \frac{1}{2} ρ V^{2} \frac{S}{m} C_{D}, L = \frac{1}{2} ρ V^{2} \frac{S}{m} C_{L}, ρ = ρ_{0} \exp^{- \frac{h}{h_{s}}},

…”

Section: Entry Problemmentioning

confidence: 99%

“…With great success in application, trajectory tracking method has become a baseline for entry guidance approach . Recently, a great number of control approaches are investigated to address the trajectory tracking problem, such as PID, linear quadratic regular, active disturbance rejection control, incremental dynamic inversion technique, and sliding mode control (SMC) . However, the closed‐loop guidance systems in the preceding literature are only asymptotic stable.…”

Section: Introductionmentioning

confidence: 99%

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Finite‐time trajectory tracking control for entry guidance

Shen

Xia

Zhang

et al. 2018

Intl J Robust & Nonlinear

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Summary In this paper, the trajectory tracking guidance problem is investigated for entry vehicle in the presence of uncertainty. First, a robust nonsingular fast terminal sliding mode control law is designed to guarantee the finite‐time tracking performance under uncertainty. Then, to eliminate the need of prior information about uncertainty and mitigate the chattering, a novel adaptive nonsingular fast terminal sliding mode control is proposed by employing adaptive parameter tuning law. Furthermore, with the help of designed adaptation mechanism, the proposed adaptive nonsingular fast terminal sliding mode control can achieve finite‐time convergence of both tracking errors and parameter estimation errors simultaneously. Finally, numerical simulations are given to demonstrate the effectiveness and high‐precision tracking performance of the proposed controllers.

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Section: Entry Problemmentioning

confidence: 99%

“…ΔC D , ΔC L , and Δ are bounded parameter uncertainties. Therefore, the error dynamic model (12) can be rewritten as…”

Section: Problem Formulationmentioning

confidence: 99%

\overset{θ}{true} = \frac{V}{r} \frac{\cos γ \sin ψ}{\cos ϕ},

\overset{ϕ}{true} = \frac{V}{r} \cos γ \cos ψ,

\overset{r}{true} = V \sin γ,

\overset{V}{true} = - D - sans-serifg \sin γ,

\overset{γ}{true} = \frac{1}{V} ([], L \cos σ - ((), sans-serifg - \frac{V^{2}}{r}) \cos γ),

\overset{ψ}{true} = \frac{1}{V \cos γ} ([], L \sin σ + \frac{V^{2}}{r} \cos^{2} γ \sin ψ \tan ϕ),

\overset{X}{true} = V \cos γ

with

D = \frac{1}{2} ρ V^{2} \frac{S}{m} C_{D}, L = \frac{1}{2} ρ V^{2} \frac{S}{m} C_{L}, ρ = ρ_{0} \exp^{- \frac{h}{h_{s}}},

…”

Section: Entry Problemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Finite‐time trajectory tracking control for entry guidance

Shen

Xia

Zhang

et al. 2018

Intl J Robust & Nonlinear

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“…10 Hence, reference-trajectory tracking is the preferred scheme for the Mars landing missions, and a great number of algorithms have been proposed to address Mars entry trajectory tracking problem. [11][12][13][14][15][16][17] Note that the aforementioned literature scarcely consider the uncertainties. However, the existence of uncertainties and parameter perturbations are inevitable in the model of Mars vehicle.…”

Section: Introductionmentioning

confidence: 99%

Adaptive sliding‐mode control for Mars entry trajectory tracking with finite‐time convergence

Shen

Xia

et al. 2018

Intl J Robust & Nonlinear

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This paper presents a novel adaptive sliding-mode control (ASMC) method for Mars entry guidance and the finite-time convergence in the presence of large uncertainties can be guaranteed. With the help of gain adaptive law, the nonoverestimating value of control gains can be achieved, and then, the chattering can be attenuated by the proposed ASMC method. Meanwhile, the extended state observer is introduced to estimate and compensate for uncertainties and the nonoverestimating problem is resolved further. In addition, the proposed method does not require any knowledge on the upper bound of uncertainty, which yields to be used in practical systems. Finally, the numerical simulation results are given to demonstrate the effectiveness of the proposed guidance law.

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