Survey of Atmosphere Re-Entry Guidance and Control Methods

Wingrove, R. C.

doi:10.2514/3.1987

Cited by 81 publications

(18 citation statements)

References 12 publications

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“…Various methods have been suggested and implemented for atmospheric guidance of such trajectories. Most fall into one of three broad categories [2,3]: numeric predictorcorrectors [4][5][6][7][8][9], analytic predictor-correctors [10,11], and reference-following controllers [12][13][14][15][16]. This Note presents a method, primarily intended for use under the latter category, that generates analytically a reference drag profile for the first entry portion of a skip entry when the exit conditions (and the initial conditions) are known.…”

Section: Introductionmentioning

confidence: 99%

Analytic Development of a Reference Trajectory for Skip Entry

Garcia-Llama

2011

Journal of Guidance, Control, and Dynamics

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Section: Introductionmentioning

confidence: 99%

Analytic Development of a Reference Trajectory for Skip Entry

Garcia-Llama

2011

Journal of Guidance, Control, and Dynamics

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“…The various guidance and control concepts so far considered may be divided into two general categories [4]: first guidance using predictive capabilities and second guidance using a nominal trajectory. In the latter method the state variables along the nominal path are precomputed and stored on-board.…”

Section: Introductionmentioning

confidence: 99%

Comparison of guidance concepts for a semi-ballistic reentry capsule

Zimmermann¹,

Burkhardt²,

Schoettle³

1996

Guidance, Navigation, and Control Conference

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Three guidance concepts based on fast-time prediction of the flight path have been analyzed for the semiballistic reentry vehicle COLIBRI. The latter vehicle is a small capsule proposed as a carrier for reentry experiments. This vehicle is capable of limited aerodynamic maneuverability. Thus, a controlled return to a specified destination subject to path constraints is possible. The robustness of each of the selected guidance concepts has been evaluated with respect to both deviations of the deorbit conditions and variations of the target coordinates. In addition, the computational effort necessary for each guidance method has been analyzed. A real-time implementation of the algorithms in on-board computers is possible. The guidance concept minimizing control efforts has been found to be a favorable option to guide a semiballistic reentry capsule regarding both the target deviations achieved and the control effort necessary. For all 3-DOF simulations it is assumed that the vehicle state can be observed and is well known. AbstractThree guidance concepts based on fast-time prediction of the flight path have been analyzed for the semiballistic reentry vehicle COLIBRI. The latter vehicle is a small capsule proposed as a carrier for reentry experiments. This vehicle is capable of a limited aerodynamic maneuverability. Thus, a controlled return to a specified destination subject to path constraints is possible.The robustness of each of the selected guidance concepts has been evaluated with respect to both deviations of the deorbit conditions and variations of the target coordinates. In addition, the computational effort necessary for each guidance method has been analyzed. A real-time implementation of the algorithms in on-board computers is possible. The guidance concept minimizing control efforts has been found to be a favorable option to guide a semi-ballistic reentry capsule regarding both the target deviations achieved and the control effort necessary. For all 3DOF simulations it is assumed that the vehicle state can be observed and is well known.

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“…Since altitude influences drag, altitude rate serves well as a first-order control dampening term to prevent overshoot and oscillation as the drag error converges. 6 It is from these realizations that the Apollo final phase algorithm was conceived. This algorithm controls to a terminal downrange and velocity target using pre-derived influence coefficients with respect to perturbations about a reference trajectory.…”

Section: B Range Control Logicmentioning

confidence: 99%

“…This overcontrol gain also improves the robustness of the algorithm for trajectory states that differ sufficiently from the reference trajectory that the linearized equations of motion may no longer be as accurate. 6 The commanded bank angle (Ф C ) is then calculated using the vertical L/D commanded and the estimated L/D as in Eq. 3.…”

Section: B Range Control Logicmentioning

confidence: 99%

Entry Guidance for the 2011 Mars Science Laboratory Mission

Mendeck

Craig

2011

AIAA Atmospheric Flight Mechanics Conference

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The 2011 Mars Science Laboratory will be the first Mars mission to attempt a guided entry to safely deliver the rover to a touchdown ellipse of 25 km x 20 km. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control the range flown. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range error while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last nine years. Key dispersions driving deploy ellipse and altitude performance are identified. Performance sensitivities including attitude initialization error and the velocity of transition from range control to heading alignment are presented.= heading alignment overcontrol gain R = current downrange to target R c = current crossrange to target R dep = parachute deploy range bias R p = current predicted range flown R ref = reference range to target = current altitude rate = reference altitude rate

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Survey of Atmosphere Re-Entry Guidance and Control Methods

Cited by 81 publications

References 12 publications

Analytic Development of a Reference Trajectory for Skip Entry

Analytic Development of a Reference Trajectory for Skip Entry

Comparison of guidance concepts for a semi-ballistic reentry capsule

Entry Guidance for the 2011 Mars Science Laboratory Mission

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