Bio-inspired guidance method for a soft landing on a Near-Earth Asteroid

Najera, R. Valenzuela; Everett, Louis e.; Ortega, Angel; Choudhuri, Ahsan; Flores-Abad, Ángel

doi:10.1016/j.asr.2020.07.048

Cited by 6 publications

(4 citation statements)

References 38 publications

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“…Nevertheless, there are limits for such improvement, which are related to factor ε. Generally speaking, when TOF is short, different values of ε, except for ε = 4 6 , have distinctive impact on the four control performance indices, as we can see that the curves on the left-hand side are more scattered in response to different values of ε. As TOF grows larger, curves are gathering, which means the impact of ε diminishes while that of TOF becomes dominant, i.e., the larger the TOF, the better the control performances.…”

Section: Baseline Trajectorymentioning

confidence: 86%

“…However, in real practice, a very long duration of time for the rendezvous is sometimes not welcome, especially in emergency cases, so one should make balance with other design parameters. From Figures 1-3, it is very interesting to see that when ε = 4 6 = 2 3 , the control performance indices, r e and v e , are much smaller than other values of ε for each N, and change little as the TOF varies (a line parallel with the TOF axis). Note that ε = 2 3 ≈ 0.667 is very close to the golden ratio (0.618), which we can see also plays an impressive role in our problem.…”

Section: Baseline Trajectorymentioning

confidence: 97%

“…This phase relies not on Earth-based telemetry, but on relative measurements and autonomous control by the spacecraft itself. It paves the way for even closer observational phases or landing [4]. Since the key problems and conditions are identical to the near-Earth rendezvous problem [5], where constraints are imposed on both the final relative position and velocity, the control issue of the transfer to the vicinity of an asteroid can be regarded as a rendezvous problem in the heliocentric two-body dynamics background, where the Tschauner-Hempel (TH) equations [5] provide good, approximated solutions to the first order for elliptical orbits.…”

Section: Introductionmentioning

confidence: 94%

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Time-Fixed Glideslope Guidance for Approaching the Proximity of an Asteroid

Wang

Lin

et al. 2021

Aerospace

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The guidance and control problem of spacecraft approaching an asteroid using constant continuous thrust is studied in this work. The range of interest is from hundreds of kilometers to several kilometers, in which relative measurements of much higher accuracy than based on Earth can be used to facilitate further hovering or landing operations. Time-fixed glideslope guidance algorithm is improved by introducing a substitute of an existing control parameter and combined with elliptical relative orbital dynamics to rendezvous the spacecraft with a prescribed location in the proximity of a given asteroid. A vast range of values for the control parameters are explored and suitable combinations are found. To fully validate the robustness and accuracy of the proposed control algorithm, Monte Carlo simulations are done with the navigational error and implementation error considered.

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Section: Baseline Trajectorymentioning

confidence: 86%

Section: Baseline Trajectorymentioning

confidence: 97%

Section: Introductionmentioning

confidence: 94%

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Time-Fixed Glideslope Guidance for Approaching the Proximity of an Asteroid

Wang

Lin

et al. 2021

Aerospace

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“…To avoid the above situation, this paper uses a biologically inspired trajectory planning algorithm called the tau theory. This method is widely used in various tasks such as trajectory planning and motion planning [16][17][18][19][20]. It can generate multiple trajectories with consistent time and has the advantages of continuous smooth velocity curve and simple optimization parameters.…”

Section: Introductionmentioning

confidence: 99%

Four-Dimensional Trajectory Planning Algorithm for Fixed-Wing Aircraft Formation Based on Improved Hunter—Prey Optimization

Wei

Fan

2023

Electronics

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The aircraft four-dimensional trajectory planning is an important technology for multiple aircraft to achieve cooperation. However, the current four-dimensional trajectory planning technology is mainly used for civil aviation and helicopters and is difficult to meet the requirements of fixed-wing aircraft. This paper proposed a four-dimensional trajectory planning algorithm for a fixed-wing aircraft formation, considering the speed range, turning radius and maximum overload. The improved tau-J strategy (ITJS) is used to generate the four-dimensional trajectory of the aircraft. This strategy is a bio-inspired trajectory planning algorithm that can generate a four-dimensional trajectory with continuous acceleration. Furthermore, the improved hunter–prey optimization (IHPO) algorithm is used to optimize the trajectory to make the generated trajectory meet the constraints and speed up the algorithm convergence. This algorithm improves the updated strategy and initialization strategy based on the hunter–prey optimization (HPO) algorithm, which prevents the algorithm from falling into local optima. The results of the benchmark test function show that the optimization result of the algorithm is improved by more than 10% compared with the original HPO algorithm. The simulation results show that the proposed algorithm jumps out of local optima and generates a trajectory that meets the constraints.

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