Optimal Lunar Landing Trajectory Design for Hybrid Engine

Cho, Dong−Hyun; Kim, Dong-Hoon; Leeghim, Henzeh

doi:10.1155/2015/462072

Cited by 9 publications

(4 citation statements)

References 11 publications

(19 reference statements)

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“…Hybrid uncertainty-based design optimization has been used to show that a hybrid propulsion system would have been well capable of substituting for the liquid ascent propulsion module of the Apollo missions [24]. Cho et al [25] optimized the landing trajectory of a lunar lander with an initial mass of 300 kg. Starting from a lunar parking orbit (100 km circular orbit), the optimized lander would be able to land 160.6 kg on the lunar surface while consuming 139.4 kg of propellant.…”

Section: Planetary and Lunar Lander Or Ascent Vehiclesmentioning

confidence: 99%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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Hybrid rocket propulsion, first demonstrated by the Russian GIRD-09 rocket in 1933, combines liquid oxidizer and solid fuel for thrust generation. Despite numerous advantages, such as enhanced safety, controllability, and potential environmental benefits, hybrid propulsion has yet to achieve its full potential in space applications. In recent years, the research on hybrid propulsion has gained enormous momentum in both academia and industry. Recent accomplishments such as the altitude record for student rockets (64 km), the launch of the first electric pump-fed hybrid rocket, and a successful 25 s hovering test highlight the potential of hybrid rockets. However, although the hybrid community is growing constantly, industrial utilizations and in-space validations do not yet exist. In this work, we reassess the possibilities of hybrid rocket engines by presenting potential fields of applications from the literature. Most importantly, we identify the technical challenges that hinder the breakthrough of hybrid propulsion in the space sector and evaluate the technologies and approaches necessary to bridge the gaps in hybrid rocket development.

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Section: Planetary and Lunar Lander Or Ascent Vehiclesmentioning

confidence: 99%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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“…e gravitational acceleration is assumed to be constant, and the downrange angle is assumed to be very small in the range of 0.5 degrees. For the computation of trajectory state parameters, this simplified dynamics (equations ( 8)-( 12)), as suggested in [33], is used.…”

Section: Mathematical Formulationmentioning

confidence: 99%

Soft Landing Parameter Measurements for Candidate Navigation Trajectories Using Deep Learning and AI-Enabled Planetary Descent

Borse

Patil

Kumar

et al. 2022

Mathematical Problems in Engineering

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Smart instruments, sensors, and AI technologies are playing an important role in many fields such as medical science, Earth science, astronomy physics, and space study. This article attempts to study the role of sensors, instruments, and AI (artificial intelligence) based smart technologies in lunar missions during navigation of trajectories. Lunar landing missions usually divide the power descent phase into three to four sub-phases. Each sub-phase has its own set of initial and final constraints for the desired system state. The landing systems depend on human competencies for making the most crucial landing decisions. Trajectory planning and designing are very significant in lunar missions, and it requires inputs with precision. The manual systems may be prone to errors. In contrast, AI and smart sensor-based measurements give an accurate idea about the trajectory paths and make appropriate decisions where manual systems may turn into disasters. The manual systems are either pre-fed or have manual controls to guide the trajectory. For autonomous landing problems, trajectory design is a very crucial task. The automated trajectories play a vital role in the measurement and prediction of landing state parameters of the space rocket. Nowadays, sensors, intelligent instruments, and the latest technologies go hand in hand to devise measurement methods for accurate calculations and make appropriate decisions during landing space rockets at the designated destination. Space missions are very expensive and require huge efforts to design smart systems for navigation trajectories. This paper attempts to design all possible candidates of reference navigation trajectories for autonomous lunar descent by employing 3D non-linear system dynamics with randomly chosen initial state conditions. The generated candidates do not rely on multiple hops and thus exhibit an ability to serve autonomous missions. This research work makes use of smart sensors and AI federated techniques for smartly training the system to serve the ultimate purpose. The trajectories are simulated in an automated simulating environment to perform exhaustive analyses. The results accurately approximate the trajectories analogous to their numerical counterparts and converge to their measured final state estimates. The generation rate of feasible trajectories measures the accuracy of the algorithm. The algorithm’s accuracy is near 0.87 for 100 sec flight time, which is reasonable.

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“…Liu et al 5,6 studied the landing guidance control by using the optimal lunar landing trajectory. In addition, several researchers have studied to find the optimal initial states of powered descent phase by using impulsive thrusters at the initial time of powered descent phase 7 and changing the initial phase angle of powered descent phase. 8 Note that most of these methods have focused on the powered descent phase without considering the final constraints for the vertical landing.…”

Section: Introductionmentioning

confidence: 99%

An optimal trajectory design for the lunar vertical landing

Leeghim

Cho²,

Kim³

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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A research for designing the optimal lunar vertical landing trajectory to reduce the total energy or mass of propellant is addressed in this paper. Most of these problems can be divided into two phases: breaking and approach phase. The optimal landing trajectory in general does not consider the pitch-up motion so that the landing problem has been only solved in the breaking phase. For this reason, there are some attempts to find the optimal trajectory including the final vertical landing phase by including the equations of angular motion of the vehicle. However, the optimal solution using this approach depends on the scale factor of a cost function because the cost function consists of two different mechanical parameters such as the final mass and total control torque. The final control constraints are augmented for vertical lunar landing instead of the equations of angular motion. The obtained optimal trajectory has an additional positive effect of the image acquisition as well as the final vertical landing.

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Optimal Lunar Landing Trajectory Design for Hybrid Engine

Cited by 9 publications

References 11 publications

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Soft Landing Parameter Measurements for Candidate Navigation Trajectories Using Deep Learning and AI-Enabled Planetary Descent

An optimal trajectory design for the lunar vertical landing

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