Mars atmospheric entry trajectory optimization with maximum parachute deployment altitude using adaptive mesh refinement

Zhao, Jingcheng; Li, Shuang

doi:10.1016/j.actaastro.2019.03.027

Cited by 26 publications

(12 citation statements)

References 28 publications

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“…The ascent profile, with the most important phases and altitudes that the vehicle goes through, can be seen in Figure 2. Moreover, the gravity field of Mars has been simulated using values of Sharaf and Selim [5], and the Martian atmosphere has been simulated following the same exponential model as Zhao and Li [6] (p. 3).…”

Section: Ascentmentioning

confidence: 99%

From the Martian Surface to Its Low Orbit in a Reusable Single-Stage Vehicle—Charon

Gaffarel¹,

Kadhum²,

Fazaeli³

et al. 2021

Aerospace

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With Mars colonisation becoming a reality for the near future, it is of importance to analyse how crew and cargo can be transported between Earth and a colony on Mars. This article is a feasibility and design study of a launch vehicle whose mission is to shuttle crew and cargo from Low Mars Orbit to a colony on the Martian surface. A single-stage reusable rocket has been selected to fulfil this mission, code-named Charon. The mission profile of such a vehicle was created, leading to a Maximum Growth Allowance (MGA) Delta-V budget of 6.2 km/s. With the mission profile in mind, each subsystem underwent a preliminary design. With reliability and maintainability in mind, subsystems were designed for redundancy and modularity, and an abort system was included for an added level of safety. The iterative design process resulted in a vehicle with a MGA mass of 198.7 tons, capable of transporting 1200 kg of cargo and a crew of 6 people to a 500 km orbit and back. The preliminary design of the vehicle is deemed safe. Following a fault tree analysis, the Single Launch Loss of Mission, Vehicle and Crew (SL-LOM, SL-LOV, SL-LOC) probabilities are computed to be of 0.975%, 0.12%, and 0.079%. Finally, from the vehicle’s constraints on the base, the feasibility of the project has been reflected upon. It is deemed that such a concept is of high interest only when the base is already operational, due to the launch and maintenance infrastructure that it requires, as well as the power it requires from the Martian base.

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Section: Ascentmentioning

confidence: 99%

From the Martian Surface to Its Low Orbit in a Reusable Single-Stage Vehicle—Charon

Gaffarel¹,

Kadhum²,

Fazaeli³

et al. 2021

Aerospace

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“…The hp method has been favored by researchers due to its efficient solving ability and the flexibility of the algorithm. In recent years, many scholars have carried out extensive research on it and greatly developed its related theory and application [26][27][28][29][30]. Li et al [31,32] apply the adaptive hp method to the field of trajectory optimization, which effectively solve this kind of complex nonlinear optimization problem, and obtain satisfactory solution accuracy.…”

Section: Introductionmentioning

confidence: 99%

An improved adaptive hp mesh refinement method in solving optimal control problems

Luo

Zhou

et al. 2022

Optim Control Appl Methods

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The adaptive hp pseudospectral method is an effective choice in solving the optimal control problem. In order to improve the computing efficiency of the adaptive hp method, an improved adaptive hp mesh refinement method is proposed in this paper. There are two main cores in this method. The first is to refine the mesh in advance based on the change rate of the control, so that the algorithm can more efficiently deal with the optimal control problem with discontinuous control. And the second is to based on the accumulation of curvature values to ensure that those positions that need to be refined more can be quickly allocated to more mesh points. These two are combined with each other to improve the solving efficiency of the algorithm proposed in this paper, which shortens the required computing time. In addition, the convergence of the algorithm is proved in this paper. The simulation results show the effectiveness and superiority of the algorithm proposed in this paper.

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“…In recent years, extensive applications of direct methods can be found in the context of flight vehicle trajectory optimization and robotic motion planning problems in difficult environments [8]- [10]. For instance, a direct collocation method was adopted in [8] in order to calculate the optimal flight trajectory for an entry vehicle during the Mars entry phase. Path constrains were imposed such that the vehicle can fly along a restricted corridor.…”

Section: Introductionmentioning

confidence: 99%

Solving Constrained Trajectory Planning Problems Using Biased Particle Swarm Optimization

Tsourdos

Chai

et al. 2021

IEEE Trans. Aerosp. Electron. Syst.

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Constrained trajectory optimization has been a critical component in the development of advanced guidance and control systems. An improperly planned reference trajectory can be a main cause of poor online control performance. Due to the existence of various mission-related constraints, the feasible solution space of a trajectory optimization model may be restricted to a relatively narrow corridor, thereby easily resulting in local minimum or infeasible solution detection. In this work, we are interested in making an attempt to handle the constrained trajectory design problem using a biased particle swarm optimization approach. The proposed approach reformulates the original problem to an unconstrained multi-criterion version by introducing an additional normalized objective reflecting the total amount of constraint violation. Besides, to enhance the progress during the evolutionary process, the algorithm is equipped with a local exploration operation, a novel-bias selection method, and an evolution restart strategy. Numerical simulation experiments, obtained from a constrained atmospheric entry trajectory optimization example, are provided to verify the effectiveness of the proposed optimization strategy. Main advantages associated with the proposed method are also highlighted by executing a number of comparative case studies.

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Mars atmospheric entry trajectory optimization with maximum parachute deployment altitude using adaptive mesh refinement

Cited by 26 publications

References 28 publications

From the Martian Surface to Its Low Orbit in a Reusable Single-Stage Vehicle—Charon

From the Martian Surface to Its Low Orbit in a Reusable Single-Stage Vehicle—Charon

An improved adaptive hp mesh refinement method in solving optimal control problems

Solving Constrained Trajectory Planning Problems Using Biased Particle Swarm Optimization

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