Probability-based hazard avoidance guidance for planetary landing

Xu, Yuan; Yu, Zhengshi; Cui, Pingyuan; Xu, Rui; Zhu, Shengying; Cao, Menglong; Luan, Enjie

doi:10.1016/j.actaastro.2017.11.039

Cited by 18 publications

(4 citation statements)

References 28 publications

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“…The parameter matrices 𝑃𝑃 𝑟𝑟 and 𝑃𝑃 𝑉𝑉 represents the weight matrices of 𝑟𝑟 and 𝑣𝑣 respectively. For simplicity, the parameter matrix 𝑃𝑃 𝑉𝑉 is assumed as identity matrix 10,11 , and the parameter matrix 𝑃𝑃 𝑟𝑟 is further analyzed.…”

Section: Setting Of the Parameter Matrices 𝑷𝑷 𝒓𝒓 And 𝑷𝑷 𝑽𝑽mentioning

confidence: 99%

“…2) The initial velocity of the spacecraft in the landing process is generally small and close to zero because of the need to synchronize with the rotation of the small celestial body during the approach segment 13 . Therefore, the setting of the parameter matrix 𝑃𝑃 𝑟𝑟 is analyzed with the assumption that the initial velocity of the spacecraft is generally less than 1m/s 7,10,11 .…”

Section: Setting Of the Parameter Matrices 𝑷𝑷 𝒓𝒓 And 𝑷𝑷 𝑽𝑽mentioning

confidence: 99%

“…In the APF method, the position of the spacecraft approaches to the target point [0,0,0] eventually. Since the gravitational acceleration of the small celestial body is much less than the thrust acceleration of the spacecraft 11 , the maximum value of the thrust acceleration is around the initial position according to Equation (11). Therefore, the recommended value of 𝑝𝑝 1 is set to guarantee the following relation…”

Section: Setting Of the Parameter Matrices 𝑷𝑷 𝒓𝒓 And 𝑷𝑷 𝑽𝑽mentioning

confidence: 99%

“…It is used to decrease the spacecraft velocity to zero when the spacecraft reaches the target point. In order to introduce the state uncertainty of spacecraft into APF, Yuan et al 11 established the repulsive potential function based on the collision probability between spacecraft and obstacles in order to improve the safety of trajectory. Wang 12 added the spacecraft state uncertainty to the relative distance between the spacecraft and obstacles in the repulsive potential function.…”

Section: Introductionmentioning

confidence: 99%

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Parameter setting and analysis for the artificial potential functions in the application of small celestial bodies landing trajectory planning

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The targets of landing missions on small celestial bodies usually have high scientific value but complex terrain. Therefore, there are high demands for the landing trajectory planning method with regard to the safety and precise landing. The artificial potential function method is one of the commonly used methods in trajectory planning for small celestial body landing. It is performed by applying attractive force form the target and repulsive force from the obstacles to the moving spacecraft. The attractive and repulsive forces are generated by the corresponding potential functions, which involves several parameters needed to be determined. Improper parameters may lead to low efficiency of trajectory calculation, collision with obstacles or failure of reaching the target. However, the parameters in the artificial potential functions are usually set as empirical values without consideration of different application scenarios. In this paper, the setting methods of the weight matrices 𝑃𝑟 and 𝑃𝑉 in the attractive potential function, the parameter matrix 𝛭 in the Lyapunov function and the parameters 𝑘1 and 𝑘2 in the Gaussian-type repulsive potential function are studied, and several simulation experiments are conducted to verify the parameter values. And suggestions are given on the setting of these parameters. Keywords: artificial potential function, parameter setting, landing trajectory planning.

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Section: Setting Of the Parameter Matrices 𝑷𝑷 𝒓𝒓 And 𝑷𝑷 𝑽𝑽mentioning

confidence: 99%

Section: Setting Of the Parameter Matrices 𝑷𝑷 𝒓𝒓 And 𝑷𝑷 𝑽𝑽mentioning

confidence: 99%