Predictor-corrector guidance algorithm for use in high-energy aerobraking system studies

1992 ◽  
Vol 15 (3) ◽  
pp. 672-678 ◽  
Author(s):  
Robert D. Braun ◽  
Richard W. Powell
Keyword(s):  
High Energy ◽  
Guidance Algorithm ◽  
Predictor Corrector

Analytical predictor–corrector entry guidance for hypersonic gliding vehicles

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Huatao Chen ◽  
Kun Zhao ◽  
Juan L.G. Guirao ◽  
Dengqing Cao
Keyword(s):  
Feedback Control ◽  
Velocity Variation ◽  
Analytical Relation ◽  
Aerodynamic Load ◽  
Quasi Equilibrium ◽  
Bank Angle ◽  
Entry Guidance ◽  
Guidance Algorithm ◽  
Predictor Corrector ◽  
Guidance Problem

AbstractFor the entry guidance problem of hypersonic gliding vehicles (HGVs), an analytical predictor–corrector guidance method based on feedback control of bank angle is proposed. First, the relative functions between the velocity, bank angle and range-to-go are deduced, and then, the analytical relation is introduced into the predictor–corrector algorithm, which is used to replace the traditional method to predict the range-to-go via numerical integration. To eliminate the phugoid trajectory oscillation, a method for adding the aerodynamic load feedback into the control loop of the bank angle is proposed. According to the quasi-equilibrium gliding condition, the function of the quasi-equilibrium glide load along with the velocity variation is derived. For each guidance period, the deviation between the real-time load and the quasi-equilibrium gliding load is revised to obtain a smooth reentry trajectory. The simulation results indicate that the guidance algorithm can adapt to the mission requirements of different downranges, and it also has the ability to guide the vehicle to carry out a large range of lateral maneuvers. The feedback control law of the bank angle effectively eliminates the phugoid trajectory oscillation and guides the vehicle to complete a smooth reentry flight. The Monte Carlo test indicated that the guidance precision and robustness are good.

scholarly journals Analytical Predictor-Corrector Guidance Algorithm Based on Drag Modulation Flight Control System for Mars Aerocapture

2018 ◽  
Vol 2018 ◽  
pp. 1-12 ◽  
Author(s):  
Yu-ming Peng ◽  
Bo Xu ◽  
Bao-dong Fang ◽  
Han-lun Lei
Keyword(s):  
Control System ◽  
Flight Control ◽  
Large Scale ◽  
Piecewise Linear ◽  
Scale Space ◽  
Flight Control System ◽  
Initial State ◽  
Aerodynamic Parameter ◽  
Guidance Algorithm ◽  
Predictor Corrector

Aerocapture is one of the essential technologies for future large-scale space exploration missions, as it can significantly reduce the Δv and fuel requirement. The performance and robustness of two different aerocapture control methods are analyzed around Mars exploration, and then an analytic predictor-corrector guidance algorithm for drag modulation flight control system is proposed. A piecewise linear function between velocity and flight path angle is established by appropriate approximations and assumptions, and then the state at atmosphere interface can be predicted by an analytical method; therefore, aerocapture guidance can be realized by feedback control. Numerical simulation is used to evaluate performance and robustness of the algorithm. The simulation results show that the guidance algorithm is accurate and robust, which can effectively overcome the influence of atmospheric density error, aerodynamic parameter error, and initial state uncertainty.

scholarly journals Algorithm of Reentry Guidance for Hypersonic Vehicle Based on Lateral Maneuverability Prediction

2020 ◽  
Vol 38 (3) ◽  
pp. 523-532
Author(s):  
Guoxiang Shi ◽  
Ke Zhang ◽  
Pei Wang ◽  
Zhiguo Han
Keyword(s):  
Mean Value ◽  
Hypersonic Vehicle ◽  
Parameters Estimation ◽  
Initial State ◽  
Bank Angle ◽  
Aerodynamic Parameters ◽  
Guidance Algorithm ◽  
Predictor Model ◽  
Process Disturbances ◽  
Predictor Corrector

Aiming at the problem that the traditional error corridor guidance method has poor adaptability in lateral guidance of predictor-corrector guidance, an algorithm of reentry guidance based on the vehicle lateral maneuverability prediction is proposed without increasing the calculation too much. The lateral component mean value of lift at reentry is calculated by using the bank angle magnitude function obtained from longitudinal guidance. According to the above-mentioned, a crossrange corridor with dynamic boundary constraint is designed to control bank angle reversal timing. Online parameters estimation is introduced to suppress the influence of the atmospheric density and aerodynamic parameters disturbance on the predictor model. The CAV-L, a kind of hypersonic vehicle, is used as an object to carry out reentry guidance simulation. The results show that the guidance algorithm can effectively guide vehicle to target for reentry missions of different range, the landing point error are small and the guidance effect is stable. The simulated results via Monte Carlo method verify that the guidance algorithm has a good adaptability and robustness to initial state deviations and process disturbances.

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