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 Skip Re-Entry Trajectory Detection and Guidance for Maneuvering Vehicles

Sensors ◽  
2020 ◽  
Vol 20 (10) ◽  
pp. 2976
Author(s):  
Hongqiang Sun ◽  
Shuguang Zhang
Keyword(s):  
Analytical Relationship ◽  
Quasi Equilibrium ◽  
Bank Angle ◽  
Control Solution ◽  
Entry Guidance ◽  
Path Constraints ◽  
Path Constraint ◽  
Guidance Algorithm ◽  
Feedback Data ◽  
Altitude Estimation

The re-entry trajectory of maneuvering vehicles with medium to high hypersonic lift-to-drag ratios is generally planned using quasi-equilibrium flight conditions known from Space Shuttles. They may exhibit an oscillation re-entry phenomenon termed skip re-entry when related components or sensors fail. However, conventional re-entry guidance only considers quasi-equilibrium flights and ignores the possibility of the occurrence of an unexpected skip trajectory; this may lead to the failure of the re-entry mission due to a lack of a corresponding guidance strategy. However, the detection of a skip trajectory is the necessary reference for the decision-making of calling a related guidance algorithm that helps improve the safety of vehicle re-entry. Herein, a skip re-entry detection and trajectory control solution is proposed to play an emergency role in the cases of skip re-entry. Firstly, the oscillation frequency characteristics of the linearized re-entry motion equation of a vehicle are analyzed, and an approximate analytical relationship is constructed for skip altitude estimation. Then, the residual deviation between the altitude feedback data and the estimated skip altitude is calculated and compared with the threshold to determine the occurrence of skip re-entry. In addition, a method for controlling the skip re-entry trajectory with the range extension is developed by controlling the bank angle with a fixed angle of attack profile, satisfying the path constraint requirements. The results indicate that the method effectively performs skip re-entry detection and that it can help extend the range of the vehicles in abnormal re-entry scenarios, keeping the flight within the path constraints and guiding it to the expected location.

scholarly journals Adaptive Entry Guidance for Hypersonic Gliding Vehicles Using Analytic Feedback Control

2020 ◽  
Vol 2020 ◽  
pp. 1-18
Author(s):  
Xunliang Yan ◽  
Peichen Wang ◽  
Shaokang Xu ◽  
Shumei Wang ◽  
Hao Jiang
Keyword(s):  
Feedback Control ◽  
Quasi Equilibrium ◽  
Dynamic Adjustment ◽  
Computationally Efficient ◽  
Bank Angle ◽  
Vehicle Data ◽  
Terminal Constraints ◽  
Flight Path Angle ◽  
And Performance ◽  
Almost All

This paper presents an adaptive, simple, and effective guidance approach for hypersonic entry vehicles with high lift-to-drag (L/D) ratios (e.g., hypersonic gliding vehicles). The core of the constrained guidance approach is a closed-form, easily obtained, and computationally efficient feedback control law that yields the analytic bank command based on the well-known quasi-equilibrium glide condition (QEGC). The magnitude of the bank angle command consists of two parts, i.e., the baseline part and the augmented part, which are calculated analytically and successively. The baseline command is derived from the analytic relation between the range-to-go and the velocity to guarantee the range requirement. Then, the bank angle is augmented with the predictive altitude-rate feedback compensations that are represented by an analytic set of flight path angle needed for the terminal constraints. The inequality path constraints in the velocity-altitude space are translated into the velocity-dependent bounds for the magnitude of the bank angle based on the QEGC. The sign of the bank command is also analytically determined using an automated bank-reversal logic based on the dynamic adjustment criteria. Finally, a feasible three-degree-of-freedom (3DOF) entry flight trajectory is simultaneously generated by integrating with the real-time updated command. Because no iterations and no or few off-line parameter adjustments are required using almost all analytic processing, the algorithm provides remarkable simplicity, rapidity, and adaptability. A considerable range of entry flights using the vehicle data of the CAV-H is tested. Simulation results demonstrate the effectiveness and performance of the presented approach.

scholarly journals Accurate predictor–corrector skip entry guidance for low lift-to-drag ratio spacecraft

2018 ◽  
Author(s):  
Y. Enmi ◽  
W. Qian ◽  
K. He ◽  
D. Di
Keyword(s):  
Trajectory Planning ◽  
Closed Loop ◽  
Initial Value ◽  
Bank Angle ◽  
Air Density ◽  
Entry Guidance ◽  
Skip Entry ◽  
Predictor Corrector ◽  
Drag Ratio ◽  
Lift To Drag Ratio

This paper develops numerical predictor–corrector skip en try guidance for vehicles with low lift-to-drag L/D ratio during the skip entry phase of a Moon return mission. The guidance method is composed of two parts: trajectory planning before entry and closed-loop gu idance during skip entry. The result of trajectory planning before entry is able to present an initial value for predictor–corrector algorithm in closed-loop guidance for fast convergence. The magnitude of bank angle, which is parameterized as a linear function of the range-to-go, is modulated to satisfy the downrange requirements. The sign of the bank ang le is determined by the bank-reversal logic. The predictor-corrector algorithm repeatedly applied onboard in each guidance cycle to realize closed-loop guidance in the skip entry phase. The effectivity of the proposed guidance is validated by simulations in nominal conditions, including skip entry, loft entry, and direct entry, as well as simulations in dispersion conditions considering the combination disturbance of the entry interface, the aerodynamic coefficients, the air density, and the mass of the vehicle.

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.

Multi-constrained predictor-corrector reentry guidance for hypersonic vehicles

2017 ◽  
Vol 232 (16) ◽  
pp. 3049-3067 ◽  
Author(s):  
Lin Cheng ◽  
Zhenbo Wang ◽  
Yang Cheng ◽  
Qingzhen Zhang ◽  
Kin Ni
Keyword(s):  
Estimation Algorithm ◽  
Descent Method ◽  
Recursive Least Squares ◽  
Steepest Descent Method ◽  
Planning Problem ◽  
Bank Angle ◽  
Root Finding ◽  
Guidance Algorithm ◽  
Predictor Corrector ◽  
Constraint Enforcement

A numerical multi-constrained predictor-corrector guidance algorithm is proposed in this study, focusing on real-time longitudinal trajectory generation, constraint management, and lateral guidance improvement. First, a new compound bank corridor is designed to help convert the complicated trajectory planning problem into a root-finding problem, which is identified by a recursive least squares estimation algorithm and solved by a newly proposed period-crossing steepest descent method within a fraction of a second in Matlab. Second, three constraint enforcement operators are designed based on state prediction and feedback theory, and the long-standing constraint violation problem of predictor-corrector algorithms is addressed by on-board bank angle compensation. Additionally, a new predictive lateral guidance algorithm is proposed based on a cross-range proportional decrement strategy, and the resulting new bank reversal logic with only one user-defined parameter has better performance on reversal controllability and guidance robustness than the traditional algorithms. Finally, extensive numerical simulations are carried out for different mission scenarios with significant dispersions, and the new methodology is proved to be capable of autonomous and robust guidance flight for reentry vehicles.

Skip entry guidance using numerical predictor–corrector and patched corridor

2015 ◽  
Vol 117 ◽  
pp. 8-18 ◽  
Author(s):  
Zong-Fu Luo ◽  
Hong-Bo Zhang ◽  
Guo-Jian Tang
Keyword(s):  
Entry Guidance ◽  
Skip Entry ◽  
Predictor Corrector

Trajectory Planning and Prediction Guidance Based on the Moon-Earth Return Reentry Dynamics

2012 ◽  
Vol 625 ◽  
pp. 100-103
Author(s):  
Biao Zhao ◽  
Nai Gang Cui ◽  
Ji Feng Guo ◽  
Ping Wang
Keyword(s):  
Monte Carlo Analysis ◽  
The Moon ◽  
Accuracy Control ◽  
Entry Guidance ◽  
On Line ◽  
Acceleration Method ◽  
Path Constraint ◽  
Predictor Corrector ◽  
Precision Landing ◽  
Bank Profile

For the lunar return mission, a concern of the entry guidance requirement is the full flight envelope applicability and landing accuracy control. A concise numeric predictor-corrector (NPC) entry guidance (NPCEG) algorithm is developed for this requirement. It plans a real-time trajectory on-line by modulating the linear parameterized bank profile. To meet the path constraint, we propose an integrated guidance strategy which combines NPC method with an analytical constant drag acceleration method. Monte Carlo analysis shows that the algorithm is sufficiently robust to allow precision landing with a delivery error of less than 2.0 km for the entire between 2,500 km and 10,000 km range.

Verification of a Fully Numerical Entry Guidance Algorithm

2016 ◽  
Author(s):  
Ping Lu ◽  
Christopher Brunner ◽  
Susan Stachowiak ◽  
Gavin F. Mendeck ◽  
Michael Tigges ◽  
...  
Keyword(s):  
Entry Guidance ◽  
Guidance Algorithm
Sign in / Sign up

Export Citation Format

Share Document