Skip Re-Entry Trajectory Detection and Guidance for Maneuvering Vehicles

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.

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Analytical predictor–corrector entry guidance for hypersonic gliding vehicles

International Journal of Nonlinear Sciences and Numerical Simulation ◽

10.1515/ijnsns-2019-0290 ◽

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.

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

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.625.100 ◽

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.

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Verification of a Fully Numerical Entry Guidance Algorithm

AIAA Guidance, Navigation, and Control Conference ◽

10.2514/6.2016-0377 ◽

2016 ◽

Cited By ~ 5

Author(s):

Ping Lu ◽

Christopher Brunner ◽

Susan Stachowiak ◽

Gavin F. Mendeck ◽

Michael Tigges ◽

...

Keyword(s):

Entry Guidance ◽

Guidance Algorithm

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Rapid trajectory planning of a reusable launch vehicle for airdrop with geographic constraints

International Journal of Advanced Robotic Systems ◽

10.1177/1729881418817971 ◽

2019 ◽

Vol 16 (1) ◽

pp. 172988141881797 ◽

Cited By ~ 1

Author(s):

Xing Wei ◽

Xuejing Lan ◽

Lei Liu ◽

Yongji Wang

Keyword(s):

Trajectory Planning ◽

Planning Process ◽

Launch Vehicle ◽

Search Problem ◽

Quasi Equilibrium ◽

Bank Angle ◽

Weighted Interpolation ◽

Reusable Launch Vehicle ◽

Terminal Constraints ◽

Planning Algorithm

Online feasible trajectory generation for an airdrop unpowered reusable launch vehicle is addressed in this article. A rapid trajectory planning algorithm is proposed to satisfy not only the multiple path and terminal constraints but also the complex geographic constraints of waypoints and no-fly zones. Firstly, the lower and upper boundaries of the bank angle that implement all the path constraints are obtained based on the quasi-equilibrium glide condition. To determine the bank angle directly, a weighted interpolation of the boundaries is then developed, which provides an effective approach to simplify the planning process as a one-parameter search problem. Subsequently, three types of lateral planning algorithms are designed to determine the sign of the bank angle according to the requirements of waypoints passage, no-fly-zones avoidance, and terminal constraints in the airdrop process, and the convergence of these methods for passing over the waypoints and meeting the terminal conditions has been clarified and formally demonstrated. Considering the constraints in the actual airdrop flight missions, the planning trajectory is divided into several subphases to facilitate the application of corresponding algorithms. Finally, the performance of the proposed algorithm is assessed through three airdrop missions of reusable launch vehicle with different geographic constraints. Besides, the effectiveness of the algorithm is demonstrated by the Monte Carlo simulation results.

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Simple Adaptive Re-entry Guidance for Path-Constraint Tracking

2018 AIAA Guidance, Navigation, and Control Conference ◽

10.2514/6.2018-1318 ◽

2018 ◽

Author(s):

Erwin Mooij

Keyword(s):

Entry Guidance ◽

Path Constraint

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Verification of a Fully Numerical Entry Guidance Algorithm

Journal of Guidance Control and Dynamics ◽

10.2514/1.g000327 ◽

2017 ◽

Vol 40 (2) ◽

pp. 230-247 ◽

Cited By ~ 31

Author(s):

Ping Lu ◽

Christopher W. Brunner ◽

Susan J. Stachowiak ◽

Gavin F. Mendeck ◽

Michael A. Tigges ◽

...

Keyword(s):

Entry Guidance ◽

Guidance Algorithm

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Predictor-Corrector Reentry Guidance Algorithm with Path Constraints for Atmospheric Entry Vehicles

Journal of Guidance Control and Dynamics ◽

10.2514/1.26306 ◽

2007 ◽

Vol 30 (5) ◽

pp. 1307-1318 ◽

Cited By ~ 51

Author(s):

Ashok Joshi ◽

K. Sivan ◽

S. Savithri Amma

Keyword(s):

Atmospheric Entry ◽

Path Constraints ◽

Guidance Algorithm ◽

Predictor Corrector

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An entry guidance algorithm based on trajectories database

2015 34th Chinese Control Conference (CCC) ◽

10.1109/chicc.2015.7260419 ◽

2015 ◽

Author(s):

Zeng Liang ◽

Zhang Hongbo ◽

Zheng Wei

Keyword(s):

Entry Guidance ◽

Guidance Algorithm

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Adaptive entry guidance for the Tianwen-1 mission

Astrodynamics ◽

10.1007/s42064-021-0120-2 ◽

2022 ◽

Vol 6 (1) ◽

pp. 17-26

Author(s):

Minwen Guo ◽

Xiangyu Huang ◽

Maodeng Li ◽

Jinchang Hu ◽

Chao Xu

Keyword(s):

Trajectory Design ◽

Accuracy Control ◽

Initial State ◽

Control Phase ◽

Guidance Law ◽

Flight Path Angle ◽

Entry Guidance ◽

Event Trigger ◽

Control Authority ◽

Guidance Algorithm

AbstractTo meet the requirements of the Tianwen-1 mission, adaptive entry guidance for entry vehicles, with low lift-to-drag ratios, limited control authority, and large initial state bias, was presented. Typically, the entry guidance law is divided into four distinct phases: trim angle-of-attack phase, range control phase, heading alignment phase, and trim-wing deployment phase. In the range control phase, the predictor—corrector guidance algorithm is improved by planning an on-board trajectory based on the Mars Science Laboratory (MSL) entry guidance algorithm. The nominal trajectory was designed and described using a combination of the downrange value and other states, such as drag acceleration and altitude rate. For a large initial state bias, the nominal downrange value was modified onboard by weighing the landing accuracy, control authority, and parachute deployment altitude. The biggest advantage of this approach is that it allows the successful correction of altitude errors and the avoidance of control saturation. An overview of the optimal trajectory design process, including a discussion of the design of the initial flight path angle, relevant event trigger, and transition conditions between the four phases, was also presented. Finally, telemetry data analysis and post-flight assessment results were used to illustrate the adaptive guidance law, create good conditions for subsequent parachute reduction and power reduction processes, and gauge the success of the mission.

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