Phugoid dynamic characteristic of hypersonic gliding vehicles

Chen, Xiaoqing; Hou, Zhanqiang; Liu, Jianxia; Chen, Xiaoqian

doi:10.1007/s11432-011-4196-9

Cited by 13 publications

(6 citation statements)

References 12 publications

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“…As we all known, if the initial glide height of the vehicle does not satisfy the balanced glide state, the trajectory of NSHV will jump [ 19 ] . When the initial altitude h a ( k ) is less than the equilibrium glide height h b ( k ), the local atmospheric density

ρ_{0} {normale}^{‐ β h_{a} (k)}

is greater than that of the equilibrium glide.…”

Section: Trajectory Prediction Methods Based On Hough Transformmentioning

confidence: 99%

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Hypersonic Vehicle Trajectory Prediction Algorithm Based on Hough Transform

Li¹,

Jia-jun²,

Lan³

et al. 2021

Chinese J of Electronics

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Trajectory prediction is a prerequisite for missile and high‐speed vehicle guidance interception. To address the trajectory problem for the near space hypersonic unpowered gliding vehicle. Firstly, the trajectory prediction mechanism is analyzed. Based on the existing NSHV trajectory prediction method, the key techniques of trajectory prediction are discussed from the perspectives of prediction parameter selection and prediction parameter description. Then, a trajectory prediction method based on Hough transform is proposed. The core of the method is to select the longitude latitude, and high direction positions as prediction parameters, and use the Hough transform to fit the prior basis functions. In the latitude and longitude direction, the rationality of predicting parameters is discussed from two aspects: position extreme point and lateral maneuverability. In the height direction, for the NSHV oscillation drop characteristic, two Hough transforms are used to separate the periodic term from the linear term. In addition, we give the approximate interval of the parameter values of the method, and design a parameter adaptive scheme. Finally, trajectory prediction is performed on two different control patterns. The error of the prediction time of 100s is within 25km, and the results show the effectiveness of the proposed method.

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ρ_{0} {normale}^{‐ β h_{a} (k)}

is greater than that of the equilibrium glide.…”

Section: Trajectory Prediction Methods Based On Hough Transformmentioning

confidence: 99%

“…While the EEMD decomposition results are unstable and severely affected by the length of historical data. Furthermore, this method is only suitable for height state prediction [ 8 ] . Zhai et al [ 9 ] proposed a hypersonic target trajectory prediction method based on new aerodynamic parameters.…”

Section: Introductionmentioning

confidence: 99%

Hypersonic Vehicle Trajectory Prediction Algorithm Based on Hough Transform

Li¹,

Jia-jun²,

Lan³

et al. 2021

Chinese J of Electronics

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show abstract

“…Using optimization methods, Ruan [3] proved that the hypersonic target can reach a larger longitudinal range gliding with the maximum lift-to-drag ratio, while the trajectory is usually not in equilibrium glide maneuver. Ferreira [4] and Chen et al [5] analyzed the long period trajectory of equilibrium glide first, fitting skip glide maneuver into shock curve by Liouville transformation and general multiple scale theory (GMS) method, and gave the formula for the number of skip maneuver. For the lateral maneuver, the target usually adopts a weaving maneuver and turning maneuver according to the need for penetration.…”

Section: Introductionmentioning

confidence: 99%

An Intelligent Trajectory Prediction Algorithm for Hypersonic Glide Targets Based on Maneuver Mode Identification

Zhou

Shao

et al. 2022

International Journal of Aerospace Engineering

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Trajectory prediction for hypersonic glide targets is a difficult task that needs to be solved. To improve the prediction precision for hypersonic glide targets, based on the analysis of the target’s maneuver characteristic, an intelligent trajectory prediction algorithm based on the maneuver mode identification is proposed in this paper. Firstly, according to the typical maneuver modes of the target, a group of parameter suitable for maneuver mode identification and parameter estimation is proposed. The proposed maneuver parameters can reflect the maneuvering characteristics of the target than the other control parameters. Then, the rationality of parameters is analyzed. Secondly, using the long-short-term memory network (LSTM), the structure of intelligent trajectory prediction based on maneuver mode identification is proposed. The proposed prediction method is designed to improve the prediction accuracy by combining the target dynamic model with the flight data. Finally, the maneuver trajectory data set is established to train and test the method. For the test data set, when the observation time for the target is 200 s and the prediction time is 150 s, with a fast prediction speed, our method’s average error of spatial distance (AESD) is less than 2.9 km, and the maximum error of spatial distance (MESD) is less than 6.9 km. The result is better than other compared mainstream methods. And it is also proved valid with some observational error.

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“…The term hypersonic vehicle (HV) generally refers to a vehicle flying at Mach 5 or above [1]; such vehicles have become a popular topic in research on the flight control of air vehicles [2][3][4][5][6][7][8][9]. Although they have many advantages, such as a large flight envelope, high maneuverability, and good penetrability, HVs are very sensitive to changes in flight conditions [10,11].…”

Section: Introductionmentioning

confidence: 99%

Sliding mode decoupling control of a generic hypersonic vehicle based on parametric commands

Wang

Tang

2014

Sci. China Inf. Sci.

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Super twisting sliding mode control for a flexible air-breathing hypersonic vehicle based on disturbance observer SCIENCE CHINA Information Sciences 58, 070207 (2015); Adaptive mode switching of hypersonic morphing aircraft based on type-2 TSK fuzzy sliding mode control SCIENCE CHINA Information Sciences 58, 070205 (2015); Dynamic decoupling tracking control for the polytopic LPV model of hypersonic vehicle SCIENCE CHINA Information Sciences 58, 092203 (2015);Nonlinear hierarchy-structured predictive control design for a generic hypersonic vehicle SCIENCE CHINA Technological Sciences 56, 2025; ${\mathcal{L}}_{1}$ adaptive control of a generic hypersonic vehicle model with a blended pneumatic and thrust vectoring control strategy Abstract A sliding mode decoupling attitude controller based on parametric commands is proposed for a generic hypersonic vehicle (GHV). This vehicle model has fast time variability and strong coupling, is highly nonlinear, and includes uncertain parameters. The design of the controller takes these features into account. First, for the purpose of decoupling, the inner loop of the controller is designed using the dynamic inversion (DI) method. Input/output linearization is achieved using full-state feedback to globally linearize the nonlinear dynamics of selected controlled outputs. Second, to improve the robustness of the attitude control system, the sliding mode control (SMC) method is used to design the outer loop of the controller. Although the DI and SMC methods result in decoupling and robustness, there exists serious inconsistency between the commands of the attitude angles and the commands of the first-order differential of the attitude angles. To solve this problem and achieve a trade-off between dynamic response speed and attitude-tracking precision, we propose a parametric method for calculating the commands of the first-order differential of the attitude angles. Finally, simulation studies are conducted for the trimmed cruise conditions of 33.5 km altitude and Mach 15, and the responses of the vehicle to the step commands of pitch angle, yaw angle, and rolling angle are examined. The simulation studies demonstrate that the proposed controller is robust with respect to the uncertain parameters and atmospheric disturbance and meets the performance requirements of the GHV with acceptable control inputs.controller for an HV [13,14], and it is essential to achieve linearization and decoupling of the dynamic model and to improve the efficiency and robustness of the attitude control system.In the past decades, nonlinear control methods have mainly been used for HVs. The dynamic inversion (DI) method has been widely and successfully used to control nonlinear systems [15][16][17][18] and is considered to be one of the most effective control methods for decoupling. The DI method was proposed by Snell, Enns, and Garrard [16] to resolve problems of nonlinearity and coupling in designing a flight control system for a supermaneuverable aircraft. This approach to nonlinear control design ach...

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Phugoid dynamic characteristic of hypersonic gliding vehicles

Cited by 13 publications

References 12 publications

Hypersonic Vehicle Trajectory Prediction Algorithm Based on Hough Transform

Hypersonic Vehicle Trajectory Prediction Algorithm Based on Hough Transform

An Intelligent Trajectory Prediction Algorithm for Hypersonic Glide Targets Based on Maneuver Mode Identification

Sliding mode decoupling control of a generic hypersonic vehicle based on parametric commands

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