Progress in reentry trajectory planning for hypersonic vehicle

Zhao, Jiang; Zhou, Rui; Jin, Xuelian

doi:10.1109/jsee.2014.00073

Cited by 37 publications

(12 citation statements)

References 81 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The PN component is derived from the PN guidance law (8), which additionally takes into account the acceleration information of the target as follows:…”

Section: Guidance Laws Against a Maneuvering Targetmentioning

confidence: 99%

“…The cooperative guidance will be performed through the following cases by using the CPN, C-CPN, and D-CPN algorithms, respectively. Figure 8 presents the simulation results of the cooperative guidance law (28) in comparison with traditional PN algorithm (8). It shows that each missile can separately intercept the maneuvering target by PN, for which the impact time is 24.18, 24.57, and 23.27 s, respectively.…”

Section: Example 2 (Maneuvering Target)mentioning

confidence: 99%

“…For a single missile, those objectives have been achieved with satisfied accuracy of the target capture. Recently, many researchers start on the development of the cooperative guidance laws for the salvo attack of multiple missiles, which may have better performance than the individual missile system in detecting the maneuvering targets, penetrating the defense systems, and surviving the threats [7][8][9]. In this case, it is more difficult to achieve a simultaneous attack against the target in the light of different initial conditions as well as the communication limitation between each missile [10][11][12][13].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Unified approach to cooperative guidance laws against stationary and maneuvering targets

Zhao

Zhou

2015

Nonlinear Dyn

Self Cite

View full text Add to dashboard Cite

This paper presents the unified cooperative strategies for the salvo attack of multiple missiles on the basis of the traditional proportional navigation (PN) algorithm. The cooperative guidance laws are developed in a quite simple formulation consisting of a PN component for target capture and a coordination component for simultaneous arrival. The centralized coordination algorithms have better performance when the global information of time-to-go can be obtained by each missile, whereas the decentralized coordination algorithms come into effect when the group member is only able to collect information from its neighbors. The cooperative strategies can achieve a simultaneous attack against both stationary and maneuvering targets. Numerical simulations are used to demonstrate that the proposed approaches are feasible and flexible for the salvo attack of multiple missiles. The capturability analyses of the cooperative guidance laws are also performed by discussing the selection of gain parameters.

show abstract

“…The PN component is derived from the PN guidance law (8), which additionally takes into account the acceleration information of the target as follows:…”

Section: Guidance Laws Against a Maneuvering Targetmentioning

confidence: 99%

Section: Example 2 (Maneuvering Target)mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Unified approach to cooperative guidance laws against stationary and maneuvering targets

Zhao

Zhou

2015

Nonlinear Dyn

Self Cite

View full text Add to dashboard Cite

show abstract

“…The standard trajectory guidance that is more mature and widely used includes two parts: trajectory planning and tracking. The entry trajectory planning is usually based on numerical optimization or numerical iteration methods which are usually time-consuming and laborious [3]. More specifically, a well-known approach, i.e., planning aerodynamic drag acceleration profile as the reference trajectory, typically implemented in the shuttle entry guidance and lately extended to other instances (e.g., Evolved Acceleration Guidance Logic for Entry, EAGLE), has proven to be very effective and successful, which becomes the baseline approach for many entry vehicles [1].…”

Section: Introductionmentioning

confidence: 99%

Adaptive Entry Guidance for Hypersonic Gliding Vehicles Using Analytic Feedback Control

Yan

Wang

et al. 2020

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

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.

show abstract

“…16–18 Although the shuttle entry guidance is the benchmark of entry guidance, 19 researches that focus on rapid generation of trajectory based on drag acceleration profile are still less. 20 In order to carry out the trajectory states faster, a reduced order dynamics system is proposed 21 based on the quasi-equilibrium glide condition (QEGC) and omission of the longitudinal motion. Currently, Yu and Chen 22 proposed an innovative method based on spectral decomposition for solving trajectory generation problem.…”

Section: Introductionmentioning

confidence: 99%

Rapid generation of landing footprint based on geometry-predicted trajectory

Zhang

Chen

Liu

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Landing footprint is critical to generate a feasible trajectory onboard for entry vehicles. In this paper, a new landing footprint calculation based on geometry-predicted trajectory is proposed. First, the lateral motion states, turning radius and angle, are analytically solved based on a planned drag acceleration vs. energy (D–E) profile. Through some simple coordinate and geometrical triangle transformation, all the trajectory states are extracted. Second, by calculating the maximum longitudinal range point, the furthest reachable boundary for planned D–E profile is obtained with proposed geometry-predicted trajectory. Finally, the landing footprint can be generated by repeatedly computing the reachable boundaries for all D–E profiles in the entry corridor. Simulation results with Common Aero Vehicle (CAV) model validate the accuracy of the geometry-predicted trajectory. Furthermore, detailed comparison of footprint generation results between the traditional and the proposed are presented at last.

show abstract

Progress in reentry trajectory planning for hypersonic vehicle

Cited by 37 publications

References 81 publications

Unified approach to cooperative guidance laws against stationary and maneuvering targets

Unified approach to cooperative guidance laws against stationary and maneuvering targets

Adaptive Entry Guidance for Hypersonic Gliding Vehicles Using Analytic Feedback Control

Rapid generation of landing footprint based on geometry-predicted trajectory

Contact Info

Product

Resources

About