Adaptive Impact Time Control Via Look-Angle Shaping Under Varying Velocity

Tekin, Raziye; Erer, Koray S.; Holzapfel, Florian

doi:10.2514/1.g002981

Cited by 74 publications

(30 citation statements)

References 17 publications

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“…Eqs. (20) and (24), it can be concluded that the proposed time-to-go estimation extends the 2D algorithm to a projected plan containing the LOS vector and missile velocity vector in the 3D scenario.…”

Section: A Impact Time Prediction In Three-dimensional Engagementmentioning

confidence: 85%

See 1 more Smart Citation

Three-Dimensional Optimal Impact Time Guidance for Antiship Missiles

Lin

2019

Journal of Guidance, Control, and Dynamics

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Section: A Impact Time Prediction In Three-dimensional Engagementmentioning

confidence: 85%

“…Remark 2 If we only consider the 2D engagement, pitch plane for example, we have σ = θ M and φ M = 0. Then, the predicted time-to-go (20) reduces to…”

Section: A Impact Time Prediction In Three-dimensional Engagementmentioning

confidence: 99%

Three-Dimensional Optimal Impact Time Guidance for Antiship Missiles

Lin

2019

Journal of Guidance, Control, and Dynamics

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“…Since the acceleration command a ξ can be considered as a proportional factor multiplied to gð⋅Þ, as shown in Equa-tion (20), the perturbed shaping trajectory (i.e., the result of impact time control), to a large extent, relies on the value of a ξ . To perform analysis, we remove the sign function hð⋅Þ from Equation 18and replace jξ T j by ξ T , obtaining the same expression as that of [6].…”

Section: Derivation Of Impact Time Control Guidance Lawmentioning

confidence: 99%

“…To avoid considerable effort to time-to-go, the ITCG law without using time-to-go has been developed in recent studies [18][19][20][21][22][23][24][25][26][27][28][29][30][31]. Tekin et al [18][19][20][21][22] proposed a series of notable guidance laws under various conditions using polynomial shaping of the look angle and range and the feedback linearization technique. Gutman [23] discussed a novel guidance law for impact time control using the concept of the zero-effort miss vector.…”

Section: Introductionmentioning

confidence: 99%

Nonsingular PNG-Based Impact Time Control Guidance with Lower Dependence on Time-to-Go Estimate

Chang

Chen

2019

International Journal of Aerospace Engineering

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In a bid to take advantage of natural characteristics of the proportional navigation guidance (PNG) in practical engineering, the PNG-based impact time control guidance (ITCG) continues to be a popular alternative for achieving the desired impact time of a missile. For most such ITCG, the performance is dependent on the accuracy of the time-to-go estimation. Along the lines of the development of PNG-based ITCG in earlier studies, a nonsingular ITCG is proposed on the basis of nonlinear formulations. It is demonstrated that, by theoretical analysis and numerical simulation, this proposed ITCG is shown to be advantageous in certain circumstances. By deriving a novel additional acceleration command, the proposed law is of lower dependence on time-to-go estimate and is capable of eliminating some singularities, leading to wider adjustable range of the desired impact time and better adaptability to more conditions. This research is expected to be supplementary to those presented in the current research literature.

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“…The guidance law applied the remaining engagement time instead of time-to-go estimation and the guidance gain was calculated by numerically solving an integral equation. In [15] Tekin extended the previous work by using adaptive guidance schemes by predicting the mean velocity to update the guidance gains in order to deal with the missiles timevarying velocity problem.…”

Section: Introductionmentioning

confidence: 99%

Impact-Time-Control Guidance Law for Hypersonic Missiles in Terminal Phase

Zhu

Wei

et al. 2020

IEEE Access

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Recent researches on hypersonic vehicles adopted in military have gained a lot of interest because of its high flight speed and efficiency. However the guidance laws for hypersonic missiles against the anti-missile system to increase survivability and defense penetration ability are still need to study. One main countermeasure to deal with this issue is to implement simultaneous attack. Therefore in this paper an impacttime-control guidance law for hypersonic missiles to impact a stationary target at the same desired final time is presented. Time-to-go estimation for time-varying velocity is derived by using a method of approximate acceleration form to extend the estimation method for constant velocity. The impact-time-control guidance law is firstly given and applied in vertical plane based on proportional navigation guidance law to control the impact time in terminal phase. Then the conditions that limit the method to apply are discussed. To overcome this issue, the guidance law applied in lateral plane is derived. The simulations are implemented using each method in vertical and lateral planes respectively and show good results for hypersonic missiles to achieve simultaneous attack. INDEX TERMS Hypersonic missile, impact-time-control, time-to-go estimation, time-varying velocity, simultaneous attack, vertical and lateral planes.

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Adaptive Impact Time Control Via Look-Angle Shaping Under Varying Velocity

Cited by 74 publications

References 17 publications

Three-Dimensional Optimal Impact Time Guidance for Antiship Missiles

Three-Dimensional Optimal Impact Time Guidance for Antiship Missiles

Nonsingular PNG-Based Impact Time Control Guidance with Lower Dependence on Time-to-Go Estimate

Impact-Time-Control Guidance Law for Hypersonic Missiles in Terminal Phase

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