Polynomial Shaping of the Look Angle for Impact-Time Control

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

doi:10.2514/1.g002751

Cited by 111 publications

(26 citation statements)

References 18 publications

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“…where N is the navigation gain of the PNG law. The look angle rate is obtained by differentiating (15): The look angle rate can also be expressed by combining (14), (16) and 17:…”

Section: Impact Time Control Guidance Law a Itcg Law Implementementioning

confidence: 99%

“…Besides the two main categories of realizing ITCG aforementioned, there is another sort of methods using trajectoryshaping-guidance concept to derive the guidance law. In [14] Tekin presented an ITCG law based on polynomial look angle profile for constant speed missiles against stationary target. 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.…”

Section: Introductionmentioning

confidence: 99%

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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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“…where N is the navigation gain of the PNG law. The look angle rate is obtained by differentiating (15): The look angle rate can also be expressed by combining (14), (16) and 17:…”

Section: Impact Time Control Guidance Law a Itcg Law Implementementioning

confidence: 99%

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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“…16 Another impact time control method based on a polynomial relationship between the look angle and time was proposed by Tekin et al. 17 Considering the terminal angle and acceleration constraints, Xu and Huang 18 proposed another trajectory shaping guidance law. In addition, Lee et al.…”

Section: Introductionmentioning

confidence: 99%

“…The authors then expanded and improved their method to address a non-maneuvering moving target. 16 Another impact time control method based on a polynomial relationship between the look angle and time was proposed by Tekin et al 17 Considering the terminal angle and acceleration constraints, Xu and Huang 18 proposed another trajectory shaping guidance law. In addition, Lee et al 19 reported a timeto-go polynomial guidance law, whose goal is to solve for the polynomial coefficients with boundary conditions under the terminal constraints.…”

Section: Introductionmentioning

confidence: 99%

Polynomial guidance law for impact angle control with a seeker look angle limit

Zhou

Yao

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, the impact angle control problem is investigated by applying the polynomial shaping method. By shaping the light-of-sight angle with relative range, a guidance law called range polynomial guidance is proposed, and the coefficients are determined by boundary conditions. The range polynomial guidance law can be applied to maneuvering targets. By profiling the seeker look angle with the light-of-sight angle, a guidance law called line-of-sight polynomial guidance is developed for impact angle control under a limitation on the seeker look angle. The line-of-sight polynomial guidance law is also effective in intercepting a non-maneuvering moving target at the desired impact angle. Guidance laws with different gain sets are discussed in this paper. The proposed guidance laws take the form of proportional navigation with a time-varying navigation gain. Nonlinear simulations are performed to validate the efficacy of the proposed guidance laws in various engagement conditions. Comparison with other studies demonstrates the practicality and flexibility of the proposed guidance laws in the design of desired impact angles and maximum look angles.

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“…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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Polynomial Shaping of the Look Angle for Impact-Time Control

Cited by 111 publications

References 18 publications

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

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

Polynomial guidance law for impact angle control with a seeker look angle limit

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

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