**Volume 17 (2024)**

**Volume 16 (2023)**

**Volume 15 (2022)**

**Volume 14 (2021)**

**Volume 13 (2020)**

**Volume 12 (2019)**

**Volume 11 (2018)**

**Volume 10 (2017)**

**Volume 9 (2016)**

**Volume 8 (2015)**

**Volume 7 (2014)**

**Volume 6 (2013)**

**Volume 5 (2012)**

**Volume 4 (2011)**

**Volume 3 (2010)**

**Volume 2 (2009)**

**Volume 1 (2008)**

#### Author = S. Hamid Jalali-Naini

Number of Articles: 11

##### Miss Distance Analysis of First-Order Explicit Guidance Law with/without Radome effect

*Volume 15, Issue 4 , December 2022, , Pages 1-18*

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**Abstract **

The miss distance analysis of the first-order explicit guidance law (EGL) is carried out using linearized equation of motion in the normalized form in order to obtain normalized miss distance curves. The initial heading error, constant target, acceleration limit, radome refraction error, and fifth-order ...
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##### A Modification to Integral Pulse-Width Pulse-Frequency Modulator

*Volume 14, Issue 1 , March 2021, , Pages 55-64*

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**Abstract **

This paper presents a modification to a type of Pulse-width Pulse-Frequency (PWPF) Modulator utilized an integrator block. In this modulator that called here as "Integral Pulse-Width Pulse-Frequency (IPWPF)," an integrator is used instead of the first-order low-pass filter. To improve the performance ...
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##### Proportional Navigation with Linear Acceleration and Line-of-Sight Acceleration Feedbacks

*Volume 13, Issue 4 , December 2020, , Pages 1-13*

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**Abstract **

In this paper, a modified proportional navigation (PN) with weighted combination of linear acceleration and line-of-sight (LOS) acceleration feedback is suggested. For this purpose, a comprehensive miss distance analysis is carried out for PN with linear acceletation feedback and PN with LOS acceleration ...
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##### Proportional Navigation Guidance with Variable Navigation Ratio in terms of the angle of relative velocity with respect to Line-of-Sight and its Rate

*Volume 13, Issue 2 , June 2020, , Pages 1-12*

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**Abstract **

In the present work, the performance of True Proportional Navigation (TPN) with different profiles for effective navigation ratio in terms of the relative velocity angle with respect to line-of-sight is investigated due to initial heading errors and target maneuvers. Since an appropriate profile of effective ...
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##### Static Analysis of Pulse-Width Pulse-Frequency Modulator Based on Analytical and Numerical Solutions

*Volume 11, Issue 1 , June 2018, , Pages 13-29*

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**Abstract **

In this study, the preferred regions of Pulse-Width Pulse-Frequency Modulator (PWPFM) are obtained analytically for the static analysis. For this purpose, a comprehensive parametric study is carried out based on the two performance indices of fuel consumption and the number of thruster firings. The preferred ...
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##### Robust Optimization of Satellite Attitude Control with Thruster Actuators based on Combined Objective Function

*Volume 10, Issue 4 , March 2018, , Pages 55-66*

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**Abstract **

his paper suggests arobust optimization algorithm for the design of the satellite attitude control system in order to increase the robustness of the performance under uncertainties. A single-axis on-off attitude control with rigid dynamics is considered using Schmitt-Trigger and PID controller. The model ...
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##### Approximate Solution of Required Velocity in Elliptical Earth Model Using Piecewise Linear

*Volume 9, Issue 3 , December 2016, , Pages 1-12*

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**Abstract **

In this paper, an approximate solution of required velocity with final position constraint is derived using a piecewise linear gravity assumption for elliptical earth model. In this approach, the total flight time is divided into several time intervals and the gravitational acceleration is assumed to ...
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##### Implicit Guidance Equations in PolarÂ Coordinates

*Volume 7, Issue 4 , January 2015, , Pages 1-9*

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**Abstract **

In this paper, implicit guidance equations are derived in polar coordinates. Depending on applications, implicit guidance equations in polar coordinates may be preferred over cartesian coordinates. Moreover, depending on the type of guidance problem, analytical solutions for sensitivity matrices may ...
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##### Ascending Phase Fuzzy Logic Guidance of Satellite Launch VehiclesÂ for Reducing the Adverse Wind Effects

*Volume 7, Issue 3 , October 2014, , Pages 75-82*

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**Abstract **

In this paper, a fuzzy logic guidance algorithm is presented for the ascending phase of satellite launch vehicles in the presence of wind effects. In this algorithm, the midcourse constraints including maximum allowable angle of attack at the maximum dynamic pressure and the product of the dynamic pressure ...
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##### Approximate Solution of Sensitivity Matrix with Final Velocity Constraint Using Linear Time-Varying Gravity Assumption

*Volume 4, Issue 2 , January 2012, , Pages 71-81*

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**Abstract **

In this research, an approximate solution of the required velocity with final velocity constraint is derived using linear gravity assumption along the path of current position to the final position vectors. Moreover, an approximate solution for sensitivity matrix of the required velocity with respect ...
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##### Closed-Loop Guidance with Final Velocity Constraint Using Time-Varying Weighting Coefficient for Shaping of Commanded Acceleration

*Volume 2, Issue 3 , December 2009, , Pages 1-12*