Abstract
In this paper, we try to understand the dynamics involved in the launch vehicle. Then, to meet the target trajectory, we have to design a controller using modern control technique which is H-infinity control technique. The major concept of this technique is the selection of weight functions, their augmentation with the plant and develo** its state-space model. Various performance metrics used to analyse the performance of the system are gain margin, aero margin, rise time, settling time, overshoot and steady state error.
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Abbreviations
- \(T_{c}\) :
-
Control thrust in pitch plane
- \(T_{s}\) :
-
Ungimballed thrust
- I :
-
Moment of inertia of vehicle about pitch axis
- m :
-
Total mass of the launch vehicle
- \(m_0\) :
-
Reduced mass of the launch vehicle
- \(L_{\alpha }\) :
-
Aerodynamic load on launch vehicle per unit angle of attack
- \(l_{c}\) :
-
Distance from centre of mass of vehicle to engine swivel point
- \(l_{\alpha }\) :
-
Distance from the centre of mass to centre of pressure
- \(\delta \) :
-
Thrust deflection angle
- \(\alpha \) :
-
Angle of attack
- V :
-
Forward velocity of vehicle
- \(V_{w}\) :
-
Wind velocity
- \(\alpha _{w}\) :
-
Wind angle of attack
- D :
-
Drag
- \(K_{a}\) :
-
Servoamplifier gain
- \(K_{r}\) :
-
Rate gyro gain
- \(l_{pi}\) :
-
Distance from hinge point of ith pendulum to origin on body axis
- L :
-
Length of the vehicle
- \(L_{pi}\) :
-
Length of ith pendulum
- \(q^{i}\) :
-
Generalised coordinate of ith bending mode
- \(U_{0}\) :
-
Forward velocity of vehicle
- \(\mu _{c}\) :
-
Control moment coefficient: = \(\frac{Tc*l_{c}}{I_{yy}}\)
- \(\mu _{\alpha }\) :
-
Aerodynamic moment coefficient: = \(\frac{L_{\alpha }*l_{\alpha }}{I_{yy}}\)
- \(\mu _{pj}\) :
-
\(\frac{m_{pj}*l_{pj}*\dot{U_{0}}}{I_{yy}}\)
- \(\omega _{a}\) :
-
Actuator frequency
- \(\omega _{slosh}\) :
-
Slosh frequency
- \(\omega _{i}\) :
-
Frequency of ith bending mode. i = 1,2
- \(\rho \) :
-
Dam** ratio
- \(\rho _a\) :
-
Dam** ratio of actuator
- \(\rho _i\) :
-
Dam** ratio of ith bending mode. i = 1,2
References
Engelberg, S.: Tutorial 15: control theory, Part 1,2. IEEE (2008)
Bhat, M.S., Jaisimha, B.S., Kumar, S.R.V.: Optimal Digital Autopilot for Satellite Launch Vehicles During Atmospheric Phase (1992)
Arthur, L.: NASA CR-826 Analysis and Design of Space Vehicle Fight Control Systems. San Diego, California (1967)
Hespanha, J.P.: Linear Systems Theory. Princeton University
Khalate, A.A., Rao, K.K.: Robust Autopilot for Atmospheric flight of Launch Vehicle based on H H\(_{\infty }\) Approach, Centre for Artificial Intelligence and Robotics, Bangalore
Deodhare, G., Patel, V.V.: A “Modern” look at Gain and Phase margins: H\(_{\infty }/\mu \) Approach , Centre for Artificial Intelligence and Robotics, Bangalore
Wie, B., Mark, W.: Analysis and design of launch vehicle flight control systems (2008)
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Vaishnavi, C., Dhekane, M.V. (2022). Launch Vehicle Autopilot Design Using H-Infinity Control Technique. In: Gu, J., Dey, R., Adhikary, N. (eds) Communication and Control for Robotic Systems. Smart Innovation, Systems and Technologies, vol 229. Springer, Singapore. https://doi.org/10.1007/978-981-16-1777-5_27
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DOI: https://doi.org/10.1007/978-981-16-1777-5_27
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