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Cruise Missile Mission Planning Using Genetic Algorithm

  • G. Naresh Kumar
  • Shweta Dadarya
  • Akshay Verandani
  • A. K. Sarkar
  • S. E. Talole
Conference paper
Part of the Lecture Notes in Mechanical Engineering book series (LNME)

Abstract

Mission planning is a critical stage in launching a cruise missile against highly defended targets. It is required to generate an optimal trajectory during combat scenario (real time) just before launch. Typically, this type of engagement is carried by cruise missiles flying at low altitudes below 100 m. In addition to air defense, terrain features also need to be avoided by following certain way-points. This study investigates use of genetic algorithms (GA) as an optimization procedure in the flight trajectory planner to be used in the real-time environment.

Keywords

Flight Trajectory Planning (FTP) Genetic Algorithm (GA) Way-point Optimization and Cruise Vehicle (CV) 

Nomenclature

\(\alpha \)

Angle of attack

\(\beta \)

Side-slip angle

\(\varGamma _i\)

Threat intensity

\(\tau _{a_n}\)

Time constant of normal accel\(^n\)

\(\tau _{\varPhi }\)

Time constant of roll

\(\varPhi \)

Roll angle

\(\varPhi _c\)

Roll angle command

\(\varPsi \)

Yaw angle

\(\varTheta \)

Pitch angle

\(a_n\)

Normal acceleration

\(a_{nc}\)

Normal acceleration command

\(a_{x}, a_{y}, a_{z}\)

Accelerations in earth frame

\(r_i\)

Radius of ith way-point

\(E_i\)

Expected fitness of a trajectory

\(F_i\)

Trajectory fitness

g

Acceleration due to gravity

\(Z_{nom}\)

Vehicle altitude

\(J_i\)

Trajectory risk

k

Bit position

l

String length

\(p_c\)

Probability of crossover

\(p_m\)

Probability of mutation

s

Distance along the trajectory

t

Time

\(\Delta t\)

Time interval

\(t_i\)

Initial time of segment

\(t_f\)

Final time of segment

T(xy)

Threat function

V

Velocity vector

\(V_{nom}\)

Nominal velocity

\(v_{x},v_{y},v_{z}\)

Velocities in earth frame

xyz

Positions in earth frame

\(X_{A},Y_{A},Z_{A}\)

Vehicle frame axes

\(X_{E},Y_{E},Z_{E}\)

Earth frame axes

Notes

Acknowledgements

The authors thank competent authorities of Defence Research and Development Laboratory (DRDL), Hyderabad, India for granting permission to publish this piece of work.

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Copyright information

© Springer Nature Singapore Pte Ltd. 2018

Authors and Affiliations

  • G. Naresh Kumar
    • 1
  • Shweta Dadarya
    • 1
  • Akshay Verandani
    • 2
  • A. K. Sarkar
    • 1
  • S. E. Talole
    • 3
  1. 1.Defence Research and Development LaboratoryHyderabadIndia
  2. 2.National Institute of TechnologyGoaIndia
  3. 3.Defence Institute of Advanced TechnologyPuneIndia

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