Consultant evaluation and lab 3

8th-Semester-Spring-2025/weapon-systems/homework/l-6-homework.md

@@ -0,0 +1,94 @@
+---
+title: ECE09426 Lecture 6 Homework
+author: Aidan Sharpe
+date: March 3rd, 2025
+geometry: margin=1in
+---
+
+# Required PDMS for a HAW System
+```python
+import numpy as np
+import matplotlib.pyplot as plt
+
+P_TX = 7E3
+LOSS_TX = 10**(5/10)
+GAIN_TX = 10**(35/10)
+MAX_RANGE = 60E3
+TARGET_AREA = 1
+
+def PDMS(tx_power, tx_gain, radar_cross_section, tx_loss, dist_source_target, dist_target_missile):
+    tx_p_gain = (tx_power*tx_gain) / (4*np.pi*tx_loss)
+    p_ref = radar_cross_section / (dist_source_target**2)
+    p_rx = 1 / (4*np.pi*dist_target_missile**2)
+
+    return tx_p_gain * p_ref * p_rx
+
+
+def main():
+    pd_min = PDMS(P_TX, GAIN_TX, TARGET_AREA, LOSS_TX, MAX_RANGE, MAX_RANGE)
+    pd_min_db = 10*np.log10(pd_min)
+    print(pd_min_db)
+```
+
+PDMS required = -144.6592668956451
+
+# PDMS for a non-HAW System
+```python
+import numpy as np
+import matplotlib.pyplot as plt
+
+MAX_RANGE = 60E3
+
+def main():
+    illumination_percent = np.arange(0.1, 1.1, 0.1)
+    max_range = MAX_RANGE/illumination_percent
+
+    plt.plot(100*illumination_percent, max_range)
+    plt.xlabel("Illumination Percent")
+    plt.ylabel("Max Range [km]")
+    plt.show()
+```
+
+![](./illumination-percent-range.png)
+
+
+# Rocket Motor Math
+```python
+import numpy as np
+import matplotlib.pyplot as plt
+
+g = 9.81
+I_SP = 250
+BURN_TIME = 14
+INITIAL_MASS = 1200
+FINAL_MASS = 700
+
+def v_burnout(I_sp, t_burn, w_launch, w_burnout):
+    return I_sp * g*np.log(w_launch/w_burnout)
+
+
+def main():
+	t = np.linspace(0, BURN_TIME, 500)
+	
+    m_propellant = INITIAL_MASS - FINAL_MASS
+    w_propellant_0 = g*m_propellant
+    w_rocket = g*FINAL_MASS
+
+    weight_flow_rate = w_propellant_0/BURN_TIME
+    v_exit = I_sp*g
+    w_propellant = w_propellant_0 - weight_flow_rate*t
+
+    thrust = weight_flow_rate*v_exit*g
+    w_total = w_rocket + w_propellant
+    
+    acceleration_g = thrust/w_total
+    
+    plt.plot(t, acceleration_g)
+    plt.show()
+
+
+if __name__ == "__main__":
+    main()
+```
+
+![](./timed_burn.png)

8th-Semester-Spring-2025/weapon-systems/homework/pdms.py

@@ -0,0 +1,35 @@
+import numpy as np
+import matplotlib.pyplot as plt
+
+P_TX = 7E3
+LOSS_TX = 10**(5/10)
+GAIN_TX = 10**(35/10)
+MAX_RANGE = 60E3
+TARGET_AREA = 1
+
+def PDMS(tx_power, tx_gain, radar_cross_section, tx_loss, dist_source_target, dist_target_missile):
+    tx_p_gain = (tx_power*tx_gain) / (4*np.pi*tx_loss)
+    p_ref = radar_cross_section / (dist_source_target**2)
+    p_rx = 1 / (4*np.pi*dist_target_missile**2)
+
+    return tx_p_gain * p_ref * p_rx
+
+
+def main():
+    pd_min = PDMS(P_TX, GAIN_TX, TARGET_AREA, LOSS_TX, MAX_RANGE, MAX_RANGE)
+    pd_min_db = 10*np.log10(pd_min)
+    print(pd_min_db)
+
+    illumination_percent = np.arange(0.1, 1.1, 0.1)
+    max_range = MAX_RANGE/illumination_percent
+
+    plt.plot(100*illumination_percent, max_range)
+    plt.xlabel("Illumination Percent")
+    plt.ylabel("Max Range [km]")
+    plt.savefig("illumination-percent-range.png")
+    plt.show()
+    
+
+
+if __name__ == "__main__":
+    main()

8th-Semester-Spring-2025/weapon-systems/homework/rocket_motor.py

@@ -10,8 +10,11 @@ g = 9.81
 def specific_impulse(v_burnout, w_launch, w_burnout):
     return v_burnout / (g*np.log(w_launch/w_burnout))
 
+def v_burnout(I_sp, t_burn, w_launch, w_burnout):
+    return I_sp * g*np.log(w_launch/w_burnout)
 
-def main():
+
+def exit_velocity():
     plt.figure(figsize=(16,9))
     v_burnout = 1000
     w_rocket = 300
@@ -61,6 +64,32 @@ def main():
     plt.savefig("rocket_motor.png")
     plt.show()
 
+def main():
+    I_sp = 250
+    t_burn = 14
+    t = np.linspace(0, t_burn, 500)
+    m_0 = 1200
+    m_final = 700
+    
+    m_propellant = m_0 - m_final
+    w_propellant_0 = g*m_propellant
+    w_rocket = g*m_final
+
+    weight_flow_rate = w_propellant_0/t_burn
+    v_exit = I_sp*g
+    w_propellant = w_propellant_0 - weight_flow_rate*t
+
+    thrust = weight_flow_rate*v_exit*g
+    w_total = w_rocket + w_propellant
+    
+    acceleration_g = thrust/w_total
+    
+    plt.plot(t, acceleration_g)
+    plt.savefig("timed_burn.png")
+    plt.show()
+
+    
+
 
 if __name__ == "__main__":
     main()