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