Bio week 7 and weapon systems midterm equations

8th-Semester-Spring-2025/biology/week-7/prelab-project-7/prelab-project-7.md

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+Video "Lung Function"
+
+### 4 volumes:
+- Tidal volume: 500-750ml and is the amount of air normally breathed in and out
+- Inspiratory reserve volume: The difference in the total volume of air inspired with maximum inspiratory effort compared to the tidal volume. Typically about 3L.
+- Expiratory reserve volume: The amount of air that can be exhaled in addition to the tidal volume. Typically about 1.5L.
+- Residual volume: The amount of air remaining in the lungs after maximum expiratory effort. Typically about 1L.
+
+### Lung capacities:
+- Total lung capacity: the sum of the four lung volumes (about 6L).
+
+### Question:
+Why can we not breathe out all the air in our lungs?

8th-Semester-Spring-2025/biology/week-7/vocab/Sharpe_VocabularyAssignment7.md

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+---
+title: BIOL01113 Vocabulary Assignment 7
+author: Aidan Sharpe
+date: March 10th, 2025
+geometry: margin=1in
+---
+
+### Nasopharynx
+Where the nasal cavity opens above the soft palate.
+
+### Epiglottis
+A structure that covers the opening to the voice box while swallowing.
+
+### Trachea
+Another word for the windpipe that connects the upper respiratory tract to the primary bronchi.
+
+### Bronchus
+The largest tubes within the lungs, branching from the trachea into the bronchioles.
+
+### Bronchial tree
+The branching structure of the bronchi and bronchioles.
+
+### Alveoli
+Air sacs where oxygen and carbon dioxide are exchanged between the lungs and pulmonary capillaries.
+
+### Partial pressure
+The amount of pressure exerted by an individual gas within a gas mixture.
+
+### Gas exchange
+The movement of gas between the alveoli and the blood in the pulmonary capillaries.
+
+### Breathing
+The process of inhaling and exhaling.
+
+### Ventilation
+The process of moving air in and out of the lungs.

8th-Semester-Spring-2025/cloud-hardware/project-4-1/table-4-7.md

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+---
+title: ECE09488 In Class Exercise - Subnetting
+author: Aidan Sharpe
+date: March 6th, 2025
+geometry: margin=1in
+---
+
+
+| Network ID     | Host IP Range                   | Broadcast Address |
+|----------------|---------------------------------|-------------------|
+| 192.168.15.0   | 192.168.15.1 - 192.168.15.14    | 192.168.15.15     |
+| 192.168.15.16  | 192.168.15.17 - 192.168.15.30   | 192.168.15.31     |
+| 192.168.15.32  | 192.168.15.33 - 192.168.15.46   | 192.168.15.47     |
+| 192.168.15.48  | 192.168.15.49 - 192.168.15.62   | 192.168.15.63     |
+| 192.168.15.64  | 192.168.15.65 - 192.168.15.78   | 192.168.15.79     |
+| 192.168.15.80  | 192.168.15.81 - 192.168.15.94   | 192.168.15.95     |
+| 192.168.15.96  | 192.168.15.97 - 192.168.15.110  | 192.168.15.111    |
+| 192.168.15.112 | 192.168.15.113 - 192.168.15.126 | 192.168.15.127    |
+| 192.168.15.128 | 192.168.15.129 - 192.168.15.142 | 192.168.15.143    |
+| 192.168.15.144 | 192.168.15.145 - 192.168.15.158 | 192.168.15.159    |
+| 192.168.15.160 | 192.168.15.161 - 192.168.15.175 | 192.168.15.175    |
+| 192.168.15.176 | 192.168.15.176 - 192.168.15.190 | 192.168.15.191    |
+| 192.168.15.192 | 192.168.15.193 - 192.168.15.206 | 192.168.15.207    |
+| 192.168.15.208 | 192.168.15.209 - 192.168.15.222 | 192.168.15.223    |
+| 192.168.15.224 | 192.168.15.225 - 192.168.15.238 | 192.168.15.239    |
+| 192.168.15.240 | 192.168.15.241 - 192.168.15.254 | 192.168.15.255    |

8th-Semester-Spring-2025/weapon-systems/equation-sheet/\

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+---
+author: Aidan Sharpe
+geometry: margin=1in
+---
+
+#### Mach number:
+$M = \frac{v_\text{missile}}{v_\text{sound}}$
+
+#### Dynamic pressure:
+$Q = \frac{\rho}{2}v^2 \approx 0.7 P M^2$
+
+#### Pressure waves:
+$\mu = \arcsin\left(\frac{1}{\text{M}}\right)$
+
+

8th-Semester-Spring-2025/weapon-systems/equation-sheet/equation-sheet.md

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+---
+title: Weapon Systems Midterm Equation Sheet
+author: Aidan Sharpe
+geometry: margin=1in
+---
+
+# Aerodynamics
+
+#### Mach number:
+$M = \frac{v_\text{missile}}{v_\text{sound}}$
+
+#### Dynamic pressure:
+$Q = \frac{\rho}{2}v^2 \approx 0.7 P M^2$, where $\rho$ is ambient density, $v$ is the missile velocity, $P$ is the ambient pressure, and $M$ is the Mach number.
+
+#### Pressure waves:
+$\mu = \arcsin\left(\frac{1}{\text{M}}\right)$, the angle of a supersonic shock wave above the direction of motion, where $M$ is the Mach number.
+
+#### Force coefficients:
+$C_N = \frac{N}{Q S_\text{Ref}} \approx C_{N_\alpha} \alpha$, where $N$ is the normal force, $S_\text{Ref}$ is the maximum cross-sectional area (calculate using diameter of the missile), $C_{N_\alpha}$ is a constant, and $\alpha$ is the angle of attack.
+
+#### Moment coefficients:
+$C_m = \frac{m}{Q S_\text{Ref} L_\text{Ref}}$, where $m$ is the pitching moment, and $L_\text{Ref}$ is the reference length.
+
+#### Induced drag:
+$C_{D_I} = C_N \alpha = C_{N_\alpha} \alpha^2 = \frac{1}{C_{N_\alpha}} \left(\frac{n_z W}{Q S_\text{Ref}}\right)^2$, where $n_z$ is the maneuver acceleration, and $W$ is the missile weight.
+
+#### Maneuver G's:
+$n_z = \frac{N}{W} = C_{N_\alpha} \frac{\alpha Q S_\text{Ref}}{W}$, where $N$ is the normal force, and $W$ is the missile weight.
+
+#### Lift:
+$L = N\cos(\alpha) - A\sin(\alpha) \approx N$, where $N$ is the normal force, and $A$ is axial drag.
+
+#### Drag:
+$D = A\cos(\alpha) + N\sin(\alpha) \approx A + N\alpha$, where $A$ is axial drag, and $N$ is normal force.
+
+#### Static margin:
+$SM = CG - CP$, where $CG$ is the center of gravity, and $CP$ is the center of pressure. Unstable when $SM > 0$ (CG is aft of CP). As a rule of thumb, $SM \approx -0.5d$, where $d$ is the missile diameter.
+
+#### Body fineness ratio:
+$BFR = \frac{l}{d}$, where $l$ is the missile length, and $d$ is the missile diameter. Typically between 5 and 25.
+
+#### Nose fineness ratio:
+$NFR = \frac{l}{d}$, where $l$ is the nose length, and $d$ is the maximum nose diameter. Typically between 2 and 4.
+
+# Rocket Propulsion
+
+#### Rocket thrust:
+$F = \frac{\dot{W} v_e}{g} + (P_e + P_a)A_e = \frac{P_0 A^*}{C^*}v_e + (P_e + P_a)A_e$, where $\dot{W}$ is the propellant weight flow rate, $v_e$ is the exhaust exit velocity, $P_e$ is the exit pressure, $P_a$ is the outside pressure, and $A_e$ is the nozzle exit area.
+
+#### Mass flow rate:
+$\dot{m} = \frac{\dot{W}}{g}$
+
+#### Weight flow rate:
+$\dot{W} = g\frac{P_0 A^*}{C^*}$, where $P_0$ is the chamber pressure, $A^*$ is the throat area, and $C^*$ is the characteristic velocity of burned propellants.
+
+#### Characteristic velocity:
+$C^* = \frac{223}{K}\sqrt{\frac{T_0}{m}}$, where $m$ is molecular weight, $K$ is a function of the specific heat ratio, and $T_0$ is the flame temperature.
+
+#### Specific impulse:
+$I_{sp} = \frac{F}{\dot{W}}$
+
+#### Exit velocity:
+$v_e = g I_{sp}$
+
+#### Ideal burnout velocity:
+$V_{BO_I} = g I_{sp} \ln\left(\frac{W_L}{W_{BO}}\right)$, where $W_L$ is the weight of the vehicle at launch, and $W_{BO}$ is the weight of the vehicle at burnout.
+
+#### Realistic burnout velocity:
+$V_{BO} = V_{BO_I} - g \sin(\bar{\gamma})T_{BO}$, where $\bar{\gamma}$ is the average flight path angle, and $T_{BO}$ is the time at burnout.
+
+#### Rocket velocity:
+$v(t) = v_0 + v_e \ln\left(\frac{m_0}{m(t)}\right) - g\sin(\bar{\gamma})t$, where $v_0$ is the initial velocity, $m_0$ is the initial mass, and $m(t)$ is the mass at time $t$.
+
+# Weapon Control Systems
+
+#### Total engagement time:
+$TET = \frac{ROF - R_\text{min}}{v_t}$, where $ROF$ is the range of open fire, $R_\text{min}$ is the range of the final shot, and $v_t$ is the velocity of the target.
+
+#### Duration of first shot:
+$TOF_1 = \frac{ROF}{v_m + v_t}$, where $v_m$ is the velocity of the missile, and $v_t$ is the velocity of the target.
+
+#### Depth of fire:
+$DOF = \frac{TET - TOF_1}{T_H} + 1$, where $T_H$ is the homing time.
+
+#### Time between launches:
+$\Delta T_L = T_H\left(1 + \frac{v_t}{v_m}\right)$, where $T_H$ is homing time, $v_t$ is the velocity of the target, and $v_m$ is the velocity of the missile.
+
+#### Total launching time:
+$N_L = N \Delta T_L$
+
+#### Time to go:
+$TGO = \frac{|\vec{R}_{TM}|}{\cos(\theta_m)|\bar{v}_m| + \cos(\theta_t)|v_t}$, where $R_{TM}$ is the vector from the missile to the target, $\theta_m$ is the angle between $\bar{v_m}$ and $\vec{R}_{TM}$, $\bar{v_m}$ is the average remaining weapon velocity, $\theta_t$ is the angle between $\vec{R}_{TM}$ and $v_t$, and $v_t$ is the target velocity (assumed constant).
+
+#### Predicted intercept point:
+$\overrightarrow{PIP} = \vec{R}_T + TGO \vec{v_t}$, where $R_T$ is the current vector from the illuminator to the target.
+
+#### Power density at the missile seeker:
+$PDMS = \frac{P_T G_T \sigma_{RCS}}{L_{IL} (4\pi)^2 R_T^2 R_{TM}^2}$, where $P_T$ is the illuminator transmit power, $G_T$ is the antenna gain, $\sigma_{RCS}$ is the radar cross section of the target, $L_{IL}$ is the total of the transmit losses of the illuminator, $R_T$ is the distance from the RF source to the target, and $R_{TM}$ is the distance from the target to the missile seeker.
+
+# Trajectory Design
+
+#### Midcourse heading error:
+$\varepsilon = \arccos\left(\frac{\vec{R}_{TGO} \cdot \vec{v}_{M}}{|\vec{R}_{TGO}| |\vec{v}_{M}|}\right)$
+
+#### Terminal guidance heading error:
+$\varepsilon = \arccos\left(\frac{\vec{R}_{TM} \cdot \vec{v}_{TM}}{|\vec{R}_{TM}| |\vec{v}_{TM}|}\right)$
+
+#### Thrust energy optimization:
+$E_\text{thrust} = E_\text{preburnout drag} + \int\limits_{s_\text{burnout}}^{s_\text{final}} \text{Drag} ds + E_\text{grain} + \frac{1}{2}\frac{W_M}{g}v_\text{final}^2 + W_M(h_\text{final} - h_\text{initial})$, where $s$ is the incremental path length of the trajectory, $v_\text{final}$ is the final velocity of the interceptor, $h$ is the interceptor altitude, $W_M$ is the weight of the interceptor without fuel. 
+
+#### Optimal dynamic pressure:
+$Q_\text{opt} = \frac{W_M}{s_\text{Ref}}\sqrt{C_A C_{N_\alpha}}$
+
+#### Cruise altitude:
+$h_\text{opt} \approx 2.3 \times 10^4 \ln\left(\frac{W_M}{s_\text{Ref} M^2 \sqrt{C_A C_{N_\alpha}}}\right)$, where $W_M$ is the weight of the empty missile and $M$ is the Mach number.
+
+#### Optimal turn:
+$R_\text{opt} = \frac{v^2}{n_z g}$