Help
Options
Didn't know it?
click below
click below
Knew it?
click below
click below
Don't Know
Remaining cards (0)
Know
retry
shuffle
restart
0:00
Embed Code - If you would like this activity on your web page, copy the script below and paste it into your web page.
Normal Size Small Size show me how
Normal Size Small Size show me how
Aero 201 Final
| Term | Definition |
|---|---|
| Wingtip Verticies | Trailing Tip Vortexs |
| Downwash | Lowered Angle of Atk/Higher Drag |
| Total Drag | D(Coefficients = Parasitic + Induced) |
| Boundary Layers | The area around a wing where friction matters |
| Laminar Flow | high lift, low drag, reduces skin Friction |
| Turbulent Flow | Low Lift, high drag |
| 2 Types of Drag caused by Friction | Skin Friction/Pressure Form |
| Lift of Finite Wings Theory | Finite Wing AOA = Infinite Wing AOA effectively |
| Stall/Critical AOA | Angle which Lift stops Increasing |
| Stall Velocity | Lowest possible velocity at SLUF |
| What is CL at critical AOA | CL=Max |
| As AR increases? | AOA decreases |
| Flap Theory | Effective Increase in camber and Virtual increase in AOA |
| Reduced Equations of Motion | T=D & L = W |
| Thrust Required Condition | Zero Drag = Induced Drag |
| Thrust Required True Equation | TR = 2W * sqrt(k * Zero Drag) |
| Min Velocity Equation(Thrust) | VMin = [(2W/P*S) * sqrt(k/Zero Drag)]^1/2 |
| Power Required Equation | PR = 4/3[(2W^3/P*S) * sqrt(3kZero Drag)]^1/2 |
| Min Velocity Equation(Power) | VMin =[(2W/P*S) * sqrt(k/3Zero Drag)]^1/2 |
| Power Required Condition | Zero Drag = (1/3)K * CL^2 |
| Range/Endurance Conditions | 1. Amt of Fuel an Aircraft can Carry 2. Rate Fuel gets consumed 3. Aerodynamics of Aircraft |
| Range/Endurance Assumptions | 1. Fuel consumption Constant 2. AOA small 3. SLUF 4. W and fuel related 5. Stationary Atmosphere |
| Prop Range Maximization | 1. Best fuel efficiency 2. Most fuel 3. Most Aerodynamics |
| Prop Endurance Maximization | 1. Lowest c 2. most fuel 3. most fuel efficient 4. fly at sea level |
| Jet Range Maximization | 1. lowest ct 2. lowest rho 3. most fuel 4. max CL/CD^2 5. stair stepping profile |
| Jet Endurance Maximization | 1. lowest ct 2. most fuel 3. maxed coefficients |
| ROC Formula | Excess Power/W |
| ROC Conditions | AOA under 20 degrees |
| ROC Factors | 1. Wing Load 2. Max Thrust 3. Zero Drag 4. Coefficient Maxed |
| Absolute Ceiling | ROC = 0 |
| Service Ceiling | 100 ft/min ROC |
| Turning Performance Necessary Conditions | 1. Altitude Constant |
| Load Factor Constraints | 1. Thrust Avaliable 2. CL Max 3. Max Load 4. Human Factors 5. Velocity |
| Turn Radius | R = V^2/g * sqrt(n^2 -1) |
| Turn Radius/Rate Maximization | Highest n/lowest V |
| Turn Rate Equation | g*sqrt(n^2-1)/V |
| V-N Diagram | Point B: Manuever Point) Point 3: Stall Velocity Point 5: If max V, structural dmg |
| Keplers Laws | 1. Orbit = Elliipse 2. Continous Turn R 3. T^2 = d^3 |
| Newton's law of gravitation conditions | 1. Spherical Body 2. Evenly distributed mass |
| Other forces | F_other = F_D + F_Thrust + F_Perturbance + F_solar pressure |
| Circular Orbit | r =a, so V = sqrt(meu/r) |
| Escaping a Planet Trajectories | Parabolic/Hyperbolic |
| Sphere of Influence | Vol of space where mass is main influence |
| Escape Speed | Hyperbolic excess speed, speed after escaping, only in hyperbolic speed |
| Ground Track | Trace of the S/C path on Earth's surface |
| Ground Track orbital information | size = (higher orbit = smaller ground track size) i = highest latitude S/C = i e: symmetrical = circular, elliptical = lopsideded |
| Launch Window conditions | Launch window & orbital plane intersection |
| Velocity to Launch | delta(V) = V_Leo + V_loss - V_EH 1. V_Leo = excess 2. V_loss = from drag 3. V_EH = from Earth Tangential velocity |
| Hofmann transfer | Uses elliptical transfer orbit trangent to both intial & final orbits |
| Hofmann transfer limitations | 1.Orbits same plane(coplanar) 2.Orbits w major axes(Lines of apside) aligned (coapsidal orbits) or circular orbits 3. Instantaneous Velocit yChanges |
| TOF | Time to travel from Perigee to Apogee |
| Julian Date | Only one number for time |
| International Atomic Time (TAI) | 200 clocks in 50 national labs |
| GPS | constellation of satellites carrying atomic clocks |
| What does the vernal equinox direction depend on? | Ecliptical/Equatorial Plane |
| Precesssion | Earth wobbling due to sun(moves vernal equinox west) |
| Nutation | Slight nodding motion caused by moon torque |
| Mean Equinox | Position equinox with only solar precession |
| Apparent Equinox | Equinox direction w precession and nutation |
| Actuator Types | 1. Thrusters 2. Momentum Control Devices 3. Magnetic Torque |
| Thrusters | Force to rotate S/C |
| Movement ctrl devices | 1. Momentum Wheels - change spin spd 2. Reaction Wheels - change spin spd 3. Ctrl moment gyroscope - change spin direction |
| Magnetic torque | aligns with Earth's magnetic field to rotate S/C |
| Disturbance Torques | External Forces that rotate the S/C |
| Gravity Gradient | Torques through gravity boom |
| Solar Radiation Pressure | Photons striking the S/C |
| Earth's Magnetic field | Charged particle impact gives the S/C a charge, causing alignment with magnetic field |
| Gravity Torque 4 | Aerodynamics |
| Gravity Torque 5 | Space Debris |
| Sensors | Observe systems and transforms them into signals |
| Earth sensors | measures position relative to Earth, can only give pitch/roll and it is accurate at higher altitudes |
| Sun Sensors | measures thru sun location, most popular, only 2 axis |
| Star sensors | measures thru star locations, highest accuracies |
| Gyroscopes | Detects altitude directly, utilizes h conserved If no torque, same direction in inertial space torque = preccssion rate Uses precession rate for altitude |
| Magnometer | Uses Earth's magnetic field to determine orientation, only used in LEO |
| Launch to Leo: Drag Effects | Slows down S/C: lowering apogee altitude and causes circular orbit Orbit decays and S/C reneters atmosphere |
| J2 Affects on Omega | gravity effect perturbs and causes Omega movements Nodal regression rate: depends on i |
| J2 effects on W | equatorial bulge cause W to rotate |
| Sun-syncronous Orbits | omega east 1 degree per day, same with the earth |
| Molniya Orbit | Effect of Earth's oblateness on perigee postion T = 12 e = 0.7 Perigee in S Hemisphere I = 63,4 w = 270 |
Created by:
atlumahu