1General Orbit: rmin is called the ___________
Periapsis
2General Orbit: rmax is called the ___________
Apoapsis
3Heliocentric Orbit: rmin is called the ___________
Perihelion
4Heliocentric Orbit: rmax is called the ___________
Aphelion
5Geocentric Orbit: rmin is called the ___________
Perigee
6Geocentric Orbit: rmax is called the ___________
Apogee
7The prefix for Orbit Type rmin is _____
Peri
8The prefix for Orbit Type rmax is _____
Ap
9Energy Equation of an Orbit
E/m = -µ/(2a)
10The Standard Gravitational Parameter (µ) ==
G*M
11The semi-major axis of an Orbit is represented by the variable ___
a
12The equation for the velocity of a spacecraft in orbit is called the _______________
Vis-Viva Equation
13The Vis-Viva Equation ==
v = sqrt( µ * ( 2 - 1/a) )
14Kepler's Third Law Equation for the Period of an Orbit (T) ==
2*pi*a**(3/2) / sqrt(µ)
15The simplest method by which a spacecraft can alter its orbit is called the _________________
Hohamann Transfer
16The Hohmann Transfer was developed in _____ by __________________
1925, Walter Hohmann
17The path of traversal from orbit a1 to orbit a2 is called the ________________
Transfer Ellipse
18The Semi-Major Axis of the Transfer Elllipse (a) ==
(a1 + a2) / 2
19The Hohmann Transfer requires ______ Impulses to Accomplish
two
20The first Impulse of a Hohmann transfer takes place at the __________ of the ______________
periapsis, transfer ellipse
21The second Impulse of a Hohmann transfer takes place at the __________ of the ______________
apoapsis, transfer ellipse
22Velocity at the Periapsis of a Hohmann Transfer (vpte) ==
vc1 + Δv1
23Velocity at the Apoapsis of a Hohmann Transfer (vate) ==
vc2 + Δv2
24The first impulse of a Hohmann Transfer (Δv1) ==
sqrt( 2*µ/a1 - 2µ/(a1+a2) ) - sqrt( µ/a1 )
25Period of a Hohmann Transfer ==
pi * sqrt( a**3 / µ )
26Radius of Earth (Re) ==
6.371 x 10**6 m
27Mass of Earth (Me) ==
3.986 x 10**14 kg
28Height (h) is the height above __________
Sea Level
29The Radius of Orbit around Earth (r) ==
h + Re
30When atmospheric particles cause drag, which decreases satellite speed and altitude, it can be labeled as a process called __________Eccentricity
Decay
31The Von Karman Line sits at _______ km above sea level
100 km
32When a satellite is in High Earth Orbit (HEO), it appears to be moving __________ in the sky, which is in the direction ____________
backwards, westward
33The constant defining the shape of the conic section of an orbit is _________
Eccentricity (ϵ)
34Orbital Elements: The angle between the plane of reference and the plane of orbit is the __________
Inclination (i)
35Orbital Elements: The angle from the reference direction to the intersection of planes is called the ___________
Longitude of Ascending Node (Ω)
36Orbital Elements: The angle between the semi-major axis of the orbital plane and the intersection of planes is called the ____________
Argument of Periapsis (w)
37An orbit coplanar to the equator is called _________
Equatorial Orbit
38The orbital plane of the earth around the sun is called _________
Eclipitcal Orbit
39The Angle between the Equatorial and Eclipitcal Planes ==2r
23 degrees, 27 inches
40What is it called when a plane of orbit is rotated about its center?
Inclination
41When a plane of orbit is inclined, its _______________ Vector must also shiftsqrt
Angular Momentum (H)
42The change in Angular Momentum of an Inclined Orbital Plane (ΔH) == (Equation 1)
2*r*V*Sin(θ/2), where V is the velocity of the object in orbit and θ is the angle of inclination
43The change in Angular Momentum of an Inclined Orbital Plane (ΔH) == (Equation 2)
r*ΔV , where ΔV is the change in velocities from orbit 1 to orbit 2
44Eccentricity (e) ==
sqrt( 1 + 2*(H**2 / µe**2 ) * (E/m) )
45Orbital Elements: The point at which the orbital planes intersect is called the ____________
Ascending Node
46Orbital Elements: The line of all intersections of orbital planes (Ascending Nodes) is called the ___________Cos
Node Vector
47Angular Momentum Vector (H) ==
r.cross(V)
48The Node Vector (n) ==
a.cross(H) , where a is the semi-major axis of the orbital plane
49Inclination (i) ==
arccos(H/||H||)
50Longtidue of Ascending Node (omega) ==
arccos(n/||n||)
51Argument of Periapsis (w) ==Paramter
arccos( (n.dot(e)) / ( ||n|| ||e|| ) )
52True Anomaly (v) ==
arccos(e.dot(r) /( ||e|| ||r|| ) )
53Sometimes, a Gravitational __________ P is given
Parameter
54Parameter (P) == (Equation 1)
H**2 / µ
55Paramter (P) == (Equation 2)
a(1-e**2)
56Given a Parameter (P), radius of a Circular Orbit ==
P / (1 + e*Cos(v))
57Rocket Engines utilize both the ____ and the ______, independent of the _______
fuel, oxidizer, atmosphere
58When only the fuel is carried onboard and the surrounding atmosphere is used at the oxidizer, we call this kind of propulsion ___________
Air Breathing Propulsion
59When both the fuel and oxidizer is onboard, we call this kind of propulsion __________
Rocket Propulsion
60Newton's First Law:
Objects at rest stay at rest etc etc
61Newton's Second Law:
The time rate of change of the Momentum of an Object is equal to the Force
62Newton's Third Law:
For every action, there is an equal and opposite reaction
63Solid Propellant is housed in the _________________
Combustion Chamber
64Solid Propellant is always in the form of a __________
Grain
65The surface of the Solid Propellant Grain must be _________, or risk of ___________ and __________ is heightened
smooth, cracks burning, explosions
66Liquid Fuel is stored in ________ next to the _________ tank that funnels liquid into a combustion chamber
tanks, pressure
67The downsides to liquid fuel are that it is highly _______ and difficult to ________
volatile (unsafe) , store
68In Rocket Kinetics, b is the symbol for ________
mass flow rate
69In Rocket Kinetics, c is the symbol for ________
exhaust velocity
70The Rocket Equation ==
m*a = -b*c + Fexternal
71The rocket nozzle that is shaped like Mrs. Fogarty is called the _________
De Laval Nozzle
72The change in Velocity due to Loss of Mass (delta V) ==
-c * ln( m0 / m )
73When does gravity and drag have the most effect on a rocket?
The initial burn closest to the Earth's surface
74Mass Ratio (Z) ==
m0 / ( m_structure + m_payload )
75Payload Ratio ( lambda ) ==
m_payload / ( m_propellant + m_structure )
76Structural Coefficient (Epsilon) ==
m_structure / ( m_propellant + m_structure )