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my school cheat sheet for aerospace course

Nasser M. Abbasi

July 2, 2015 page compiled on July 2, 2015 at 5:52pm


Equation of a conic section: r =  1+epcosν-

Ellipse equation: a2 = b2 + c2

relating energy to geometry

E = − 2a

relating energy to velocity and position:

     V 2   μ
E =  ---−  --
      2    r

Velocity found from geometry and position: using equatings (1a) (1b), we get


Velocity can be found knowing Energy and position: from (1b) we solve for V

V  = ∘2 -(-μ-+-E-)-

Relating angular momentum to geometry:

p = h--

Which is valid for any orbit.

h = r × V

p = a − a e2 = ⇒ p = a (1 − e2)  from geometry (1)

rp = a − a e =⇒ rp = a(1 − e)  from geometry (2)

ra = a + a e =⇒ ra = a (1 + e)  from geometry (3)

c = a e  by geometry definition.

e  can also be found from physics as

    ∘  ----------
e =    1 + ---2--

so, given the angular momentum and the mechanical energy, we can find e

e = ra −-rp
    ra + rp

            ∘ ---
Period = 2π   -μ-

rp = -----
     1 + e

ra = 1 − e

These can be derived from (1) and (2)

e = V--×-h-−  r-
       μ      r

conic eccentricity Energy E a

circle 0  −  ve  + ve

ellipse 0 ≺ e ≺ 1  −  ve  + ve

parabola 1  0  ∞

hyperbola e ≻ 0  +  ve  − ve

Figure 1: elements

           ∘ ------
    (ν )      1 + e    ( E )
tan  --  =    -----tan   --
     2        1 − e      2

M  = E  − esin E

where M  = ωt  where ω  is the average angular velocity of the probe, and t  is the time we wish to find the angle E  at which the probe is located. hence M  is the distance traveled (in radian angles) by the probe in the eccentric model. But                       ∘ ---
ω =  -2π-- = --2∘π-3=    -μ3
     Period   2π  aμ-     a   (you see this have units as radians per unit time). so (4) is

ωt = E  − esin E

M  = E  − esin E

F (E ) = E − e sin E − M

  Solve using Newton method. use

           ∘ ---
E0 =  M  =   a3 t

r = a(1 − ecos E ) = ----------
                     1 + ecosν

1 Rocket Equations

effective Isp  officially is the total impulse per total mass expelled to generate this impulse.

i.e. effective           I
Isp = total mtopt ealxpelled   =thrust∗time
-total mp-
in units: NT-   M-TL2T-   L-
 M  =   M   =  T  so it has the units of speed!

To convert it to Isp  , Isp = effectgiv_e-Isp = Vge_-
           c        c   notice that effective Isp  is the same as Ve.

In units then        L-
Isp = (T L-)-= T
       T2  i.e. seconds, which is what we use

The above is the average specific impulse.

To find the instantaneous specific impulse        d-Isp
Ispi = ddtmp- = thrβust

From the net

  Specific impulse is defined as the number of seconds for which a
  pound of propellant will produce a pound of thrust

from the net

  Outside of the United States
  specific impulse is in metres per second, and is identical to the effective
  velocity of the exhaust gas from the rocket.

from net

  Specific Impulse is a measure of the Thrust produced by an engine per
  the mass flowrate of propellant and thus the correct SI unit is Ns/kg or
  when the Newton is expanded and the units are cancelled down, m/s.

from net

  The unit of seconds comes from some very silly cancelling when using old
  units. If you measure thrust in lbf and you measure flowrate in lb/sec then
  you get lbf.s/lb. Then if you cancel the two lb parts.... you get left with
  seconds. This means that to make any use of the value it has to be multiplied
  by g to put it into sensible units (s.m/s\symbol{94}2 = m/s again).

impulse = change in momentum

Specific impulse is defined as dI∕dm  , in any system of units you care to name.

One definition I saw of specific impulse is

  how long you can thrust at a given force with a pound of fuel.

from net

  specific impulse is a measure of how long
  a given amount of fuel can provide a thrust equal to its own

Isp  is the momentum gained per unit weight of propellant used during this momentum change. The momentum gained results from the loss of the mp  from the total mass.

Hence, assume we consume mp  propellant mass, then

     (m0-−mf)Ve   mpVe    Ve   smec-
Isp =    mp g    = mp g =  g =  smec2 = sec

mo = mL  + mp  + ms

mf =  mL +  ms

Final velocity = V  ln Z

Where      m0-  mL+ms+mp--
Z =  mf =   mL+ms

payload ratio (Prussing def) λ = msm+Lmp-    this is class definition also

structural ratio 𝜖 = --ms--

payload ratio (Wisel def)      ---mL-----   mL-
π =  mL+ms+mp  =  m0

mmf0-= 𝜖 + (1 + 𝜖)π

Notice that Z  can also be written as Z =  1+-λ-
     𝜖+ λ

Methods: Given masses, if asked to find ΔV  do

use similar stages. set up the λ1 = λ2   solve for m02, m01
set up 𝜖 =  𝜖
 1    2   , solve for m  ,m
 s1   s2   . Need to use result of step 1 (m
  02   or m
  01   ) to help solve. Also, given that ms1 +  ms2 = ms  (which is given)
Now that we know the ms  and m0   for the stages, we calculate λ1   and 𝜖1   and find Z =  1+λ
ΔV  =  nVeln Z  where n  is the number of stages.

β  is the rate at which the propellant is consumed =  dm--
   dt  assumed constant. Also called engine mass flow rate. in other words, it is the rate at which MASS is exiting the nozzle of the rocket engine. If we multiply this quantity by how fast this rate of mass is changing (i.e. Ve  ), we get an acceleration time mass, hence force, which is the engine thrust. This causes the rocket to go up.

For space shuttle, V =  4500
 e  m/sec. β = 222  kg/sec, hence engine generates a thrust (force) of 4500 ∗ 222 ≃ 1,000, 000  Newton

Impulse = thrust * time thrust applied.

i.e. total impulse I = T t

So, Thrust T,  is the rate of change of impulse. The faster the impulse changes, the larger the thrust.

thrust =  β Ve

     mf-−-m0-  −-mp
β =    tbo    =  tbo   so, if I can find β  given Isp  , then I can find the time it takes to reach burn out for some given mp.

In other words, time it takes to burnout      m
tbo = -βp

Specific Impulse (ISP), or how much thrust you get from each pound of fuel is very important.

Generally, DELTA V = LN(MASS RATIO)* ISP*G That means that the Specific Impulse (ISP), or how much thrust you get from each pound of fuel is very important, and the Mass Ratio, or what percentage of your vehicle is propellant is less important. For each stage you can set an ISP to determine how much propellant you will use for the thrust you need. Then set a mass ratio to determine how much metal you wish to wrap around the propellant. The rule of Thumb is that higher stages get the better ISPs and Mass Ratios because they are smaller and they include the cost of the boosters. Boosters are the work horses, low ISP because of atmospheric back pressure, and heavy, but you can buy them by the pound cheap. Also, the ISP is set mostly by the propellant choice, the Mass Ratio on the other hand is determined by how much money you wish to spend on light weight materials. The lightest know material for construction is Unobtainium.

Solve for η  :

         ∑          (      )
ΔVtotal −  Ni=1Vei ln  ηVηVeiei−𝜀1i  =  0

Next find Z :

Zi =  ηVei𝜀i