Recent content by Philosophaie

I would like to know a initial launch radius and velocity vectors after the orbiter first establishes a ballistic orbit of a typical rocket launch (Space Shuttle, Saturn V, etc). R = (rx)*i + (ry)*j + (rz)*k V = (vx)*i + (vy)*j + (vz)*k i - Direction of the Vernal Equinox j - Righthand rule 90...

Juno Spacecraft flyby Juno Spacecraft Launch : Aug 5, 2011 16:25 UTC Separation : Aug 5, 2011 17:18:11.12 UTC DSM-1 : Aug 30, 2012 22:29 UTC (344.95 m/s) DSM-2 : Sep 3, 2012 22:29 UTC (387.77 m/s) Earth Flyby : Oct 9, 2013 14:01 UTC...

All Data is in Ecliptic form. x is on the Vernal Equinox, y is on the Ecliptic plane 90 degree from the Vernal Equinox and z is perpendicular to the Ecliptic plane. Are there some changes to this coordinate system that needs changing?

At the Apogee I have a radius (rx,ry,rz) and a velocity (vx,vy,vz). I want to expand the ellipse using Hohmann Transfer. v=Math.Sqr(vx^2+vy^2+vz^2) uv=(vx/v,vy/v,vz/v) Here is where my delema is: vNew is the desired instantaneous velocity which will keep on the same plane you must...

(ax,ay,az)X(arx,ary,arz) = 0 where a is the original acceleration and ar is the introduced roll acceleration perpendicular to vector (ax,ay,ay). Find ar. Introducing vector ap = (apx,apy,apz). It is also perpendicular to a. How do I tell if it us on the same plane as ar?

I would like to know how to find a acceleration perpendicular to the center of mass for an object traveling in a RA and DEC direction at an arbitrary angle away from the perpendicular to an object. I want to know this to be able to produce a Roll with a constant vectoring of the engines to...

Where can I get supersonic (above the speed of sound and in the Roll) equation for Air Drag Force? Below .8 the speed of sound this equation works: Fd = 1 / 2 * Cd * density * A * v ^ 2 How do I find the air drag coefficient Cd and Surface Area for subsonic? Sorry for double posting...

Looking for Air Drag Coefficient, Cd, and the Surface Area, A, for the Space Shuttle, Saturn V and other rockets so I can calculate the Air Drag Force on the Shuttle. I know the Air Density as it varies with km height. density @sea level is about 1.2kg/m^3...

Is there any further limiting factor than: acceleration=Force/mass that may limit the acceleration?

What is the average acceleration of the Space Shuttle in its first stages from liftoff? I get 15 km/s^2. That seems a little high where the gravitational forces toward the Earth are mu / R^2 = 0.00981 km/s^2 at liftoff.

Just stating a fact on the MN conversion factor. Need to know if acceleration equation is correct!

I am trying to make a computer model of a Space Shuttle launch. Wikipedia give some data but does not give a path to follow. Any more comprehensive sites would be helpful. Here is my math: MN = 1e6 * kg * m / s^2 = 1e3 * kg * km / s^2 acceleration = Force(in MN) / Mass (Is this...

Is a Rocket tilted South in the Northern Hemisphere Launch Site due to the Geocentric Latitude and Geodetic Latitude being different? Would there be no tilt at the equator because LATGeo = LAT = 0 neglecting the wind?

I have a program that takes three Geocentric Equitorial Radius vectors then give a result of the Keplerian Elements.: a, e, i, w N or TA. I need a long string data of Req,RA and DEC then any Keplerian Elements for a double check on my work. The Satellite does not matter, a low-earth or...

So a hyperbolic transfer manuver would be best to straighten an orbit into an stable ellipse just after launch.