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**Flat Earth Debate / Re: Voyager 1 - fake?**

« **on:**November 09, 2013, 11:28:07 PM »

Clearly, neither the FES or the REr's understand what an orbit IS.

Allow me to clarify:

According to Round Earth Theory, what keeps a satellite in orbit is it's HORIZONTAL velocity, not its vertical velocity. It doesn't just get a rocket to fly it up, then it just hangs there magically like the Flat Earth Sun.

What an orbit

When a rocket is launched, it flies vertically until it is out of the thickest part of the atmosphere, then

To calculate orbital velocities using RET, we use a=v

so, for a realistic altitude of 350 000m:

radius=r=350 000m + 6 400 000m (Earth's equatorial radius) = 6 750 000m

a=acceleration due to gravity=9.8 m•s

solving for v we get an orbital horizontal velocity of v=√(9.8*6 750 000)≈8100m/s

This is a ∆v of 8100m/s to get it going that fast.

For a 1,000 kg satellite, that is E=0.5•m•v

By comparison, the energy required to lift 1000kg 350 000m vertically is

E=m*g*h

h=350 000

m=1000

g=9.8

Evaluating, we get E=34 GJ.

As these two numbers are about the same, it shows that the orbiter will need about as much vertical thrust as it does horizontal.

Additionally, the further from the Earth you are, the weaker its gravitational pull is. It follows the inverse square law, which means that if you double the distance between yourself and the Centre of the Earth, the gravitational pull will be a quarter as strong. Explanation:" class="bbc_link" target="_blank">

Once one is in some kind of orbit (even a decaying one), you do something called a Hohmann transfer to raise your orbit and make it circular. Here is a video of such a transfer: " class="bbc_link" target="_blank">

This means that the most fuel is expended in the vertical stage, it requires relatively little to raise the orbit from 100,000 m to 350, 000m.

Allow me to clarify:

According to Round Earth Theory, what keeps a satellite in orbit is it's HORIZONTAL velocity, not its vertical velocity. It doesn't just get a rocket to fly it up, then it just hangs there magically like the Flat Earth Sun.

What an orbit

*is*is constantly falling (accelerating towards the centre of the Earth at 9.8m•s^{-2}), but moving so fast horizontally (normal to the direction of gravitational force) that the earth curves downwards by the same amount you've fallen.When a rocket is launched, it flies vertically until it is out of the thickest part of the atmosphere, then

**turns**to face about 45ş to vertical and begin accelerating sideways.To calculate orbital velocities using RET, we use a=v

^{2}/r. (derivation: http://blogs.msdn.com/b/matthew_van_eerde/archive/2010/01/24/deriving-the-centripetal-acceleration-formula.aspx)so, for a realistic altitude of 350 000m:

radius=r=350 000m + 6 400 000m (Earth's equatorial radius) = 6 750 000m

a=acceleration due to gravity=9.8 m•s

^{-2}solving for v we get an orbital horizontal velocity of v=√(9.8*6 750 000)≈8100m/s

This is a ∆v of 8100m/s to get it going that fast.

For a 1,000 kg satellite, that is E=0.5•m•v

^{2}= 32.8 GJ.By comparison, the energy required to lift 1000kg 350 000m vertically is

E=m*g*h

h=350 000

m=1000

g=9.8

Evaluating, we get E=34 GJ.

As these two numbers are about the same, it shows that the orbiter will need about as much vertical thrust as it does horizontal.

Additionally, the further from the Earth you are, the weaker its gravitational pull is. It follows the inverse square law, which means that if you double the distance between yourself and the Centre of the Earth, the gravitational pull will be a quarter as strong. Explanation:" class="bbc_link" target="_blank">

Once one is in some kind of orbit (even a decaying one), you do something called a Hohmann transfer to raise your orbit and make it circular. Here is a video of such a transfer: " class="bbc_link" target="_blank">

This means that the most fuel is expended in the vertical stage, it requires relatively little to raise the orbit from 100,000 m to 350, 000m.