Calculation ex. The volume of a r=13,5*10^9 ly universe can fit 2,2*10^12 galaxies 3,3*10^6 ly apart. Looking trough a r=13*10^9 ly and 13*10^9 ly long cylinder , it is having 1,06*10^12 galaxies of 1,2*10^31 m3/s2 (90 billion sun masses ). Randomly dispersed average distance from centerline is 8,2*10^25m giving average of 500 simulated z=8,6*10š-12 times 1,06*10^12 give redshift about 9. Reminding me of something I've read. The distances r,l,d are assumed but their ratio hold.

For shorter stints or distances s=c/t the redshift is z=gtot*t/c where gtot is sum of all gravitation from all directions. Using 21.century celestial masses Mi that are 1,13 times mainstream masses and mn mass of nucleon 1,671*10^-27kg

Formulas can be written (delta)E/E=Mi*mn*c*t/(2*rš2) and (delta)E/t=Mi*mn*c^2/(2*rš2*(lambda)) =gtot*hi/(lambda). Close to planets gtot values are very different from classic g (mainstream). Here a few picked values from earth altitudes for using in calculating photon decay onboard satellites.

Altitude over sea level 0km 15,92m/s2 10km 15,82m/s2 20km15,73m/s2 50km15,48m/s2 100km15,11m/s2 200km14,45m/s2 300km13,86m/s2 400km13,32m/s2 500km12,82m/s2 1000km10,77m/s2 2000km8,02m/s2 5000km4,12m/s2 10000km1,936m/s2 20000km0,736m/s2 30000km0,385m/s2. For higher altitudes gtot=1,27*classic g +0,0075m/s2 for sun.

For the moon I have not calculated, but rough comparisons surprised me by suggesting proportionally same size heavy core as earths. This would mean that moon is a miniature of earth with high altitude g=1,27*classic. ]]>

Calculating v^2*rINT^-1 The integral is for calculating the energy of orbits E=”*INT. Using a=ap+btot , p=per-btot

rc^-1=((a^2+p^2)^0,5*(8a^2+8p^2)-2^(5/2)*p^3-3*2^(5/2)*a^2*p)/(3*2^0,5*(p^4-2*a^2*p^2+a^4))+

((a^2+p^2)^0,5*(8a^2+8p^2)-2^(5/2)*a^3-3*2^(5/2)*p^2*a)/(3*2^0,5*(p^4-2*a^2*p^2+a^4)) . A would be nice column table show that multiplication of Wiki values v^2*semimajor give for most very similar numbers, except. Mercury and Pluto, others are less smaller.

This become useful for calculating elliptical (equatorial) orbits (artificial planets) . v^2=rc^-1*”tot. ”tot is 1,326*10^20 m3/s2 +2*M*G of every inside the planned orbit planets. a is still ap+btot and p=per-btot.

This give much more accurate results (tested with the small planets) than older methods.

0km 3,877 10km 3,888 20km 3,896 25km 3,899 30km3,903 50km3,915 100km3,938 200km 3,973 300km4,000 400km4,020 500km4,037 600km4,051 700km4,063 800km4,073 1000km4,088 1500km4,111 2000km4,019 2500km4,1208 3000km 4,118 5000km 4,096 10000km4,049 20000km4,011 30000km3,998 40000km3,993 70000km3,987 100000km3,985 160000km3,9844 moon=> forever 4,02*10^14 m3/s2.

These number are from rough input and can easily be 1/0,005 of (0,5%)

I can use mainstream parameters but I need remind free fall g is ”*4/(pi*r^2), as the Voyager probes experienced.

EXAMPLE. We send up a satellite to orbit from outside Venus per=1,09*10^11m to inside of Mars ap=2,06*10^11m . The sum total wobble btot=5*10^9m, so we put rc^1 formula a=2,11*10^11m and p=1,04*10^11m and get rc^-1=6,528978*10^-12m-1. To ” we ad M*G of Merc. Venus and Earth 7,47*10^14+1,326*10^20=1,326007*10^20m3/s2. (”*rc^-1)^0,5= 29287,6m/s sat. mean speed Since a light satellite b=0 and perimeter (ap+per)^0,5*(2*ap^2+2*per^2)^0,25*pi= 1,0122705*10^12m . This give perim/v=398,18 days orbit.

EXAMPLE2 We want to have a sat. 25,000km to 43,41km over the equator. Earth grav. parameter seem quite constant aver. 3,977*10^14 m3/s2. Since btot is bmoon 4,671*10^6 , we have a=51,33*10^6m and p=32,918*10^6m This give from the (long formula) rc^-1=2,437232*10^-8 m-1. (3,977*10^14*rc^-1)^0,5=3107,74m/s, perimeter=(a+p)^0,5*(2*aš2+2*p^2)^0,25*pi= 267778150m that give a T=23,9344h. A geostationary "bouncer";-) ]]>