Wernher Von Braun And Anti Gravity
Von Braun's 50-Year-Old Secret:
The US Explorer I Discovery that Could Have Saved the World ….
The secret of gravity and inertia themselves ... revealed as a true "anti-gravity effect" -- somehow operating on Explorer I ... radically affecting its very orbit!
http://www.enterprisemission.com/Von_Braun.htm
https://web.archive.org/web/20150413181733/http://www.enterprisemission.com/Von_Braun.htm
The above website gives a detailed look at the launch of America's first sattelite. It seems to be another case where rotating bodies may have anti gravitational anomalies. An important lesson could have been learned, but as usual anomalies are buried and ignored.
In summary:
The launch velocity, and therefore the orbital height and duration, was 20% greater than expected using normal physics calculations.
The solid fuel booster section, about 2000lb, was a cluster of 11 rocket engines for the second stage, and which also contained 3 rocket engines for the 3rd stage. This was spun up to about 750 RPM before launch. This was designed to stabilize the rocket if the multi engine array of the 2nd or 3rd stages burned unevenly. (Compensate for thrust imbalance.)
Subsequent satelite launchings exhibited the same characteristics.
It is unknown if any further development of this anomaly has taken place.
The US Explorer I Discovery that Could Have Saved the World ….
The secret of gravity and inertia themselves ... revealed as a true "anti-gravity effect" -- somehow operating on Explorer I ... radically affecting its very orbit!
http://www.enterprisemission.com/Von_Braun.htm
https://web.archive.org/web/20150413181733/http://www.enterprisemission.com/Von_Braun.htm
The above website gives a detailed look at the launch of America's first sattelite. It seems to be another case where rotating bodies may have anti gravitational anomalies. An important lesson could have been learned, but as usual anomalies are buried and ignored.
In summary:
The launch velocity, and therefore the orbital height and duration, was 20% greater than expected using normal physics calculations.
The solid fuel booster section, about 2000lb, was a cluster of 11 rocket engines for the second stage, and which also contained 3 rocket engines for the 3rd stage. This was spun up to about 750 RPM before launch. This was designed to stabilize the rocket if the multi engine array of the 2nd or 3rd stages burned unevenly. (Compensate for thrust imbalance.)
Subsequent satelite launchings exhibited the same characteristics.
It is unknown if any further development of this anomaly has taken place.
JUPITER C Fact Sheet Written and Edited by Cliff Lethbridge
Like the Juno I, the Jupiter C clustered second and third stages were housed inside a distinctive rotating "tub", spin-stabilized at several hundred revolutions per minute (actual spin rate depended on the weight of the payload) during ascent. This rotating motion was designed to stabilize the upper stages during flight. http://www.spaceline.org/rocketsum/jupiter-c.html
Fuel Tub rotated on pad before launch.
Jupiter-C
Characteristics
The Jupiter-C rocket was originally developed to test the ablative re-entry nose cone of the Jupiter IRBM, although its satellite-launching capabilities were recognized at the time it was designed.
The vehicle consists of a modified Redstone ballistic missile topped by three solid propellant upper stages. The tankage of the Redstone was lengthened by eight feet to provide additional propellant. The instrument compartment is also smaller and lighter than the Redstone's. The second and third stages are clustered in a "tub" atop the vehicle, while the fourth stage is atop the tub itself. The second stage is an outer ring of eleven scaled-down Sergeant rocket engines; the third stage is a cluster of three scaled down Sergeant rockets grouped within. These are held in position by bulkheads and rings and are surrounded by a cylindrical outer shell. The webbed base plate of the shell rests on a ball-bearing shaft mounted on the first-stage instrument section. Two electric motors spin in the tub at a rate varying from 450 to 750 rpm to compensate for thrust imbalance when the clustered motors fire. The rate of spin is varied by a programmer so that it does not couple with the changing resonant frequency of the first stage during flight.
The upper-stage tub was spun-up before launch. During first-stage flight, the vehicle was guided by a gyro-controleld autopilot controlling both air-vanes and jet vanes on the first stage by means of servos. Following a vertical launch from a simple steel table, the vehicle was programmed so that it was travelling at an angle of 40 degrees from the horizontal at burnout of the first stage, which occurred 157 seconds after launch. At first-stage burnout, explosive bolts fired and springs separated the instrument section from the first-stage tankage. The instrument section and the spinning tub were slowly tipped to a horizontal position by means of four air jets located at the base of the instrument section. When the apex of the vertical flight occurred after a coasting flight of about 247 seconds, a radio signal from the ground ignited the eleven-rocket cluster of the second stage, separating the tub from the instrument section. The third and fourth stages were fired in turn to boost the satellite and fourth stage to an orbital velocity of 18,000 miles per hour.
When used as a satellite launching vehicle, the Jupiter-C is sometimes referred to as the Juno-I. https://history.nasa.gov/sputnik/expinfo.html
