An analytical and experimental study of boost phase heating of satellite 1963 22A has been accomplished. Two stages of heating were considered: (1) Radioactive and convective heat transfer between heat shield and payload, and (2) Direct aerodynamic heating after heat shield ejection. The results show that a maximum temperature rise possible on any portion of the payload is 38°F before heat shield ejection and about 240°F after heat shield ejection. However, the latter temperature rise is highly localized and the associated heat input is easily accommodated by the payload without any perceptible overall temperature increase. It was concluded that, for the contemplated boost trajectory, no serious heating of the satellite would be encountered.
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