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  • Die Satellitenrakete 1952

    Paper ID



    • Helmut Hoepner





    After the design of the Satellite Rocket 51 other projects have been developed by other engineers which show that the design of the SR 51 was a suitable project for its purpose and mature for advanced development. The project SR 52 treats details which up till now were neglected in the SR 51 and all other designs, which however are vitally important for a successful satellite program. There are, mainly, the requirements for safety in takeoff. The SR 52 shows the following major characteristics! 1. Takeoff safety through guided acceleration - on a catapult platform in a launching tower * until an aerodynamically stable state of flight is reached (velocity v= 200 km/h at an altitude h= 200 m). 2. Takeoff safety through the possibility of terminating unsatisfactory launching (continued control from ground installation during the launching period) up to v= 200 km/h at h= 200 m. 5. Takeoff safety through the possibility of performing optionally frequent firing and static power plant tests. Ascertaining and elimination of faults in operation. 4. Takeoff safety through the possibility of practically exercising the launching performance as often as desired and to train in launching (training program) up to v= 200 km/h at h= 200 m. 5. Takeoff safety through the possibility of detaching the last step IY (with crew, equipment and payload) during an unsatisfactory, launching up to v= 200 km/h at h= 200 m or at any other point in the ascent and landing this last step as a separate aircraft under its own power. 6. Reduction of weight and performance increase through fuelling the power plants during takeoff up to v= 200 km/h at h= 200 m from tanks installed in the catapult platform. 7. Favorable structural weight factors by proper use of possible variations open in this design, such as a) exterior mounting of power plants of the steps I, II and IV, thus simultaneous firing of the power plants of steps I & II and of steps III & IV, eventually also of steps II & III (reduction of the number of power plants required for the individual step!); b) installing the exterior power plants in an aerodynamically shaped ring (instead of in individual fins); c) designing the entire body of step I as a hanging fuel tank; d) using the wings of step IV for attaching the power plants of this step (wing-tip mount). 8. Design of the SR 52 (similar to the SR 51) for Monocoque construction with steel tubing for longitudinal and ring frame and using steel sheet planking; connections by spot welding. Power plant and tank attachments and mountings consisting of trusses made of steel tubing. Step IV in conventional airframe construction using heat resistant steel, if necessary with heat insulation layers at nose tip and leading edges. Catapult platform ring- shaped with subsonic profile (v = 200 km/h). ITlciX 9. Projected design of an artificial satellite to be constructed without any additional construction elements which would have to be carried as payload. 10. This artificial satellite as a unit can remain in its orbit for research purposes, or - as a whole - may be used for an expedition to the moon with landing and return to its former orbit. 11. Main data of the SR 52s Takeoff weight 915 tons No. of steps 4 Total length 35 m Largest Diameter (body) 8 m Mean diameter (ring) 14 m Empty Weight of step IV 8 t Wing span step IV 13 m Total fuel weight 745 t Height of launching tower 250 m Catapulted height 200 m Catapult breaking 50 m Catapulted velocity 200 km/sec Duration of one full orbit of the satellite 2 h Distance of orbit from the surface of the earth 1670 km.