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Extra info for Spacecraft Structures
The structure must be able to support this load without failing. The calculated stresses when the ultimate loads were applied are known as ultimate stress. 4 Buckling Load The buckling load is the design load multiplied by the buckling safety factor. The most unfavourable combination of buckling loads must not lead to buckling or failure of the structure. Imperfections should also be accounted for (knock down factors). 5 Yield Load The yield load is the design load multiplied by a yield safety factor.
Fig. 3. 6 a. 4 Mechanical Dynamic loads The mechanical dynamic loads during launch can subdivided into: • Low frequency sinusoidal vibrations in a frequency domain of 5–100 Hz. • Random vibrations in a frequency range of 20 – 2000 Hz. An example of the low frequency acceleration is illustrated in Fig. 2 and an example of high frequency acceleration is shown in Fig. 3. 1 Sinusoidal loads Low frequency sinusoidal vibrations occur as a result of the interaction between launch vehicle mode forms and loads occuring during [NASA Practice No.
3 Ultimate Load In general, the ultimate load is the design load multiplied by a factor of safety (FOS). The ultimate loads are the most critical loads for the design. The structure must be able to support this load without failing. The calculated stresses when the ultimate loads were applied are known as ultimate stress. 4 Buckling Load The buckling load is the design load multiplied by the buckling safety factor. The most unfavourable combination of buckling loads must not lead to buckling or failure of the structure.