The finite element model of structural dynamics of fuselage frame of unmanned helicopter was established and the natural frequencies and mode shapes of its first 6 orders were obtained. Compared with modal test, the maximum error of calculation was less than 3 %. It shows that the finite element model is correct and accurately reflects the structural dynamics character of the fuselage frame of unmanned helicopter. The computational natural frequencies of frame avoided the natural frequencies of main rotor, tail blade and engine and can meet the request of dynamic of unmanned helicopter. The dynamic analysis method based on finite element analyses, which combines verification test and modal modification, can effectively guarantee the accuracy of the fuselage frame of unmanned helicopter. And it also provides the refrence for finite element dynamic modeling about other structure??of unmanned helicopter.