• Linear Analysis - Linear control system and structural model • The SSPS can be modeled as a free-free beam • The SSPS is structurally symmetric. Discussion.- The objective of this study phase was to (a) evaluate the flight control performance of the baseline system, and (b) to conduct a parametric sizing study to determine the sensitivity of the system's performance to variations in structural stiffness. These tasks were performed by using the parametric performance indices developed in Reference 35 and the resluts of the structural analysis presented in Reference 36. Additional studies were also conducted using a non-real time 360-75 digital simulation of ti e .. ntrolled dynamics of the SSPS. Since the overall study has assumed that the rotational dynamics of the SSPS are uncoupled, individual analyses have been performed for the pitch, roll, and yaw modes. The results of each of these evaluations are presented below. a. Pitch Mode Pitch mode dynamics have been defined to be rotation about the spacecraft's Y axis in the X-Z plane as shown in Figure 16. FIGURE 16. PITCH AXIS TABLE 6 PITCH AXIS MASS PROPERTIES 1 YY Length 123. x 106 kg-km1 12 km 90.53 x 1012slug-ft2 7.46 miles The baseline rigid body mass properties of the SSPS about this axis are listed in Table 6.
RkJQdWJsaXNoZXIy MTU5NjU0Mg==