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Modeling and prototype of this instrument are shown in Figure 3 and Figure 4. Figure 3 Modeling of gyroscopic mounting instrument. (a) Gyroscopic-mounting; (b) Dynamic load applied; (c) Mounting on PCB. Figure 4 Prototype of gyroscopic mounting instrument. This mounting is a simple and cheap passive component and does not need to any power supply. It must be as quick as possible to respond to dynamic loads. We manufactured it from low-density materials and the softness of surfaces AZD9291 molecular weight should be high as well. After installation of the crystal oscillator on it, dynamic load-induced disturbances can be expressed as: ��fgyro(��=1s)=f0��Asin�� (5) ����gyro(Bn=1Hz)=2�СҦ�fgyrodt (6) ?(f)gyro=20log|����gyro2| (7) where ��?gyro: frequency disturbance; ����gyro: phase disturbance; ?gyro (?): phase noise. The maximum effect of gyroscopic mounting appears in the critical state shown in Figure 2b. In this case, gyroscopic mounting protects the system from the maximum probable instabilities. 4. G-Sensitivity Vector Each crystal blank has its own g-sensitivity vector. Apart from its magnitude ��, its angular orientation, especially the elevation angle ��, plays an important role on the instability induced in the oscillator output. Commonly SC-cut crystal oscillators are used PR-171 research buy under highly dynamic conditions [36]. Therefore, statistical studies have been done on the elevation angle of SC-cut crystals [25,37,38,39]. According to these studies, the angle �� follows the distribution with 1�� = 19�� (42%), 2�� = 38�� (84%) and 3�� = 57�� (98%), ��min = 2.6�� and ��max = 62�� as shown in Figure 5. Figure 5 Distribution of YES1 angle |��| for different SC-cut crystals. 5. Impacts of Dynamic Loads on Stability of Crystal Oscillator and Proof of Gyro Efficiency Commonly GPS disciplined crystal oscillators are used as primary frequency standards for calibration and metrology in laboratories [40]. Therefore, in this paper this kind of oscillator is used to do the numerical analysis. To simulate highly dynamic conditions, the Ariane launch vehicle has been assigned as host vehicle. The parameters of this oscillator can be found in Table 1. The parameters of the Ariane launch vehicle will be mentioned in Section 5.2, Section 5.3 and Section 5.4. Table 1 Characteristics of the GPS disciplined crystal oscillator. 5.1. Attitude and Altitude Changes of Host Vehicle As shown in Figure 6, the attitude of the host vehicle changes n�� (i.e., 0