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 Posted: Tue 13:30, 23 Nov 2010 Post subject: tory burch shoes A small unmanned helicopter vibra |
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A small unmanned helicopter gyro attitude and flight test vibration platform
New shock absorber mounted gyro integrated frequency response function diagram, as shown in Figure 9. The figure thick lines for the two vertical gyro frequency of vibration of the two main components of 13.75Hz, 27.5Hz. And the new non-linear damper has improved since the gyro bow l natural frequency deviation is less than 1.25Hz. From Table 5, Figure 9 can get the following two conclusions: (1) gyro rigid body natural frequencies of the order to avoid the 13.75Hz and 27.5Hz, Y gyro translational natural frequency of 17.6Hz to close l7Hz. Aircraft engine rated speed, the gyro is no resonance. (2) gyro damping about 15% larger. Start to start the aircraft engine rated speed of the transition phase, the vibration amplitude of resonance gyro smaller natural frequency excitation signal and staggered, the vibration decreases rapidly, the initial attitude of the gyro data less affected. Figure 9 gyro know eggs (the improved shock absorber) with integrated frequency response function map # 33 absorber with the same material, tooling, technology and size,[link widoczny dla zalogowanych], creating a 34 #, 35 # and 36 # shock absorber for consistency test. The results in Table 6. The results show that: the same batch performance close to the production of shock absorber, which is very conducive to mass production. 6 Gyro Wrap (34 loops, 35 #, 36 #) rigid code of modal parameters to the Z-axis to y l, No. Z-axis type of translational translational translational reverse reverse reverse the natural frequency (Hz) l0.116.7lO . 334.522.723.734 damping ratio (%) 16.1l8.5l7.4l6.813.2l6.7 natural frequency (1Iz) l0.5l6.4l0.234.522.924.135 damping ratio (%) l6. 5l8.3l8.6l6.4l7.014.7 natural frequency (1Iz) 10.016.49.933.222.723.436 damping ratio (%) 14.0l8.314.2l6.8l8.3l7.5 will install 34 # damper group gyroscope onto the plane, the acceleration sensor in accordance with, y, z directions attached to the gyroscope, in accordance with 2 tests,[link widoczny dla zalogowanych], the flight vibration tests. Table 7 is the gyro vibration test results. Table 7 and Table 2, Table 3, the corresponding direction of the bottom measurement points compared damping effect can be seen clearly,[link widoczny dla zalogowanych], especially in isolated out 55Hz or more incentive points. Table 7 gyro in the hover, forward flight test results (unit: g) measuring point RMS13.75Hz27.5Hz55Hz state to 0. O55O. 0270. O48O. Y to 003 hanging 0.1300.0o6O. Z stopped O950.013 to 0.173O. 0210.1l7O. O43 to 0.0670. O26o. O520.0o3 Y to 0.1270 before. Oo7o. 0950.015 Fei Z to 0.1720.023O. 1180.055 will be tested several groups of shock absorbers, good logo, are mounted to the aircraft for a prolonged period, several tests, the results overturned the phenomenon does not appear gyro, gyro vibration platform that success. 3 Conclusion In summary, the aircraft attitude gyro is a core component of the autopilot system, it works, sense the correctness of the aircraft attitude is bound to ensure the stability of the aircraft. Attitude Gyro Gyro damping platform can work without distortion to provide a guarantee. In this paper, theoretical design, product trial, a large number of tests, developed a practical use of gyro vibration platform. Platform in the actual flight was a lot of flight-proven, validated platform design methods, testing methods basically correct. [References [1] is high. Chen Renliang book. Helicopter Flight Dynamics [M]. Beijing: Science Press, 2003 [2] Gu Dong-lei. Xia Xianming, high positive. Helicopter flight control system design and application [J]. Nanjing University of Aeronautics and Astronautics, 2oo5. 37 (4) :476-478 [3] ZHANG Ling-Mi a. Vibration testing and dynamic analysis [M]. Beijing: Aviation Industry Press,[link widoczny dla zalogowanych], 1992 [4】 Hu Haiyan primary Die late at night. Mechanical vibration and shock [M】. Beijing: Aviation Industry Press, 1998 [5] GentAN. Cameroon ∞ dIlgwithRubber: BowtoDe roundworm RubberCempmumts [M]. NewYock: HaneerPubli ~ m, 1992 [6】 GebelEF. Grimm | f ~] [afn [M】. Berlin: Springe ~. 1945 [7】 Gong plot ball, Gongzhen Zhen, Zhao Zion ed. Rubber parts, engineering design and application [M】. Shanghai: Shanghai Jiaotong University Press, 2003
A small unmanned helicopter gyro attitude and flight test vibration platform
New shock absorber mounted gyro integrated frequency response function diagram, as shown in Figure 9. The figure thick lines for the two vertical gyro frequency of vibration of the two main components of 13.75Hz, 27.5Hz. And the new non-linear damper has improved since the gyro bow l natural frequency deviation is less than 1.25Hz. From Table 5, Figure 9 can get the following two conclusions: (1) gyro rigid body natural frequencies of the order to avoid the 13.75Hz and 27.5Hz, Y gyro translational natural frequency of 17.6Hz to close l7Hz. Aircraft engine rated speed, the gyro is no resonance. (2) gyro damping about 15% larger. Start to start the aircraft engine rated speed of the transition phase, the vibration amplitude of resonance gyro smaller natural frequency excitation signal and staggered, the vibration decreases rapidly, the initial attitude of the gyro data less affected. Figure 9 gyro know eggs (the improved shock absorber) with integrated frequency response function map # 33 absorber with the same material, tooling, technology and size, creating a 34 #, 35 # and 36 # shock absorber for consistency test. The results in Table 6. The results show that: the same batch performance close to the production of shock absorber, which is very conducive to mass production. 6 Gyro Wrap (34 loops, 35 #, 36 #) rigid code of modal parameters to the Z-axis to y l, No. Z-axis type of translational translational translational reverse reverse reverse the natural frequency (Hz) l0.116.7lO . 334.522.723.734 damping ratio (%) 16.1l8.5l7.4l6.813.2l6.7 natural frequency (1Iz) l0.5l6.4l0.234.522.924.135 damping ratio (%) l6. 5l8.3l8.6l6.4l7.014.7 natural frequency (1Iz) 10.016.49.933.222.723.436 damping ratio (%) 14.0l8.314.2l6.8l8.3l7.5 will install 34 # damper group gyroscope onto the plane,[link widoczny dla zalogowanych], the acceleration sensor in accordance with, y, z directions attached to the gyroscope, in accordance with 2 tests, the flight vibration tests. Table 7 is the gyro vibration test results. Table 7 and Table 2, Table 3, the corresponding direction of the bottom measurement points compared damping effect can be seen clearly, especially in isolated out 55Hz or more incentive points. Table 7 gyro in the hover, forward flight test results (unit: g) measuring point RMS13.75Hz27.5Hz55Hz state to 0. O55O. 0270. O48O. Y to 003 hanging 0.1300.0o6O. Z stopped O950.013 to 0.173O. 0210.1l7O. O43 to 0.0670. O26o. O520.0o3 Y to 0.1270 before. Oo7o. 0950.015 Fei Z to 0.1720.023O. 1180.055 will be tested several groups of shock absorbers, good logo, are mounted to the aircraft for a prolonged period, several tests, the results overturned the phenomenon does not appear gyro, gyro vibration platform that success. 3 Conclusion In summary, the aircraft attitude gyro is a core component of the autopilot system, it works, sense the correctness of the aircraft attitude is bound to ensure the stability of the aircraft. Attitude Gyro Gyro damping platform can work without distortion to provide a guarantee. In this paper, theoretical design, product trial, a large number of tests, developed a practical use of gyro vibration platform. Platform in the actual flight was a lot of flight-proven, validated platform design methods, testing methods basically correct. [References [1] is high. Chen Renliang book. Helicopter Flight Dynamics [M]. Beijing: Science Press, 2003 [2] Gu Dong-lei. Xia Xianming, high positive. Helicopter flight control system design and application [J]. Nanjing University of Aeronautics and Astronautics, 2oo5. 37 (4) :476-478 [3] ZHANG Ling-Mi a. Vibration testing and dynamic analysis [M]. Beijing: Aviation Industry Press, 1992 [4】 Hu Haiyan primary Die late at night. Mechanical vibration and shock [M】. Beijing: Aviation Industry Press, 1998 [5] GentAN. Cameroon ∞ dIlgwithRubber: BowtoDe roundworm RubberCempmumts [M]. NewYock: HaneerPubli ~ m, 1992 [6】 GebelEF. Grimm | f ~] [afn [M】. Berlin: Springe ~. 1945 [7】 Gong plot ball, Gongzhen Zhen, Zhao Zion ed. Rubber parts, engineering design and application [M】. Shanghai: Shanghai Jiaotong University Press, 2003
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