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This paper treats the Brillouin backscattering in a single mode optical fiber and its implications on the Brillouin Ring Laser Gyroscope (BRLG). The BRLG consists of a fiber ring cavity in which stimulated Brillouin scattering is induced and provides two resonant counterpropagating backscattered waves. If this cavity is rotating around its axis, the backscattered waves get different resonant frequencies because of the Sagnac effect. The frequency difference is proportional to the rotation rate (Omega) by inducing a frequency offset between the counterpropagating waves. Some reported Brillouin spectra exhibit several peaks, which means that one pump wave provides at least two backscattered waves with distinguishable frequencies. In order to understand this multi-backscattering and to take advantage of it for the BRLG, we present results of a simulation of the Brillouin backscattering in a single mode optical fiber.
The prototype of an optical gyro encoder (OGE) has been successfully tested on the NTT telescope in September '93. The OGE consists of a ring laser gyro and a fiber optic gyro with their input axis parallel. The gyro outptu signals are compensated for earth rotation and misalignment and are subsequently integrated to get the angles. An adaptive digital control loop locks the fiber optic gyro to the laser gyro data. Thus the combined output has the precision of the laser gyro and the low noise of the fiber optic gyro. Specifically, the bias stability is better than 2 X 10-3 deg/h, the scale factor accuracy better than 1 ppm, the random walk coefficient better than 5 X 10-4 deg/(root)h and the resolution better than 3 X 10-4 arcsec. The OGE has been mounted in the altitude and in the azimuthy axis of the telescope. The data were compared with the telescope disk encoder data. The test data show that the pointing accuracy is about 1 arcsec and the tracking accuracy 0.1 arcsec over a time of 30 seconds. This accuracy is sufficient for the very large telescope, for instance.
An investigation is underway regarding the usefulness of altazimuth-mounting telescopes' incorporation of laser gyros for pointing and fiber gyros with extremely small random-walk coefficient for telescope inertial stabilization during tracking. A star tracker is expected to help stabilize long-term gyro bias. Gyro and telescope specifications have been derived by means of computer simulations and systems analyses.
In the recent two years the authors have developed a light weight and low power flight control system for model helicopters consisting of an attitude and heading reference system (AHRS), a navigator (INS) augmented with GPS, barometric altitude sensor and a magnetic sensor, a flight control computer (FCC) and bidirectional ground data links. The system has been tested on a commercial stunt flight model helicopter. The AHRS consists of three MEMS-gyros, two 2-axis MEMS accelerometers and a microcontroller performing the required sensor compensation and data processing to generate attitude angles and true rate and acceleration data of the flying platform. The heading angle is augmented with a 2-axis magnetic sensor. The AHRS is stunt flight capable. The INS integrates the acceleration data to obtain velocity and position data. All data are calculated in both the helicopter and the local earth frame with 50 Hz rate. The algorithm is augmented with GPS data for the lateral movement and with a barometric altitude sensor for the vertical movement. The barometric data are compensated for air pressure changes due to the helicopter main rotor. The FCC contains a set of control loops in order to stabilize the helicopter in all axis and to perform commanded velocity and position tasks. The sampling rate for the control loops is again 50 Hz allowing flight control with high bandwidth. Various safety features are implemented in the software. The bidirectional data link is based on a 2.4 GHz Bluetooth Class I RF-link with a 115 kbaud data rate. A dipole antenna is used on the helicopter, an automatically tracking patch antenna is used on the ground. For commanded velocity flight a standard 35 MHz RF-link is used. For data sampling, monitoring and mode control a laptop is used on the ground. Several operating modes are implemented ranging from commanded velocity flight to simple automatic stunt flight according to predefined flight tracks. The model helicopter is an ALIGN TREX 600 with 3 kg flight mass and a brushless electric motor. The rotor diameter is 1.40 m. The helicopter is able to carry a payload which mass depends on the size of the installed LiPo-cells and the purpose of the flight mission. The system has been tested in quite a few flight tests and missions. The helicopter is controlled safely up to wind loads of at least 5 Beaufort - 6 Beaufort. Data and video captures will be presented. If permission is granted, a demonstration flight will be performed on the premises of the conference.
Monitoring of the molecular structure of lubricant oil using a FT-Raman spectrometer prototype
(2014)
The determination of the physical state of the lubricant materials in complex mechanical systems is highly critical from different points of view: operative, economical, environmental, etc. Furthermore, there are several parameters that a lubricant oil must meet for a proper performance inside a machine. The monitoring of these lubricants can represent a serious issue depending on the analytical approach applied. The molecular change of aging lubricant oils have been analyzed using an all-standard-components and self-designed FT-Raman spectrometer. This analytical tool allows the direct and clean study of the vibrational changes in the molecular structure of the oils without having direct contact with the samples and without extracting the sample from the machine in operation. The FT-Raman spectrometer prototype used in the analysis of the oil samples consist of a Michelson interferometer and a self-designed photon counter cooled down on a Peltier element arrangement. The light coupling has been accomplished by using a conventional 62.5/125μm multi-mode fiber coupler. The FT-Raman arrangement has been able to extract high resolution and frequency precise Raman spectra, comparable to those obtained with commercial FT-Raman systems, from the lubricant oil samples analyzed. The spectral information has helped to determine certain molecular changes in the initial phases of wearing of the oil samples. The proposed instrument prototype has no additional complex hardware components or costly software modules. The mechanical and thermal irregularities influencing the FT-Raman spectrometer have been removed mathematically by accurately evaluating the optical path difference of the Michelson interferometer. This has been achieved by producing an additional interference pattern signal with a λ= 632.8 nm helium-neon laser, which differs from the conventional zero-crossing sampling (also known as Connes advantage) commonly used by FT-devices. It enables the FT-Raman system to perform reliable and clean spectral measurements from the analyzed oil samples.