Instrument Transfer Function of RIME aboard JUICE
Authors: Hahnel Ronny , Plettemeier Dirk , Bruzzone Lorenzo 
Published: July 2024

. IntroductionThe subsurface-radar RIME operates at a center frequency of 9 MHz with a bandwidth of 3 MHz. Due to the relatively low frequency range, RIME is capable to penetrate the surface up to a depth of about 9 km with a maximum vertical resolution of 30 m. The 16.6 m long RIME dipole antenna consists of two 8.3 m longrods, each fed by a 50 &#937; coaxial cable. Both coaxial cables are connected to a matching network in order to achieve the required bandwidth. The definition of the solar panel angle is shown in Fig. 1. As already mentioned, an antenna simulator was built to simulate the properties of the radar system on earth. This&#160; should provide the same behavior as the real antenna system in the Jovian system.The goal is to estimate the distortion of the ideal chirp signal by the instrument itself, because the level of distortion influences the performance of the radar system. Therefore, the calculation of the instrument transfer function from available measurements of TX- and RX-path was performed, which were done in time domain. Difference between antenna simulator and realantenna system can be calculated and a calibration of the antenna simulator is possible. This is necessary because the AS only approximates the behavior.The AS consists of the matching network (CMN),the terminal matching networks (TMN), the dummy loads (DL) and the combiner (CMB). Due to the lowcenter frequency of 9 MHz, the behavior of the antenna can only be integrated using simulation results, because there are no measurements. This is based on the assumption that the simulation results reproduce the real behavior of the antenna with negligible deviations.However, measurement results are available for all other components. The CMN, TMN and the DL were measured in the entire frequency range and andin the temperature range of &#8722;67 &#176;C to 80 &#176;C. The transmission characteristics were determined separately for the TX- and RX-path with the original flight electronics of the radar system and the AS. The setup for the TX-path is shown in Fig. 2, the RX-path is shown in Fig. 3.&#160; &#160; &#160; &#160; &#160; &#160; 2. MeasurementsTo determine the load-dependent behavior, it is necessary to de-embed the AS in the corresponding path. This allows the frequency-dependent behavior of the antenna system to be taken into account in the simulations. It is assumed that an ideal chirp signal is fed in. With this assumption, the transfer functions can be calculated for the power amplifier (PA) and the Receiver and Digital Subsystem (RDS), as shown in Eqs. 1 and 2, because HAS(f) is known. Eq. 3 shows the transfer function for the antenna system&#160; Hant(f). It contains the properties of the antenna itself as well as the coaxial cables and electronic components. Gsys(f) is thesystem gain of the antenna in nadir direction including all effects of the antenna, the matching network and cables. Theoretically, there are two reference functions, one for E&#977;- and one for E&#966;-component of the dipole antenna. However, the E&#966;-component of the dipole isnegligible, because it is at least 40 dB lower than E&#977;. The reference function Href (f) is shown in Eq. 4. It takes into account the characteristics of the PA in theTX-path and the Receiver and RDS in the RX-path as well as the antenna characteristics.Fig. 4 and 5 show the instrument transfer functions based on measurements for the entire frequency range and various temperatures. Fig. 4 shows the result for a solar panel angle of 0&#176;, i.e. the coupling between S/Cand SP is the lowest. The case of the strongest coupling for an angle of 90&#176; is shown in Fig. 5. It can be seen that the highest losses occur in the lower and upper frequency range. A strong frequency dependence can also be seen. Due to the lower coupling, the losses for a solar panel angle of 0&#176; are lower than for 90&#176;.&#160; &#160; &#160; &#160; &#160; 3. Summary and ConclusionsThe highest attenuation occurs at the lower and upper frequency limits. The lowest attenuation is achieved for a solar panel angle of 0&#176; at 8.2 MHz, due to lowest coupling between antenna and SP. It can be seen that the temperature dependence is negligible at frequencies below 9 MHz. In the frequency range above 9 MHz the attenuation increases with lower temperature. During JUICE&#8217;s Earth flyby in August 2024, a comparisonwill be made between the real and the simulated signal. This makes it possible to verify how well the real behavior is reproduced.AcknowledgementThe research on the RIME experiment is supported by funding of the Deutsches Zentrum f&#252;r Luft- und Raumfahrt (DLR). This research was funded by Bundesministerium f&#252;r Wirtschaft und Energie under Contract 50 QJ 2302.