安裝於衛星與探空火箭上之阻滯電位分析儀為全世界太空任務中，執行電離層離子現地量測的主要科學酬載，由於此儀器與蘭摩爾探針均屬於靜電場式粒子偵測器，因此，與蘭摩爾探針相同，儀器的電極污染為量測誤差的主要原因之一。電極上的污染層在儀器量測的過程中形成額外的電阻與電容，此電阻與電容會造成兩種效應：阻抗變化與電荷累積效應，這兩種效應會改變儀器之電壓—電流量測曲線並造成誤差。在蘭摩爾探針的量測上，我們可藉由改變電壓掃描頻率以降低阻抗變化效應，然而，由於儀器結構的緣故，阻滯電位分析儀電極污染造成的電荷累積效應遠大於阻抗變化效應，此電荷累積效應會直接造成量測離子流速與離子溫度的改變，當阻滯電位分析儀應用於探空火箭上時，由於火箭飛行速度較衛星低（約每秒1至2公里），且在火箭量測高度（100至300km）範圍內之離子溫度可低達200至300K，此時電極污染效應會對離子溫度與流速量測造成顯著的影響。在本篇論文中我以理論模擬與太空電漿實驗腔(SPOC)實驗的方式，討論阻滯電位分析儀的電極污染效應，並提出解決的方法與可應用於探空火箭之無電極污染阻滯電位分析儀系統。

太空電漿實驗腔（SPOC）為一可模擬地球電離層環境之真空實驗腔，腔體長3公尺、直徑2公尺，腔體內安裝了兩組逆擴散式電漿源以產生電離層電漿，本篇論文將介紹SPOC的設計細節、功能與使用無電極污染阻滯電位分析儀及蘭摩爾探針量測的實驗結果，包含離子與電子之能量分佈函數與空間分佈。當背景中性氣體密度約為1012 cm-3時，SPOC可產生的電漿密度範圍為103 至106 cm-3，電子的能量分佈函數為馬克士威分佈，溫度為1000至3000K，SPOC產生離子的能量分佈函數，由溫度接近中性氣體溫度（室溫）的馬克士威函數與高能離子流組成。SPOC未來可廣泛應用於太空電漿實驗、衛星與火箭之科學酬載校正與飛行系統環境測試。

In situ ion measurements in the ionosphere are mostly done with retarding potential analyzers (RPA) onboard satellites and sounding rockets. However, like most of the electrostatic analyzers such as Langmuir probes, the electrode contamination can be a serious problem for the RPA measurement. The contamination layer acts as extra capacitance and resistance and leads to distortion in the measured I-V curve, which leads to erroneous measurement results. There are two main effects of the contamination layer: one is the impedance effect and the other is the charge attachment and accumulation due to the capacitance of the contamination layer. The impedance effect can be reduced or eliminated by choosing the proper sweeping frequency. However, for RPA the charge accumulation effect becomes serious because the capacitance of the contamination layer is much larger than that of the Langmuir probe of similar dimension. This effect causes the measured ion drift velocity (ion temperature) to be higher (lower) than the actual values. The error caused by the RPA electrode contamination is expected to be significant for sounding rocket measurements with low rocket velocity (1~ 2 km/s) and low ion temperature of 200-300K in the height range of 100-300 km. In this thesis I discussed the effects associated with the RPA contaminated electrodes based on theoretical analysis and experiments performed in the space plasma operation chamber (SPOC). The development of a contamination-free RPA for sounding rocket missions is presented.

SPOC is a research plasma device designed to produce plasmas similar to those in the ionosphere. It is a cylindrical chamber of 2 meters in diameter and 3 meters in length. The SPOC plasma is produced by two back-diffusion type plasma sources. In this thesis the SPOC machine details and its capabilities on plasma experiments and space environmental tests are described. The spatial and energy distributions of ions and electrons in SPOC measured by contamination-free RPA and Langmuir probe systems are presented. The plasma density in SPOC and be varied from 103 to 106 cm-3, and the neutral density is ~1012 cm-3. Electrons have Maxwellian distribution with temperature of 1000-3000K. The ion distribution has two components: one is a drift-Maxwellian component with temperature close to the neutral particle temperature (room temperature), and another is a small ion beam component. SPOC can be used for studying space plasma processes and for the calibration and test of satellite/rocket-borne instruments.

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