本論文中所發展的增強型阻滯電位分析儀將安裝於成功大學研製之探空火箭上，為「中氣層與電離層電漿探索儀器組」(MIPEX)的其中一組感測器。MIPEX之科學目標是透過現地量測，分析中氣層與低電離層的環境電漿參數，包括電子與離子之速度、溫度與能量分布等，了解其動態過程。
增強型阻滯電位分析儀是在傳統阻滯電位分析儀為基礎的創新設計。阻滯電位分析儀廣泛地運用在太空電漿現地量測中，透過量測離子能量分布可分別獲得飛行方向離子飄移速度、密度及溫度。使用電子倍增管取代傳統的金屬集極，增強型阻滯電位分析儀可有效增加其量測動態範圍、訊噪比及頻率響應，以滿足此次探空火箭任務的科學需求。儀器設計原理、電路結構、離子入射軌跡之理論模擬及飛行體在實驗中的測試結果將在本論文中探討。
在實際測量中，離子入射軌跡易受儀器內電位分布影響，為了瞭解並估計其誤差貢獻，使用SIMION軟體來檢驗由增強型阻滯電位分析儀結構所造成的牆壁效應和網格電位溢出效應，發現造成最大的誤差大約為7%，而最主要造成此誤差的原因是，由於網格電位溢出效應所造成的電流-電壓曲線偏移。因此，為了降低結構所造成的誤差，增強型阻滯電位分析儀飛行體設計使用較大的口徑。
經由太空電漿實驗腔實驗，可以驗證電子倍增管增益及動態範圍。在實際實驗中，金屬電極上很容易附著汙染層，造成電位改變，進而影響實驗結果。為了移除電極汙染效應，篩選離子能量時，IRPA使用脈衝三角波作以掃描電壓。從實驗結果可知，藉由使用脈衝三角波，其有著時變的高電壓及維持0V的低電壓，電極汙染所造成的阻抗效應和電位偏移效應均可被移除。另在電漿密度為為50 cm-3 的極低電漿密度下，增強型阻滯電位分析儀的性能也在太空電漿實驗腔實驗中獲得驗證。

The development and verification of the intensified retarding potential analyzer (IRPA) as one of the sensors in the space plasma instrument package ‶Mesosphere and Ionosphere Plasma Exploration complex (MIPEX)″ which is going to be installed onboard a university-based hybrid sounding rocket to investigate the electrodynamic processes in-situ in the D, E layers of the ionosphere above Taiwan is reported.
IRPA is innovated from the conventional retarding potential analyzer (RPA), a widely used in-situ plasma measurement instrument, to obtain ion drift velocity in ram direction, ion density and ion temperature by measuring the ion energy distribution. By replacing the conventional metal collector with a channelelectron multiplier (CEM), IRPA is capable of effectly increasing the dynamic range, signal-to-noise ratio and frequency response to satisfy the scientific needs of this hybrid rocket mission. In this work, the design concept, performance analysis by simulation, hardware development and in-lab experiment of IRPA is presented respectively.
In practical measurement, the trajectories of the incident ions are easily affected by the external potential distribution of the instrument. To investigate the effects and to estimate the error, the wall effect and the grid potential leakage effect caused by the IRPA structure are examined comprehensively by the SIMION software, and the maximum induced uncertainty is about 7%, which is mainly contributed by the shift of the I-V curve resulting from the grid potential leakage effect. As the result, the flight model of the IRPA is designed with a larger aperture to reduce the structure effect and a reduced error is expected.
The gain and dynamic range of CEM are verified in the space plasma operation chamber (SPOC) at NCKU. Metal electrodes are easily contaminated by a thin dielectric, which significantly affects the measurement result. To remove the effect caused by this contamination, a pulsed triangular waveform as a sweeping voltage was utilized for the ion energy selection. It is demonstrated that both the contamination impedance effect and the potential shift effect are removed by the waveform with a varying VH and a VL with 0V respectively. The performance of the IRPA under the environment with an extremely low plasma densities, ~50 cm-3, is also verified in SPOC.

陳炳志(民106)。106年度國家實驗研究院國家太空中心採購計畫書「前瞻混合式探空火箭酬載」(案號：NSPO-S-106081 )，未出版。
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