臺灣博碩士論文加值系統

自20世紀發展至今，無人飛行載具已成為航太產業不可或缺的一環，但無人飛行載具在設計沒有一套固定的方法，所以本研究以長滯空無人飛行載具為例，並應用載人飛機概念設計方法找出其相關的概念設計參數；除了能清楚了解這類型無人飛行載具的主要設計參數、性能數據與初步構型特性，還能作為後續構型改良的依據，未來也能透過飛行模擬軟體驗證這些概念設計參數的可行性。最後本研究希望透過這套研究方法與結果，提升國內無人飛行載具設計能量。
本研究首先蒐集長滯空無人飛行載具相關的設計參數與任務規格，例如掠奪者RQ-1與其它同等級的偵蒐型無人飛行載具，再運用載人飛機概念設計方法，從有限的設計數據找出更多的概念設計參數。本研究過程主要分成三階段，首先訂出長滯空無人飛行載具的規格、任務需求、酬載等目標，然後對起飛重量、空重、燃油重量進行初步估算；在第一階段會探討長滯空無人飛行載具的起飛總重靈敏性、第二階段探討性能需求，最後第三階段進行初步構型設計。

The development of UAVs become more and more important since the 20 century. However, there is not a fixed design methodology for UAVs. Therefore, this research takes a long-endurance UAV as an example and adopts airplane conceptual design methodology to search its conceptual design parameters. Moreover, these parameters can be adopted to the further configuration improvement and be verified by flight simulators in future. As a result, this research is able to provide some conceptual design parameters of the similar long-endurance UAV, RQ-1 Predator for the further configuration improvement and determine the feasibility. In other words, this research hopes to enhance Taiwanese design capability of UAV in the near future.
This research will refer to some basic and restricted design data and mission specifications of long-endurance UAVs such as RQ-1 Predator and others with similar mission specifications. Thus, this research can find out more relevant design data and acquire some knowledge about the preliminary design of the long-endurance UAV by using airplane design methodologies. The long-endurance UAVs include High-Altitude Long-Endurance (HALE) and Medium-Altitude Long-Endurance (MALE) UAVs. This research would focus on the conceptual design with long-endurance requirements and go through three parts. Deciding the specification, mission profile and payload weight is the first priority. Then, this research would estimate the gross take-off weight, empty weight and mission fuel weight. The first phase is to discuss the gross take-off weigh sensitivity. The second phase is to discuss the performance requirements. Finally, the third phase is to implement the preliminary configuration design.

Contents
List of Tables.........................................xii
List of Figures.......................................xiii
Nomenclature...........................................xiv
Acronym................................................xix
1. Introduction.....................................1
1.1 Motivation and Objective...........................3
1.2 Literature Review..................................4
1.3 Outline............................................4
2. Weight Estimation................................6
2.1 General Outline of the Weight Estimation...........7
2.2 Determination of Mission Fuel Weight...............8
2.3 Sizing Long-Endurance UAV..........................9
2.4 Summary.............................................13
3. Analysis of Gross Take-off Weight Sensitivity...14
3.1 Sensitivity of Gross Take-off Weight to Payload Weight
.............16
3.2 Sensitivity of Gross Take-off Weight to Empty Weight .............16
3.3 Sensitivity of Gross Take-off Weight to Other Basic Parameters...16
3.4 Summary...........................................20
4. Specific Performance Requirements Estimation....21
4.1 Sizing to Stall Speed Requirements................22
4.2 Sizing to Take-off Distance Requirements..........23
4.3 Sizing to Landing Distance Requirements...........27
4.4 Sizing to Climb Requirements......................30
4.4.1 Estimating Drag Polars at Low Speed...........30
4.4.2 Sizing to FAR 23 Rate-of-Climb Requirements...33
4.4.3 Sizing to FAR 23 Climb Gradient Requirements..36
4.4.4 Synopsis of FAR 23 Climb Requirements.........37
4.4.5 FAR 23.65 (AEO)...............................39
4.4.6 FAR 23.77 (AEO)...............................40
4.4.7 Sizing to Time-to-Climb Requirements..........42
4.5 Matching of All Performance Requirements..........45
4.6 Conclusions.......................................47
5. Preliminary Configuration Design................48
5.1 Class Ⅰ Methods...................................48
5.2 Overall Configuration.............................49
5.3 Fuselage Layout...................................51
5.4 Propulsion System.................................52
5.5 Wing Planform and Lateral Control Surfaces........54
5.6 Weight and Balance................................60
5.7 V-tail and Stability..............................65
5.8 Conclusions.......................................68
6. Summary and Conclusions.........................69
References..............................................72

List of Tables
Table 2.1 Mission Specification for This Research.......10
Table 2.2 Weight Comparison.............................13
Table 3.1 Sensitivity Parameters........................15
Table 3.2 Breguet Partials for Propeller Driven.........18
Table 3.3 Cruise and Loiter Phases Data.................19
Table 3.4 Growth Factors of Cruise and Loiter Phases....19
Table 4.1 Stall Requirements............................22
Table 4.2 Take-off Requirements: (W/P)_TO psf...........26
Table 4.3 Landing Requirements..........................29
Table 4.4 Results of Equivalent-Flat-Plate Drag Method..31
Table 4.5 First Estimates for and with Flaps and Gear Down...........32
Table 4.6 Primary Drag Polars for Specific Configurations ...............32
Table 4.7 FAR 23.65 RC Requirements.....................39
Table 4.8 FAR 23.65 CGR Requirements....................40
Table 4.9 FAR 23.77 CGR Requirements....................41
Table 4.10 Time-to-Climb Requirements...................44
Table 4.11 Characteristic Design Parameters.............46
Table 5.1 Fuselage Parameters...........................52
Table 5.2 Engine Parameters.............................53
Table 5.3 Wing Design Input Data........................55
Table 5.4 Wing Design Parameters........................58
Table 5.5 Aileron Design Parameters.....................60
Table 5.6 Weight Fraction Results.......................61
Table 5.7 Component Weight and Coordinate Data..........63
Table 5.8 Loading Scenarios.............................64

List of Figures
Figure 2.1 Weight Estimate Flow Chart....................7
Figure 2.2 Mission Profile..............................10
Figure 4.1 Take-off Process.............................23
Figure 4.2 Effect of TOP23 on Take-off Distance.........25
Figure 4.3 Effect of Wing Loading on Power Loading for Take-off Phase...............................................25
Figure 4.4 Landing Process..............................27
Figure 4.5 Forces in an Accelerated Climb...............33
Figure 4.6 Climb Requirements...........................42
Figure 4.7 Linear Relationship between RC and Altitude..43
Figure 4.8 Matching Plot................................45
Figure 5.1 RQ-1 Threeviews..............................50
Figure 5.2 Preliminary Flight Envelop...................53
Figure 5.3 Wing Planform................................56
Figure 5.4 Aileron Planform.............................59
Figure 5.5 Three Coordinates Sketch.....................62
Figure 5.6 CG Excursion Diagram.........................64

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