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# System prepended metadata

title: 數值紀錄

---

# 數值紀錄
[TOC]

## 限制分析



| 飛行參數設定 |          |
| ------------ |:--------:|
| 起飛距離     |    50    |
| 最大爬升率   |    5     |
| 巡航高度     |   100    |
| 巡航距離     |  3000*   |
| 巡航速度     |    19    |
| 降落距離     |    50    |
| 最大速度     |    22    |
| 最小迴轉半徑 |    50    |
| 最大滾轉傾角 |    45    |
| 最大起飛重量 |   6.5    |
| 最大升力係數 |   1.2    |
| 寄生阻力係數 |   0.02   |
| 起飛升力係數 |   0.9    |
| 起飛阻力係數 |   0.7    |
| 摩擦係數     |   0.1    |
| 奧斯華常數   | 0.878406 |
| 展弦比       |   5.5    |
| 漸縮比       |    1     |
| 失速速度     |    12    |
| 螺旋槳效率   |   0.6    |
| 馬達效率     |   0.8    |
| 空氣密度     |  1.225   |
| 巡航空氣密度 |  1.2137  |
| 負載因子     | 1.414214 |
| k            | 0.063574 |
| 降落速度     |   14.4   |
| 起飛速度     |   15.6   |
| q            | 219.0729 |
| g            |   9.81   |
| 翼負載       | 151.0037 |
| 水尾翼展    | 0.49 |
| 水尾弦長            | 0.14 |
| 垂尾翼展     |   0.192   |
| 垂尾弦長     |   0.1746   |
| 氣動力力臂            | 0.85 |
| 全機長            |   1.5|

*未定
![image](https://hackmd.io/_uploads/ByDEftzhle.png)
![image](https://hackmd.io/_uploads/r1rBzYM2gg.png)
![image](https://hackmd.io/_uploads/SkxW9wtM2xx.png)


| 最大需求功率 | 巡航功率 | 
| -------- | -------- | 
| 751.7     | 187.04    | 



## 馬達初步選擇
1. T-MOTOR AT3520 550KV ![image](https://hackmd.io/_uploads/HyVvXYGhxg.png)
2. DUALSKY XM3542EA-18 540KV ![image](https://hackmd.io/_uploads/Sy14VKf2xg.png)
3. DUALSKY XM3548EA-14 530KV ![image](https://hackmd.io/_uploads/Hk6PVFf3ll.png)
4. DUALSKY XM5050EA-12 610KV ![image](https://hackmd.io/_uploads/HkE0VKz3xx.png)


## 主尾翼設計
主翼限制:5ft = 1.524m
![image](https://hackmd.io/_uploads/S19LPYf3lg.png)

## Proposal
### Preliminary Design

Based on the mission plans for M2 and M3, an effective aircraft design must **maximize structural strength, flight stability, velocity, and payload capacity**, while **minimizing aerodynamic drag and assembly time** to efficiently accomplish the ground mission.
To meet these objectives, the design team selected a **high-wing monoplane** with an **elliptical planform**, which enhances the **lift-to-drag ratio (L/D)** during Mission M2 and improves stability under heavy-weight conditions. A **tricycle landing gear** was adopted to ensure good ground handling and weight distribution, while a **conventional tail configuration** was chosen for its simplicity, balanced center of gravity, and ease of construction.

The selected airfoil is the **NACA 6412**, a **low-speed airfoil** known for its **high lift-to-drag ratio** and **moderate thickness**, providing excellent aerodynamic efficiency at the flight speeds of both M2 and M3 missions. This airfoil offers a strong balance between performance, manufacturability, and stability—making it well-suited to the design’s overall mission requirements.
Performance Analysis and Configuration

To achieve maximum efficiency during M2 and M3 missions, the design algorithm incorporated a dedicated module that calculated the velocity and required thrust corresponding to the maximum lift-to-drag ratio (L/Dmax). The analysis produced the following key results:

Aspect Ratio: 5.5

Maximum Takeoff Weight: 14.44 lb

### Propulsion System and Energy Configuration

The propulsion system was designed under several key constraints:
165 ft takeoff distance design

High takeoff weight

Efficiency requirements for M2,M3 flight

After evaluating multiple motors based on power demand and current draw during both takeoff and M3 cruise, the DualSky XM5050EA-12 610KV motor was selected. This motor provides the Maximum 12.78 lb of takeoff thrust while drawing 81.4 A.
The total estimated energy consumption for a 5-minute M2 flight is approximately 20.8 Wh, equivalent to a 6S 4800 mAh LiPo battery.
The motor is installed in a tractor configuration, and the propeller size and current draw will be refined experimentally for optimal performance.






