https://research.ku.ac.th/kurdi-api/api/v1/
URL: https://research.ku.ac.th/kurdi-api/api/v1/projects/20186010511000
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"projectDetail": {
"forestUrl": "https://research.ku.ac.th/forest/Project.aspx?ProjectNumber=6010511000&BudgetYear=2018",
"projectID": "20186010511000",
"projectName": "อากาศพลศาสตร์ของปีกที่เลขเลย์โนล์ดต่ำและมุมปะทะสูงสำหรับการลงแนวดิ่งของอากาศยานไร้คนขับแบบปีกตรึง ",
"projectNameEn": "-",
"source": {
"name": "ทุนอุดหนุนวิจัยมก.",
"type": "Internal"
},
"budget": 250000,
"organization": {
"orgID": "010613",
"name": "ภาควิชาวิศวกรรมการบินและอวกาศ คณะวิศวกรรมศาสตร์"
},
"type": "โครงการเดี่ยว",
"budgetYear": "2018",
"startYear": "2017",
"endYear": "2019",
"head": "ดร.ชินภัทร ทิพโยภาส, ผู้ช่วยศาสตราจารย์",
"team": [
{
"sequence": 1,
"researcherID": "530139",
"prefix": "ดร.",
"researcherName": "ชินภัทร ทิพโยภาส",
"academicPosition": "ผู้ช่วยศาสตราจารย์",
"position": "หัวหน้าชุดโครงการ",
"type": "Internal Researcher",
"workRatio": 100
}
],
"category": "โครงการวิจัยที่ได้รับงบเงินรายได้ ส่วนกลาง มก.",
"background": "Not only for military, unmanned air vehicles (UAVs) are now used in many civil applications. This is resulted by a high progressive development of open source autopilot software as well as a low cost electronic autopilot control board and sensor. Opposed to a multi-rotor drone (UAV), a fixed-wing UAV is more suitable for observation, surveillance, mapping mission since it has great aerodynamic efficiency and high endurance. However, there are some drawbacks, in particularly its take-off and landing capabilities. Fixed-wing UAV has to gain a forward speed in order to produce lift force by the wing. Therefore, fixed-wing UAV needs a large area or land in take-off and landing phase. Then, it cannot be operated in a confined area such as in a forest, mountain, and etc. Hand -launch, catapult, and bungee usually are the solutions used for solving the take-off problem. For the landing phase, landing to a net or to a string is one of the popular method. However, it needs a lot of equipment installation on the ground. Deep stall landing (perching) or related methods are another interested solution since it needs no extra equipment and installation. UAV is descending to low altitude (10-50meters) and suddenly stop by using deep stall method or using perching trajectory. Then leave it free-fall to the ground after shut down the propeller. In order to minimize ground impact speed and to protect nose and tail of the UAV, it is designed to be falling with horizontal attitude (to have highest drag force). The angle of attack of Wing and of tail are at 90 degrees and more. During the phase of post stall, angle of attack of wing and/or tail may increase from 20 to 150 degrees. Therefore wing aerodynamic characteristics at very high angle of attack must be known. Secondly, existing UAV with deep stall or perching landing capability are now only let the UAV free-fall by itself, so precision landing on the desired position is difficult to be achieve. Therefore, researcher strongly believes that the UAV can be controlled by deflect conventional control surfaces of the UAV (during wing and tail are approximately at 90degrees)). For this reason, this research aim to understand and know the characteristic of wing and the affect the control surface at high angle of attack for various wing planforms. Then the outcomes of this research can be used for design of a UAV with high precision free -fall vertical-landing capability.",
"objective": "1. Find and understanding of effectiveness of control surface of wing at high angle of attack\r\n2. Able to use above information to design a UAV with stable free-fall vertical-landing capability",
"abstract": "Fixed wing unmanned air vehicle (UAV) has advantage for observation in large area but it has difficult for a take-off and landing in a confined area. Deep stall landing is the vertical landing which can solve this problem. It occurs by make the wing going into deep stall and losing lift then UAV vertically drop to ground. To minimize impact and softly landing, the UAV should maintain in horizontal position; wing is in position of 90deg angle of attack to maximize drag force. Therefore aerodynamic of wing at high AoA must be known. In addition the finding of this research can be used and applied for take-off and landing phase of vertical take-off and landing UAV which now is very interesting and attractive for UAV developer and numerous applications. \r\nThis research aims to study wing characteristic of NACA 4412 wings with AoA between 0 to 180 degree in wind tunnel by various wing aspect ratio, taper ratio and swept angle. Some of CFD simulation is also compared. Then use the result to analyze about dropping vertically with longitudinal stability including of drop test of the prototype UAV to demonstrate this landing technique.\r\nThe result of three wing planform at AoA of 90 – 110 deg are found that the wing planform does not have a significant effect to wing characteristic for doing a deep stall landing of the UAV. Maximum drag coefficient of approximately 1.5 occurs at 90 deg. The deep stall landing can performed by move the center of gravity (CG) backward after the neutral point (NP) of the UAV as 30-40% combine with deflect horizontal tail to –55 deg. or use normal CG as normal flight but need to deflect horizontal tail plane as much to –90 deg to be stable. When deflect the horizontal tail more negative angle of incidence can reduce the moving of CG backward, deep stall landing can be achieved without moving the CG of UAV when the incidence of horizontal tail deflect to -90 deg.",
"referenceUrl": "",
"status": "Closed"
}
}
]
}