Performance analysis, dynamic simulation and control of mass-actuated airplane
Başlık çevirisi mevcut değil.
- Tez No: 508396
- Danışmanlar: Prof. Dr. ATİLLA DOĞAN
- Tez Türü: Doktora
- Konular: Havacılık Mühendisliği, Uçak Mühendisliği, Aeronautical Engineering, Aircraft Engineering
- Anahtar Kelimeler: Belirtilmemiş.
- Yıl: 2016
- Dil: İngilizce
- Üniversite: The University of Texas at Arlington
- Enstitü: Yurtdışı Enstitü
- Ana Bilim Dalı: Belirtilmemiş.
- Bilim Dalı: Belirtilmemiş.
- Sayfa Sayısı: 242
Özet
Özet yok.
Özet (Çeviri)
The control of space, aerial and underwater vehicles requires moment generation mechanisms to change their orientation. In addition to or in place of conventional moment generation actuators, internally moving-mass actuation has been proposed and/or used for such vehicles. The primary principle for mass-actuation is to reposition gravitational force to change the associated moment while the secondary e ect may come from the inertial force due to the motion of the masses. Recent development/ miniaturization in ight control sensor, computing and actuation, and electric motors and expansion of applications for small UAV (Unmanned Aerial Vehicle) o er a potential for implementation of internal mass-actuation in small UAV. The massactuation o ers various advantages over the conventional mechanisms in airplane ight such as reduced drag and lift loss due to aerodynamic control surface de ections, simpli ed wing and tail design, improved lift-generation performance of wing, smaller radar signature for stealth aircraft. This dissertation research investigates the feasibility and bene t of mass-actuation of a small UAV in various ight phases and full missions consisting of all these ight phases and transitions between them. Three di erent con gurations of the same airplane are considered: (1) aero-actuated, conventional airplane with three standard aerodynamic control surfaces, aileron, elevator and rudder, (2) mass-actuated, a mass moving along the fuselage to mainly generate pitching moment, and another mass moving along the wing to generate rolling moment, and (3) mass-rudder actuated, mass-actuation as in case-2 augmented with a rudder. The airplane is an electric powered and has a single propeller at the nose. A full 6-DOF (Degrees of Freedom) nonlinear equations of motion are derived, including the terms modeling inertia forces induced by the motion of the internal masses, and the e ect of this internal mass motion on the variation of the center of mass and inertia matrix. The dynamics of the electric motor of the propeller and the servos of the actuators are also modeled. The e ect of the propeller on the dynamics of the aircraft is also included. Modeling also includes electric power consumption by the electric motor driving the propeller, and servos of the aerodynamic and mass actuators. An integrated simulation environment is developed that includes all these factors and can be switched between the di erent con gurations de ned above. Trim analyses of all three con gurations of the airplane are carried out in all four ight conditions (steady climb, cruise, steady turn, steady descent). Trim analyses consider all the constraints of the control and state variables such as limits on the de ections of the aerodynamic surfaces, position of the mass actuators, battery provided voltage, and angle of attack. These analyses demonstrate the feasibility of ying the airplane with mass-actuation only within varying speed ranges depending on the actuation mechanism. The results also show the bene t of mass-actuation over the conventional aero-actuation in terms of range and endurance especially in cruise ight, as compared to the other two con gurations. In the second phase of the research, controllability of the airplane with each actuation mechanisms is determined and compared over the feasible speed range of each trim condition. A new relative controllability metrics is de ned and calculated for this purpose. This analysis, based on the linearized model of the aircraft in each trim ight condition, show that the mass-actuation provides full controllability with various degree over the speed ranges. Once the controllability is veri ed, an LQR-based gain scheduling controller is designed for each aircraft con guration to track commanded climb/descent rate, altitude, airspeed, and turn rate. These controllers are implemented in the integrated simulation environment to simulate various ight pro les including full missions that start with a hand-launch of the airplane, climb to a speci ed altitude, and cruise at that altitude with various commanded speed, and loiter with commanded left and right turn rates, and descend to land with varying approach speed. These simulations also demonstrate the feasibility potential bene ts, and/or limitations of mass actuation.
Benzer Tezler
- Esnek mekanizmaların tasarlanması ve kontrolü
Design and control of compliant mechanisms
AYŞE TEKEŞ
Doktora
Türkçe
2013
Makine Mühendisliğiİstanbul Teknik ÜniversitesiMakine Mühendisliği Ana Bilim Dalı
DOÇ. DR. MEHMET SALIH DOKUZ
- Electromechanical analysis of linear compressor for household refrigerators
Ev tipi buzdolabı için lineer kompressörün elektromekanik analizi
ADNAN HASSAN
Doktora
İngilizce
2017
Makine MühendisliğiKoç ÜniversitesiMakine Mühendisliği Ana Bilim Dalı
PROF. DR. İSMAİL LAZOĞLU
- Model-based identification and control of a one-legged hopping robot
Tek-bacaklı zıplayan robot üzerinde model tabanlı tanımlama ve kontrol
HASAN EFTUN ORHON
Yüksek Lisans
İngilizce
2018
Elektrik ve Elektronik Mühendisliğiİhsan Doğramacı Bilkent ÜniversitesiElektrik-Elektronik Mühendisliği Ana Bilim Dalı
PROF. DR. ÖMER MORGÜL
- Analysis and control of periodic gaits in legged robots
Bacaklı robotlar için periyodik yürüme davranışlarının analizi ve kontrolü
HASAN HAMZAÇEBİ
Doktora
İngilizce
2017
Elektrik ve Elektronik Mühendisliğiİhsan Doğramacı Bilkent ÜniversitesiElektrik-Elektronik Mühendisliği Ana Bilim Dalı
PROF. DR. ÖMER MORGÜL
- Kanat çırpma hareketi bulunan dinamik sistemlerin stabilizasyonu
Stabilization of dynamic systems with wing flapping motion
MUSTAFA KAAN ATİK
Yüksek Lisans
Türkçe
2024
Mekatronik Mühendisliğiİstanbul Teknik ÜniversitesiMekatronik Mühendisliği Ana Bilim Dalı
PROF. DR. ATA MUĞAN