S. M. Ali, "Stability and Takeoff Ground Roll Issues of Hybrid Buoyant Aircraft," vol. 660, Advanced Material Research, pp. 503-507, 2014Haque, A.U., W. Asrar, A.A. Omar, E. Sulaeman and J.S.M. Ali, 2014. Stability and takeoff ground roll issues of hybrid buoyant aircraft. ...
The initial conditions are shown in Table3. These variables are nondimensionalized by the characteristic speed and densityU=340m/sandρ=1.25kg/m3. The boundary conditions are the slip wall conditions on the ground and at the aircraft surface and the Riemann invariant boundary conditions at the o...
MOTIONTRACKINGMOMENTSThis report presents a non-interactive 'MIMIC' program developed to generate the time history of an aircraft undergoing an engine failure during its ground roll. The program calculates the forces and moments acting on the aircraft, and uses MIMIC's implicit integration routine to...
The upper limits of ground velocity and horizontal acceleration are, respectively, v l m t = 4 m/s and a l m t = 2 m/s2. The fuselage fronts straight onto the track, and the command limits of roll angle and pitch angle are set as ± 0.26 rad . The directional angular velocity ...
The attitude angle is defined in the ground axis, and the control usually acts on the vehicle body frame. Therefore, the first step is to convert the attitude command to the body frame by Equation (8), and with simple calculations, the angular rates in the body frame can be written as:...
Figure 7. Attitude tracking performance in airplane mode: (a) The tracking performance of roll angle; (b) The tracking performance of yaw angle. Figure 8. Required moments by control effectors in airplane mode: (a) The roll angle control channel; (b) The pitch angle control channel; (c...
During the transitional flight, both the aerodynamic surfaces and the vectoring nozzle achieve the commanded roll angular acceleration. Considering the uncertainty of moment, Equation (9) can be expressed as: 𝒙˙2=⎡⎣⎢⎢⎢⎢𝐿𝛽+𝐿̂𝛽𝑀𝛼+𝑀̂𝛼𝑁𝛽+𝑁̂...
According to Equation (19), the roll angular rate can be expressed as: 𝑝𝑐=𝜙˙𝑐−tan𝜃(𝑞sin𝜙+𝑟cos𝜙)pc=ϕ˙c−tanθ(qsinϕ+rcosϕ) (27) In the speed channel, the desired ground velocity, 𝑉𝑔𝑑Vgd, is controlled by a proportional and integral con...