Guidance of Receiver Aircraft to Rendezvous with Tanker in the Presence of Wind

Kampoon, Jane-Wit

doi:10.2514/6.2010-8326

Cited by 9 publications

(5 citation statements)

References 8 publications

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“…NUWEMT has been validated before against CFD, 11 wind tunnel 2, 3 and flight data, 12,13 and successfully implemented in simulations for aerial refueling 6-10, 14 and formation flight. 4,15 The biggest advantage of the NUWEMT is that it can be implemented directly in real time simulations and thus eliminates the need for generating and managing lookup tables in simulation.…”

Section: Model Validation With Cfd Resultsmentioning

confidence: 99%

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Application of Sweet Spot Determination to a Conventional Pair of Aircraft

Okolo

Dogan²,

Blake

2012

AIAA Atmospheric Flight Mechanics Conference

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This paper investigates the optimal fuel-saving location for an aircraft flying in formation behind another. A pair of KC-135R tanker aircraft is used as the leading aircraft and the trailing aircraft. The trailing KC-135R is placed or commanded to fly at different locations in a vertical rectangular grid located 3.8 wingspans behind the lead KC-135R aircraft. This is to determine the optimal location for formation flight. This optimal location, termed the sweet spot, is first determined using a static simulation by examining the lift-to-drag ratios and other aerodynamic force and moment coefficients of the trail aircraft at all points in the grid. The location of highest lift-to-drag ratio is then designated as the sweet spot based on the static simulation. A dynamic simulation is then used to determine if the sweet spot remains the same after considering the effects of trimming the aircraft. The trail KC-135R thrust required, along with the magnitudes of its control effectors, were investigated in the dynamic study, using the same grid as in the static case. The metric for sweet spot location in the dynamic case is the location of the least thrust required for the trail KC-135R. The results showed that the location of the sweet spot remains the same as that obtained using the static simulation. The effect on the static sweet spot, of varying the mass of the leader was also studied. It was observed that increasing the mass of the leading KC-135R aircraft affected only the aerodynamics of the trail aircraft and not the location of the sweet spot.

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Section: Model Validation With Cfd Resultsmentioning

confidence: 99%

“…ρ yo = l zo cos δ Tz o cos δ Ty o + l xo cos δ Tz o sin δ Ty o (15) ρ zo = l yo cos δ Tz o cos δ Ty o + l xo sin δ Tz o (16) and ρ xi = −l zi sin δ Tz i + l yi cos δ Tz i sin δ Ty i (17) ρ yi = l zi cos δ Tz i cos δ Ty i + l xi cos δ Tz i sin δ Ty i (18) ρ zi = l yi cos δ Tz i cos δ Ty i + l xi sin δ Tz i…”

Section: Aircraft Linear State-space Modelunclassified

Application of Sweet Spot Determination to a Conventional Pair of Aircraft

Okolo

Dogan²,

Blake

2012

AIAA Atmospheric Flight Mechanics Conference

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“…Note that, BDS approximates time derivative of a variable using its value at the current discrete time and that at the previous time. 36 The time derivative of state x is, then, approximated asẋ ∼ = x (n) − x (n−1) ∆t (47) where ∆t is the difference time step. Note that the equation of motion includes derivative of wind components.…”

Section: Discretized Dynamics Model For Input Predictionmentioning

confidence: 99%

“…For the details of derivation, see in Ref. 47 The curvilinear trajectory is used for defining a prescribed racetrack maneuver as depicted in Fig. 5.…”

Section: Figure 5 Prescribed Racetrack Trajectorymentioning

confidence: 99%

Aircraft Input Prediction in the Presence of Spatially Varying Wind Field

Kampoon

Okolo

Erturk

et al. 2015

AIAA Atmospheric Flight Mechanics Conference

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This paper presents a method of input prediction for an aircraft flying in spatially and/or temporally varying wind field. Input prediction is done using inverse simulation to compute the required control variables (control surface deflections and thrust level) for an aircraft to fly through a prescribed trajectory. Various simulation cases are presented to demonstrate the feasibility of input prediction method and the importance of including wind field information in inverse simulations.

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“…The UAV, UGV rendezvous can be considered either as a docking or landing problem. Aerial rendezvous between multiple aircrafts for refueling [10], [11] and formation flight [12], [13], [14] are related but the type of vehicles taken into account are the same and secondly, the rendezvous typically is in 2D, unlike the landing, which is in 3D. Carnes et al [15] developed an autotakeoff and auto-landing capabilities for a low-cost UAV, which is essential for many of the envisioned applications.…”

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Optimal Rendezvous Trajectory for Unmanned Aerial-Ground Vehicles

Rucco

Sujit

Aguiar

et al. 2018

IEEE Trans. Aerosp. Electron. Syst.

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Fixed-wind unmanned aerial vehicles (UAVs) are essential for low cost aerial surveillance and mapping applications in remote regions. One of the main limitations of UAVs is limited fuel capacity and hence requires periodic refueling to accomplish a mission. The usual mechanism of commanding the UAV to return to a stationary base station for refueling can result in fuel wastage and inefficient mission operation time. Alternatively, unmanned gound vehicle (UGV) can be used as a mobile refueling unit where the UAV will rendezvous with the UGV for refueling. In order to accurately perform this task in the presence of wind disturbances, we need to determine an optimal trajectory in 3D taking UAV and UGV dynamics and kinematics into account. In this paper, we propose an optimal control formulation to generate a tunable UAV trajectory for rendezvous on a moving UGV taking wind disturbances into account. By a suitable choice of the value of an aggressiveness index in our problem setting, we are able to control the UAV rendezvous behavior. Several numerical results are presented to show the reliability and effectiveness of our approach. I. INTRODUCTIONFixed-wing unmanned aerial vehicles (UAVs) are essential components of remote monitoring applications like surveillance, mapping, aerial photography, etc., where the UAVs need to cover large regions. Typical UAVs used for these applications are of low cost with limited fuel capacity and hence require periodic refueling to accomplish the mission. For the case of using low cost

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Guidance of Receiver Aircraft to Rendezvous with Tanker in the Presence of Wind

Cited by 9 publications

References 8 publications

Application of Sweet Spot Determination to a Conventional Pair of Aircraft

Application of Sweet Spot Determination to a Conventional Pair of Aircraft

Aircraft Input Prediction in the Presence of Spatially Varying Wind Field

Optimal Rendezvous Trajectory for Unmanned Aerial-Ground Vehicles

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