This paper proposes a method that uses an aircraft with single-antenna GPS receiver and Pitot tube to estimate wind speed direction calibrate the airspeed. sensor combination alone does not determine true attitude of aircraft, so parameters cannot be obtained directly from measurements. However, if flies at different headings, such as in banking turns or circle maneuvers, magnitude can estimated geometrical relation between An extended Kalman filter (EKF) is applied parameters. The EKF also...

This paper proposes a novel robust attitude estimation algorithm for small unmanned aerial vehicle (UAV) in the absence of GPS measurements. A synthetic sideslip angle (SSA) measurement formulated use under zeroangle assumption is newly proposed UAV without angle-of-attack (AOA)/SSA sensors to enhance state performance during outage. In addition, nongravitational acceleration estimated using Kalman filter and then subtracted from raw yield reliable gravity estimate. Then, fuzzy-logic-aided...

This article proposes a novel fault-tolerant dynamic model-aided navigation filter to cope with accelerometer faults. An algorithm estimate the three-axis accelerations of high-altitude long-endurance (HALE) unmanned aerial vehicle (UAV) utilizing control input signals and aerodynamic coefficient parameters is newly proposed. To address fault accelerometer, two filters that utilize measured acceleration, denoted as Acc-measure algorithm, estimated Acc-free respectively, are effectively...

This paper presents automatic taxiing, takeoff and landing of a UAV based on single-antenna GPS receiver. In this paper, inertial sensors such as gyros accelerometers are not used at all to show the full potential receiver attitude determination system. DGPS is implemented give high accuracy position information for runway. For fixed wing aircraft, under assumption coordinated flight, called pseudo-attitudes can be estimated from measurements So state variables control obtained addition...

This article proposes a novel dynamic model-aided navigation filter to estimate the safety-critical states of an aircraft including effect wind. Aerodynamic coefficients and control signals are used predict angular rates. Experimental flight results high-altitude long-endurance unmanned aerial vehicle (UAV) demonstrated improvement in attitude estimation compared model-based algorithm that does not consider wind, as well accurate without using gyroscope signals, demonstrating its...

Purpose The purpose of this paper is to present an efficient method integrate path generation and following for unmanned aerial vehicle. Design/methodology/approach shortest briefly reviewed using a straight line circular arc in horizontal plane. Based on paths, various algorithms oriented waypoints are described. Path design unit, which structured concatenations segments arcs, proposed represent different paths as one structure. Simple controller follow circle was also implemented with...

The aircraft autopilot needs the feedback of airflow angles, that is, angle-of attack and sideslip angle to control aircraft. angles measured by a mechanical vane are not accurate very noisy for low airspeed. Moreover, has failure risk. This paper describes extended Kalman filter based method estimate three-dimensional wind speed under constant condition. In addition, it can correct scaling error airspeed an It uses measurements, condition computed from GPS/INS navigation data stability...

The performance of global navigation satellite system (GNSS) receivers in dynamic modes is mostly assessed using results obtained from independent maneuvering vehicles along similar trajectories at different times due to limitations receivers, payload, space, and power moving vehicles. However, such assessments do not ensure valid evaluation because the same GNSS signal environment cannot be ensured a test session irrespective how accurately it mimics original session. In this study, we...

The development of a tilt-duct UAV is presented herein. In order to develop UAV, the power-train characteristics vehicles during helicopter-to-airplane conversion are investigated. full-scale model reflects tethered hover test information and realistic data from scaled down model. prop governor maneuvers handled by proportional–integral controller in both main-prop tail-prop. This provides stable control forces forward backward conversions ducts. path between flight speed tilt angle defined...

This paper presents an efficient method of designing appropriate navigation message format for airborne pseudolite system using unmanned aerial vehicle (UAV) platforms. We briefly describe the concept UAV system, which can be used as a GPS augmentation or local system. Because motion UAVs is very variable, special necessary messages. Our approach based on specialized formats each UAV, including both line and circle tracking, separation nominal values deviations. It reduce total size diminish...

Flight tests of TR-60 in order to evaluate the control performance helicopter, conversion and airplane mode were completed. In reduce development risk schedule, single channel out dual flight computer Smart UAV (TR-100) was used without other modification. Therefore operational program (OFP) had minimum changes only on laws. Even though similar system applied scaled tilt-rotor aircraft, named as TR-60, many unexpected anomalies occurred during test from hover mainly due different bandwidth...

Tilt Rotor UAV of KARI has been developed for ground surveillance, which performance verified through flight test in 2013. Today the use becomes popular field not only surveillance but also reconnaissance, rescue, science investigation, and home delivery etc. rotor a merit vertical take-off landing, so that it is convinient to be used oceanic operation with shipboard landing. However environment ocean much severer than one on very risk because small landing area, nonuniform wind moving...

To put the binocular 3-D image system into practical use, it is necessary to investigate relationship between and human subjects in order make an ergonomic evaluation of system. In this study, a comparative analysis made changes accommodation pupil functions before after observing images as visual distance varies. The results suggest that: (1) discordance information on when compensated by miosis altering focal depth, (2) from consideration effect condition functions, believed that are...

Shipboard landing of Vertical Take-Off and Landing (VTOL) aircraft is an important consideration to operate in the ocean. The oceanic operation has more difficult environment than one on ground due salty, fogy, windy condition. Especially gust vortex around structures ship make approach difficult. movement board roll, pitch, heave by wind sea wave also makes severe. Tilt rotor UAV developed Korea Aerospace Research Institute (KARI) basically aimed be operated expanded operation. simulation...

The direction of propeller rotation in a distributed electric-powered vertical take-off and landing (eVTOL) aircraft significantly influences control forces induced drag during both helicopter fixed-wing modes. This study proposes strategy to determine the most effective rotational for each propeller. approach effectively mitigates one-engine-inoperative (OEI) conditions mode subscale eVTOL referred as optionally piloted personal air vehicle (OPPAV). Moreover, developed an optimal law using...