Navigation, Guidance and Control For the CICADA Expendable Micro Air Vehicle

Kahn, Aaron D.; Edwards, Daniel

doi:10.2514/6.2012-4536

Cited by 13 publications

(7 citation statements)

References 3 publications

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“…Due to the different attitude and orientation of each UAV when it leaves the high-altitude balloon platform, the speeds u, v, and w assigned by v hu to the UAV BCS are also different, which further makes the initial angle of attack and side-slip angle of each wing different. (5). Comparing the separation status values of each UAV in Figure 9, the northward movement of the high-altitude balloon platform makes the initial launching position of the subsequent UAV increase on the basis of the original position, and the launching height also increases gradually.…”

Section: Simulation Of the Ejection Process From The Balloon Platformmentioning

confidence: 98%

“…The time and speed trends of front and rear wings are similar. (5). A major feature of the folding wing UAV is that each wing will experience a high attack angle and high side-slip angle flight during the wing deployment process.…”

Section: Simulation Of the Wing Deploying And Trajectory Leveling Pro...mentioning

confidence: 99%

“…Naval Research Laboratory has developed a disposable micro air vehicle CICADA. Kahn 5 and Edwards 6 described the design concept, navigation, and flight control developed for CICADA. Japan Aerospace Exploration Agency has carried out several experiments at the Esrange Space Center in northern Sweden to launch the low explosive supersonic aircraft model from the balloon platform (D-SEND program).…”

Section: Introductionmentioning

confidence: 99%

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Dynamics simulation of folding wing UAVs launched from a high-altitude balloon platform

Zhang

Yang

Cai

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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It is a new application of the high-altitude balloon system to launch multiple small folding wing unmanned aerial vehicles (UAVs). Based on the design of the launching system, we conduct numerical simulations of the ejection process from the balloon platform and the subsequent UAV wing deployment with trajectory leveling operation. We use the Kane method to establish the dynamic model of the balloon launching platform in the inertial coordinate system (ICS). By introducing the degree of freedom of UAV sliding along the sliding track, we realize the dynamic simulation of eight UAV launching processes and obtain the instantaneous separated states. The folding wing UAV first deploys its wings after ejection, which has the coupling characteristics between structural deformation and attitude adjustment. It is regarded as a multi-rigid body connecting structure composed of the fuselage and four wings. We establish the dynamic simulation model by the Kane method in the UAV body coordinate system (BCS). The Radau pseudo-spectral method is used to calculate the flight trajectory of each UAV. This paper is an engineering application research and can provide a simulation reference for the launching test of the balloon-borne folding wing UAV program.

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Section: Simulation Of the Ejection Process From The Balloon Platformmentioning

confidence: 98%

Section: Simulation Of the Wing Deploying And Trajectory Leveling Pro...mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Dynamics simulation of folding wing UAVs launched from a high-altitude balloon platform

Zhang

Yang

Cai

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The new method is based on the wind estimator used on the NRL CICADA Mk 3 micro air vehicle [13]. An extended Kalman filter (EKF) was designed to estimate the airspeed sensor bias and the wind components based on the ground speed, ground track angle, and true airspeed.…”

Section: Estimate Windsmentioning

confidence: 99%

Autonomous Locator of Thermals (ALOFT) Autonomous Soaring Algorithm

Edwards¹

2015

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Standard Form 298 (Rev. 8-98) Prescribed by ANSI Std. Z39.18 Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. 5a. CONTRACT NUMBER a. REPORT 19a. NAME OF RESPONSIBLE PERSON 19b. TELEPHONE NUMBER

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“…1,2 There are many application cases of launching UAVs with high-altitude balloons. [3][4][5][6][7][8] In order to facilitate storage and reduce occupied space, it is necessary to design a folding mechanism at the wing root to fold and deploy the front and rear wings within the 90°range. At the same time, it can also prevent damage to the UAV structure during the ground launching and ascend process of the high-altitude balloon system.…”

Section: Introductionmentioning

confidence: 99%

Dynamics simulation of a folding wing unmanned aerial vehicle with the parachute system assisted launching

Zhang

Yang

Cai

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper mainly focuses on a series of dynamic problems caused by a small folding wing Unmanned Aerial Vehicle (UAV) with a parachute system assisted launched from the high-altitude balloon platform. The simulation contents are the four-stage motion processes of the “parachute-UAV system” after separation from the balloon platform, including the straightening stage, the inflation process, the stable descend under the influence of the wing deployment action, and the trajectory leveling of the UAV. The “parachute-UAV system” is equivalent to a multi rigid body connection structure. We introduce the straightening length parameter and the wing deployment angles based on the Kane method to establish the dynamic model. And we choose the inflation time method to simulate the parachute deployment process and the flat plate high angle of attack model to describe the wing aerodynamic force. In the simulation, we compare six launching processes of different wing deployment time periods and obtain the separation state of each UAV when cut from the parachute. We adopt the Radau Pseudo-Spectral method to calculate the leveling trajectory of six UAVs. This paper is an engineering application research study and can provide a simulation reference for the launching test of the balloon-borne folding wing UAV system.

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Navigation, Guidance and Control For the CICADA Expendable Micro Air Vehicle

Cited by 13 publications

References 3 publications

Dynamics simulation of folding wing UAVs launched from a high-altitude balloon platform

Dynamics simulation of folding wing UAVs launched from a high-altitude balloon platform

Autonomous Locator of Thermals (ALOFT) Autonomous Soaring Algorithm

Dynamics simulation of a folding wing unmanned aerial vehicle with the parachute system assisted launching

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