Guidance and control for high dynamic rotating artillery rockets

Celis, Raúl de; Cadarso, Luís; Sánchez, Jesús

doi:10.1016/j.ast.2017.01.026

Cited by 34 publications

(35 citation statements)

References 18 publications

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“…Simulation results are presented using the nonlinear flight dynamics model [24] in order to demonstrate suitability of attitude determination algorithm. A set of ballistic simulated shots was performed as defined in the previous section, in order to compare real (denoted with subindex "real") and estimated attitudes.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…For this purpose, the similar model as defined in [24] is employed, but with some modifications in the aerodynamics. The first modification is that the effective incidence aerodynamic speed on each of the four fins must be estimated.…”

Section: International Journal Of Aerospace Engineeringmentioning

confidence: 99%

“…The flight dynamics model in [24] is employed. The equations of motion are integrated using a fixed time step Runge-Kutta scheme of fourth order to obtain a single flight trajectory.…”

Section: Flight Dynamics and Sensor Modelmentioning

confidence: 99%

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Attitude Determination Algorithms through Accelerometers, GNSS Sensors, and Gravity Vector Estimator

Celis

Cadarso

2018

International Journal of Aerospace Engineering

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Aircraft and spacecraft navigation precision is dependent on the measurement system for position and attitude determination. Rotation of an aircraft can be determined measuring two vectors in two different reference systems. Velocity vector can be determined in the inertial reference frame from a GNSS-based sensor and by integrating the acceleration measurements in the body reference frame. Estimating gravity vector in both reference frames, and combining with velocity vector, determines rotation of the body. A new approach for gravity vector estimations is presented and employed in an attitude determination algorithm. Nonlinear simulations demonstrate that using directly the positioning and velocity outputs of GNSS sensors and strap-down accelerometers, aircraft attitude determination is precise, especially in ballistic projectiles, to substitute precise attitude determination devices, usually expensive and forced to bear high solicitations as for instance G forces.

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Section: Simulation Resultsmentioning

confidence: 99%

Section: International Journal Of Aerospace Engineeringmentioning

confidence: 99%

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Attitude Determination Algorithms through Accelerometers, GNSS Sensors, and Gravity Vector Estimator

Celis

Cadarso

2018

International Journal of Aerospace Engineering

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“…According (24), (27), we can obtain the approximate variance of displacement in lateral vibration and rotation angle in torsional vibration, the variance is on 3 …”

Section: The Influence On Navigation Calculating Of the Lever Arm Effmentioning

confidence: 99%

“…The complex dynamic environment will change the IMU's error coefficient such as installation error,scale factor and etc, which is calibrated in pure static environment. [1][2][3] Most aircraft navigation error model didn't consider the dynamic error, so the navigation calculation will hold that the sensitive value of the IMU is complete accurate and directly introduce measurement error to the model.…”

Section: Introductionmentioning

confidence: 99%

Influence of Lateral-torsional Coupling Vibration on SINS Lever-arm Error Compensation

Yang¹,

Liu²,

Meng³

et al. 2017

2017 2nd International Conference on Mechatronics and Information Technology (ICMIT 2017)

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Abstract. The influence of complex dynamic environment in apparatus cabin for strapdown inertial navigation system(SINS) is one of the technical problems to improve navigation accuracy. The SINS was equivalent to Timoshenko-beam hybrid system, which was considered under the lateraltorsional coupling vibration. The system motion was described by dynamic differential equations, decoupled and solved by the Timoshenko-beam's Green function. The vibration response of the SINS would make the lever arm vector changed and incomplete compensation, at the same time, vibration response also introduced measurement error. Finally, with the flight simulation, the influence of lever arm error incomplete compensation and measurement error were analysed separately.

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An Estimator for UAV Attitude Determination based on Accelerometers, GNSS Sensors, and Aerodynamic Coefficients

Celis

Cadarso

2018

J Inst Navig

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Accurate navigation and control of Unmanned Air Vehicles (UAV) are strongly linked to the estimation of position and attitude. Rotation of an aircraft can be determined measuring two vectors, for example, velocity and gravity vectors, in two independent reference frameworks, for example, inertial and the body reference frames. The velocity vector can be determined in inertial reference frame from a GNSS‐based sensor and in the body reference frame by integrating accelerometer measurements. A novel approach is presented for gravity vector estimation in the body reference frame, which is based on UAV aerodynamics and mass properties. Combining both vectors enables determination of body rotation. Nonlinear simulations show that, utilizing GNSS sensors, strap‐down accelerometers and the proposed approach, aircraft attitude determination is accurate. The developed calculations are implemented on a fixed‐wing UAV, permitting the substitution of specific attitude determination gadgets, which are normally costly for several applications. © 2018 Institute of Navigation.

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Guidance and control for high dynamic rotating artillery rockets

Cited by 34 publications

References 18 publications

Attitude Determination Algorithms through Accelerometers, GNSS Sensors, and Gravity Vector Estimator

Attitude Determination Algorithms through Accelerometers, GNSS Sensors, and Gravity Vector Estimator

Influence of Lateral-torsional Coupling Vibration on SINS Lever-arm Error Compensation

An Estimator for UAV Attitude Determination based on Accelerometers, GNSS Sensors, and Aerodynamic Coefficients

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