Using haptic feedbacks for obstacle avoidance in helicopter flight

An obstacle avoidance function based on haptic feedback has been developed and tested on a simulation environment at ONERA. The objective was to calculate and provide effcient haptic feedback through active (motorized) sidesticks for the piloting task of a rotary wing (RW) aircraft, in the vicinity of visible and known obstacles, corresponding to emergency avoidance procedure, or navigation in a congested area. Two different methods have been designed to generate the force bias based on virtual force fields (VFF) surrounding obstacles and on a geometric approach (GA) combined with T-theory, respectively. Piloted simulations were performed in order to evaluate the benefits for obstacle avoidance.

Analysis of generic reentry vehicle flight dynamics

The knowledge of reentry vehicles (RV) flight characteristics regarding geometrical shape, dimensions, and mechanical properties is essential for precise prediction of their flight trajectory, impact point, and possible deviations according to simulation uncertainties. The flight characteristic estimations of existing RV require both body dimensions and mechanical properties of the objects. Due to comparatively simple and reliable methods of specifying the vehicle outer dimensions, e. g., photos and videomaterials, the estimation of mechanical properties is a subject of higher uncertainties. Within this study, a generic medium range ballistic missile (MRBM) RV was examined for several modifications such as center of gravity (CoG) position, weight moment of inertia, and initial reentry flight states. Combinations of these variables with constant aerodynamic properties for maximal lateral accelerations will be determined. Basing on these, potential evasion maneuver capabilities of the RV will be described.

On active disturbance rejection based framework for flight control: principle and applications

Active Disturbance Rejection Control (ADRC) offers a viable framework for flight control that both inherits what is right about proportional-integral-derivative (PID) controllers that makes it a long lasting industrial solution and addresses its weaknesses. Building on this foundation, ADRC as a way of thinking and a methodology can be understood and accepted by practicing engineers. Several flight control applications are used to show flexibility and applicability of the proposed framework in tackling diverse problems in flight control. It appears that such a solution is simple to understand, easy to implement, and convenient to tune, thus making it highly user friendly and effective.

Accurate predictor–corrector skip entry guidance for low lift-to-drag ratio spacecraft

This paper develops numerical predictor–corrector skip en try guidance for vehicles with low lift-to-drag L/D ratio during the skip entry phase of a Moon return mission. The guidance method is composed of two parts: trajectory planning before entry and closed-loop gu idance during skip entry. The result of trajectory planning before entry is able to present an initial value for predictor–corrector algorithm in closed-loop guidance for fast convergence. The magnitude of bank angle, which is parameterized as a linear function of the range-to-go, is modulated to satisfy the downrange requirements. The sign of the bank ang le is determined by the bank-reversal logic. The predictor-corrector algorithm repeatedly applied onboard in each guidance cycle to realize closed-loop guidance in the skip entry phase. The effectivity of the proposed guidance is validated by simulations in nominal conditions, including skip entry, loft entry, and direct entry, as well as simulations in dispersion conditions considering the combination disturbance of the entry interface, the aerodynamic coefficients, the air density, and the mass of the vehicle.

Genetic algorithms for GNC settings and DACS design application to an asteroid Kinetic Impactor

This paper deals with an application of Genetic Algorithm (GA) tools in order to perform and optimize the settings phase of the Guidance, Navigation, and Control (GNC) data set for the endgame phase of a Kinetic Impactor (KI) targeting a medium-size Near Earth Object (NEO). A coupled optimization of the GNC settings and of the GC-oriented design of the Divert and Attitude Control System (DACS) is also proposed. The illustration of the developed principles is made considering the NEOShield study frame.

Optimization of the launcher ascent trajectory leading to the global optimum without any initialization: the breakthrough of the Hamilton–Jacobi–Bellman approach

The resolution of the launcher ascent trajectory problem by the so-called Hamilton–Jacobi–Bellman (HJB) approach, relying on the Dynamic Programming Principle, has been investigated. The method gives a global optimum and does not need any initialization procedure. Despite these advantages, this approach is seldom used because of the dicculties of computing the solution of the HJB equation for high dimension problems. The present study shows that an eccient resolution is found. An illustration of the method is proposed on a heavy class launcher, for a typical GEO (Geostationary Earth Orbit) mission. This study has been performed in the frame of the Centre National d’Etudes Spatiales (CNES) Launchers Research & Technology Program.

AOCS operations preparation for the BepiColombo mission to mercury

The 2018 ESA/JAXA BepiColombo mission to Mercury features a complex modular design, with two scientific Mercury orbiters and a cruise module. The spacecraft (S/C) and mission design lead to a number of challenges for the attitude and orbit control system (AOCS), including electric propulsion usage during cruise to Mercury, AOCS capability to deal with several S/C configurations, and strict attitude constraints owing to the harsh thermal environment. This paper presents the activities for AOCS operations preparation by ESA/ESOC, covering the current preparation status as well as an outlook on upcoming activities before launch.

LIRIS flight database and its use toward noncooperative rendezvous

ESA’s fifth and last Automated Transfer Vehicle, ATV Georges Lemaître, tested new rendezvous technology before docking with the International Space Station (ISS) in August 2014. The technology demonstration called Laser Infrared Imaging Sensors (LIRIS) provides an unseen view of the ISS. During Georges Lemaître’s rendezvous, LIRIS sensors, composed of two infrared cameras, one visible camera, and a scanning LIDAR (Light Detection and Ranging), were turned on two and a half hours and 3500 m from the Space Station. All sensors worked as expected and a large amount of data was recorded and stored within ATV-5’s cargo hold before being returned to Earth with the Soyuz flight 38S in September 2014. As a part of the LIRIS postflight activities, the information gathered by all sensors is collected inside a flight database together with the reference ATV trajectory and attitude estimated by ATV main navigation sensors. Although decoupled from the ATV main computer, the LIRIS data were carefully synchronized with ATV guidance, navigation, and control (GNC) data. Hence, the LIRIS database can be used to assess the performance of various image processing algorithms to provide range and line-of-sight (LoS) navigation at long/medium range but also 6 degree-of-freedom (DoF) navigation at short range. The database also contains information related to the overall ATV position with respect to Earth and the Sun direction within ATV frame such that the effect of the environment on the sensors can also be investigated. This paper introduces the structure of the LIRIS database and provides some example of applications to increase the technology readiness level of noncooperative rendezvous.

Manipulator trajectories during orbital servicing mission: numerical simulations and experiments on microgravity simulator

It is considered to use a manipulator-equipped satellite for performing On-Orbit Servicing (OOS) or Active Debris Removal (ADR) missions. In this paper, several possible approaches are reviewed for end-effector (EE) trajectory planning in the Cartesian space, such as application of the Bézier curves for singularity avoidance and method for trajectory optimization. The results of numerical simulations for a satellite equipped with a 7 degree-of-freedom (DoF) manipulator and results of experiments performed on a planar air-bearing microgravity simulator for a simplified two-dimensional (2D) case with a 2-DoF manipulator are presented. Differences between the free-floating case and the case where Attitude and Orbit Control Systems (AOCS) keep constant position and orientation of the satellite are also shown.

Neural network adaptive control of wing-rock motion of aircraft model mounted on three-degree-of-freedom dynamic rig in wind tunnel

High-angles-of-attack dynamics of aircraft are complicated with dangerous phenomena such as wing rock, stall, and spin. Autonomous dynamically scaled aircraft model mounted in three-degree-of-freedom (3DoF) dynamic rig is proposed for studying aircraft dynamics and prototyping of control laws in wind tunnel. Dynamics of the scaled aircraft model in 3DoF manoeuvre rig in wind tunnel is considered. The model limit-cycle oscillations are obtained at high angles of attack. A neural network (NN) adaptive control suppressing wing rock motion is designed. The wing rock suppression with the proposed control law is validated using nonlinear time-domain simulations.