Haider Benzeniar

Centre de Développement des Technologies Avancées

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i-10 index

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Mohamed Kameche

Centre de Développement des Technologies Avancées

A. Boudjemai

Centre de Développement des Technologies Avancées

Nadir Bouanani

Centre de Développement des Technologies Avancées

R. Amri

University of Blida

Ayhane Bey Benbouzid

Centre de Développement des Technologies Avancées

M. Benyettou

Université des Sciences et de la Technologie d'Oran Mohamed Boudiaf

A. M. Si Mohammed

Centre de Développement des Technologies Avancées

Mohammed Amine Meghabber

Centre de Développement des Technologies Avancées

M. Fellah

University of Sciences and Technology Houari Boumediene

Martin Sweeting

University of Surrey

Cooperative Institutions

Centre de Développement des Technologies Avancées

CRSTRA

Université des Sciences et de la Technologie d'Oran Mohamed Boudiaf

University of Sciences and Technology Houari Boumediene

University of Science and Technology

Université Djilali de Sidi Bel Abbès

University of Surrey

Surrey Satellite Technology (United Kingdom)

Département d'Informatique

Université Oran 1 Ahmed Ben Bella

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Disaster Monitoring Constellation Using Nanosatellites

Journal of Aerospace Technology and Management (2014)

Mohamed Kameche Haider Benzeniar Ayhane Bey Benbouzid R. Amri Nadir Bouanani

In this paper, a constellation of four low earth orbit nanosatellites for disaster monitoring is presented; their small size, low cost, and short time development give them the opportunity to be widely selected. The space segment is based on existing subsystems that are assembled on the bottom part of a developed structure and present acceptable performance for the mission. The payload is a multispectral camera which fulfills the mission's requirements (remote sensing). The ground segment is based on an existing modular ground station, used for the ALSAT-1 DMC, which will be adapted to fit with the specifications of the mission.

Payload (computing)

Satellite constellation

Ground segment

Orbit (dynamics)

Ground station

10.5028/jatm.v6i1.281

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Citations (15)

Initial Attitude Acquisition in-orbit Status of ALSAT-2A Remote Sensing Satellite

WSEAS TRANSACTIONS ON SYSTEMS (2020)

Haider Benzeniar

- In this paper we present the in orbit performance during the initial attitude acquisition, immediately after separation from the final stage of the launcher, until the satellite converges toward a sun pointing. On 12th july 2010 ALSAT-2A microsatellite was launched into a 670 km sun synchronous orbit, with a solar local time at an ascending node of 22h15. In the initial acquisition mode or even in the safe mode, only sun sensors and magnetometer are used for attitude determination. Knowing that, the satellite once is separated from the launcher it starts tumbling. So, as to detumble the satellite, a strategy consisting of three phases is set. The first phase consists on reducing the velocity using only the magnetorquers, until reaching the threshold angular momentum of 0.05 Nms, once this is done, the second phase is automatically enabled in such a way, the four reaction wheels are ON and speed up to get an angular momentum of -0.15 Nms along the satellite x-axis. At the end of this phase the satellite is completely detumbled and a third phase is carried out, in which the satellite minus X axis is pointed toward sun with a small rotation.

Orbit (dynamics)

Reaction wheel

Momentum (technical analysis)

Mode (computer interface)

10.37394/23202.2020.19.9

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Citations (0)

A Microsatellite Reaction Wheel Based on a Fuzzy Logic Controller for the Attitude Control System

International Review of Aerospace Engineering (IREASE) (2014)

Haider Benzeniar M. Fellah

Current interest in small satellites lies in the feasibility of achieving specific but limited objectives, by necessity, small satellites technology requires simple control schemes. In this paper, we present a fuzzy logic controller, as an attempt to replace the classical proportional derivative (PD) controller that is widely used in the spacecraft attitude determination control system (ADCS). The fuzzy logic controller is implemented on the Z axis (yaw) closed loop reaction wheel of a low earth orbit microsatellite with a gravity gradient stabilization. The yaw axis is pointed toward earth. We mention here that, when the spacecraft is not in the imaging mode, it starts spinning along the yaw axis to keep it within thermal limits. So that, in this axis the spacecraft is either in the imaging mode (freeze mode) or barbeque mode (BBQ mode).

Reaction wheel

Mode (computer interface)

Orbit (dynamics)

10.15866/irease.v7i5.4973

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Citations (3)

Disaster Monitoring Constellation Using Nanosatellites

Figshare (2018)

Mohamed Kameche Haider Benzeniar Ayhane Bey Benbouzid R. Amri Nadir Bouanani

ABSTRACT: In this paper, a constellation of four low earth orbit nanosatellites for disaster monitoring is presented; their small size, low cost, and short time development give them the opportunity to be widely selected. The space segment is based on existing subsystems that are assembled on the bottom part of a developed structure and present acceptable performance for the mission. The payload is a multispectral camera which fulfills the mission's requirements (remote sensing). The ground segment is based on an existing modular ground station, used for the ALSAT-1 DMC, which will be adapted to fit with the specifications of the mission.

Satellite constellation

10.6084/m9.figshare.7507277

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Citations (0)

Development of an orbit analysis tool for LEO satellites

Mohamed Kameche Mohammed Amine Meghabber Haider Benzeniar A. Boudjemai Abdelaziz Himeur

After the successful experiences of the two first earth observation satellites ALSAT-1 and ALSAT-2A, launched respectively, in November 2002 and July 2010, the Satellites Development Centre started developing mission analysis tools to be used for the future mission planed by the Algerian Space Agency. In this paper, we focus on the preliminary orbit analysis which represents a critical parameter for the feasibility and the definition of a space mission. The results of orbit analysis are used in the design of the payload, the propulsion and the communication subsystems and to guarantee that the defined ground track and local solar time control windows allow in addition to the quality of the mission data, the station keeping of the satellite in its reference orbit over the lifetime period and the required fuel for de-orbiting the satellite at the end of life.

Payload (computing)

Orbit (dynamics)

Earth's orbit

Ground track

Circular orbit

Polar orbit

Geocentric orbit

Earth observation

10.1109/rast.2013.6581208

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Citations (0)

In-orbit results from the attitude determination and control system of ALSAT-2B

The Aeronautical Journal (2021)

Haider Benzeniar

ABSTRACT The Algerian Space Agency has been active in the field of microsatellite engineering for more than 15 years and has successfully developed microsatellites under several know-how transfer technology programs, six to date. This paper presents the flight results and lessons learned from the attitude determination and control system (ADCS) flown on the ALSAT-2B satellite, an Earth observation microsatellite, by analysing the behaviour of the satellite from the initial attitude acquisition through the coarse pointing mode then the nominal mode, where the payload is first tested, and finally the orbit control mode. The spacecraft was launched on 26 September 2016 and placed into a 670km Sun-synchronous orbit with a solar local time at an ascending node of 22:15. The ADCS performance presented here mainly focuses on the launch and early operation results. ALSAT-2B includes four reaction wheels in a pyramidal configuration, three gyros, three Sun sensors, three magneto-torquers, one magnetometer, and one star tracker for agile and accurate attitude control. In addition, a propulsion system based on four 1N hydrazine thrusters is also used on board the microsatellite. The main new development in this platform compared with previous ones of the same type is the fusion of the star tracker and measurements by the three gyroscopes into one gyrostellar estimator that was implemented for the first time on ALSAT-2B, and the pyramidal configuration of the wheels, aiming to increase the angular momentum. The results obtained from the early launch operations for different ADCS modes are very encouraging and fulfil all the requirements set during design and testing. Currently, the satellite has accomplished its fourth year in orbit and is still operational and producing high-quality images.

Orbit (dynamics)

Star tracker

Payload (computing)

Halo orbit

Reaction wheel

10.1017/aer.2021.48

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Citations (0)

Analytic solution of Nadir attitude pointing for LEO microsatellite

WSEAS TRANSACTIONS on COMMUNICATIONS archive (2008)

A. M. Si Mohammed M. Benyettou A. Boudjemai Haider Benzeniar Y. Hashida

An Analytic solution of Nadir attitude pointing equation of gravity gradient satellite stabilised is presented. The attitude equation is Euler linearised equation for near Nadir pointing axially symmetric satellite including only gravity gradient torque and assuming other torques such as magnetic torque, aerodynamic torque, solar radiation pressure torque and controller are constants. The obtained analytical solution was compared to numerical solution of satellite attitude equation.

Nadir

Axial symmetry

10.5555/1455946.1455950

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Citations (1)