Could this be the European rival for Virgin Galactic’s White Knight 2? Yes and no. This is EOLE, one of
the Perseus family of projects. Perseus is an initiative of CNES towards the research of innovative technologies for space transportation
and their respective demonstrators, through an educative perspective. It was launched 6 years ago with the participation of many Universities and agencies. This particular system is
called EOLE and it is the demonstrator for L3AR (Lancement Assisté par Aéroporteur Automatique Réutilisable, or Assisted launch via an
automatic reusable aircraft.). The project started in 2008 and its design, aerodynamic configuration and internal arrangement are developed by ONERA, Aviation
Design and Planète Sciences. The design was frozen in Mars 2010.—
EOLE has many similarities with Scaled Composites White Knight
1 and 2. All three are specifically designed as aerial launch platforms. The main requirement is the ability to transport a variety of payloads and drop them safely from a relatively
high altitude. In order to accommodate the captive aircraft (like SpaceShipOne and Two), expendable rocket or even a re-usable rocket/winged vehicle there is a need for a
centrally located big empty space. There the payload will be placed and then dropped. Also this area should be near the centerline and cq of the carrier aircraft in order for it to be
insensitive to the weight of the payload or its absence after the drop.
The EOLE is a small-unmanned validation prototype. It will have a wingspan of 6,7m, a weight of 100kg and a payload of 50kg. It can fly up to 8km (~26k ft) with maximum speed of 0.6 mach. It
will drop its payload at 4km while flying at 0.2 mach. The aircraft in the pictures is the even smaller scale model (1/2.2) made by Aviation Design. Eole will have
two small turbojets with 45kg of thrust each while the scale model has two electric ducted fans with 5kg each.
As you can see in the comparative graph above (scaled to size), Eole (blue) is much smaller than White Knight 1 (red) or 2 (green). In the Perseus website they claim
that this is an original configuration, although the tier one influence is obvious. Being unmanned it doesn’t need to accommodate a pilot, it may look similar to WK2 but its general
arrangement and engine placement is closer to WK1. Due to its size it is strictly a research vehicle. It will be used to study the dynamic behavior during the separation and rocket launch.
Apart from remote controlled take-off and landing it will fly autonomously within a range of 30km with its GPS assisted autopilot. Tests are already taking place with large part of the work
conducted by students. The rocket drops and firing will be conducted next year or 2013 by DGA EM (Direction Générale de
l’Armement – Essais de Missiles), the missile test sector of French armed forces.
Apart from EOLE , Perseus covers a variety of other projects mostly aimed at rocket propulsion and even complete launch vehicles like the ARES/ARCADIA. The HERA-F for example is a hybrid rocket that use oxidizer and solid rubber
fuel (multi-core polyethylene or single-core paraffin). SpaceShipOne used a similar motor, it may not have the performance of a solid rocket booster but it is much safer because it can be
stopped and started at any time by throttling the oxidizer. It is also much simpler than a throttled liquid fuel rocket. Other concepts cover multi-staged rockets and fuel containers. Virgin
Galactic also have hinted the use of White Knight Two as a platform for launching expendable or reusable rockets that could place satellites to orbit. The images above show the
‘LauncherOne’ on the right; a two stage expendable rocket (image from Virgin Galactic) and the two concepts on the left show a possibly reusable winged orbital vehicle (images from a Virgin
Galactic presentation via Flightglobal).
The goal of Eole and Perseus in general is to stimulate space transport innovation throughout the new generation of engineers. By itself it won’t bring a product or service to the market but
not unlike Scaled Composite and Paul Allen funded Tier One that led to Virgin Galactic, Perseus may spin-off a variety of innovative companies that may be the European VG or Space-X.
5830 mm / 6670 mm (mit Aufsteckflügel und Winglets)
Rumpflänge
2750 mm
Gewicht
ab 16,5 kg (je nach Ausbau und Ausstattung)
Flächeninhalt
5830 mm = 170 qdm bzw. 6670 mm = 184,7 qdm
Profil
HQ 1,5 Acro / 12 %
Maßstab
1 : 3
Schwerpunkt
Querruder
oben unten
24 12
Höhenruder
Höhenruderzumischung zu den Störklappen + 1,5 mm
oben unten
22 16
Seitenruder
links rechts
50 50
Alle Maße in mm im tiefsten Klappenbereich gemessen (Innen, Mitte, Unten). Die angegebenen Werte bewirken ein sehr wendiges Flugverhalten. Individuelle Abweichungen sind möglich. RAL-Ton 9003 (weiß). Achtung, bitte den Lack nur mit
Politur reinigen (kein Aceton oder Spiritus) !!
Le Planeur est arrivé déjà bien avancé, décision d' Etienne
reste : la fixation de la dérive
le montage des servos et de la radio
le montage du moteur et du réservoire
la déco à coller.
comme d'habitude pas de surprise avec PARITECH la qualité est au rendez vous.
les circuits imprimés des connecteurs MULTIPLEX viennent de chez NESSEL ELEKTRONIK GMBH (cela évite de tirer sur
les fils et beaucoup plus facile à souder)
la commande des parties mobiles est calssique chez PARITECH
DOC PARITECH
le pylone moteur est déjà posé ,et l'on aperçoit l'opercule de condamnation du trou du pylone (à droite du
pylone) au cas ou l'on retirerait le moteur.
sous le support moteur le réservoire
platine avant pour les LIPOS et la POWERBOX et la fixation du plomb de centrage
réservoire 1.8 litre
FIXATION servo AF support LAB coolé cyano , étrier alu vissé
FIXATION servo aileron, glissière en LAB,verrouillage tube alu de 6
SERVO DE DERIVE le plus simple est de demonter la roue arrière pour accéder plus facilement à la platine.
connextion profondeur: la prise femelle est en fixe sur le stab
nouveau moteur 8KG UT80 JETS MUNT
ECU intégrée, pompe extérieur, photos ci-dessous
fixation moteur sur le pylone , toutes les connections passent à l'intérieur du pylone.
la fixation comporte d'origine l'angle de callage latéral .L'incidence du moteur est réglée pour le premier vol
sur l'incidence de l'aile.
photo du haut ,on aperçoit la cale en téflon fournie pour faire sortir le saumon ,permettant
d'ajouter les rallonges d'ailes
téton automatique de fixation de
saumon
une corde à piano de 4, à été ajoutée sur le patin de saumon pour les pistes en dure.
déco à votre convenance.
la commande d'ouverture de verrière est actionnée par l'ouverture d'entrée d'air verrière.
CENTRAGE AVEC 1.8 KG de plomb dans le nez et 3 lipos de 3000