Office National D'etudes Et De Recherches Aerospatiales

Office National D'etudes Et De Recherches Aerospatiales (onera)

Office Natioanl D'etudes Et De Recherches Aerospatiales Styled O.n.e.r.a

Francois Falempin

Claude Sans

Gerard Laruelle

Jacques Isbert

Olivier Fourt

Andre Delfour

Champigny Patrick

Jean-Marie Garrel

Jean-Louis Pastre

The air intake includes two main flaps (1, 2) facing each other and each pivoting about a pin (4, 5) adjacent to a wall (6, 7) extending the flap in question (1, 2) rearwards, and in which a first boundary layer bleed (8a, 8b) is arranged, the pins (4, 5) being substantially parallel to the plane of the wings or of the fuselage so that the flaps (1, 2) move perpendicularly to this plane, and a ramp (11) pivoting about a pin (12) adjacent to its leading edge (11a) by which it is adjacent to the wings and to the fuselage and substantially parallel to the pins (4, 5) is upstream of the flap (1) which is closest to the wings and with which it delimits another boundary layer bleed (13) of variable cross section.

Two-dimensional supersonic and hypersonic air intake, with three movable

A two dimensional supersonic air intake is provided for the combustion air f an aircraft engine comprising on one side a front flap (3) forming a visor and on the other side a fairing (4). The front flap (3) is movable about a pivoting axis (5) situated opposite the fairing (4). The front flap (3) is fast with a mobile fairing nose (6) situated in front of fairing (4) and moving in front of the latter when the front flap (3) moves in the direction which increases the air intake section.

Two dimensional and asymmetric supersonic air intake for the combustion

Two dimensional, supersonic and hypersonic air intake for the combustion air of an aircraft engine, comprising two front flaps (3) forming a visor, disposed symmetrically on each side of a longitudinal plane (P), each front flap (3) being movable about a pivoting axis (4) situated in the vicinity of the wall of the air intake which extends the front flap considered. The pivoting axis (4) of each front flap (3) is situated in the vicinity of a first boundary layer trap (5) disposed in the wall of the air intake which extends said front flap (3).

Symmetrical, two dimensional, supersonic and hypersonic air intake for

A granulometry device embodying the invention comprises a measuring probe and a micro-computer. The micro-computer provides digital filtering on a first discrete distribution function that is calculated by statistical inversion from a plurality of radiation measurements supplied by the probe and a theoretical radiation coefficient matrix thereby determining, after an iterative calculation, an optimum relation which should be satisfied by the nodes defining a discrete distribution function so as to offer a maximum correlation with uncertainty measurements. All the discrete distribution functions satisfying this relation are then calculated by statistical inversions. The mirco-computer provides an optimum statistical evaluation of the distribution of particles in a gas or liquid fluid.

Optical granulometry process and devices for broad measuring ranges

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Saint Michel sur Orge, France

Francois Falempin