Accueil
Dernières images
S'enregistrer
ConnexionCanadair CL-84
aeronewsline :: Accueil :: Histoire :: Aéronefs 1956 à 1965
Page 1 sur 3
Page 1 sur 3 • 1, 2, 3 
Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:32
L'aile basculante de Canadair sur Wikipedia de langue anglaise
[Vous devez être inscrit et connecté pour voir ce lien]
-----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
The Canadair CL-84, designated by the [Vous devez être inscrit et connecté pour voir ce lien] as the CX-131, was a [Vous devez être inscrit et connecté pour voir ce lien] turbine tilt-wing monoplane designed and manufactured by [Vous devez être inscrit et connecté pour voir ce lien] between 1964 and 1972.
Only four of these experimental aircraft were built with three entering flight testing.
[Vous devez être inscrit et connecté pour voir ce lien]
-----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
The Canadair CL-84, designated by the [Vous devez être inscrit et connecté pour voir ce lien] as the CX-131, was a [Vous devez être inscrit et connecté pour voir ce lien] turbine tilt-wing monoplane designed and manufactured by [Vous devez être inscrit et connecté pour voir ce lien] between 1964 and 1972.
Only four of these experimental aircraft were built with three entering flight testing.
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Re: Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:35
Two of the CL-84s crashed due to mechanical failures, but no loss of life occurred as a result of these accidents.
Despite the fact that the CL-84 was very successful in the experimental and operational trials carried out between 1972 and 1974, no production contracts resulted.
Despite the fact that the CL-84 was very successful in the experimental and operational trials carried out between 1972 and 1974, no production contracts resulted.
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Re: Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:37
Development
Between 1957 and 1963, Canadair carried out research in VTOL (vertical takeoff and landing) technology with the assistance of the National Research Board (NRB) and the Defense Research Board (DRB) of Canada.
[Vous devez être inscrit et connecté pour voir ce lien]
The studies pointed the way to a unique tilt-wing design.
Between 1957 and 1963, Canadair carried out research in VTOL (vertical takeoff and landing) technology with the assistance of the National Research Board (NRB) and the Defense Research Board (DRB) of Canada.
[Vous devez être inscrit et connecté pour voir ce lien]
The studies pointed the way to a unique tilt-wing design.
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Re: Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:40
The wing and the powerplants of the aircraft could be tilted hydro-mechanically (recirculating ball actuator) so that the wing incidence changed through 100 degrees from a normal flight angle to those for [Vous devez être inscrit et connecté pour voir ce lien] and [Vous devez être inscrit et connecté pour voir ce lien].
The incidence of the tailplane (or stabilizer) was automatically altered to deal with trim changes as the wing-incidence varied.
The two sets of blades were locked in a fore and aft position in conventional flight.
The incidence of the tailplane (or stabilizer) was automatically altered to deal with trim changes as the wing-incidence varied.
The two sets of blades were locked in a fore and aft position in conventional flight.
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Re: Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:43
Design
Contra-rotating rotors on a vertical axis in the tail provided fore-and-aft (pitch) control during hovering and transitional flight.
The propulsion and lifting propellers were handed (i.e. revolved in opposite directions) and were interconnected by shafts through a central gearbox from which the tail rotors and accessories were also driven.
The thrust from the propellers was matched automatically except when over-ridden by the pilot for lateral (roll) control in slow or hovering flight.
Contra-rotating rotors on a vertical axis in the tail provided fore-and-aft (pitch) control during hovering and transitional flight.
The propulsion and lifting propellers were handed (i.e. revolved in opposite directions) and were interconnected by shafts through a central gearbox from which the tail rotors and accessories were also driven.
The thrust from the propellers was matched automatically except when over-ridden by the pilot for lateral (roll) control in slow or hovering flight.
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Re: Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:44
A mechanical "mixing" unit was used to adjust the functions of the various controls in the different modes of flight.
The flap/ailerons gave yaw control when hovering. In the cockpit fore and aft stick was always pitch, side to side was always roll and the rudder pedals were always yaw, irrespective of the wing position through its full range.
The flap/ailerons gave yaw control when hovering. In the cockpit fore and aft stick was always pitch, side to side was always roll and the rudder pedals were always yaw, irrespective of the wing position through its full range.
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Re: Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:48
Two 1,500 shp (1,100 kW) [Vous devez être inscrit et connecté pour voir ce lien] shaft-turbines were used to drive the two 14 ft (4.3 m) four-bladed propellers.
The engines were interconnected by cross shafts, so that in the event of the failure of one engine, it would
automatically disconnect (through torque spring clutches) and both propellers would be driven by the remaining engine.
The engines were interconnected by cross shafts, so that in the event of the failure of one engine, it would
automatically disconnect (through torque spring clutches) and both propellers would be driven by the remaining engine.
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Re: Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:50
There were two main reasons for the technical success of the CL-84 design.
Aerodynamic considerations were given a very high priority, and the controlling of power was kept as simple and direct as possible.
Aerodynamic considerations were given a very high priority, and the controlling of power was kept as simple and direct as possible.
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Re: Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:53
The propeller disks extended slightly beyond the wingtips, so the whole of the wing (except for the portion above the fuselage) was immersed in the propeller slipstream.
This, together with full-span leading edge and trailing edge flaps which were programmed with wing tilt angle, ensured
that the wing was never stalled.
Trim changes were minimized by programmed tilting of the tailplane.
All programming was based on extensive testing in the wind tunnel and on an outdoor mobile test rig.
This, together with full-span leading edge and trailing edge flaps which were programmed with wing tilt angle, ensured
that the wing was never stalled.
Trim changes were minimized by programmed tilting of the tailplane.
All programming was based on extensive testing in the wind tunnel and on an outdoor mobile test rig.
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Re: Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:54
The power of both engines was controlled by a single "power lever" in all flight regimes.
To provide crisp thrust control during hover, movement of the power lever caused a direct adjustment of blade angle,
analogous to the collective pitch control of a helicopter, with the propeller cpu governor making a follow-up adjustment of blade angle to maintain the selected rpm.
The direct adjustment of blade angle was faded out automatically as the blade angle increased with increasing
forward speed.
To provide crisp thrust control during hover, movement of the power lever caused a direct adjustment of blade angle,
analogous to the collective pitch control of a helicopter, with the propeller cpu governor making a follow-up adjustment of blade angle to maintain the selected rpm.
The direct adjustment of blade angle was faded out automatically as the blade angle increased with increasing
forward speed.
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Re: Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:56
The only unfamiliar control function the pilot had to deal with was the wing tilt control, which was a switch on the power lever (and took the place of controlling the flaps).
The combination of smooth aerodynamics and simple power control made it easy for fixed-wing pilots to perform
transitions between hover and wing-down modes on their first flight in the CL-84.
The combination of smooth aerodynamics and simple power control made it easy for fixed-wing pilots to perform
transitions between hover and wing-down modes on their first flight in the CL-84.
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Re: Canadair CL-84
par FARHEN Sam 17 Juil 2010, 10:57
Operational history
Testing
CF-VTO-X, the CL-84 prototype first flew in hover on 7 May 1965, flown by Canadair Chief Pilot Bill Longhurst.
On 12 September 1967, after 305 relatively uneventful flights, CF-VTO-X was at 3,000 ft (910 m) when a bearing in the propeller control system failed.
Both pilot and observer successfully ejected but the prototype was lost.
Canadair redesigned its replacement, the CL-84-1 incorporating over 150 engineering changes including the addition of dual controls, upgraded avionics, an airframe stretch (1.6 m, 5 ft 3 in (1.60 m) longer) and more powerful engines (boosted by 100 hp).
Testing
CF-VTO-X, the CL-84 prototype first flew in hover on 7 May 1965, flown by Canadair Chief Pilot Bill Longhurst.
On 12 September 1967, after 305 relatively uneventful flights, CF-VTO-X was at 3,000 ft (910 m) when a bearing in the propeller control system failed.
Both pilot and observer successfully ejected but the prototype was lost.
Canadair redesigned its replacement, the CL-84-1 incorporating over 150 engineering changes including the addition of dual controls, upgraded avionics, an airframe stretch (1.6 m, 5 ft 3 in (1.60 m) longer) and more powerful engines (boosted by 100 hp).
FARHEN- CLUB
- Messages : 369
Localisation : IDF
Page 1 sur 3 • 1, 2, 3
aeronewsline :: Accueil :: Histoire :: Aéronefs 1956 à 1965
Page 1 sur 3
Permission de ce forum:
Vous ne pouvez pas répondre aux sujets dans ce forum|
|
|