US2798362A - Means for slowing down an aircraft, particularly during landing, when powered by a turbo-jet - Google Patents

Means for slowing down an aircraft, particularly during landing, when powered by a turbo-jet Download PDF

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US2798362A
US2798362A US491122A US49112255A US2798362A US 2798362 A US2798362 A US 2798362A US 491122 A US491122 A US 491122A US 49112255 A US49112255 A US 49112255A US 2798362 A US2798362 A US 2798362A
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Prior art keywords
flaps
jet
aircraft
slowing down
powered
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Expired - Lifetime
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US491122A
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Horace S Rainbow
Pym Derek
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Armstrong Siddeley Motors Ltd
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Armstrong Siddeley Motors Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/62—Reversing jet main flow by blocking the rearward discharge by means of flaps

Definitions

  • This invention relates to means for slowing down an aircraft, particularly during landing, when powered by a gas turbine jet engine.
  • the main object of the invention is to provide means for producing a reverse thrust by diverting the direction of flow of a substantial portion of the jet gases in a very simple and satisfactory manner.
  • the means comprises, downstream of and around the jet nozzle, oppositely opening flaps which are pivotally mounted at or adjacent their downstream ends, adjacent flaps overlapping to provide, when opened, a complete annulus of V-shaped crosssection having one curved flange extending well into the path of the jet gases and the other extending to outside the jet nozzle so as to change the direction of flow of a material part of the jet gases.
  • the upstream ends of the internal flaps (adapted when opened to extend well into the path of the jet gases) abut a casing adjacent the downstream end of the jet nozzle when in the closed position, the casing being separated from the jet nozzle by an annular space, and the internal flaps, when closed, forming a slightly divergent nozzle portion.
  • the invention further consists in the provision of a number of stationary curved annuli downstream of the end of the jet nozzle, between the internal and external flaps, serving to guide the diverted portion of the jet gases in an appropriate manner.
  • FIGS. 1 and 2 are diagrammatic sections through a jet pipe of a gas turbine engine embodying the invention, the flaps being in closed and open positions respectively;
  • Figure 3 is a fragmentary sectional plan through one wall of the downstream end of the jet pipe of a gas turbine jet engine embodying the invention
  • Figure 4 is a perspective view of a two-part pivot bracket shOWn in Figure 3;
  • Figure 5 is a section on line 55 of Figure 3;
  • Figure 6 is a fragmentary elevation on the line 6--6 of Figure 3, showing the positions occupied by flaps when open;
  • Figure 7 is a similar fragmentary elevation showing the positions occupied by the flaps when closed.
  • FIG. 8 is a somewhat diagrammatic fragmentary elevation, partly in section, of an alternative embodiment of the invention.
  • FIGs 1 and 2 is shown the downstream end of a jet nozzle 10 separated from an outer casing 11 by an annular space 12.
  • the casing 11 and a casing 11a support, downstream of the jet nozzle 10, oppositely-opening flaps 23, 24, shown closed in Figure 1 and open in Figure 2.
  • the flaps when opened, form a complete annulus of V-shaped cross-section having one curved flange extending well into the path of the jet gases and the other extending to outside the jet nozzle Patented July 9, 1957 so as to change the direction of flow of a material part of the jet gases.
  • Figure 3 shows, in more detail, .the downstream end of the jet nozzle 10 separated from the outer casing 11 by the annular space 12 through which cooling air flows.
  • the casing 11 and a casing 11a support a stationary annulus 13 which is sited externally of the nozzle 10, and which, in turn, supports longitudinally-extending struts 14 of elliptical cross-section.
  • the struts 14 carry stationary members in the form of curved annuli 15, 15a for guiding a diverted portion of the jet gases, one of them, 15a, being additionally supported by the annulus ,13 and serving to enclose the downstream ends of actuators, later described, and at the downstream ends of each strut is supported one part 16 of a two-part pivot bracket 16, 16a, shown in more .detail in Figure 4.
  • the part 16, and the annulus 13 are provided with fingers 16b, 13a respectively, which are received in slots in the strut 14 and welded thereto.
  • At the downstream ends of at least three of the bracket parts 16a are apertures 17 in which are fitted pins 18 in turn supporting a streamlined end casing 19.
  • the stationary annulus 13 supports a cylinder 20 in which is reciprocablea piston (not shown) connected to an actuator rod 22, this mechanism forming a hydraulic ram for actuating inner and outer flaps 23 and 24 respectively.
  • Each actuator rod 22 (only one of which is shown,
  • a block 33 Integral with theactuator rod 22 is a block 33 ( Figures 3 and 5) through which passes a pin 34 pivotally supporting one end of each of links 35 and 36, respectively.
  • the other ends of the links 35 and 36 are pivoted to the downstream ends of the flaps 23 and 24'respectively by pins 37 and 38 respectively.
  • the internal surfaces of the flaps 23 and 24- are formed with internally projecting portions 39 which are recessed at 39:: to embrace the strut 14 when the flaps 'are in their closed position, the portions 39 being curved inwardly, so that in the open position of the flaps 23 and 24 they assist in providing a smooth change of direction of the flow of the gases.
  • All the parts 16 are mounted in a curved annulus 39b for a similar purpose, the annulus additionally serving to shroud the brackets and pivots of the flaps 23 and 24.
  • the hydraulic ram is actuated thereby causing the actuator rod 22 to move upstream, together with the box-section ring 26, carrying with it the block 33.
  • This movement of the block 33 causes the links 35 and 36 to pass over their deadcentre position and to exert a force on the downstream ends of the flaps 23 and 24 causing them to pivot inwardly and outwardly respectively about their pivot pins 32.
  • the flaps 23 and 24 are arranged to overlap in their open positions as shown in Figure 6 and in their closed positions as shown in Figure 7.
  • a rod 22a actuable by fluid pressure from a cylinder 20 is connected, through a ring 40 and pivot pin 41, to links 42 and 43 respectively.
  • the link 42 is connected to an inner flap 44 between its ends by means of a pivot pin 45 and the link 43 is connected to an outer flap 46 between its ends by means of a pivot pin 47.
  • the downstream ends of the flaps 44 and 46 have a common pivot pin 48 which is carried by fixed struts 49 supported from the casings 11, 11a. 7
  • the struts 49 carry curved annuli 50 between the flap for guiding the diverted portion of the jet. In this embodiment there is no annular space between the nozzle and the casing.
  • a means for slowing down an aircraft, particularly during landing, when powered by a jet engine including a jet nozzle, and a plurality of pairs of oppositely opening flaps, each pair of flaps being pivotally mounted near their downstream ends downstream of and around the jet nozzle, adjacent ones of said flaps overlapping one another to provide, when opened, a complete annulus of generally V-section, one flange of said annulus extending well into the path of the jet gases and the other extending to outside the jet nozzle so as to change the direction of flow of a material part of the jet gases.
  • a means for slowing down an aircraft, particularly during landing, when powered by a jet engine including a jet nozzle, a plurality of pair of oppositely opening flaps which are pivotally mounted near their downstream ends downstream of and around the jet nozzle, adjacent flaps overlapping to provide when open a complete annulus of generally V-shaped cross-section, said annulus having one flange extending well into the path of the jet gases and the other flange extending to outside the jet nozzle so as to change the direction of flow of a material part of the jet gases, and a number of fixed curved annuli downstream of the jet nozzle and disposed between the oppositely opening flaps, the internal and external flaps being provided with curved surfaces in order to coact With said curved annuli in guiding the diverted portion of the jet gases.
  • a means for slowing down an aircraft including a casing around and outside the jet nozzle, the upstream ends of the flaps being adapted when closed to abut the casing adjacent the trailing end of the jet nozzle.
  • Means for slowing down an aircraft including a casing outside the jet nozzle and separated therefrom by an annular space.
  • one of said curved annuli forming a wall at the downstream end of a cavity, actuators being provided for said flaps the actuators being disposed in said cavity.
  • Means for slowing down an aircraft including actuators for the flaps, one actuator being provided for each pair of flaps, and a single stationary annulus, outside the jet nozzle, which supports the actuators.
  • Means for slowing down an aircraft comprising for each actuator a hydraulic ram supported by said stationary annulus, and for each hydraulic ram a rod which is movable in a direction substantially parallel to the longitudinal axis of the jet nozzle, a pair of links for each rod, each rod being connected near its downstream end to said pair of links, said links being connected to a pair of said flaps.
  • Means for slowing down an aircraft including pins on which the pair of flaps are respectively pivoted, said pins being just upstream of where the links are connected to the flaps.
  • Means for slowing down an aircraft characterized in that the links are arranged to be over-centre in the closed position of the flaps so as to lock the flaps in the closed position.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)

Description

July 9, 1957 H. S..RAINBOW ETAL 2,798,
MEANS FOR SLOWING. DOWN AN AIRCRAFT; RARTICULARLY DURING LANDING, WHEN POWERED BY A TURBO-JET Filed Feb. 28, 1955 4 Sheets-Sheet l 1. m lal s l a 4 36 July 9, 1957 H. S. RAINBOW ET AL MEANS FOR SLOWING DOWN AN AIRCRAFT, PARTICULARLY DURING LANDING, WHEN POWERED BY A TURBO-JET Filed Feb. 28, 1955 4 Sheets-Sheet 2 Ila. ll .42
l3 I'. |3a ,6, [3a
'39 /39 lab: A65 .39a 39a P :2 9
2 2 5 32 k |a- 5 3| 23o.
FIG. 3-
July 9, 1957 H. s. RAINBOW ET AL 2.7983
MEANS FOR SLOWING DOWN AN AIRCRAFT, PARTICULARLY DURING LANDING, WHEN POWERED BY A TURBO-JET Filed Feb. 28, 1955 I 4 Sheets-Sheet 3 July 9, 1957 H. s. RAlNBOW ETAL 2,798,
MEANS FOR SLQWING DOWN AN AIRCRAFT, PARTICULARLY DURING LANDING, WHEN POWERED BY A TURBO-JET 4 Sheets-Sheet 4 Filed Feb. 28, 1955 MEANS FQR SLGWHNG DOWN AN AIRCRAFT, PARTICULARLY DURENG LANDlNG, WHEN PGWERED BY A. TURBO-3E1 Horace S. Rainbow and Derek Pym, Coventry, England,
assignors to Armstrong Siddeley Motors Limited, Coventry, England Application February 28, 1955, Serial No. 491,122
Claims priority, application Great Britain March 1, 1954 9 Claims. (Cl. Gil-35.54)
This invention relates to means for slowing down an aircraft, particularly during landing, when powered by a gas turbine jet engine.
The main object of the invention is to provide means for producing a reverse thrust by diverting the direction of flow of a substantial portion of the jet gases in a very simple and satisfactory manner.
According to-the invention, the means comprises, downstream of and around the jet nozzle, oppositely opening flaps which are pivotally mounted at or adjacent their downstream ends, adjacent flaps overlapping to provide, when opened, a complete annulus of V-shaped crosssection having one curved flange extending well into the path of the jet gases and the other extending to outside the jet nozzle so as to change the direction of flow of a material part of the jet gases.
According to a further feature of the invention, the upstream ends of the internal flaps (adapted when opened to extend well into the path of the jet gases) abut a casing adjacent the downstream end of the jet nozzle when in the closed position, the casing being separated from the jet nozzle by an annular space, and the internal flaps, when closed, forming a slightly divergent nozzle portion.
The invention further consists in the provision of a number of stationary curved annuli downstream of the end of the jet nozzle, between the internal and external flaps, serving to guide the diverted portion of the jet gases in an appropriate manner.
In the drawings:
Figures 1 and 2 are diagrammatic sections through a jet pipe of a gas turbine engine embodying the invention, the flaps being in closed and open positions respectively;
Figure 3 is a fragmentary sectional plan through one wall of the downstream end of the jet pipe of a gas turbine jet engine embodying the invention;
Figure 4 is a perspective view of a two-part pivot bracket shOWn in Figure 3;
Figure 5 is a section on line 55 of Figure 3;
Figure 6 is a fragmentary elevation on the line 6--6 of Figure 3, showing the positions occupied by flaps when open;
Figure 7 is a similar fragmentary elevation showing the positions occupied by the flaps when closed; and
Figure 8 is a somewhat diagrammatic fragmentary elevation, partly in section, of an alternative embodiment of the invention.
In Figures 1 and 2 is shown the downstream end of a jet nozzle 10 separated from an outer casing 11 by an annular space 12. The casing 11 and a casing 11a support, downstream of the jet nozzle 10, oppositely- opening flaps 23, 24, shown closed in Figure 1 and open in Figure 2. As can be seen from Figure 2 the flaps, when opened, form a complete annulus of V-shaped cross-section having one curved flange extending well into the path of the jet gases and the other extending to outside the jet nozzle Patented July 9, 1957 so as to change the direction of flow of a material part of the jet gases.
Figure 3 shows, in more detail, .the downstream end of the jet nozzle 10 separated from the outer casing 11 by the annular space 12 through which cooling air flows. The casing 11 and a casing 11a support a stationary annulus 13 which is sited externally of the nozzle 10, and which, in turn, supports longitudinally-extending struts 14 of elliptical cross-section.
The struts 14 carry stationary members in the form of curved annuli 15, 15a for guiding a diverted portion of the jet gases, one of them, 15a, being additionally supported by the annulus ,13 and serving to enclose the downstream ends of actuators, later described, and at the downstream ends of each strut is supported one part 16 of a two- part pivot bracket 16, 16a, shown in more .detail in Figure 4. The part 16, and the annulus 13 are provided with fingers 16b, 13a respectively, which are received in slots in the strut 14 and welded thereto. At the downstream ends of at least three of the bracket parts 16a are apertures 17 in which are fitted pins 18 in turn supporting a streamlined end casing 19.
The stationary annulus 13 supports a cylinder 20 in which is reciprocablea piston (not shown) connected to an actuator rod 22, this mechanism forming a hydraulic ram for actuating inner and outer flaps 23 and 24 respectively. Each actuator rod 22 (only one of which is shown,
although of course there isra hydraulic ram and actuator rod for each pair of flaps) extends through a strut and is connected by a joint 25 to a box-section ring 26 contained in the end casing 19, the ring 26 ensuring that the nrovements of all of the rods 22 will be synchronized.
.journalled through integral lugs 23a and 24a.
Integral with theactuator rod 22 is a block 33 (Figures 3 and 5) through which passes a pin 34 pivotally supporting one end of each of links 35 and 36, respectively. The other ends of the links 35 and 36 are pivoted to the downstream ends of the flaps 23 and 24'respectively by pins 37 and 38 respectively.
In the position shown in Figure 3 the flaps 23 and 24 are closed and the links 35 and 36 are at their deadcentre position. The links 35 and 36 are moved slightly further by the actuator rod 22 until they are over-centre (i. e., their common pivot pin 34 is downstream of the pins 37 and 38), the movement of links 35 and 36 being limited by the block 33 engaging the adjacent end of the bush in the bore 28. Thus, should the actuators fail, the danger of the flaps being forced open by the gaseous stream is reduced, since the links cannot be moved back over-centre by a force acting on the pins 37, 38. The internal surfaces of the flaps 23 and 24- are formed with internally projecting portions 39 which are recessed at 39:: to embrace the strut 14 when the flaps 'are in their closed position, the portions 39 being curved inwardly, so that in the open position of the flaps 23 and 24 they assist in providing a smooth change of direction of the flow of the gases. All the parts 16 are mounted in a curved annulus 39b for a similar purpose, the annulus additionally serving to shroud the brackets and pivots of the flaps 23 and 24.
To open the flaps 23 and 24 the hydraulic ram is actuated thereby causing the actuator rod 22 to move upstream, together with the box-section ring 26, carrying with it the block 33. This movement of the block 33 causes the links 35 and 36 to pass over their deadcentre position and to exert a force on the downstream ends of the flaps 23 and 24 causing them to pivot inwardly and outwardly respectively about their pivot pins 32.
The flaps 23 and 24 are arranged to overlap in their open positions as shown in Figure 6 and in their closed positions as shown in Figure 7.
To close the flaps 23 and 24 the hydraulic ram is actuated in the reverse direction, the final movement of the rod 22 causing the links 35 and 36 to pass over their dead centre. p
In the alternative embodiment shown in Figure 8 a rod 22a actuable by fluid pressure from a cylinder 20, is connected, through a ring 40 and pivot pin 41, to links 42 and 43 respectively. The link 42 is connected to an inner flap 44 between its ends by means of a pivot pin 45 and the link 43 is connected to an outer flap 46 between its ends by means of a pivot pin 47.
The downstream ends of the flaps 44 and 46 have a common pivot pin 48 which is carried by fixed struts 49 supported from the casings 11, 11a. 7
The struts 49 carry curved annuli 50 between the flap for guiding the diverted portion of the jet. In this embodiment there is no annular space between the nozzle and the casing.
As will be obvious, movement of the rod 22a from its position shown, in an upstream direction, will collapsethe links 42, 43, causing the flaps 44, 46 to move to their closed position.
What we claim as our invention and desire to secure by Letters Patent of the United States is: i
1. A means for slowing down an aircraft, particularly during landing, when powered by a jet engine, including a jet nozzle, and a plurality of pairs of oppositely opening flaps, each pair of flaps being pivotally mounted near their downstream ends downstream of and around the jet nozzle, adjacent ones of said flaps overlapping one another to provide, when opened, a complete annulus of generally V-section, one flange of said annulus extending well into the path of the jet gases and the other extending to outside the jet nozzle so as to change the direction of flow of a material part of the jet gases.
2. A means for slowing down an aircraft, particularly during landing, when powered by a jet engine, including a jet nozzle, a plurality of pair of oppositely opening flaps which are pivotally mounted near their downstream ends downstream of and around the jet nozzle, adjacent flaps overlapping to provide when open a complete annulus of generally V-shaped cross-section, said annulus having one flange extending well into the path of the jet gases and the other flange extending to outside the jet nozzle so as to change the direction of flow of a material part of the jet gases, and a number of fixed curved annuli downstream of the jet nozzle and disposed between the oppositely opening flaps, the internal and external flaps being provided with curved surfaces in order to coact With said curved annuli in guiding the diverted portion of the jet gases.
3. A means for slowing down an aircraft, according to claim 1, including a casing around and outside the jet nozzle, the upstream ends of the flaps being adapted when closed to abut the casing adjacent the trailing end of the jet nozzle.
4. Means for slowing down an aircraft, according to claim 1, including a casing outside the jet nozzle and separated therefrom by an annular space.
5. Means for slowing down an aircraft, according to claim 2, one of said curved annuli forming a wall at the downstream end of a cavity, actuators being provided for said flaps the actuators being disposed in said cavity.
6. Means for slowing down an aircraft, according to claim 1, including actuators for the flaps, one actuator being provided for each pair of flaps, and a single stationary annulus, outside the jet nozzle, which supports the actuators.
7. Means for slowing down an aircraft, according to claim 6 and comprising for each actuator a hydraulic ram supported by said stationary annulus, and for each hydraulic ram a rod which is movable in a direction substantially parallel to the longitudinal axis of the jet nozzle, a pair of links for each rod, each rod being connected near its downstream end to said pair of links, said links being connected to a pair of said flaps.
8. Means for slowing down an aircraft, according to claim 7, and including pins on which the pair of flaps are respectively pivoted, said pins being just upstream of where the links are connected to the flaps.
9. Means for slowing down an aircraft, according to claim 8, characterized in that the links are arranged to be over-centre in the closed position of the flaps so as to lock the flaps in the closed position.
Imbert Dec. 9, 1952 Robson et a1. May 5, 1953
US491122A 1954-03-01 1955-02-28 Means for slowing down an aircraft, particularly during landing, when powered by a turbo-jet Expired - Lifetime US2798362A (en)

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2919545A (en) * 1956-08-06 1960-01-05 Goodyear Aircraft Corp Thrust reverser nozzle
US2968921A (en) * 1957-12-23 1961-01-24 Ryan Aeronautical Co Aerodynamic jet deflecting nozzle
US2979893A (en) * 1958-04-02 1961-04-18 United Aircraft Corp Thrust reverser
US3172256A (en) * 1961-02-13 1965-03-09 Rolls Royce Jet engine thrust reversers
DE1285328B (en) * 1965-06-07 1968-12-12 Gen Electric Jet engine with jet deflection
US3475913A (en) * 1966-06-29 1969-11-04 Rolls Royce Fluid flow reversers
FR2354453A1 (en) * 1976-06-08 1978-01-06 Short Brothers & Harland Ltd GAS TURBINE ENGINE EQUIPPED WITH A THRUST INVERTER DEVICE
US4073440A (en) * 1976-04-29 1978-02-14 The Boeing Company Combination primary and fan air thrust reversal control systems for long duct fan jet engines
US5782434A (en) * 1996-02-15 1998-07-21 Societe Hispano Suiza Self-closing pivoting door thrust reverser with gear actuated panel
FR2887225A1 (en) * 2005-06-21 2006-12-22 Airbus France Sas Double flow nacelle for aircraft, has thrust reversers, each with outer and inner doors respectively opened in directions of nacelle exterior and inner volume of inner cowl so that displacements for opening doors are in opposite direction
EP2573375A3 (en) * 2011-09-20 2014-04-30 United Technologies Corporation Thrust reverser for the fan of a gas turbine engine
US20180002029A1 (en) * 2016-07-01 2018-01-04 Airbus (S.A.S.) Support device for actuator, air intake system and aircraft

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2620623A (en) * 1946-02-07 1952-12-09 Rateau Soc Fluid directing device for reaction jet nozzle
US2637164A (en) * 1945-03-22 1953-05-05 Power Jets Res & Dev Ltd Jet spoiling means for aircraft gas turbines

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2637164A (en) * 1945-03-22 1953-05-05 Power Jets Res & Dev Ltd Jet spoiling means for aircraft gas turbines
US2620623A (en) * 1946-02-07 1952-12-09 Rateau Soc Fluid directing device for reaction jet nozzle

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2919545A (en) * 1956-08-06 1960-01-05 Goodyear Aircraft Corp Thrust reverser nozzle
US2968921A (en) * 1957-12-23 1961-01-24 Ryan Aeronautical Co Aerodynamic jet deflecting nozzle
US2979893A (en) * 1958-04-02 1961-04-18 United Aircraft Corp Thrust reverser
US3172256A (en) * 1961-02-13 1965-03-09 Rolls Royce Jet engine thrust reversers
DE1285328B (en) * 1965-06-07 1968-12-12 Gen Electric Jet engine with jet deflection
US3483702A (en) * 1966-06-29 1969-12-16 Rolls Royce Fan thrust reverser for a jet propulsion plant
US3475913A (en) * 1966-06-29 1969-11-04 Rolls Royce Fluid flow reversers
US4073440A (en) * 1976-04-29 1978-02-14 The Boeing Company Combination primary and fan air thrust reversal control systems for long duct fan jet engines
FR2354453A1 (en) * 1976-06-08 1978-01-06 Short Brothers & Harland Ltd GAS TURBINE ENGINE EQUIPPED WITH A THRUST INVERTER DEVICE
US5782434A (en) * 1996-02-15 1998-07-21 Societe Hispano Suiza Self-closing pivoting door thrust reverser with gear actuated panel
FR2887225A1 (en) * 2005-06-21 2006-12-22 Airbus France Sas Double flow nacelle for aircraft, has thrust reversers, each with outer and inner doors respectively opened in directions of nacelle exterior and inner volume of inner cowl so that displacements for opening doors are in opposite direction
EP2573375A3 (en) * 2011-09-20 2014-04-30 United Technologies Corporation Thrust reverser for the fan of a gas turbine engine
US9181898B2 (en) * 2011-09-20 2015-11-10 United Technologies Corporation Thrust reverser for a gas turbine engine with moveable doors
US20180002029A1 (en) * 2016-07-01 2018-01-04 Airbus (S.A.S.) Support device for actuator, air intake system and aircraft
US10814997B2 (en) * 2016-07-01 2020-10-27 Airbus (S.A.S.) Support device for actuator, air intake system and aircraft

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