US20110014044A1 - Locking system for air intake structure for turbojet engine nacelle - Google Patents

Locking system for air intake structure for turbojet engine nacelle Download PDF

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Publication number
US20110014044A1
US20110014044A1 US12/865,842 US86584208A US2011014044A1 US 20110014044 A1 US20110014044 A1 US 20110014044A1 US 86584208 A US86584208 A US 86584208A US 2011014044 A1 US2011014044 A1 US 2011014044A1
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US
United States
Prior art keywords
air intake
nacelle according
nacelle
inner panel
locking
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US12/865,842
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English (en)
Inventor
Guy Bernard Vauchel
Jean-Philippe Dauguet
Stephane Beilliard
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Nacelles SAS
Original Assignee
Aircelle SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aircelle SA filed Critical Aircelle SA
Assigned to AIRCELLE reassignment AIRCELLE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BEILLIARD, STEPHANE, DAUGUET, JEAN-PHILIPPE, VAUCHEL, GUY BERNARD
Publication of US20110014044A1 publication Critical patent/US20110014044A1/en
Abandoned legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/08—Inspection panels for power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines

Definitions

  • the present invention concerns a locking device for a translatable air intake structure equipping a turbojet engine nacelle.
  • An airplane is propelled by one or several propeller assemblies comprising a turbojet engine housed in a tubular nacelle.
  • Each propeller assembly is attached to the airplane by a mast situated generally under a wing or at the fuselage.
  • a nacelle generally has a structure comprising an air intake upstream from the engine, a middle section designed to surround a fan of the turbojet engine, and a downstream section intended to surround the combustion chamber of the turbojet engine and housing thrust reverser means.
  • the air intake comprises, on one hand, an intake lip adapted to allow optimal collection toward the turbojet engine of the air necessary to supply the fan and the internal compressors of the turbojet engine, and on the other hand, a downstream structure on which the lip is attached and designed to suitably channel the air toward the blades of the fan, said downstream structure comprising an outer shroud and an inner acoustic panel.
  • the assembly is attached upstream from a case of the fan belonging to the middle section of the nacelle.
  • the middle structure surrounds the fan and generally breaks down into an inner wall forming said fan case and an outer wall assuming the form of removable cowls mounted pivotably around a longitudinal axle forming a hinge in the upper portion (at 12:00) of the nacelle in order to allow access to the inside of the nacelle.
  • This solution consists of integrating the air intake lip into the outer shroud, including all or part of the cowl there surrounding the fan case so as to form a single-piece structure.
  • the whole of the wall thus formed is mounted mobile in translation.
  • the inner edge of the air intake lip comes, when said translatable structure is in closed position, into contact with a zone upstream from an inner wall of the air intake structure, inner wall generally realized in the form of an acoustic panel.
  • the translatable structure is guided and maintained on a fixed structure, comprising the inner wall of the air intake structure, by a plurality of rails.
  • the interface is made sealed by a joint system and is reinforced by a system of centering pins arranged on the periphery of the air intake lip/acoustic shroud junction and making it possible to improve its resistance to radial movements.
  • the maintenance of the mobile structure along longitudinal directions is done primarily by bolting the mobile structure on a fixed structure in a zone close to an installation interface of the acoustic shroud on the fan case.
  • the interface between the air intake lip and the inner acoustic panel is of particular importance, because said interface must penalize the internal aerodynamic continuity of the nacelle as little as possible and avoid any deformation of the interface as much as possible during load stresses undergone by the air intake or the inner acoustic panel.
  • a manual locking system comprising a system for gripping the mobile structure by the handle at the end of maneuver of the structure. This technique makes it possible to avoid a long and tedious assembly/disassembly with a system of maintenance by bolting.
  • a system is not suited to motorized driving of the mobile structure since the manual drive system and the locking are coupled.
  • adjusting the prestressing of the bolts is also long and tedious.
  • the present invention concerns a nacelle for a turbojet engine comprising an air intake structure capable of directing an air flow towards a fan of the turbojet engine and a middle structure for surrounding said fan and to which the air intake structure is attached in order to provide aerodynamic continuity
  • the air intake structure comprising, on one hand, at least one inner panel attached to the middle structure and defining, with the latter, a nacelle fixed structure and, on the other hand, at least one longitudinal outer panel removably attached to the fixed structure and including an air intake lip in order to define a removable air intake structure, characterized in that the removable air intake structure is provided with peripheral locking means including at least one electric lock attached to the inner panel or to the air intake lip and each capable of interaction with a complementary retaining means attached to the air intake lip or to the inner panel, respectively.
  • the locking means comprises a hook.
  • the hook is a hook with three-point projection system.
  • the hook is a rotating hook.
  • the complementary retaining means is a yoke. Also preferably, the complementary retaining means assumes the form of a return presented by one end of the air intake lip or of the inner panel.
  • the inner panel or the air intake lip comprises at least one centering pin capable of cooperating with a corresponding bore of the air intake lip or of the inner panel, respectively.
  • the centering pin is mounted rotatingly mobile and has a first end in the form of a cam capable of passing alternatingly between an unlocking position in which the cam-type end can be removed from the complementary retaining means and a locking position in which the cam-type end abuts against the complementary retaining means and cannot be removed from it.
  • the centering pin is mounted rotatingly mobile and has an outer thread capable of cooperating with an inner tapping of the corresponding bore.
  • the tapped bore comprises a ball bearing system.
  • the centering pin has a transverse bore capable of forming a complementary retaining means.
  • the locking means is an electric locking means capable of being remotely controlled.
  • the locking means is a manual locking means capable of being remotely controlled by a manual drive means of the cable type or cardan mechanical return type.
  • control means of the locking means are centralized.
  • control member is a handle, preferably retractable, capable of allowing the driving of the air intake structure in motion.
  • the electric bolt(s) is/are associated with at least one means for detecting the locking and/or unlocking position.
  • the prestressing of the locking means is adjustable.
  • FIG. 1 is a partial diagrammatic illustration of an air intake structure of a nacelle according to the invention, the air intake structure being in the closing position.
  • FIG. 2 is a partial diagrammatic illustration of the air intake structure of FIG. 1 , the air intake structure being in the opening position.
  • FIG. 3 is an enlarged diagrammatic illustration of a three-point bolt in the locking position.
  • FIG. 4 is an enlarged diagrammatic illustration of the bolt of FIG. 3 in the opening position.
  • FIG. 5 is a diagrammatic illustration of a locking method by rotating hook, said hook being in the opening position.
  • FIG. 6 is an illustration of the rotating hook of FIG. 5 in the locking position.
  • FIG. 7 is an illustration of a locking mode by rotating pin having an end forming a cam, said pin being in the unlocking position.
  • FIG. 8 is an illustration of the pin of FIG. 7 in the locking position.
  • FIGS. 9 and 10 show a locking mode via threaded rotating pin.
  • FIGS. 10 to 14 show two locking modes by hooking of a centering pin, by a beveled hook, respectively, and a hook having a cavity corresponding to the pin.
  • a nacelle according to the invention as partially illustrated in FIGS. 1 and 2 constitutes a tubular housing for a turbojet engine (not shown) for which it serves to direct the air flows it generates by defining inner and outer aerodynamic lines necessary to obtain optimal performance. It also houses different components necessary to the operation of the turbojet engine as well as related systems such as a thrust reverser.
  • the nacelle is intended to be attached to a fixed structure of an airplane, such as a wing, via a pylon.
  • the nacelle has a structure comprising a front section forming an air intake 2 , a middle section 3 (partially visible) comprising a case 3 a surrounding a fan (not visible) of the turbojet engine, and a rear section (not visible) surrounding the turbojet engine and able to house a thrust reverser system (not shown).
  • the air intake 2 is divided into two zones, i.e. on one hand, an intake lip 2 a adapted to allow optimal collection toward the turbojet engine of the air necessary to supply the fan and inner compressors of the turbojet engine, and on the other hand, a downstream structure 2 b comprising an outer panel 20 and an inner panel 21 , generally acoustic.
  • the lip 2 a is integrated into the outer panel 20 so as to form a single disassemblable piece, the inner panel 21 being attached upstream from the case 3 a of the fan belonging to the middle section 3 of the nacelle via fastening flanges 4 , integral with an inner panel 21 and the case 3 a , respectively.
  • the air intake structure 2 can be modular and comprise a plurality of outer panels 20 each defining a corresponding air intake lip portion 2 a.
  • the inner panel 21 is made from an acoustic shroud and is connected via flanges 4 to the case 3 a of the middle section 3 .
  • This inner panel 21 therefore constitutes a fixed part of the air intake structure 2 on which the outer panel 20 , integrating the air intake lip 2 a , is designed to be removably attached and fixed.
  • outer panel 20 can also comprise all or part of an outer panel of the middle structure.
  • each flange 4 can support a radial peripheral partition 5 .
  • This partition 5 can support center finders and secondary center finders extending perpendicularly to said partition 5 toward the upstream of the nacelle.
  • the air intake structure 2 can extend axially via its outer panel 20 beyond a valve guide plate of an inner plate 21 to the fixed structure of the nacelle 1 to be close to an outer structure of a thrust reverser structure belonging to the downstream section of the nacelle and possibly to cover the cowls.
  • a system of bolts can then be provided to maintain the air intake structure on the partition 5 integral with the structure of the case or a structure upstream from the downstream structure.
  • the radial peripheral partition 5 can be supported directly by the very structure of the fan case in order to provide a maximum inner envelope for the air intake 2 .
  • the outer panel 20 integrating the air intake lip 2 a therefore forms, according to the prior art, a removable portion designed to be attached on the fixed portion and more particularly on the peripheral partition 5 .
  • Inner reinforcements of the existing inner and outer panels are not shown and depend on the stiffness desired by the person skilled in the art.
  • the removable structure can be mounted, for example, on a rail/guideway sliding system comprising a plurality of rails/guideways distributed on the periphery of the air intake structure 2 and/or the case 3 a.
  • the removable structure is maintained at the junction between the air intake lip using discrete locking means comprising at least one hook 10 , in this case mounted on the inner panel 21 , capable of cooperating with a complementary retaining means 11 of the yoke type, itself attached to the air intake lip 2 a.
  • FIGS. 1 and 2 show the removable structure in the closed and open positions, respectively.
  • FIGS. 3 and 4 are an enlarged view of the locking hook 10 cooperating with the yoke 11 . It will be noted that the interface between the air intake lip 2 a and the inner panel 21 is completed by centering pins 12 , arranged essentially at each hook 10 and supported by a peripheral return 15 of the inner panel 21 , each cooperating with a corresponding bore 13 arranged in a return 14 of the air intake lip.
  • the described example uses a hook 10 with three-point locking system.
  • a locking system is known in particular from document FR 2 857 400.
  • the lower shape of the hook 10 serves as a release ramp of the yoke 11 during the unlocking maneuver.
  • the proper release of the hook 10 relative to the yoke 11 is ensured through the shape given to the hook 10 in contact with a fixed axis of rotation of a rod of the three-point system.
  • the projection of the three-point system makes it possible to ensure the security of the locking and be assured of the latter in all flight cases and in case of break of the drive system of the locking rods.
  • the hook 10 and the three-point locking system are actuated by an electric motor 30 .
  • the locking and unlocking controls for the electric locking means are grouped together at an external control means of the nacelle and/or at the cockpit of the airplane.
  • the retaining means 11 are positioned on the air intake lip 2 a of the nacelle in a zone guaranteeing the best structural rigidity in order to avoid any deflection of that interface.
  • FIGS. 5 and 6 present a second embodiment of the locking comprising a rotating hook 40 driven by an electric motor 41 capable of engaging with the return 15 of the inner panel 21 , which then serves as complementary retaining means.
  • the centering pins can also be used directly in the locking means.
  • FIGS. 7 and 8 show a third embodiment in which the centering pin 50 is passed through by a blocking cam 52 capable of being driven in rotation by an electric motor 51 supported by the return 14 of the air intake structure 2 a.
  • the pin 50 is capable of cooperating with a bore 54 formed in the return 15 of the inner panel 21 .
  • the return 21 also supports retaining means 55 of the cam 52 designed such that said cam 52 has an unblocking position in which it can be removed from the retaining means 55 through the bore 54 and a blocking position in which it abuts against the retaining means 55 , which then prevent its removal.
  • the cam 52 can be an integral part of the pin 50 , which is then itself driven in rotation.
  • the pin shall, however, be kept fixed in rotation.
  • FIGS. 9 and 10 present a screw locking system.
  • the return 15 of the inner panel 21 supports a threaded centering pin 60 capable of being driven in rotation by an electric motor 61 .
  • the centering pin 60 is capable of cooperating with a tapped bore 62 supported by the return 14 of the air intake lip 2 a .
  • the rotation can be improved by the presence of ball bearings 63 .
  • FIGS. 11 to 14 illustrate a locking mode by wedging.
  • FIGS. 11 and 12 show a locking mode by wedging with beveled cam.
  • the inner panel 21 supports a hook 70 capable of being actuated essentially perpendicularly to the inner panel 21 by an electric motor 71 .
  • the hook 70 is actuated in the direction of the inner panel 21 , it is intended to penetrate a bore 72 arranged in a centering pin 73 when the latter has been inserted through a corresponding bore 74 of the air intake structure 2 a.
  • the beveled form of the hook 70 allows adjustment of the prestressing of the locking system depending on the penetration depth of the hook 70 .
  • FIGS. 13 and 14 illustrate a locking system by wedging and rectilinear retraction of the pin or cam.
  • the inner panel 21 supports a straight hook 80 capable of being actuated essentially perpendicularly to the inner panel 21 by an electric motor 81 .
  • the hook 80 When the hook 80 is actuated towards the inner panel 21 , it is intended to penetrate the bore 72 formed in the centering pin 73 when the latter has been inserted through a corresponding bore 74 of the air intake structure 2 a.
  • a cavity 82 can be formed near one end of the hook 80 .
  • the pin 73 will then be maneuvered first so as to release the cavity 82 and allow the distancing of the hook 80 .
  • the prestressing stress is done by the pin 73 during the closing of the system.
  • All of the locking systems described in this application may include means for signaling the locking and/or unlocking position, the information from which may be escalated to the cockpit, for example.
  • the signaling means could be positioned relative to an active locking element guaranteeing an “all or nothing” signal.
  • the signaling means is preferably placed on the inner panel 21 constituting a fixed portion of the nacelle in order to reduce the disconnection interfaces, which is one of the factors reducing the reliability of the system.
  • the prestressing of the described locking systems can also be adjusted.
  • the adjustment of the prestressing may be done by fastening of the locking means on an adjustable platen (for example by screw) allowing a slight translation along the inner panel 21 .
  • the adjustment of the yoke 11 may be done in the same way.
  • the adjustment of the prestressing may be done by adjusting the position of the bolt by wedging of the housing of the motor 41 or by action on an axis of the hook 40 .
  • the electric and/or manual control means of the locking means may be centralized, said control being able to be, for example, situated inside the middle structure and accessible after opening of an outer panel of that structure, or apparent to the structure and directly accessible from the outside of the nacelle.
  • control can, for example, assume the form of an appendix not aerodynamically protected, or be protected by a hatch or a switchbox allowing outer aerodynamic smoothing.
  • each bolt should be accessed individually by a dedicated access hatch. These hatches would then generate significant aerodynamic disturbances in addition to being heavy, costly and disrupting the structural integrity of the outer structure.
  • Each electric motor can then advantageously be equipped with a manual drive unit (MDU) capable of being actuated by a mechanical drive system with centralized manual control.
  • MDU manual drive unit
  • a mechanical inhibition system of the locking means preferably visible from the outside.
  • Such a mechanical inhibition may assume the form of a locking lug having an appendage introduced into the manual drive member and capable of blocking the latter.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US12/865,842 2008-02-01 2008-11-21 Locking system for air intake structure for turbojet engine nacelle Abandoned US20110014044A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0800560A FR2927061B1 (fr) 2008-02-01 2008-02-01 Systeme de verrouillage pour structure d'entree d'air d'une nacelle de turboreacteur
FR08/00560 2008-02-01
PCT/FR2008/001631 WO2009101273A1 (fr) 2008-02-01 2008-11-21 Système de verrouillage pour structure d'entrée d'air d'une nacelle de turboréacteur

Publications (1)

Publication Number Publication Date
US20110014044A1 true US20110014044A1 (en) 2011-01-20

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ID=39731653

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/865,842 Abandoned US20110014044A1 (en) 2008-02-01 2008-11-21 Locking system for air intake structure for turbojet engine nacelle

Country Status (8)

Country Link
US (1) US20110014044A1 (fr)
EP (1) EP2252511A1 (fr)
CN (1) CN101925515A (fr)
BR (1) BRPI0821929A2 (fr)
CA (1) CA2711830A1 (fr)
FR (1) FR2927061B1 (fr)
RU (1) RU2500586C2 (fr)
WO (1) WO2009101273A1 (fr)

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US20110308634A1 (en) * 2009-02-24 2011-12-22 Snecma Turbojet nacelle having a removable air intake structure
US20140133977A1 (en) * 2011-07-25 2014-05-15 Aircelle Device for connecting a front frame to a fan casing
US20160053719A1 (en) * 2014-08-22 2016-02-25 Rohr, Inc. Automatic deflection limiting latches for a thrust reverser
US20160281539A1 (en) * 2015-03-29 2016-09-29 Rohr, Inc. Inner fixed structure leading edge latch
US9702375B2 (en) 2013-07-16 2017-07-11 United Technologies Corporation Liner attaching scheme
US9719421B2 (en) 2011-06-01 2017-08-01 Rolls-Royce Deutschland Ltd & Co Kg Gas-turbine engine with telescope-type air inlet of the engine cowling (nacelle)
US20170283081A1 (en) * 2016-04-05 2017-10-05 Rohr, Inc. Securing a translating fanlet for an aircraft propulsion system nacelle
EP3323710A1 (fr) * 2016-11-18 2018-05-23 Rohr, Inc. Alignement autobloquant pour une nacelle
US20180201385A1 (en) * 2014-04-25 2018-07-19 Rohr, Inc. Latch hooks, latch housings, and latch assemblies
US10543927B2 (en) * 2016-11-18 2020-01-28 Rohr, Inc. Lockable track system for a translating nacelle structure
WO2020072365A1 (fr) * 2018-10-02 2020-04-09 Woodward, Inc. Verrou tertiaire
WO2020216713A1 (fr) * 2019-04-26 2020-10-29 Safran Nacelles Entrée d'air de nacelle de turboréacteur
EP3733525A1 (fr) * 2019-04-29 2020-11-04 Rohr, Inc. Dispositifs de retenue de fixation de capot de ventilateur
US20210262384A1 (en) * 2014-08-19 2021-08-26 Pratt & Whitney Canada Corp. Variable geometry inlet system
US11247781B2 (en) * 2018-09-04 2022-02-15 Airbus Operations Sas Aircraft turbine engine assembly comprising a hinged cover
US11414200B2 (en) * 2019-04-29 2022-08-16 Rohr, Inc. Fan cowl securement retainers
US11441482B2 (en) * 2019-06-04 2022-09-13 Rohr, Inc. Single track translating inlet
US11525372B2 (en) * 2018-03-27 2022-12-13 Rohr, Inc. Diaphragm latch
US11591098B2 (en) * 2017-12-21 2023-02-28 Airbus Operations S.A.S. Nacelle forward part of a propulsion assembly comprising an inclined stiffening frame
US20230349323A1 (en) * 2019-10-15 2023-11-02 Institut Superieur De L Aeronautique Et De L Espace Assembly for a turbomachine

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US8181905B2 (en) * 2008-12-17 2012-05-22 Rohr, Inc. Aircraft engine nacelle with translating inlet cowl
FR3020040B1 (fr) * 2014-04-17 2018-06-29 Societe Lorraine De Construction Aeronautique Ensemble propulsif pour aeronef
FR3031341B1 (fr) * 2015-01-07 2017-07-14 Aircelle Sa Ensemble propulsif pour aeronef
FR3052809B1 (fr) * 2016-06-17 2019-05-03 Safran Nacelles Systeme de guidage axial pour des capots d'inverseur de poussee comprenant un doigt de securite
CN107985599A (zh) * 2017-12-27 2018-05-04 天机智汇科技（深圳）有限公司 自动载货装置、无人机及载货舱

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US1488393A (en) * 1923-03-31 1924-03-25 Fred W Jackson Plug retainer
US2284180A (en) * 1938-04-27 1942-05-26 Havilland Aireraft Company Ltd Securing device, particularly for such parts as aircraft cowlings and the like
US2919569A (en) * 1955-03-30 1960-01-05 Gen Dynamics Corp Fastening device having a rotatable latch
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CA2711830A1 (fr) 2009-08-20
FR2927061A1 (fr) 2009-08-07
CN101925515A (zh) 2010-12-22
RU2500586C2 (ru) 2013-12-10
BRPI0821929A2 (pt) 2015-06-16
WO2009101273A1 (fr) 2009-08-20
FR2927061B1 (fr) 2010-02-12
EP2252511A1 (fr) 2010-11-24
RU2010135894A (ru) 2012-03-10

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