CN1931666A - Reverse thrust device including locking mechanism and producing method thereof - Google Patents
Reverse thrust device including locking mechanism and producing method thereof Download PDFInfo
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- CN1931666A CN1931666A CN 200510124934 CN200510124934A CN1931666A CN 1931666 A CN1931666 A CN 1931666A CN 200510124934 CN200510124934 CN 200510124934 CN 200510124934 A CN200510124934 A CN 200510124934A CN 1931666 A CN1931666 A CN 1931666A
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Abstract
The present invention discloses one kind of reverse thrust device with locking mechanism and its manufacture process. One embodiment of the flyer system includes one reverse thrust device with one first inner plate and one opposite second inner plate, each of which has an inner surface and an upper part. The system includes also one lock catch protuberant upwards from the upper part and the inner surface of the first inner plate, and one latch protuberant upwards from the upper part and the inner surface of the second inner plate. The latch is so located that it may interlock optionally with the lock catch to arrest the relative move between the first inner plate and the second inner plate.
Description
Technical field
The present invention relates to the method that has the thrust reverser of lockout mechanism and make this thrust reverser.
Background technology
Air injection aerial vehicle comprises and is used to hold driving engine and driving engine is connected to engine nacelle on the wing.The profile of this engine nacelle generally is designed to reduce aerodynamic drag during aircraft flight.Traditional engine nacelle comprises a pair of thrust reverser fairing, has constituted a pincer (clam-shaped) structure that covers on the aircraft engine periphery.During aircraft flight, this thrust reverser fairing must be able to bear by sizable annular load that jet-stream wind produced of flowing through in it.
Traditional thrust reverser fairing is rotatably connected at the top and a hanger of engine nacelle.Therefore thereby this thrust reverser fairing can upwards rotate and can safeguard or repair driving engine.During aircraft flight, this thrust reverser fairing is in closure state, and its end is pressed close to mutually in the bottom of nacelle.The end of this thrust reverser fairing can comprise a lockout mechanism, at the driving engine run duration this fairing is pinned.
A shortcoming of traditional thrust reverser fairing is its inwall insufficient rigidity and can't avoid producing bigger flexure deformation when being used for high trust engine.For example, under the situation of aborting, a high trust engine applies an increased load on the baffling door of this thrust reverser, and this can cause the flexure deformation of inwall.The remarkable distortion of thrust reverser inwall can change the loading transfer path between driving engine and the thrust reverser, and this will damage driving engine and thrust reverser parts.Since the space constraint in some concrete application, and impassabitity increases the problem that the thickness of inwall is eliminated remarkable distortion.Therefore, there are the needs that increase thrust reverser inwall rigidity.
Summary of the invention
Several aspects of the present invention content is directly about thrust reverser that has lockout mechanism and the method for making this thrust reverser.Aerocraft system according to an embodiment comprises a thrust reverser, and it has first inner panel and second inner panel relative with this first inner panel.This first and second inner panel has an inside face and a top.This system also comprises snap close inwardly outstanding on the top of first inner panel and the inside face; With door bolt inwardly outstanding on the top of this second inner panel and inside face.This door bolt is oriented to optionally and the snap close interlocking, to stop relatively moving between first inner panel and second inner panel.
In another embodiment, an aerocraft system comprises a strut member and a thrust reverser, and this thrust reverser comprises first inner panel and second inner panel relative with this first inner panel.This first and second inner panel respectively has an inside face and and is pivotally attached to top on the strut member.This system also comprise one from the inside face on this first inner panel top inwardly outstanding snap close and from the inside face on this second inner panel top inwardly outstanding door bolt.This snap close has an opening, this door bolt comprises a fastener, its can (a) this fastener be contained at least in part in the latch openings with stop latched position that first and second inner panels rotate relative to strut member and (b) this fastener between the releasing position outside the latch openings, move.
In another embodiment, an aerocraft system comprises the thrust reverser with first inner panel and second inner panel, and first inner panel and second inner panel can move between open position and make position.This first and second inner panel has an inside face and a front portion.This system also comprise one from the inside face of the front portion of this first inner panel inwardly outstanding snap close; Fasten with a bolt or latch to the indirect actuating of inner process from the inside face of the second interior prelaminar part with one.This door bolt have (a) optionally with latch engagement first and second inner panels are remained on fastener and (b) actuator that drives this fastener on the make position.
Another aspect of the present invention content is about making the method for thrust reverser on the aircraft.This thrust reverser has first and second inner panels.In one embodiment, a kind of method comprises a snap close is connected on the inside face on the first inner panel top; With door bolt is connected on the inside face on the second inner panel top, thereby this door bolt is positioned to optionally and the snap close interlocking, to stop moving mutually between first and second inner panels.
Description of drawings
Fig. 1 is according to an embodiment of the invention, has a schematic perspective view of the aircraft of a plurality of power plants;
Fig. 2 is the front schematic view of several assemblies of thrust reverser according to an embodiment of the invention;
Fig. 3 is roughly along Fig. 2 line A-A place schematic side view;
Fig. 4 is the amplification schematic perspective view of snap close according to an embodiment of the invention;
Fig. 5 be fasten with a bolt or latch according to an embodiment of the invention and Fig. 4 in the enlarged diagram of snap close;
Fig. 6 is the door bolt of Fig. 5 when door bolt is in the releasing position and the schematic top plan view of snap close;
Fig. 7 is the door bolt of Fig. 5 when door bolt is in latched position and the schematic top plan view of snap close;
Fig. 8 is the section front elevational schematic of a thrust reverser part according to another embodiment of the present invention;
Fig. 9 is the section front elevational schematic of a thrust reverser part according to another embodiment of the present invention;
The specific embodiment
Hereinafter disclosure has been described thrust reverser that has lockout mechanism and the method for making this thrust reverser.Detail illustrate hereinafter and accompanying drawing 1-9 in illustrate, thereby can comprehensively understand the embodiments of the present invention.The known configurations that other is relevant with thrust reverser usually and the detail of system have not just been set forth in the explanation hereinafter, to avoid producing unnecessary confusion in the process of describing various embodiments of the present invention.
Various parts, size, angle and the further feature that shows in the accompanying drawings only is casehistory specific embodiment of the present invention.Therefore, other embodiment with other part, size and/or feature does not exceed aim of the present invention and protection domain yet.In addition, other embodiments of the invention can not have following some details and realize that perhaps the various aspects of any described embodiment can be combined into different combinations.
A. the embodiment that has the thrust reverser of lockout mechanism
Fig. 1 is the schematic perspective view of aircraft 100, and aircraft has a plurality of power plants according to an embodiment of the invention 110.This aircraft 100 also comprises fuselage 102, a plurality of wing 104 that links to each other with fuselage 102 and the afterbody 106 that links to each other with fuselage 102.In the illustrated embodiment, power plant 110 is installed on the corresponding wing 104; Yet in other embodiments, power plant 110 can be connected on fuselage 102 and/or the afterbody 106.Each power plant 110 comprises jet engine 112 and thrust reverser 114 respectively.
Fig. 2 is the front schematic view of several assemblies of thrust reverser 114 according to an embodiment of the invention.Diagram thrust reverser 114 comprises the first inner panel 120a, second inner panel 120b, the snap close 140 that with first wallboard 120a link to each other and the door bolt 160 that with second wallboard 120b link to each other relative with the first inner panel 120a.Door bolt 160 can be optionally and snap close 140 interlockings, thereby can (a) prevent relatively moving of the first and second inner panel 120a-b, (b) increases by the rigidity of the first and second wallboard 120a-b at run duration.This thrust reverser 114 also can have one and can move at run duration and turn to the spout (not shown) with the deflection air-flow.Alternatively, this thrust reverser 114 can have other configuration.
Each first and second inner panel 120a-b comprises top 122a-b, bottom 124a-b and the arcuate section 126a-b between top 122a-b and bottom 124a-b.The arcuate section 126a-b of the first and second wallboard 120a-b has formed the engine air flow that is in operation and has passed wherein tube (barrel).Each first and second inner panel 120a-b also comprise inside face 128a-b, with inside face 128a-b opposed outer surface 130a-b, leading edge 132a-b and the trailing edge (not shown) relative with leading edge 132a-b.In the one side content of illustrated embodiment, the spaced apart clearance G 1 of the top 122a-b of the first and second inner panel 120a-b, and be pivotally attached on a hanger 116 (schematically showing) or other support component.Like this, the first inner panel 120a can rotate to the open position (not shown) from make position (shown in Figure 2) around the first fulcrum X1 on direction P1, and the second inner panel 120b can rotate to the open position (not shown) from make position (shown in Figure 2) around the second fulcrum X2 on direction P2.This first and second inner panel 120a-b is closed during aircraft flight, can open when safeguarding or fixing over an engine.Although in the illustrated embodiment, the first and second inner panel 120a-b are sound absorption walls, and in certain embodiments, wallboard 120a-b can be other structural constituent that is used for other purpose.
Fig. 3 is roughly along the side schematic view of Fig. 2 line A-A.Diagram thrust reverser 114 also comprises binary pair 194 that is connected in the second inner panel 120b bottom 124b and the embedding cable 198 that extends between binary pair 194 and door bolt 160.Binary pair 194 can comprise that one is connected to the handle 196 on the cable 198, is used for optionally pushing away and/or draws cable 198 with indirect actuating door bolt 160.The second inner panel 120b can comprise an access door (not shown) between binary pair 194 and outside face 130b (Fig. 2), thereby the staff can overhaul binary pair 194.In other embodiments, thrust reverser 114 can comprise electrically operated, hydraulic pressure and/or other system that is fit to substitutes cable 198 and binary pair 194 or together make with cable 198 and binary pair 194 and to be used for activating indirectly fastening 160 with a bolt or latch.In addition, in several embodiment, binary pair 194 can be connected on other position, and/or to fasten 160 with a bolt or latch can not be a door bolt that indirectly activates.
Fig. 4 is the amplification schematic perspective view of snap close 140 according to an embodiment of the invention.Diagram snap close 140 comprises the base portion 141 that is connected to the first inner panel 120a inside face 128a, from the outstanding first element 142a of base portion 141 with from the second outstanding element 142b of base portion 141.This first element 142a and the second element 142b almost parallel, and the spaced apart clearance G 2 of the first and second element 142a-b.The first element 142a comprises the first hole 144a, and the second element 142b comprises from the second hole 144b of the first hole 144a biased downward.More particularly, the first end 146a of the first hole 144a is above the first end 146b of the second hole 144b, and the second end 148a of the first hole 144a is above the second end 148b of the second hole 144b.The first and second hole 144a-b be oriented to make door bolt 160 fastener (it being made an explanation) below with reference to Fig. 5 can (a) fastener be contained among the 144a-b of hole latched position and (b) fastener be between the releasing position outside the 144a-b of hole and rotate.In other embodiments, snap close 140 can have other structure.For example, snap close 140 can include only the first element 142a, and/or hole 144a-b can be slit or other opening.
Fig. 5 is the snap close 140 of Fig. 2 and fastens 160 enlarged diagram with a bolt or latch.Diagram door bolt 160 comprises driver train 162 and the fastener 180 that links to each other with driver train 162.When staff's actuating trigger 194 (Fig. 3), driver train 162 makes fastener 180 rotate between releasing position (shown in Figure 5) and latched position (shown in Figure 7) around axis B-B.Particularly, the driver train 162 that illustrates comprises a gear that has tooth 163 (among the figure shown in the dotted line), its be constituted as with cable 198 on respective teeth 199 (among the figure shown in the dotted line) engagement, thereby move can driver train 162 for the linearity of cable 198, this mechanism is rotational engagement part 180 subsequently.The driver train that is fit to can comprise the Part No.7-45880-1 by the TriumphControls Incorporated of North Wales manufacturing of Pennsylvania.In a further embodiment, those 8 and 9 embodiment that are described with reference to the accompanying drawings for example, driver train 162 can have other structure, with mobile fastener 180 optionally.
Fig. 6 is the schematic top plan view of snap close 140 and the door bolt 160 of Fig. 5.On the releasing position, the head 186 of fastener 180 is in first element 142a of snap close 140 and the clearance G between the second element 142b
2In, thereby the first and second end 188a and 188b (Fig. 4) are in outside the first and second hole 144a-b.When snap close 160 was in the releasing position, the first and second inner panel 120a-b can relatively move and turn to open position, thereby made the staff can be near driving engine and/or thrust reverser with place under repair or maintenance.
Fig. 7 be door bolt 160 when being in latched position snap close 140 and fasten 160 schematic top plan view with a bolt or latch.In response to staff's input (for example, driving handle 196 (Fig. 3)), driver train 162 makes fastener 180 rotate about 90 degree around axis B-B from the releasing position to latched position.On latched position, first end 188a is contained among the first hole 144a of snap close 140, and the second end 188b is contained among the second hole 142b of snap close 140.Door bolt 160 that pins and snap close 140 can stop the first and second wallboard 120a-b to relatively move and turn on the open position like this, mutually.
The feature of thrust reverser 114 embodiment shown in Fig. 2-7 is the snap close 140 of pinning mutually and the rigidity that door bolt 160 has increased by the first and second wallboard 120a-b.The benefit of this feature is exactly that the rigidity that increases has reduced first and second distortion of inner panel 120a-b during flying.Therefore, aircraft can use a high trust engine, and can not cause the excessive deformation of thrust reverser 114 owing to the load that increases.The excessive deformation of the first and second inner panel 120a-b can obviously change the loading transfer route of thrust reverser 114 and damage assembly.In addition, snap close 140 that pins mutually and the door bolt 160 bandings first and second wallboard 120a-b, thus leading edge 132a-b can obviously be offset, and during flying, remain in the V-shaped groove of blade case.
Another feature of thrust reverser 114 embodiment shown in Fig. 2-7 is that door bolt 160 is activated indirectly by the binary pair 194 that is positioned on the second inner panel 120b bottom 124b.The benefit of this feature is exactly that binary pair 194 is positioned on one of the thrust reverser 114 bottoms position that easily, is easy to get at, thereby is convenient to fasten with a bolt or latch 160 actuating.
B. be used in other embodiment of the lockout mechanism on the thrust reverser
Fig. 8 is the cross-section front view of the part of thrust reverser 214 according to another embodiment of the present invention.Graphic thrust reverser 214 roughly is similar to the described thrust reverser 114 of Fig. 2-7.For example, the door bolt 260 that diagram thrust reverser 214 comprises the first inner panel 220a, the second inner panel 220b relative with the first inner panel 220a, the snap close 240 that links to each other with the inside face 228a of the first wallboard 220a top 222a links to each other with inside face 228b with the second wallboard 220b top 222b.Yet graphic snap close 240 comprises the isolated part 242 with inside face 228a.This part 242 has hole 244, and this hole size and location are designed to hold the part of door bolt 260.
Fig. 9 is the cross-section front view of the part of thrust reverser 314 according to another embodiment of the present invention.Graphic thrust reverser 314 roughly is similar to the described thrust reverser 114 of Fig. 2-7.For example, the door bolt 360 that diagram thrust reverser 314 comprises the first inner panel 320a, the second inner panel 320b relative with the first inner panel 320a, the snap close 340 that links to each other with the inside face 328a of the first wallboard 320a top 322a links to each other with inside face 328b with the second wallboard 320b top 322b.Yet, diagram snap close 340 comprise base portion 341, from the outstanding first element 342a of base portion 341 and from base portion 341 the second element 342b outstanding and that separate with the first element 342a.This first element 342a comprises the first hole 344a, and the second element 342b comprises the second hole 344b that aligns with the first hole 344a.
Diagram door bolt 360 comprises screw actuator 362 (briefly showing among the figure) and the pin 380 that links to each other with screw actuator 362.Screw actuator 362 is moving pin 380 on direction D2 optionally, makes it be contained in latched position among the first and second hole 344a-b with (b) pin 380 is mobile between the releasing position outside the first and second hole 344a-b at (a) pin 380.On latched position, door bolt 360 that locks and snap close 340 can stop the first and second wallboard 320a-b to turn on the open position at P1 and P2 direction respectively.
Content specific embodiment of the present invention described herein as can be seen is only used for explaining from above, thereby can make the various remodeling that do not depart from aim of the present invention and scope.For example, many features of an embodiment can combine or substitute some feature of other embodiment with other embodiment.Therefore, the present invention is limited by claims.
Claims (41)
1. aerocraft system comprises:
One thrust reverser, this device comprise first inner panel and second inner panel relative with this first inner panel, and this first and second inner panel has inside face and top;
Inwardly outstanding snap close on the top of this first inner panel and the inside face; With
Inwardly outstanding door bolt on the top of this second inner panel and the inside face, this door bolt are oriented to optionally and the snap close interlocking, to stop relatively moving between first inner panel and second inner panel.
2. aerocraft system as claimed in claim 1 is characterized in that:
This snap close comprises that this first element and the second element spaced apart also are roughly parallel to this second element with first element in first hole with second element in second hole;
Door bolt is the indirect actuating door bolt of a fastener that has driver train and link to each other with driver train, and this fastener has first end and the second end; With
Driver train be constituted as (a) first end be contained in first hole at least in part and the second end be contained at least in part in second hole latched position and (b) first end outside first hole and the second end mobile fastener between the releasing position outside second hole.
3. aerocraft system as claimed in claim 1 is characterized in that:
Snap close comprises an opening; With
Door bolt comprises a fastener, and it can be contained in latched position in the latch openings with (b) this fastener is mobile between the releasing position outside the latch openings at least in part at (a) this fastener.
4. aerocraft system as claimed in claim 1 is characterized in that:
Snap close comprises an opening;
Door bolt comprises a fastener, and it can be contained in latched position in the latch openings with (b) this fastener is mobile between the releasing position outside the latch openings at least in part at (a) this fastener; With
This fastener rotates between latched position and releasing position.
5. aerocraft system as claimed in claim 1 is characterized in that:
Door bolt comprises driver train and the fastener that links to each other with this driver train; With
This fastener has "T"-shaped structure.
6. aerocraft system as claimed in claim 1 is characterized in that, first and second inner panels also comprise bottom and the arcuate section between top and the bottom.
7. aerocraft system as claimed in claim 1 is characterized in that, door bolt is one and activates door bolt indirectly.
8. aerocraft system as claimed in claim 1 is characterized in that:
First and second inner panels also comprise bottom and the arcuate section between top and the bottom; With
This system also comprises one at least near the binary pair of second inner panel lower and the actuator that connects binary pair and door bolt.
9. aerocraft system as claimed in claim 1 also comprises a strut member;
Wherein the top of first inner panel is pivotally attached on this strut member;
Wherein the top of second inner panel is pivotally attached on this strut member; With
Wherein when door bolt and snap close interlocking, can stop first and second inner panels moving with respect to this strut member.
10. aerocraft system as claimed in claim 1 is characterized in that:
First and second inner panels also comprise front portion and the rear portion relative with the front portion; With
Snap close is connected to the front portion of first inner panel, and door bolt is connected to the front portion of second inner panel.
11. aerocraft system as claimed in claim 1 is characterized in that:
First and second inner panels also comprise front portion and the rear portion relative with the front portion; With
Snap close is connected to the rear portion of first inner panel, and door bolt is connected to the rear portion of second inner panel.
12. aerocraft system as claimed in claim 1 is characterized in that:
The top of the top of first inner panel and second inner panel separates a gap; With
This door bolt and snap close are projected in this gap.
13. aerocraft system as claimed in claim 1 is characterized in that also comprising:
Be connected to the wing on the thrust reverser;
Be connected to the fuselage on the wing; With
Be connected to the tail on the fuselage.
14. an aerocraft system comprises:
One strut member;
One thrust reverser comprises first inwall and second inwall relative with this first inwall, and this first inwall has inside face and the top that is pivotally attached on the strut member, and second inwall has inside face and the top that is pivotally attached on the strut member;
One snap close is inwardly given prominence to from the inside face of this first upper inside wall, and this snap close has an opening; With
One door bolt is inwardly given prominence to from the inside face of this second upper inside wall, this door bolt comprises a fastener, and it can be contained at least in part at (a) this fastener, and this fastener is mobile between the releasing position outside the latch openings with respect to the latched position of strut member rotation and (b) to stop first and second inwalls in the latch openings.
15. the aerocraft system as claim 14 is characterized in that, this door bolt also comprises (a) driver train of mobile fastener and elastic element that (b) forces fastener to move along a direction between latched position and releasing position.
16. the aerocraft system as claim 14 is characterized in that, this fastener rotates between latched position and releasing position.
17. the aerocraft system as claim 14 is characterized in that, this fastener is linear moving between latched position and releasing position.
18. the aerocraft system as claim 14 is characterized in that, this door bolt is one and activates door bolt indirectly.
19. the aerocraft system as claim 14 is characterized in that, first and second inwalls also comprise bottom and the arcuate section between top and the bottom.
20. an aerocraft system comprises:
Thrust reverser comprises first inner panel and second inner panel, and first inner panel and second inner panel can move between open position and make position, and this first and second inner panel has an inside face and front portion;
From the inwardly outstanding snap close of the inside face of the front portion of this first inner panel; With
From the inwardly outstanding indirect actuating door bolt of the inside face of the front portion of this second inner panel, this door bolt have (a) optionally with latch engagement first and second inner panels remained on the fastener on the make position and (b) to drive the actuator of this fastener.
21. the aerocraft system as claim 20 is characterized in that:
This first and second inner panel also comprises the arcuate section between top, bottom and the top and the bottom;
Be connected the snap close on the top of first inner panel; With
Be connected the door bolt on the top of second inner panel.
22. the aerocraft system as claim 20 is characterized in that:
Snap close comprises a hole; With
Fastener can (a) this fastener be contained at least in part in the latch openings latched position and (b) this fastener between the releasing position outside the latch openings, move.
23. the aerocraft system as claim 20 is characterized in that, actuator comprises a screw actuator.
24. an aerocraft system comprises:
Thrust reverser comprises first inner panel and second inner panel relative with first inner panel, and this first and second inner panel has the arcuate section between top, bottom and the top and the bottom;
The receiving element of inwardly giving prominence to from the first inner panel top; With
The inwardly outstanding fastener from the second inner panel top, this fastener can be optionally (a) this fastener and receiving element interlocking with stop the latched position that relatively moves between first and second inner panels and (b) fastener can not stop between the releasing position that first and second inner panels relatively move mobile.
25. the aerocraft system as claim 24 is characterized in that:
First and second inner panels also comprise an inside face;
Receiving element links to each other with the inside face of first inner panel; With
The inside face of the fastener and second inner panel can be operatively connected.
26. an aerocraft system comprises:
Thrust reverser comprises first inner panel and second inner panel relative with this first inner panel, and this first and second inner panel has inside face and top, and wherein at least one of first inner panel and second inner panel can move relative to another; With
Be used for the device that optionally stops first and second inner panels to relatively move, this holdout device is inwardly outstanding from the inside face and the top of first and second inner panels.
27. the aerocraft system as claim 26 is characterized in that, this is used for optionally stoping the device of first and second inner panels to comprise snap close that is connected on first inner panel and the door bolt that is connected on second inner panel.
28. the aerocraft system as claim 26 is characterized in that, this is used for optionally stoping the device of first and second inner panels to comprise plate and the fastener that has the hole, and the size of this fastener is set as and can be contained at least in part in this hole.
29. the aerocraft system as claim 26 is characterized in that, this is used for optionally stoping the device of first and second inner panels to comprise indirect actuating door bolt.
30. an aerocraft system comprises:
Thrust reverser comprises first inner panel and second inner panel relative with this first inner panel, and this first and second inner panel has top, and wherein at least one in first and second inner panels can move relative to another; With
Be connected the latch-up structure on this first and second inner panel, be used for optionally stoping first and second inner panels to relatively move.
31. a method of making thrust reverser on the aircraft, this thrust reverser has first and second inner panels, and this method comprises:
Snap close is connected on the inside face on the first inner panel top; With
Door bolt is connected on the inside face on the second inner panel top, thereby this door bolt is positioned to optionally and the snap close interlocking, to stop moving mutually between first and second inner panels.
32. the method as claim 31 is characterized in that:
The step that connects snap close comprises a plate is connected to first inner panel that this plate has an opening; With
The step of coupler latch comprises links second inner panel with fastener, and this fastener has an end, and its size is suitable for being contained at least in part in this opening.
33. the method as claim 31 is characterized in that:
The step that connects snap close comprises a plate is connected to first inner panel that this plate has an opening; With
The step of coupler latch comprises links second inner panel with fastener and driver train, can mobile fastener thereby this driver train is oriented to, make its (a) this fastener be contained at least in part in this plate opening latched position and (b) fastener between the releasing position outside the opening, move.
34. the method as claim 31 is characterized in that, the step of coupler latch comprises connecting to activate indirectly fastens second inner panel with a bolt or latch.
35. the method as claim 31 is characterized in that:
The step that connects snap close comprises the front portion that snap close is connected to first inner panel; With
The step of coupler latch comprises the front portion that door bolt is connected to second inner panel.
36. the method as claim 31 also comprises:
First inner panel is pivotally attached on the strut member; With
Second inner panel is pivotally attached on this strut member.
37. the method as claim 31 also comprises:
Connect the bottom of a binary pair to second inner panel; With
Actuator position between binary pair and door bolt, is made itself and snap close interlocking to activate door bolt.
38. the method as claim 31 is characterized in that, first and second inner panels also comprise the arcuate section between bottom and the top and the bottom.
39. the method as claim 31 is characterized in that:
A spaced apart gap, the top of the top of first inner panel and second inner panel;
The step that connects snap close comprises snap close connected into makes snap close be projected into this gap from first inner panel; With
The step of coupler latch comprises door bolt connected into makes door bolt be projected into this gap from second inner panel.
40. the method for the lockout mechanism of an operate aircraft thrust reverser, this thrust reverser have first inner panel and second inner panel, this method comprises:
Activate the fastener that door bolt moves this door bolt indirectly, make its from (a) fastener and snap close interlocking so that door bolt and snap close can stop the latched position that relatively moves between first and second inner panels to move to (b) door bolt and snap close can not stop the releasing position that relatively moves between first and second inner panels, wherein this snap close is inwardly outstanding from the inside face on the first inner panel top, and door bolt is inwardly outstanding from the inside face on the second inner panel top; With
In first and second inner panels at least one moved relative to another.
41. the method as claim 40 is characterized in that, activates door bolt indirectly and comprises that actuating is positioned at the binary pair of second inner panel lower.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200510124934A CN100575690C (en) | 2005-09-12 | 2005-09-12 | The thrust reverser and the manufacture method thereof that comprise locking framework |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200510124934A CN100575690C (en) | 2005-09-12 | 2005-09-12 | The thrust reverser and the manufacture method thereof that comprise locking framework |
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| CN1931666A true CN1931666A (en) | 2007-03-21 |
| CN100575690C CN100575690C (en) | 2009-12-30 |
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| CN200510124934A Active CN100575690C (en) | 2005-09-12 | 2005-09-12 | The thrust reverser and the manufacture method thereof that comprise locking framework |
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| CN101959758A (en) * | 2008-02-28 | 2011-01-26 | 空中客车运作股份公司 | The engine pack that is used for aircraft that comprises the loop configuration that is used to the power of transmitting of the central casing that surrounds turbojet |
| CN101801789B (en) * | 2007-09-20 | 2012-10-17 | 空中客车运作股份公司 | Lower rear aerodynamic fairing for an aircraft engine attachment device |
| CN101959759B (en) * | 2008-02-28 | 2013-03-06 | 空中客车运作股份公司 | Aircraft engine assembly comprising a turbojet engine with reinforcing structures connecting the fan casing to the central casing |
| CN101765542B (en) * | 2007-08-20 | 2013-03-20 | 埃尔塞乐公司 | Attachment of a jet engine nacelle structure by means of a reinforced knife-edge/groove coupling |
| CN102066198B (en) * | 2008-06-25 | 2013-07-31 | 埃尔塞乐公司 | Aircraft engine nacelle air intake assembly |
| CN101848836B (en) * | 2007-11-07 | 2014-02-12 | 空中客车运作有限责任公司 | Locking mechanism for cargo door in aircraft |
| CN104554736A (en) * | 2013-10-24 | 2015-04-29 | 罗尔公司 | Gimbal pin for jet propulsion system |
| CN107097962A (en) * | 2016-02-23 | 2017-08-29 | 空中客车运营简化股份公司 | Engine pack and aircraft for aircraft |
| CN111279061A (en) * | 2017-10-27 | 2020-06-12 | 赛峰短舱公司 | Thrust reverser with system for locking and unlocking under load |
| CN112937835A (en) * | 2021-03-31 | 2021-06-11 | 成都纵横大鹏无人机科技有限公司 | Wing form self-locking assembly and wing form locking mechanism |
-
2005
- 2005-09-12 CN CN200510124934A patent/CN100575690C/en active Active
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101765542B (en) * | 2007-08-20 | 2013-03-20 | 埃尔塞乐公司 | Attachment of a jet engine nacelle structure by means of a reinforced knife-edge/groove coupling |
| CN101801789B (en) * | 2007-09-20 | 2012-10-17 | 空中客车运作股份公司 | Lower rear aerodynamic fairing for an aircraft engine attachment device |
| CN101848836B (en) * | 2007-11-07 | 2014-02-12 | 空中客车运作有限责任公司 | Locking mechanism for cargo door in aircraft |
| CN101959759B (en) * | 2008-02-28 | 2013-03-06 | 空中客车运作股份公司 | Aircraft engine assembly comprising a turbojet engine with reinforcing structures connecting the fan casing to the central casing |
| CN101945808A (en) * | 2008-02-28 | 2011-01-12 | 空中客车运作股份公司 | Be included in the engine pack that is used for aircraft of the engine fasteners that offsets downward on the blower-casting |
| CN101959758A (en) * | 2008-02-28 | 2011-01-26 | 空中客车运作股份公司 | The engine pack that is used for aircraft that comprises the loop configuration that is used to the power of transmitting of the central casing that surrounds turbojet |
| CN102066198B (en) * | 2008-06-25 | 2013-07-31 | 埃尔塞乐公司 | Aircraft engine nacelle air intake assembly |
| CN104554736A (en) * | 2013-10-24 | 2015-04-29 | 罗尔公司 | Gimbal pin for jet propulsion system |
| CN107097962A (en) * | 2016-02-23 | 2017-08-29 | 空中客车运营简化股份公司 | Engine pack and aircraft for aircraft |
| CN107097962B (en) * | 2016-02-23 | 2022-03-25 | 空中客车运营简化股份公司 | Engine assembly for aircraft and aircraft |
| CN111279061A (en) * | 2017-10-27 | 2020-06-12 | 赛峰短舱公司 | Thrust reverser with system for locking and unlocking under load |
| CN112937835A (en) * | 2021-03-31 | 2021-06-11 | 成都纵横大鹏无人机科技有限公司 | Wing form self-locking assembly and wing form locking mechanism |
| CN112937835B (en) * | 2021-03-31 | 2023-05-26 | 成都纵横大鹏无人机科技有限公司 | Wing form self-locking assembly and wing form locking mechanism |
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|---|---|
| CN100575690C (en) | 2009-12-30 |
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