US20080267694A1 - Dual action structural latch - Google Patents
Dual action structural latch Download PDFInfo
- Publication number
- US20080267694A1 US20080267694A1 US11/741,872 US74187207A US2008267694A1 US 20080267694 A1 US20080267694 A1 US 20080267694A1 US 74187207 A US74187207 A US 74187207A US 2008267694 A1 US2008267694 A1 US 2008267694A1
- Authority
- US
- United States
- Prior art keywords
- joint
- aperture
- handle
- latch
- latching member
- 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.)
- Granted
Links
- 230000009977 dual effect Effects 0.000 title claims abstract description 19
- 230000001747 exhibiting effect Effects 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Images
Classifications
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- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05C—BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS
- E05C19/00—Other devices specially designed for securing wings, e.g. with suction cups
- E05C19/10—Hook fastenings; Fastenings in which a link engages a fixed hook-like member
- E05C19/12—Hook fastenings; Fastenings in which a link engages a fixed hook-like member pivotally mounted around an axis
- E05C19/14—Hook fastenings; Fastenings in which a link engages a fixed hook-like member pivotally mounted around an axis with toggle action
- E05C19/145—Hook fastenings; Fastenings in which a link engages a fixed hook-like member pivotally mounted around an axis with toggle action flush
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T292/00—Closure fasteners
- Y10T292/08—Bolts
- Y10T292/0911—Hooked end
- Y10T292/0913—Sliding and swinging
- Y10T292/0914—Operating means
- Y10T292/0917—Lever
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T403/00—Joints and connections
- Y10T403/32—Articulated members
- Y10T403/32254—Lockable at fixed position
- Y10T403/32262—At selected angle
- Y10T403/32319—At selected angle including pivot stud
- Y10T403/32327—At selected angle including pivot stud including radially spaced detent or latch component
Definitions
- the present invention generally relates to latches and more particularly to a dual action structural latch for securing aircraft hinged access doors.
- the access panels for the tailcone may incorporate two over-center latches and two shear pins, requiring the simultaneous alignment of four features to properly close the panel.
- a dual action structural latch for securing aircraft hinged access doors to a frame.
- the latch of one exemplary embodiment comprises a latching member secured to the frame and defining a first aperture.
- a cross member defines a second aperture and is rotationally coupled to the frame.
- a primary link comprises a first end coupled to the cross member by a first joint, and an ear formed at a second end.
- a handle is rotationally mounted to the ear by a second joint and is moveable between a closed position and an open position.
- a hook member is rotationally mounted to the primary link near the second end by a third joint and engages the latching member when the handle is in the closed position and disengages the latching member when the handle is in the open position.
- a shear link is rotationally mounted to the handle by a fourth joint.
- a shear pin is rotationally mounted to the shear link by a fifth joint and extends through the second aperture and beyond the first end of the primary link so as to engage within the first aperture when the handle is in the closed position and disengage the first aperture when the handle is in the open position.
- the shear pin is withdrawn from the first aperture in the latching member, the primary link is rotated counterclockwise around the first joint, the hook member is disengaged from the latching member, a vector between the first aperture and third joint passes through the second aperture enabling an over-center feature, and the hook member is rotated around the third joint and away from the latching member.
- the handle is rotated around the second joint to a closed position, the hook member is rotated around the third joint and toward the latching member, the vector between the first aperture and third joint passes through the second aperture, the hook member is engaged with the latching member, the primary link is rotated clockwise around the first joint; and the shear pin is engaged with the aperture in the latching member.
- FIG. 1 is an isometric view of an exemplary embodiment in an open position
- FIG. 2 is a side view of the exemplary embodiment in the open position
- FIG. 3 is a side view of the exemplary embodiment in a partially closed position
- FIG. 4 is a side view of the exemplary embodiment in a closed position.
- a compact low profile over-center tension latch assembly including an integral, retractable shear pin reduces the difficulty in closing panels, thus allowing simultaneous engagement of two features at one location and in one operator motion, effectively reducing the resources required to properly close the panel.
- the latch may be used in aerospace applications with very demanding envelope requirements. Incorporation of the retractable shear pin into the latch assembly allows greater convenience to operators as well as potential reductions in aircraft weight.
- the latch assembly 10 may be used to secure any panel, or access door, to a frame, but the preferred use is envisioned for aircraft access doors to compartments wherein aircraft systems, such as, hydraulic (e.g., pumps), electronic (e.g., generators), engine or engine systems (e.g., compressors), are maintained.
- aircraft systems such as, hydraulic (e.g., pumps), electronic (e.g., generators), engine or engine systems (e.g., compressors), are maintained.
- the aircraft frame refers to the structure surrounding the compartment to which the latch assembly 10 is providing access, and may be integrally formed with the aircraft, secondarily attached thereto, or be included as part of a keeper assembly with the latch assembly 10 .
- a primary link, or quaternary member, 12 is mounted by a cross member 14 rotationally coupled to the aircraft frame (not shown) through a closed revolute joint 16 .
- Revolute joints known in the industry include male and female components and are not explicitly described herein.
- the primary link 12 includes an ear 18 extending from a second, or aft, end 19 .
- a handle 20 is rotationally mounted at the ear 18 to the primary link 12 by a closed revolute joint 22 .
- the handle 20 is a binary link positioned within an opening in the access door (not shown) for ease of access and preferably comprises a longitudinal member with a transverse cross-sectional shape having flanges 21 , 21 ′ approximating a “U” having a channel width sufficient for containing the primary link 12 .
- the handle 20 may include a secondary locking feature, designed to require deliberate operator action before the handle can rotate from the closed position. Such features are typical within the Latch Industry, and are not explicitly described herein.
- a hook member 24 is rotationally mounted at a first end 26 to the primary link 12 by a closed revolute joint 28 .
- the hook member 24 comprises a binary link having an aftly concave hook 30 at a second end 32 .
- the hook member 24 defines a relief 34 positioned approximately midspan of the hook member 24 to allow for clearance with the cross member 14 when the latch assembly 10 is in the closed position.
- the latch apparatus 10 may be designed with single members 13 and 25 .
- the two members 13 , 13 ′ are separated a distance sufficient to allow the hook member 24 , a shear pin 36 and a shear link 38 to be disposed therebetween.
- the cross member 14 extends outboard from each longitudinal member and forms the interface for the joint 16 .
- a longitudinal aperture 40 is formed in the cross member 14 , which forms a prismatic joint with the shear pin 36 .
- the dual members 25 , 25 ′ comprising the hook member 24 preferably comprises two similar parallel longitudinal members which may optionally be coupled by a cross member (not shown).
- the dual members 25 , 25 ′ are separated a distance sufficient to allow the shear link 38 to be disposed therebetween.
- the shear pin 36 is a ternary link rotationally mounted at a first, or aft, end 42 to a first, or forward, end 44 of the shear link 38 by a closed revolute joint 46 and extends through the aperture 40 (closed prismatic joint) in the cross member 14 .
- a second, or aft, end 48 of the shear link 38 is rotationally mounted to a cross member 50 by joint 52 and is rotationally mounted to first and second flanges 21 , 21 ′ of the handle 20 at closed revolute joints 54 .
- the shear pin 36 and shear link 38 may be formed integrally with a link or may be installed separately.
- a second end 56 of the shear pin 36 is of a form suitable, e.g., a bullnose, for self-piloting into the aperture 60 .
- the latch assembly 10 further includes a latching member 58 mounted to the aircraft frame (not shown).
- the latching member, or striker pin, 58 comprises a prismatic joint that defines an aperture 60 for securing the shear pin 36 when the latch assembly 10 is in the closed position.
- the over-center mechanism comprises moving the vector established between joint 60 and joint 28 , passing through and below joint 16 during movement of the handle 20 .
- the handle 20 will rotate counter-clockwise about closed revolute joint 22 , thereby causing the shear link 38 to impart motion on the shear pin 36 to engage the aperture 60 ( FIG. 4 ).
- the primary link 12 extends nominally parallel to the approximated major axis 62 of the latch assembly 10 in the closed position.
- an improved dual action structural latch for securing aircraft hinged access doors and suitable for opposing tension and shear loads may be operated by one person in one swift motion.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Hinges (AREA)
- Lock And Its Accessories (AREA)
Abstract
A dual action structural latch (10) is provided for securing hinged access doors to a frame. The latch (10) comprises a latching member (58) secured to the frame and defining a first aperture (60). A hook member (24) engages the latching member (58) to resist a tensile force when the latch (10) is in a closed position, and disengages the latching member (58) when the latch (10) is in the open position. A shear pin (36) extends so as to engage within the first aperture (60) to resist a shear force when the latch (10) is in the closed position and to disengage the first aperture (60) when the latch (10) is in the open position. A handle (20), when moved from the closed position to the open position, sequentially withdraws the shear pin (36) from the first aperture (60) and disengages the hook member (24) from the latching member (58), and when moved from the open position to the closed position, sequentially engages the hook member (24) with the latching member (58) and inserts the shear pin (36) in the first aperture (60).
Description
- The present invention generally relates to latches and more particularly to a dual action structural latch for securing aircraft hinged access doors.
- Modern aircraft are equipped with a large number of external access panels that are flush mounted so as to provide an aerodynamic, low drag surface when airborne. These external access panels conventionally allow access to, for example, hydraulic, electronic, and engine or engine systems. In order to maintain a panel in the closed position, while still providing quick access to the area behind the panel while the aircraft is parked on the ground, low-profile flush mounted latches of the over-center tension type typically are incorporated into the design of the panel for securing the panel to the aircraft frame. For example, see U.S. Pat. Nos. 4,743,052 and 6,343,815.
- When the size of the panel exceeds a certain limit, there is a need to incorporate one or more shear pins into the panel as well. The shear pin maintains the structural rigidity of the panel in the closed position when twisting loads are present. Latches capable of supporting both tension loading and shear loading are known. For example, see U.S. Pat. No. 5,556,142 which describes a combination tension-shear latch of the rotary hook type. However, this rotary action is unsuitable for applications which must be flush mounted to panels with complex curvatures and is prohibitively large for smaller panel applications exhibiting minimal loading.
- Furthermore, when an aircraft incorporates both over-center latches and shear pins, it is often difficult for one person to close the panel, as all the latches and pins must be aligned simultaneously. In a typical regional jet application, the access panels for the tailcone may incorporate two over-center latches and two shear pins, requiring the simultaneous alignment of four features to properly close the panel. In commercial aircraft having significantly larger panels, it is not uncommon to have six or eight features.
- Accordingly, it is desirable to provide a dual action structural latch suitable for opposing tension and shear loads and which may be operated by one person. Furthermore, other desirable features and characteristics of the present invention will become apparent from the subsequent detailed description of the invention and the appended claims, taken in conjunction with the accompanying drawings and this background of the invention.
- A dual action structural latch is provided for securing aircraft hinged access doors to a frame. The latch of one exemplary embodiment comprises a latching member secured to the frame and defining a first aperture. A cross member defines a second aperture and is rotationally coupled to the frame. A primary link comprises a first end coupled to the cross member by a first joint, and an ear formed at a second end. A handle is rotationally mounted to the ear by a second joint and is moveable between a closed position and an open position. A hook member is rotationally mounted to the primary link near the second end by a third joint and engages the latching member when the handle is in the closed position and disengages the latching member when the handle is in the open position. A shear link is rotationally mounted to the handle by a fourth joint. A shear pin is rotationally mounted to the shear link by a fifth joint and extends through the second aperture and beyond the first end of the primary link so as to engage within the first aperture when the handle is in the closed position and disengage the first aperture when the handle is in the open position.
- In operation, when the handle is rotated around the second joint to an open position, the shear pin is withdrawn from the first aperture in the latching member, the primary link is rotated counterclockwise around the first joint, the hook member is disengaged from the latching member, a vector between the first aperture and third joint passes through the second aperture enabling an over-center feature, and the hook member is rotated around the third joint and away from the latching member. When the handle is rotated around the second joint to a closed position, the hook member is rotated around the third joint and toward the latching member, the vector between the first aperture and third joint passes through the second aperture, the hook member is engaged with the latching member, the primary link is rotated clockwise around the first joint; and the shear pin is engaged with the aperture in the latching member.
- The present invention will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements, and
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FIG. 1 is an isometric view of an exemplary embodiment in an open position; -
FIG. 2 is a side view of the exemplary embodiment in the open position; -
FIG. 3 is a side view of the exemplary embodiment in a partially closed position; and -
FIG. 4 is a side view of the exemplary embodiment in a closed position. - The following detailed description of the invention is merely exemplary in nature and is not intended to limit the invention or the application and uses of the invention. Furthermore, there is no intention to be bound by any theory presented in the preceding background of the invention or the following detailed description of the invention.
- A compact low profile over-center tension latch assembly including an integral, retractable shear pin reduces the difficulty in closing panels, thus allowing simultaneous engagement of two features at one location and in one operator motion, effectively reducing the resources required to properly close the panel. The latch may be used in aerospace applications with very demanding envelope requirements. Incorporation of the retractable shear pin into the latch assembly allows greater convenience to operators as well as potential reductions in aircraft weight.
- Referring to the isometric view of
FIG. 1 and the side view ofFIG. 2 , an exemplary embodiment of the dual actionstructural latch assembly 10 is shown in an open position. Thelatch assembly 10 may be used to secure any panel, or access door, to a frame, but the preferred use is envisioned for aircraft access doors to compartments wherein aircraft systems, such as, hydraulic (e.g., pumps), electronic (e.g., generators), engine or engine systems (e.g., compressors), are maintained. The aircraft frame as used herein refers to the structure surrounding the compartment to which thelatch assembly 10 is providing access, and may be integrally formed with the aircraft, secondarily attached thereto, or be included as part of a keeper assembly with thelatch assembly 10. The open position is generally used when the aircraft is on the ground, when access to equipment behind the panel is desired. A primary link, or quaternary member, 12 is mounted by across member 14 rotationally coupled to the aircraft frame (not shown) through a closedrevolute joint 16. Revolute joints known in the industry include male and female components and are not explicitly described herein. Theprimary link 12 includes anear 18 extending from a second, or aft,end 19. Ahandle 20 is rotationally mounted at theear 18 to theprimary link 12 by a closedrevolute joint 22. Thehandle 20 is a binary link positioned within an opening in the access door (not shown) for ease of access and preferably comprises a longitudinal member with a transverse cross-sectionalshape having flanges primary link 12. To prevent an inadvertent disengagement of the latch, thehandle 20 may include a secondary locking feature, designed to require deliberate operator action before the handle can rotate from the closed position. Such features are typical within the Latch Industry, and are not explicitly described herein. Ahook member 24 is rotationally mounted at afirst end 26 to theprimary link 12 by a closedrevolute joint 28. Thehook member 24 comprises a binary link having an aftlyconcave hook 30 at asecond end 32. Thehook member 24 defines arelief 34 positioned approximately midspan of thehook member 24 to allow for clearance with thecross member 14 when thelatch assembly 10 is in the closed position. - It will be appreciated that while the preferred
primary link 12 comprises two similar parallellongitudinal members cross member 14, and thehook member 24 comprisesdual members latch apparatus 10 may be designed withsingle members members hook member 24, ashear pin 36 and ashear link 38 to be disposed therebetween. Thecross member 14 extends outboard from each longitudinal member and forms the interface for thejoint 16. Alongitudinal aperture 40 is formed in thecross member 14, which forms a prismatic joint with theshear pin 36. Thedual members hook member 24 preferably comprises two similar parallel longitudinal members which may optionally be coupled by a cross member (not shown). Thedual members shear link 38 to be disposed therebetween. - The
shear pin 36 is a ternary link rotationally mounted at a first, or aft,end 42 to a first, or forward,end 44 of theshear link 38 by a closedrevolute joint 46 and extends through the aperture 40 (closed prismatic joint) in thecross member 14. A second, or aft,end 48 of theshear link 38 is rotationally mounted to across member 50 byjoint 52 and is rotationally mounted to first andsecond flanges handle 20 at closedrevolute joints 54. Theshear pin 36 andshear link 38 may be formed integrally with a link or may be installed separately. Asecond end 56 of theshear pin 36 is of a form suitable, e.g., a bullnose, for self-piloting into theaperture 60. - The
latch assembly 10 further includes a latchingmember 58 mounted to the aircraft frame (not shown). The latching member, or striker pin, 58 comprises a prismatic joint that defines anaperture 60 for securing theshear pin 36 when thelatch assembly 10 is in the closed position. - To close the
latch assembly 10, pressure is applied to the handle 20 (FIG. 2 ) in a counterclockwise direction (towards the latching member 58). Thehook member 24 will move to contact the latchingmember 58 and a downward force on theaft end 19 of theprimary link 12 via thehandle 20 which causes theprimary link 12 to rotate clockwise around closed revolute joint 16 and engage the over-center mechanism (FIG. 3 shows thelatch assembly 10 in a partially closed/open position). The over-center mechanism comprises moving the vector established between joint 60 and joint 28, passing through and below joint 16 during movement of thehandle 20. - As the pressure is continued to be applied to handle 20, the
handle 20 will rotate counter-clockwise about closed revolute joint 22, thereby causing theshear link 38 to impart motion on theshear pin 36 to engage the aperture 60 (FIG. 4 ). Theprimary link 12 extends nominally parallel to the approximatedmajor axis 62 of thelatch assembly 10 in the closed position. - To open the
latch assembly 10, pressure is applied to thehandle 20 to move it in a clockwise direction around joint 22 (away from the latching member 58). Theshear link 38 withdraws theshear pin 36 completely from theaperture 60. Note that theshear pin 36 remains withinaperture 40. As the handle continues to rotate clockwise around joint 22, theprimary link 12 rotates counterclockwise around the joint 16. The vector from the latchingmember 58 to joint 28 passes through and above joint 16, releasing the tension in thehook member 24, which disengages from latchingmember 58. As thelatch assembly 10 continues to rotate counterclockwise about joint 16, thehook member 24 freely rotates clockwise about joint 28 until thelatch assembly 10 is completely disengaged as shown inFIGS. 1 and 2 . - Thus, an improved dual action structural latch for securing aircraft hinged access doors and suitable for opposing tension and shear loads may be operated by one person in one swift motion.
- While at least one exemplary embodiment has been presented in the foregoing detailed description of the invention, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the invention in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an exemplary embodiment of the invention, it being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope of the invention as set forth in the appended claims.
Claims (12)
1. A dual action structural latch for securing an access door to a frame, the latch comprising:
a latching member secured to the frame and defining a first aperture;
a primary link;
a shear link;
a hook member rotationally attached to the primary link for engaging the latching member when the latch is in a closed position to resist a tensile force, and for disengaging the latching member when the latch is in the open position, including an over-center mechanism where a vector between the latching member and the joint between the hook member and the primary link passes below a joint containing the second aperture when moving between the open and closed positions;
a shear pin extending so as to engage within the first aperture when the latch is in the closed position to resist a shear force and to disengage the first aperture when the latch is in the open position;
a cross member rotationally coupled to the frame and defining a second aperture having the shear pin extending therethrough, the a primary link having a first end rotationally coupled to the cross member; and
a handle rotationally attached to the primaly link and coupled to the shear pin by the shear link, the shear link reacting a pivotal action of the handle to a translation motion of the shear pin for, when moved from the closed position to the open position, sequentially withdrawing the shear pin from the first aperture and disengaging the hook member from the latching member, and when moved from the open position to the closed position, sequentially engaging the hook member with the latching member and inserting the shear pin in the first aperture.
2. (canceled)
3. (canceled)
4. The dual action structural latch of claim 1 wherein the primary link comprises two similar parallel longitudinal members spaced on opposed sides of the shear pin; and the hook member comprises two similar parallel longitudinal members spaced on opposed sides of the shear pin.
5. (canceled)
6. The dual action structural latch of claim 1 wherein the frame comprises one of a) integrally formed with an aircraft, b) secondarily attached to the aircraft, and c) included as part of a keeper assembly for attachment to the aircraft.
7. A dual action structural latch for securing an access door to a frame, the latch comprising:
a latching member secured to the frame and defining a first aperture;
a cross member defining a second aperture and rotationally coupled to the frame;
a primary link having a first end coupled to the cross member by a first joint, and an ear formed at a second end;
a handle rotationally mounted to the ear by a second joint, the handle moveable between a closed position and an open position;
a hook member rotationally mounted to the primary link near the second end by a third joint, the hook member engaging the latching member when the handle is in the closed position and disengaging the latching member when the handle is in the open position;
a shear link rotationally mounted to the handle by a fourth joint; and
a shear pin rotationally mounted to the shear link by a fifth joint and extending through the second aperture, and extending beyond the first end of the primary link so as to engage within the first aperture when the handle is in the closed position and disengage the first aperture when the handle is in the open position.
8. The dual action structural latch of claim 7 further defining an over-center mechanism when a vector between the latching member and the third joint passes through a joint containing the second aperture when the handle is moving between the open and closed positions.
9. The dual action structural latch of claim 7 wherein the primary link comprises two similar parallel longitudinal members spaced on opposed sides of the shear link and the shear pin; and the hook member comprises two similar parallel longitudinal members spaced on opposed sides of the shear link.
10. The dual action structural latch of claim 7 wherein the frame comprises one of 1) integrally formed with an aircraft, and 2) secondarily attached to the aircraft.
11. The dual action structural latch of claim 7 further comprising a keeper assembly for attachment to the frame, and the frame comprises a portion of an aircraft.
12. A method of operating a dual action structural latch for securing an access door to a frame; the latch comprising a latching member secured to the frame and defining a first aperture; a cross member rotationally coupled to the frame and defining a second aperture; a primary link having a first end rotationally coupled to the cross member at a first joint, and an ear formed at a second end; a handle rotationally mounted to the ear by a second joint; a hook member rotationally mounted to the primary link near the second end by a third joint, the hook member engaging the latching member when the handle is in a closed position; a shear link rotationally mounted to the handle by a fourth joint; and a shear pin rotationally mounted to the shear link by a fifth joint and extending through the second aperture, and extending beyond the first end of the primary link so as to engage within the first aperture when the handle is in the closed position; the method comprising:
rotating the handle around the third joint to an open position, thereby creating the steps comprising;
withdrawing the shear pin from the first aperture in the latching member;
rotating the primary link counterclockwise around the first joint;
disengaging the hook member from the latching member;
passing the vector between the latching member and third joint through and above ajoint containing the second aperture;
rotating the hook member around the third joint and away from the latching member; and
rotating the handle around the second joint to a closed position, thereby creating the steps comprising:
rotating the hook member around the third joint and toward the latching member;
passing the vector between the latching member and third joint through and below a joint containing the second aperture;
engaging the hook member with the latching member;
rotating the primary link clockwise around the first joint; and
engaging the shear pin with the first aperture in the latching member.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
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US11/741,872 US7448656B1 (en) | 2007-04-30 | 2007-04-30 | Dual action structural latch |
EP20080155416 EP1988239B1 (en) | 2007-04-30 | 2008-04-29 | Dual action structural latch |
CA 2630071 CA2630071A1 (en) | 2007-04-30 | 2008-04-30 | Dual action structural latch |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US11/741,872 US7448656B1 (en) | 2007-04-30 | 2007-04-30 | Dual action structural latch |
Publications (2)
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US20080267694A1 true US20080267694A1 (en) | 2008-10-30 |
US7448656B1 US7448656B1 (en) | 2008-11-11 |
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Application Number | Title | Priority Date | Filing Date |
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US11/741,872 Expired - Fee Related US7448656B1 (en) | 2007-04-30 | 2007-04-30 | Dual action structural latch |
Country Status (3)
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US (1) | US7448656B1 (en) |
EP (1) | EP1988239B1 (en) |
CA (1) | CA2630071A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20210300579A1 (en) * | 2020-03-26 | 2021-09-30 | Hartwell Corporation | Latching system with movable anti-shear mechanism |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8419088B2 (en) * | 2007-12-17 | 2013-04-16 | Avibank Manufacturing, Inc. | Latches and latching systems having a positive status indicator |
US20100264673A1 (en) * | 2009-04-21 | 2010-10-21 | Zeljko Baic | Command latch and pin latch system |
CA2835647C (en) | 2011-05-12 | 2019-05-28 | Bombardier Inc. | Latch |
US20170089107A1 (en) * | 2015-09-29 | 2017-03-30 | Alcoa Inc. | Tri-links latch |
US11274479B2 (en) * | 2018-05-31 | 2022-03-15 | Metal Works, Inc. | Heavy-duty jamb latch for sliding building doors |
EP3614001B1 (en) | 2018-08-21 | 2023-02-22 | Goodrich Actuation Systems Limited | Locking mechanism |
US11111705B2 (en) | 2018-12-18 | 2021-09-07 | Rohr, Inc. | Latch having shear load carrying capability |
Citations (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2714032A (en) * | 1954-11-24 | 1955-07-26 | Camloc Fastener Corp | Latch fastener |
US2978266A (en) * | 1958-08-12 | 1961-04-04 | Hartwell Aviat Supply Co | Sliding and rotating bolt latch |
US4127305A (en) * | 1976-01-10 | 1978-11-28 | Nielsen Kjeld R | Coupling device for tractor twin wheels |
US4365775A (en) * | 1980-12-08 | 1982-12-28 | The Boeing Company | Cowl structure alignment and shear device |
US4369937A (en) * | 1981-05-18 | 1983-01-25 | The United States Of America As Represented By The Secretary Of The Army | Hinging and latching apparatus |
US4421349A (en) * | 1981-12-28 | 1983-12-20 | The Boeing Company | Cowling latch |
US4531769A (en) * | 1982-08-25 | 1985-07-30 | The Boeing Company | Hook latch for an engine cowling |
US4743052A (en) * | 1986-01-24 | 1988-05-10 | Rexnord Inc. | Tension latch assembly |
US4758031A (en) * | 1986-09-25 | 1988-07-19 | Thermodyne International Ltd. | Retractable safety latch for cases |
US4768815A (en) * | 1986-04-23 | 1988-09-06 | Rexnord Inc. | Supplemental locking mechanism for a tension latch assembly |
US4826221A (en) * | 1987-04-03 | 1989-05-02 | Hartwell Corporation | Tension and shear latching mechanism |
US4828299A (en) * | 1987-03-31 | 1989-05-09 | Hartwell Corporation | Latch |
US5435615A (en) * | 1993-02-17 | 1995-07-25 | Wilhelm Karmann Gmbh | Locking device for convertible tops |
US5556142A (en) * | 1995-04-13 | 1996-09-17 | Hartwell Corporation | Rotary hook tension-shear latch |
US6343815B1 (en) * | 2000-10-04 | 2002-02-05 | Hartwell Corporation | Cinch-up latch |
US6729661B2 (en) * | 2002-01-14 | 2004-05-04 | Eads Deutschland Gmbh | Locking device for locking two structural parts |
US7066501B2 (en) * | 2004-09-22 | 2006-06-27 | Avibank Mfg., Inc. | Aircraft latch |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4602812A (en) * | 1983-05-20 | 1986-07-29 | Hartwell Corporation | Adjustable double hook latch |
FR2857400B1 (en) * | 2003-07-10 | 2005-10-21 | Hurel Hispano | LATCH FOR CONNECTING TWO PANELS OF AN AIRPLANE STRUCTURE |
-
2007
- 2007-04-30 US US11/741,872 patent/US7448656B1/en not_active Expired - Fee Related
-
2008
- 2008-04-29 EP EP20080155416 patent/EP1988239B1/en not_active Expired - Fee Related
- 2008-04-30 CA CA 2630071 patent/CA2630071A1/en not_active Abandoned
Patent Citations (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2714032A (en) * | 1954-11-24 | 1955-07-26 | Camloc Fastener Corp | Latch fastener |
US2978266A (en) * | 1958-08-12 | 1961-04-04 | Hartwell Aviat Supply Co | Sliding and rotating bolt latch |
US4127305A (en) * | 1976-01-10 | 1978-11-28 | Nielsen Kjeld R | Coupling device for tractor twin wheels |
US4365775A (en) * | 1980-12-08 | 1982-12-28 | The Boeing Company | Cowl structure alignment and shear device |
US4369937A (en) * | 1981-05-18 | 1983-01-25 | The United States Of America As Represented By The Secretary Of The Army | Hinging and latching apparatus |
US4421349A (en) * | 1981-12-28 | 1983-12-20 | The Boeing Company | Cowling latch |
US4531769A (en) * | 1982-08-25 | 1985-07-30 | The Boeing Company | Hook latch for an engine cowling |
US4743052A (en) * | 1986-01-24 | 1988-05-10 | Rexnord Inc. | Tension latch assembly |
US4768815A (en) * | 1986-04-23 | 1988-09-06 | Rexnord Inc. | Supplemental locking mechanism for a tension latch assembly |
US4758031A (en) * | 1986-09-25 | 1988-07-19 | Thermodyne International Ltd. | Retractable safety latch for cases |
US4828299A (en) * | 1987-03-31 | 1989-05-09 | Hartwell Corporation | Latch |
US4826221A (en) * | 1987-04-03 | 1989-05-02 | Hartwell Corporation | Tension and shear latching mechanism |
US5435615A (en) * | 1993-02-17 | 1995-07-25 | Wilhelm Karmann Gmbh | Locking device for convertible tops |
US5556142A (en) * | 1995-04-13 | 1996-09-17 | Hartwell Corporation | Rotary hook tension-shear latch |
US6343815B1 (en) * | 2000-10-04 | 2002-02-05 | Hartwell Corporation | Cinch-up latch |
US6729661B2 (en) * | 2002-01-14 | 2004-05-04 | Eads Deutschland Gmbh | Locking device for locking two structural parts |
US7066501B2 (en) * | 2004-09-22 | 2006-06-27 | Avibank Mfg., Inc. | Aircraft latch |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20210300579A1 (en) * | 2020-03-26 | 2021-09-30 | Hartwell Corporation | Latching system with movable anti-shear mechanism |
US11866189B2 (en) * | 2020-03-26 | 2024-01-09 | Hartwell Corporation | Latching system with movable anti-shear mechanism |
Also Published As
Publication number | Publication date |
---|---|
EP1988239A3 (en) | 2011-08-03 |
EP1988239A2 (en) | 2008-11-05 |
EP1988239B1 (en) | 2012-07-25 |
CA2630071A1 (en) | 2008-10-30 |
US7448656B1 (en) | 2008-11-11 |
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Owner name: HONEYWELL INTERNATIONAL, INC., NEW JERSEY Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:HEIN, JEFFREY M.;WILLIAMS, NICHOLAS A.;REEL/FRAME:019226/0916 Effective date: 20070427 |
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STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
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Effective date: 20161111 |