Pressure-Release Latch With Tension Calibration

Abstract

A pressure-release latch for releasably locking closed a door panel on the frame to which the door panel is hingedly connected. The latch has a base and a latch bolt rotatable between a closed position that locks the door panel closed and an open position that allows the door to swing open. A latch bolt actuator connected to the latch bolt rotates the latch bolt between the closed and open positions from outside the door panel, locks the latch bolt in the closed position, and automatically unlocks and moves the latch bolt to the open position when a predetermined opening force is applied to the latch bolt. A calibration mechanism adjusts the magnitude of the predetermined opening force required to automatically unlock the latch.

Claims

1. A pressure-release latch for releasably locking closed a door panel on a frame to which the door panel is hingedly connected, comprising: a. a base having a proximal end, distal end, top side, bottom side, a central aperture, and means for mounting the bottom side of said base to the door panel; b. a latch bolt having an elongate shank with a distal end, proximal end, and a head formed on the proximal end, said shank of said latch bolt being mounted by a first pivot pin to the top side of said base near the proximal end of said base, and being rotatable between a closed position that locks the door panel closed and an open position that allows the door panel to swing open; c. a latch bolt actuator mounted by a second pivot pin to the top side of said base and connected to the shank of said latch bolt, said latch bolt actuator including: i. manual rotation means for rotating said latch bolt between the closed and open positions from outside door panel; ii. lock means for locking the latch bolt in the closed position; ii. automatic unlock means for rotating said latch bolt to the open position when a predetermined opening force is applied to the latch bolt; and, iv. calibration means for calibrating the magnitude of the predetermined opening force required to automatically release said locking means.

2. The pressure-release latch recited in claim 1, wherein said manual rotation means comprises an actuator arm connected to the shank of said latch bolt between the distal end of the shank and said first pivot pin, wherein said actuator arm extends from said shank through the central aperture in said base;

3. The pressure-release latch recited in claim 1, wherein said latch bolt actuator comprises a spring-biased toggle-linkage tensioner pivotally mounted at one end by a second pivot pin to the distal end of said base and pivotally connected at the other end to said shank.

4. The pressure-release latch recited in claim 3, wherein said spring-biased, toggle-linkage tensioner includes: a. a restraining arm having a distal end, and a proximal end pivotally connected to said latch bolt shank by a first linkage pin; b. a lever arm having a proximal end pivotally connected to said distal end of said restraining arm by a second linkage pin, and a distal end pivotally mounted to said second pivot pin; and, c. a spring that biases said lever arm and restraining arm towards the head of said latch bolt.

5. The pressure-release latch recited in claim 4, wherein said spring comprises a coil spring wound around said second pivot pin and having first and second radiating legs, wherein the free end of said first leg sits in contact with at least one of said linkage pins when said latch is oriented in at least the closed position.

6. The pressure-release latch recited in claim 5, wherein said calibration means comprises a screw mechanism that changes the degree of deflection of said coil spring when said latch is oriented in the closed position.

7. The pressure-release latch recited in claim 6, wherein said screw mechanism comprises a capture slot and a calibration screw that can be extended into and retracted from said capture slot, and wherein the free end of said second leg sits in said capture slot in contact with said calibration screw.

8. The pressure-release latch recited in claim 7, wherein said free end of said second leg abuts said calibration screw so that movement of said screw within said capture slot changes the degree of deflection of said coil spring and the force it exerts on the toggle linkage.

10. The pressure-release latch recited in claim 4, wherein said latch bolt moves to the open position when the force on the head of the latch bolt rotates the latch bolt and urges said tensioner from a first angular configuration to a linear configuration, and then to an opposed second angular configuration;

10. The pressure-release latch recited in claim 4, wherein said first pivot pin and said second linkage pin define an over-center axis, said tensioner being constructed and arranged so that said first linkage pin is out of alignment with said over-center axis in the closed position.

11. The pressure-release latch recited in claim 10, wherein said first linkage pin rotates past the over-center axis to move said latch bolt from the closed position to the open position when the pressure on said latch bolt exceeds the predetermined opening force.

12. The pressure-release latch recited in claim 11, wherein rotation of said first linkage pin past the over-center axis releases all restraining force of said toggle linkage on said latch bolt;

13. The pressure-release latch recited in claim 10, wherein the moment exerted by said tensioner on the latch bolt reverses direction when said toggle linkage rotates and said first linkage pin crosses said over-center axis.

14. The pressure-release latch recited in claim 4, including a second torsion spring wrapped around said first pivot pin that biases said latch bolt toward the open position;

15. The pressure-release latch recited in claim 4, comprising a pair of restraining arms mounted on opposed sides of said lever arm and said latch bolt.

16. The pressure-release latch recited in claim 2, wherein said actuator arm has a head formed at its free end that seats flush within the outer surface of the door panel when the latch is in the closed position, and extends outwardly transverse to the door panel when the latch is in the open position.

17. The pressure-release latch of claim 1, wherein the head of said latch bolt abuts a frame when said latch bolt is oriented in the closed position;

18. The pressure-release latch of claim 1, including a bumper made of elastomeric material fixed to the head of said aid latch bolt.

19. A pressure-release latch for releasably locking closed a door panel on a frame to which the door panel is hingedly connected, comprising: a. a base having means for mounting to the door panel; b. a latch member being movable between a closed position that locks the door panel closed and an open position that allows the door panel to swing open; c. a latch member actuator connected said latch member including: i. means for moving said latch member between the closed and open positions from outside the door panel; ii. means for locking said latch member in the closed position until a predetermined opening force is applied to said latch member and then moving said latch member to the open position; and, iii. means for calibrating the magnitude of said predetermined opening force.

20. A pressure-release latch for releasably locking closed a door panel on a frame to which the door panel is hingedly connected, comprising: a. a base having means for mounting to the door panel; b. a latch member mounted on said base and movable between a closed position that locks the door panel closed and an open position that allows the door panel to swing open; c. a spring-biased, toggle-linkage tensioner connected to said latch member, said tensioner constructed and arranged to exert a predetermined lock force on said latch member, and constructed and arranged to automatically move said latch member to the open position when an opposed force in excess of the predetermined lock force is exerted on said latch member; and, d. means for calibrating the magnitude of the predetermined lock force exerted by said tensioner on said latch member.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0016] FIG. 1 is a bottom perspective view of a pressure-release latch in accordance with a preferred embodiment of the invention;

[0017] FIG. 2 is bottom plan view of the pressure-release latch of FIG. 1;

[0018] FIG. 3 is a cross-section taken along lines 3-3 of FIG. 2;

[0019] FIG. 4 is a top perspective view of the pressure-release latch of FIG. 1;

[0020] FIG. 5 is an assembly view of the pressure-release latch of FIG. 1;

[0021] FIG. 6 is a bottom plan view of the pressure-release latch of FIG. 1 installed on a door panel of an aircraft frame; and,

[0022] FIGS. 7a-c are sequential side elevations of the pressure-release latch in closed, partially-open and fully-open configurations, respectively.

DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0023] For the purpose of illustrating the invention, several embodiments of the invention are described with respect to the accompanying drawings. However, it should be understood by those of ordinary skill in the art that the invention is not limited to the precise arrangements and instrumentalities shown therein and described below. Throughout the specification, like reference numerals are used to designate like elements.

[0024] A latch in accordance with preferred embodiments of the invention is shown in FIGS. 1-7c and is designated generally by reference numeral 10. The latch 10 is shown oriented horizontally in FIGS. 3 and 7a-c for use with, and installed on, a generally-horizontally-oriented door panel DP of an aircraft. The door panel DP covers an access port in the aircraft frame AF such as the engine housing. However, it should be understood that the latch 10 can be used with a door panel DP having any orientation, including a vertical orientation.

[0025] The latch 10 is operable between a closed position such as shown in FIGS. 1-4, 6 and 7a, intermediate positions such as shown in FIG. 7b, and a fully-open position such as shown in FIG. 7c to provide temporary access through the access port. In preferred embodiments, the latch 10 has a symmetrical construction about a central axis A shown in FIG. 2. For this reason, the latch 10 is illustrated from only one side in FIGS. 1-7. Along the central axis A, the reference point for the terms proximal and distal is the head 14b of the bolt 14, which abuts the aircraft frame AF when the latch 10 is closed.

[0026] The latch 10 generally includes a base 12, a pivotable latch bolt 14, and a bias-adjustable bolt actuator, generally designated by reference numeral 16. In preferred embodiments, the lock bolt 14 is pivotally connected to the proximal end 12a of the base 12, while the bolt actuator 16 is mounted on the distal end 12b of the base 12. As described in greater detail below, the bolt actuator 16 performs multiple functions. First, it moves the latch bolt 14 between open and closed positions by application of a manual force to the manual actuator arm 37 described below. Second, it locks the latch bolt 14 in the closed position with sufficient force so that the door panel DP does not open during normal flight conditions. Third, it unlocks and moves the latch bolt 14 from the closed position to the open position when a predetermined opening force is applied to the interior of door panel DP usually caused by an excessive build-up of pressure inside the aircraft housing.

[0027] In the embodiment shown in FIGS. 1-7c, the base 12 has a generally-planar, irregular shape including opposed, proximal mounting tabs 20a, opposed, distal mounting tabs 20b, a central aperture 22, a top side 12c, and a bottom side 12d. Because the latch 10 can be utilized on door panels DP having a variety of orientations, the term bottom side 12d refers to the side of the base 12 that abuts the door panel DP when the latch 10 is fastened thereto, while the top side 12c refers to the opposite side to which the several structural elements of the latch 10 are mounted. Each tab 20 has an aperture 21 through which a fastener (not shown) is inserted to mount the latch 10 on the inner surface of the door panel DP as shown in FIG. 7a.

[0028] The door panel DP is pivotally connected to the aircraft frame AF by one or more hinges (not shown) at a hinged end so that the opposed latch end of the door panel can swing between open and closed positions. In preferred embodiments, the latch 10 is mounted close enough to the latch end of the door panel DP so that the head 14b of the latch bolt 14 can engage and abut the inner surface of the aircraft frame AF surrounding the door panel and prevent the door panel DP from opening until a predetermined internal air pressure is exceeded or the latch is intentionally opened by an operator. In the embodiment shown in FIGS. 7a-c, the door panel DP can only swing outwardly from its closed position relative to the aircraft frame AF; however, it should be appreciated by those of ordinary skill in the art that the latch 10 would work similarly and just as effectively if mounted on the outside of a door panel that is only capable of swinging inwardly if an excessive negative pressure built up in the inside of the door panel DP.

[0029] Referring to FIGS. 4 and 5, the base 12 includes a pair of opposed, proximal hinge brackets 24 and distal hinge brackets 26, both of which are fixed to and project from the top side 12c. The brackets 24, 26 have opposed outer planar surfaces 24a, 26a and opposed inner planar surfaces 24b, 26b, which extend transverse to the plane of the top side 12c of the base 12. The brackets 24, 26 have a circular bore 25, 27, respectively, extending through the planar surfaces of the brackets 24, 26 and having a central axis extending transverse to the planar surfaces 24a, 24b and 26a, 26b, respectively, and generally parallel to the plane of the top side 12c of the base 12. Each bore 25, 27 supports the ends of a proximal and distal pivot pin 29, 31, respectively, as described below. Each of the distal brackets 26 has a spring capture slot 33 extending through the planar surfaces 26a, 26b, and a threaded bore 35 extending from the edge surfaces 26c of the bracket 26 to the spring capture slot 33. A calibration screw 34 engages the threaded bore 35 and is long enough so that a portion extends into the spring capture slot 33 as best seen in FIGS. 3 and 4.

[0030] In the embodiment shown in FIGS. 1-7c, the central aperture 22 in the base 12 has a generally-square shape having dimensions slightly larger than the head 39 of a manual actuator arm 37 (described below), which is used to lock the latch 10 by depressing the head 39 with force sufficient to overcome the locking force of the bolt actuator 16, or open the latch 10 by prying the head 39 outwardly using a tool, such as a flathead screwdriver, inserted in a slot 41 formed in the head 39.

[0031] Referring to FIGS. 1 and 3, the latch bolt 14 has an elongate shank 14a with an integrally-formed head 14b at the proximal end, and integrally-formed hinge brackets 14c in the middle for attachment to the proximal pivot pin 29 and proximal hinge brackets 24. In a preferred embodiment shown in FIGS. 1-7c, the latch bolt 14 is formed from a pair of distally-spaced plates 45 oriented parallel to one another, and a pair of transversely-extending struts 47a, 47b fixed to the proximal ends of the parallel plates 45. In the embodiment shown in FIGS. 1-7c, the struts 47a, 47b have the form of rectangular plates, one or more of which may be integrally formed with the parallel plates 45 or fastened to the plates 45 using welding or other attachment means. When the bolt 14 is configured in the closed position, one strut 47a is aligned in a plane generally parallel to the plane of the base 12, while the second strut 47b is aligned generally transverse to the plane of the base 12. In preferred embodiments, a bumper 49 is fixed to the first strut 47a and is preferably made from an elastomeric material. In this preferred embodiment, the bumper 49 is affixed to the first strut 47a by fasteners that extend through bores 51 in the first strut 47a. As described below, the bumper 49 abuts the aircraft frame AF when the latch is closed and, because it is elastomeric, the bumper 49 compresses to accommodate a small amount of deviation in the thickness of the aircraft frame AF.

[0032] The distal end of the bolt shank 14a is connected to the bolt actuator 16. In one preferred embodiment, the bolt actuator 16 comprises a toggle linkage, designated generally by reference numeral 53, a linkage tensioner designated generally 55, and the manual actuator arm 37. In one preferred embodiment, the toggle linkage 53 comprises a first link pivotally connected to the distal end of the bolt shank 14a and a second link pivotally connected to the distal end of the base 12. The links are pivotally connected to one another.

[0033] As best seen in FIG. 4, the first link comprises a pair of opposed restraining arms 59, each of which is pivotally connected the distal end of the latch shank 14a by a first linkage pin 61 and separated by a spacer 62. The second link comprises a lever arm 65, which is pivotally connected at one end to the restraining arms 59 by a second linkage pin 63 and is centrally located between the restraining arms 59 by a pair of spacers 64. The other end of the lever arm 65 is pivotally connected to the base 12 by the distal pivot pin 31. Alignment of the restraining arms 59 and lever arm 65 is important for creating proper force transmission through the latch 10.

[0034] In a preferred embodiment, the manual actuator arm 37 is integrally formed with the bolt shank 14a. In this embodiment, the manual actuator arm 37 comprises a pair of plate extensions 71 of the parallel bolt plates 45, which are co-planar with the bolt plates 45 but extend transversely to the length of the bolt shank 14a as best seen in FIGS. 1 and 3.

[0035] Referring to FIG. 5, a plurality of transverse side struts 73 and a transverse bottom strut 74 (relative to the orientation shown in FIG. 1) extend between and join the plate extensions 71. The actuator head 39 is fixed to the ends of the plate extensions 71. Application of a force to the head 39, either in depression or retraction, causes the latch bolt 14 to rotate about the proximal pivot pin 29. An elongated slot 41 is formed in the head 39, which is constructed to receive the head of a work tool to retract the head 39 by prying. Preferably, the slot 41 extends through the head so that any condensation that forms in the slot 41 will drain through the slot and through a drain hole 75 in the bottom strut 74. As used in this paragraph, transverse refers to a direction relative to the plane of the plate extensions 71.

[0036] Those of ordinary skill in the art should appreciate that the manual actuator arm 37 need not be integrally formed with the bolt shank so long as its construction can exert a rotational force on the latch bolt 14 sufficient to overcome the locking force of the toggle linkage 53. For example, the plate extensions 71 could comprise separate structural elements pivotally connected to the proximal pivot pin 29, or separate structural elements pivotally connected to the bolt shank 14a at a location different than the pivot pin 29.

[0037] In this preferred embodiment, the manual actuator arm 37 is long enough so that the head 39 extends through the central aperture 22 in the base 12 and sits higher than the base 12 as best seen in FIG. 3. This spatial differential allows the head 39 to sit flush with the outer surface of the door panel DP within a cutout in the door panel as best seen in FIG. 7a.

[0038] In a preferred embodiment shown in FIGS. 1-7c, the linkage tensioner 55 comprises a pair of torsion coil springs 67 surrounding the distal housing pivot pin 31 on opposed sides of the lever arm 65. Each coil spring 67 has a pair of legs 67a, 67b. For easier rotation, the coil springs 67 are seated on bushings 77 surrounding the distal pivot pin 31 as best seen in FIG. 5. The first leg 67a engages the spacers 64 on the second linkage pin 63 that surround the lever arm 65. The second leg 67b is seated in the spring capture slot 33 of its respectively-adjacent distal hinge bracket 26. When the latch is oriented in the closed position, the first legs 67a exert a predetermined force on the latch bolt 14 based on the degree of deflection of the springs 67 from their free position.

[0039] The linkage tensioner 55 includes a mechanism for calibrating the tension exerted by the coil springs 67. In one preferred embodiment, the calibration mechanism adjusts the tension by changing the degree of rotation of the springs when they are preloaded. In this embodiment, the calibration mechanism comprises the spring capture slot 33 and the calibration screw 34. The capture slot 33 is longer than the diameter of the first leg 67a to allow movement/position adjustment along the length of the slot 33. In the closed position, each spring 67 is deflected in the clockwise direction (relative to the image shown in FIG. 3) from its free position so that the second leg 67b is biased in a downward direction (relative to the image shown in FIG. 3) until it contacts the calibration screw 34. The torsional bias force of the second leg 67b on the second linkage pin 63 is adjusted by extending or retracting the portion of the calibration screw 34 that extends into the capture slot 33, which causes the degree of deflection of the torsion spring 67 to increase or decrease, respectively. In the embodiment shown in FIGS. 1-7c, the torsion spring bias force is increased by extending the calibration screw 34 into the capture slot 33 and pushing the base end 67a of the spring 67 toward the bottom of the slot 33. In contrast, the torsional spring force is reduced by retracting the calibration screw 34 and allowing the base end 67a of the spring 67 to move toward the top of the slot 33.

[0040] Preferably, a second torsion spring 69 is mounted on and surrounds the proximal base hinge pin 29. One leg of the spring 69 abuts the bolt shank 14a while the other abuts the base 12. The second torsion spring 69 is oriented so that it normally urges the latch bolt toward the open position as shown in FIG. 7c.

[0041] Operation of the latch 10 is illustrated in FIGS. 7a-c, which show the latch installed on an aircraft door panel DP. FIG. 7a (along with FIGS. 1-4) shows the latch 10 oriented in the closed position. In this orientation, the latch bolt 14 is restrained in the closed position by a counterclockwise locking force exerted on the latch bolt 14 by the bolt actuator 16. In FIG. 7a, the locking force is illustrated by force vector LF. More specifically, the restraining arms 59 of the toggle linkage 53 exert a locking force LF on the first linkage pin 61, which is connected to the shank 14a of the latch bolt 14. That locking force LF exerts a counterclockwise moment on the latch bolt 14 about the proximal pivot pin 29, which causes the latch bolt 14 to rotate until the head 14b abuts the aircraft frame AF. The moment is in the counterclockwise direction because the force vector LF is skew to an over-center axis C between the second linkage pin 63 and the proximal pivot pin 29. The magnitude of the counterclockwise moment created by the locking force LF at the first pivot pin 29 is directly proportional to the angle theta (0) formed between the over-center axis C and the locking force vector LF as shown in FIG. 7a. More specifically, the magnitude of the locking force LF creating the counterclockwise moment is equal to the locking force LF multiplied by the sine of the angle theta (8) formed between the over-center axis and the locking force vector LF as shown in FIG. 7a. In this orientation, the greater the angle theta, the greater the clockwise force created by the internal pressure of the compartment on the latch bolt head 14b (or, alternatively, bumper 49) would be required to overcome the locking force LF. When the internal pressure of the compartment is equal to the atmospheric pressure outside the compartment, the clockwise force on the latch bolt head 14b (or, alternatively, bumper 49) is insufficient to overcome the counterclockwise moment at the first pivot pin 29 created by the locking force LF. In this orientation, the force on the latch bolt head 49 created by the internal pressure of the compartment is insufficient to overcome lock force LF.

[0042] As illustrated in FIG. 7a, the portion of the bumper 49 that traverses the phantom lines is meant to illustrate that the bumper 49 compresses because it is elastomeric. In preferred embodiments, the force of the bumper 49 does not cause any depression in the aircraft frame.

[0043] FIG. 7b shows the latch in a partially open position after the internal pressure created a force sufficient to overcome the locking force LF of the bolt actuator 16. More specifically, as the internal pressure on the door panel builds up, the force on the latch bolt head 14a increases to a critical point where the clockwise moment on the latch bolt 14 exceeds the counterclockwise moment of the locking force LF. When this occurs, the latch bolt 14 rotates clockwise causing the first linkage pin 61 to swing past the over-center axis C and the latch 10 unlocks. In this position, internal pressure is relieved through a gap between the door panel DP and the aircraft frame AF sufficient to avoid damage to the internal components.

[0044] When the first linkage pin 61 swings past the over-center axis C, the locking force LF of the bolt actuator 16 transitions from a counterclockwise moment to a clockwise moment until the first leg 67a disengages from the second linkage pin 63. After that point, the rotational force of the second torsion spring 69 continues to move the latch bolt to a more fully-open position shown in FIG. 7c wherein the latch bolt 14 is extending nearly perpendicular to the base 12. In this position, the door panel DP can be fully opened to allow a worker to access the internal components of the aircraft. The partially and fully open positions shown in FIGS. 7b and 7c, respectively, can also be achieved by prying the manual actuator arm 37 open from outside the door panel by using a work tool inserted in the slot 41 in the actuator head 39 to pull the manual actuator arm 37 out.

[0045] Referring to FIG. 7c, when the latch 10 is configured in the fully-open position, the head of the manual actuator arm 39 protrudes from the door panel and is very visible, and remains highly visible until it is returned to the closed position. Therefore, even if the door panel DP is closed, the protruding head 39 serves as a visual safety indicator that the door panel DP is not secured.

[0046] It will be readily understood by those in the mechanical arts that the dimensions of the various components of the invention can be selected to operate as described above without limitation to the particular configuration, proportions and dimensions shown in the preferred embodiment. As such, the invention is to be defined only by the following claims and their legal equivalents.