US3620489A - Runway sheave assembly for aircraft-arresting gear - Google Patents

Runway sheave assembly for aircraft-arresting gear Download PDF

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Publication number
US3620489A
US3620489A US20004A US3620489DA US3620489A US 3620489 A US3620489 A US 3620489A US 20004 A US20004 A US 20004A US 3620489D A US3620489D A US 3620489DA US 3620489 A US3620489 A US 3620489A
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United States
Prior art keywords
sheave
assembly
runway
cover assembly
disposed
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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.)
Expired - Lifetime
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US20004A
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English (en)
Inventor
Harry C Riblett Jr
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All American Industries Inc
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All American Industries Inc
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Assigned to IBJ SCHRODER BANK & TRUST COMPANY, A NEW YORK BANKING CORP., SIEVERS, GEORGE, R. reassignment IBJ SCHRODER BANK & TRUST COMPANY, A NEW YORK BANKING CORP. SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ALL AMERICAN ENGINEERING COMPANY
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/02—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
    • B64F1/027—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables using net or mesh
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/02—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
    • B64F1/029—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables using a cable or tether

Definitions

  • the strong tensioning of the linear payout element during the initial phase of arrestment breaks the shear pins and raises the cover assembly.
  • the cover assembly is then latched in a raised position to maintain the sheave and payout element elevated above ground level and facilitate their action during arrestment of the aircraft.
  • Fairleads and slots smoothly guide the linear payout element under and through the cover assembly, which is efficiently fabricated from a cover plate and a lower plate disposed at an acute angle beneath it.
  • the sheaves are mounted between an inner plate spaced above and parallel to the lower plate and the knee element extends downwardly from the edge of the inner plate remote from the hinge.
  • the cover assembly is of truncated V-shape in plan with its narrow end adjacent the runway and a hinge at its wider opposite end.
  • the cover and inner plates are spaced apart by angular channels disposed parallel to the sides of the assembly and a slotted cross channel is secured between the inner and lower plates.
  • a striker bar for the latch is conveniently made from the extended web of a lateral channel mounted beneath the narrower end of the assemblies.
  • the latches and shear pin retainers are mounted on catch plates secured to the pit ad- 7 jacent the narrow end of the cover assembly.
  • This invention relates to a pit-mounted runway sheave assembly for an aircraft arresting gear and it more particularly relates to an automatically raised device.
  • Sheave assemblies are mounted alongside airport runway to guide and restrain the linear payout element of aircraft-arresting gear during an arrestment.
  • Intermediate cross runway elements are bidirectional and require a pair of sheaves, whereas terminal runway units are unidirectional and only require a single sheave. Since the sheaves are mounted close to or on the edge of the runway, they must not create an above-ground obstruction in the path of aircraft or personnel.
  • U.S. Pat. No. 3,] 82,935 shows an arrangement for holding a runway sheave assembly down in a depression until the aircraft-arresting gear is actuated. It utilizes a lifting motor, thus complicating the device and its control and making it subject to malfunction.
  • An object of this invention is to provide a pit-mounted runway sheave assembly which is simple, rugged and dependable In operation.
  • the sheave or pair of sheaves are mounted beneath a hinged cover assembly disposed within a pit prior to activation.
  • the linear payout element is deflected into a deep bend under the cover assembly by a knee element in line with the sheave.
  • the cover assembly is releasably locked in a closed position to permit the payout element to be pretensioned a predetermined amount without raising the cover assembly.
  • the substantially deep bend creates an upwardly directed component of force in response to tensioning of the payout element, which is sufficient during the initial phase of arrestment to exceed the predetermined upward force for releasing the lock. This quickly elevates the cover assembly in response to the resultantly strong tensioning of the payout element.
  • a latch holds the cover assembly and its sheave and payout element elevated above ground level during arrestment of the aircraft to facilitate their action.
  • the payout element on both sides of the sheave assembly may be disposed above ground level and fairleads and suitable slots are provided for smoothly guiding the payout element under and through the cover assembly.
  • the cover assembly is efficiently fabricated from a cover plate and a lower plate disposed at an acute angle below it and which are connected adjacent the hinge.
  • the sheave is mounted between an inner plate spaced above and parallel to the lower plate, and the knee element extends downwardly from the edge of the inner plate remote from the hinge.
  • An advantageous form of cover assembly is a truncated V-shape in plan with its narrow end adjacent the runway and its hinge at the wider opposite end.
  • the cover and inner plates are spaced apart by angular channels disposed parallel to the sides of the assembly, and a slotted cross channel is secured between the inner and lower plates.
  • a striker bar for the latch is conveniently comprised of the extended web ofa lateral channel mounted beneath the narrower end of the cover assembly, which engages the latches on catch plates secured to the walls of the pit.
  • These catch plates may also include shear pin retainers for locking the cover assembly down in the closed position.
  • FIG. 3 is a plan view partially broken away of the embodiment shown in FIGS. 1 and 2;
  • FIG. 4 is a cross-sectional view taken through FIG. 3 along the line 4-4;
  • FIG. 5 is a cross-sectional view in elevation of the embodiment shown in FIGS. 1, 3 and 4 in the raised position;
  • FIG. 6 is a cross-sectional view taken through FIG. 5 along the line 6-6;
  • FIG. 7 is a cross-sectional view taken through FIG. 5 along the line 7-7;
  • FIG. 8 is a cross-sectional view of another embodiment of this invention in the raised activated position.
  • FIG. 9 is a cross-sectional view in elevation of the embodiment shown in FIG. 8 in the closed lowered position.
  • FIG. 1 a pair of pit-mounted runway sheave assemblies 10 for an aircraft-arresting gear 12 having a linear payout element 14 connecting a cross runway element 16 with energy absorber 18.
  • Cross runway pendant I6 is, for example, steel cable or a nylon rope as described in US. Pat. No. 3,456,908.
  • Linear payout element 14 is, for example, nylon tape or steel cable as described in US. Pat. No. 3,467,347.
  • Energy absorber I8 is, for example, of the type described in US. Pat. No. 3,172,625, which also describes a nylon tape suitable for use as linear payout element [4.
  • Tape I4 is connected to cross runway pendant 16 by connector 20.
  • Hook 22 on aircraft 24 engages pendant 16 during the arrestment shown in FIG. 1.
  • Hook 22 is, for example, of the type shown in US. Pat. No. 2,989,272. This arrestment raises sheave assembly 10 from the closed lower position shown in FIG. 2 to the raised position shown in FIG. 1 as later described in detail.
  • FIGS. 3 and 4 show sheave assembly 10 in the lowered position in which the portions of tape 14 at the entrance end 26 and exit end 28 are disposed flat to the ground in contact with entrance fair-lead 30 and exit fair-lead 32 mounted at the corresponding edges of pit 34 through slots 108 and 110.
  • the sheave assembly is mainly comprised of a cover assembly 36 which is a truncated V-shape in plan with its narrower end 38 disposed adjacent the runway and its wider end 40 oppositely disposed and rotatably connected to the corresponding entrance wall 42 of pit 34 by hinge 44 secured to wall 42 by anchoring beam 46.
  • Hinge 44 includes a pair of hinge arms 48 connected to the wider end 40 of cover assembly 36.
  • Cover assembly 36 includes a cover plate 50 and an angularly disposed lower plate 52.
  • An inner plate 54 is spaced below cover plate 50 by a pair of angular channels 56 disposed substantially parallel to the sides of the narrow end 38 of cover plate 50 as shown in FIG. 3.
  • Inner plate 54 is spaced parallel and above lower plate 52 by slotted cross channel 58 having a central slot 60 to provide a path for tape I4.
  • a pair of sheaves 62 are rotatably mounted between inner plate 54 and lower plate 52 and tape 14 passes between them thus making sheave assembly 10 bidirectional in action. As shown in FIGS. 3 and 4, the portion of tape 14 between entrance section 26 and sheaves 62 is twisted approximately
  • a knee element 64 is mounted below cover assembly 36 remote from hinge 44.
  • Tape 14 is thus deflected in a deep bend within pit 34 as shown in FIG. 4.
  • the portion of tape 14 between sheaves 62 and knee 64 is twisted in an additional 90 to make tape 14 twist approximately from entrance fairlead 30 to knee 64 and exit fair-lead 32.
  • Striker channel 66 is mounted under the end of lower plate 52 remote from hinge 44. It includes web extensions 68 shown in FIG. 7 which engage latches 70 secured to catch plates 72 mounted at the narrow end of pit 34 and connected to frame 74 about the perimeter of pit 34. The action of latches 70 is later described in detail in conjunction with FIGS. 5 and 6.
  • a pair of releasable locks provided by shear pin assemblies 76 connects the narrow end 38 of cover plate 50 to catch plates 72 to releasably lock it in a closed position. This permits tape 14 to be pretensioned a predetermined amount without raising cover assembly 10.
  • Shearable assemblies 76 include shear pin retainers 78, catch plates 72 and shear pins 80 which engage over the narrow end of cover plate 50.
  • the rewind motor 82 in energyabsorber I8 is actuated to pretension tape 14, for example, about l,500 lbs. to hold cross runway pendant 16 straight across runway 84 in position for engaging landing aircraft 24.
  • Shear pins 80 are designed to hold cover assembly 36 in the closed position against this pretensioning load.
  • FIGS. -7 show the condition of sheave assembly in the raised position of FIG. 1.
  • the substantially deep bend of tape 14 shown in FIG. 4 below cover assembly 36 creates an upwardly directed component of force along tape section 86 between knee 64 and exit fair-lead 32.
  • This upwardly directed component of force designated by arrow 88 is sufficient during the initial phase of arrestment shown in FIG. 1 to exceed the breaking strength of shear pins 80 and thus raise cover assembly 36 in response to the resultantly strong tensioning of tape 14 by the initial shock of engagement of aircraft 24 with pendant 16.
  • This strong shock forcibly rotates cover assembly 36 upwardly from pedestal 89 at the bottom of pit 34 into the raised position shown in FIGS. 5-7.
  • Web extensions 68 of striker channel 66 engage latch 70 to hold cover assembly 36 in the raised position.
  • sheave assembly 10 Additional structural features include frame 74 within which cover plate 50 nests in the lowered position shown in FIGS. 2-4 to allow it to smoothly traverse aircraft wheels over it.
  • Inner plate 54 also includes a pair of lateral extensions 92 secured under the hinged portion of cover plate 50.
  • FIG. 6 shows vertical slot 94 in knee 64. It provides apath for tape 24 when cover assembly 36 is in the raised position shown in FIGS. 5 and 6.
  • FIGS. 8 and 9 show runway sheave assembly 10A which is adapted for use with a cross runway net 16A instead of cross runway pendant 16X.
  • the axis of rotation 96A ofsheaves 62A is thus inclined at an oblique angle to the ground 98A to incline tape 14A for direct connection to the end of net 16A.
  • a restraining and deflecting roller 100A is mounted between roller 96A and energy absorber 18A to prevent tape 14A from being lifted above the line of action of sheave 62A during arrestment. Only one sheave 62A is provided because nets, such as 16A, arenormally mounted at the terminal ends of the runway and only unidirectional action need be provided.
  • runway sheave assembly 62A and its associated net 16A and energy absorber 18A is their complete underground installation.
  • Energy absorber 18A is mounted in pit l02A and with a substantial horizontal axis of rotation to provide an untwisted section 104A of tape 14A from energy absorber 18A to horizontal roller 100A.
  • Horizontal roller 100A cooperates with entrance fair-lead 30A to confine tape 14A between them.
  • tape 14A from knee 64A is guided through covered trough 103A over entrance fair-lead 32A to net 16A which is stored in the unactivated condition within a cross runway trough 106A.
  • a net installation of such type is, for example, described in US. Pat. No. 3,058,703. The entire installation is thus maintained below ground level and out of the path of personnel and aircraft prior to activation. This below ground installation is shown in conjunction with a terminal runway system, but is even more advantageous in an intermediate runway position, which is more subject to aircraft and personnel ground traffic.
  • the canted position of sheave 62A shown in FIG. 8 provides a direct efficient line of action therebetween and prevents rubbing of the edge of 14A on flanges (not shown) which might be provided on sheave 62A. Such edge rubbing has been the source of extensive friction and wear.
  • sheave assembly 10 Prior to actuation, sheave assembly 10 is in the lowered closed position shown in FIG..2. The pretensioning of tape 14 causes portion 26 entering sheave assembly 10 and portion 28 leaving sheave assembly 10 to lie flat against the ground. This maintains cover plate 50 and runway pendant 16 in firm smooth contact with the ground to prevent them from interfering with personnel and aircraft trafiic.
  • Landing aircraft 24 shown in FIG. 1 engages pendant 16 by hook 22 and exerts a strong tensioning force on pendant l6 and connected tape 14.
  • the locking action of shear pins first prevents cover assembly 36 from rising and holds it in a lowered position shown in FIGS. 2-4, until the breaking strength of shear pins 80 is exceeded.
  • a strong component of force illustrated by arrow 88 in FIG. 4 reacts upwardly against knee 64 which snaps cover assembly 36 up to the raised position shown in FIGS. 5 and 6.
  • Tape 14 untwists from the 180 bend of the lowered position in FIGS. 2-4 to assume the vertical untwisted position of FIGS. 1. 5 and 6.
  • Slot 94 in the center of knee 64 provides an unimpeded path for tape 14 in the activated position.
  • Bumper pads smoothly arrest the upward movement of cover assembly 36 by stopping the upward movement of web extensions 68 on striker channel 66. Webs 68 also engage over latches 70 to hold cover assembly 36 in the raised position during arrestment and rewind.
  • sheave assembly 10A in FIGS. 8-9 is similar to that previously described with the exception of the use of single sheave 62A, the connection to net [6A, the advantageous inclination of sheave 62A and the complete below-ground installation of the system. Also as shown in FIGS. 8 and 9, no twist ever occurs in the portion 104A of tape 14A between energy absorber 18A and opposed deflecting roller A and fair-lead 30A.
  • a pit-mounted runway sheave assembly for an aircraft arresting gear having a linear payout element connecting a cross runway element with an energy absorber comprising a cover assembly, horizontal hinge means connecting said cover assembly to a side of said pit to provide raising and closing movement thereof, a knee element mounted beneath said cover assembly remote from said hinge means and extending downwardly below it, rotatable sheave means mounted beneath said cover assembly between said knee element and said hinge means, said knee element being long enough to indent said linear payout element downwardly into a substantially deep bend into said pit, locking means which is releasable at a predetermined upward force securing said cover assembly to a wall of said pit when said cover assembly is down in the closed position whereby said linear payout element may be pretensioned a predetermined amount without raising said cover assembly, said substantially deep bend creating an upwardly directed component of force in response to tensioning of said payout element which is sufficient during the initial phase of arrestment to exceed said predetermined upward force for releasing said locking means whereby said cover assembly is allowed to rise in response to the resultantly
  • a runway sheave assembly as set forth in claim I wherein said locking and latching means are mounted on a pair of catch plates mounted on the walls of said pit remote from said hinge means, said locking means comprising shear pin means and shear pin receiving means in said catch plates and on the upper portion of said cover assembly adjacent said plates when said assembly is in closed position and said latch means comprising latches mounted upon said catch plates and striker bars on a lower portion of said cover assembly for engaging said latches when said cover assembly is in said raised position.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Operating, Guiding And Securing Of Roll- Type Closing Members (AREA)
  • Pulleys (AREA)
  • Footwear And Its Accessory, Manufacturing Method And Apparatuses (AREA)
  • Refuge Islands, Traffic Blockers, Or Guard Fence (AREA)
US20004A 1970-03-16 1970-03-16 Runway sheave assembly for aircraft-arresting gear Expired - Lifetime US3620489A (en)

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US (1) US3620489A (enExample)
DE (1) DE2056335B2 (enExample)
FR (1) FR2083298B1 (enExample)
GB (1) GB1300456A (enExample)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6758440B1 (en) * 2003-03-21 2004-07-06 Curtiss-Wright Electro-Mechanical Corporation Electromagnetic aircraft arrestor system
US20100143033A1 (en) * 2006-03-15 2010-06-10 Metzger John C Vehicle barrier
WO2019199390A1 (en) * 2018-04-09 2019-10-17 Engineered Arresting Systems Corporation Tape elevation adjustment device for aircraft arresting systems
WO2020068167A2 (en) 2018-05-03 2020-04-02 Engineered Arresting Systems Corporation Retractable runway edge sheave
US11148829B2 (en) * 2018-05-03 2021-10-19 Engineered Arresting Systems Corporation Arresting cable retraction system

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2720386C1 (ru) * 2019-10-16 2020-04-29 Владимир Иванович Винокуров Устройство для торможения самолета
CN110979713B (zh) * 2019-12-25 2023-04-07 湖南省地面无人装备工程研究中心有限责任公司 无人机回收装置

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB916588A (en) * 1960-10-26 1963-01-23 John Brown S E N D Ltd Improvements in or relating to devices for arresting aircraft on runways
US3182935A (en) * 1964-07-30 1965-05-11 William J G Wischhoefer Vehicle arresting gear system

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB916588A (en) * 1960-10-26 1963-01-23 John Brown S E N D Ltd Improvements in or relating to devices for arresting aircraft on runways
US3182935A (en) * 1964-07-30 1965-05-11 William J G Wischhoefer Vehicle arresting gear system

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6758440B1 (en) * 2003-03-21 2004-07-06 Curtiss-Wright Electro-Mechanical Corporation Electromagnetic aircraft arrestor system
WO2005000673A1 (en) * 2003-03-21 2005-01-06 Curtiss-Wright Electro-Mechanical Corporation Electromagnetic aircraft arrestor system
US20100143033A1 (en) * 2006-03-15 2010-06-10 Metzger John C Vehicle barrier
US7901155B2 (en) * 2006-03-15 2011-03-08 Taylor Devices, Inc. Vehicle barrier
WO2019199390A1 (en) * 2018-04-09 2019-10-17 Engineered Arresting Systems Corporation Tape elevation adjustment device for aircraft arresting systems
US11148828B2 (en) 2018-04-09 2021-10-19 Engineered Arresting Systems Corporaiton Tape elevation adjustment device for aircraft arresting systems
WO2020068167A2 (en) 2018-05-03 2020-04-02 Engineered Arresting Systems Corporation Retractable runway edge sheave
KR20210003265A (ko) * 2018-05-03 2021-01-11 엔지니어드 어레스팅 시스템즈 코포레이션 철회 가능한 활주로 에지 시브
JP2021524822A (ja) * 2018-05-03 2021-09-16 エンジニアード・アレスティング・システムズ・コーポレーションＥｎｇｉｎｅｅｒｅｄ Ａｒｒｅｓｔｉｎｇ Ｓｙｓｔｅｍｓ Ｃｏｒｐｏｒａｔｉｏｎ 格納式滑走路端滑車
US11136142B2 (en) 2018-05-03 2021-10-05 Engineered Arresting Systems Corporation Retractable runway edge sheave
US11148829B2 (en) * 2018-05-03 2021-10-19 Engineered Arresting Systems Corporation Arresting cable retraction system

Also Published As

Publication number Publication date
DE2056335A1 (de) 1971-09-23
FR2083298B1 (enExample) 1974-03-22
DE2056335C3 (enExample) 1974-05-02
GB1300456A (en) 1972-12-20
FR2083298A1 (enExample) 1971-12-17
DE2056335B2 (de) 1973-10-04

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AS Assignment

Owner name: SIEVERS, GEORGE, R.

Free format text: SECURITY INTEREST;ASSIGNOR:ALL AMERICAN ENGINEERING COMPANY;REEL/FRAME:004886/0088

Effective date: 19880520

Owner name: IBJ SCHRODER BANK & TRUST COMPANY, A NEW YORK BANK

Free format text: SECURITY INTEREST;ASSIGNOR:ALL AMERICAN ENGINEERING COMPANY;REEL/FRAME:004886/0088

Effective date: 19880520