Energy absorbing landing gear/tail skid including means for indicating the magnitude of impact loads

• US 5,927,646 A
• Filed: 09/14/1995
• Issued: 07/27/1999
• Est. Priority Date: 09/14/1995
• Status: Expired due to Fees

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Furnes, Kenneth M., Sandy, David F.
• Primary Examiner(s): Jordan, Charles T.
• Assistant Examiner(s): MONTGOMERY, CHRISTOPHER KEITH
• Application Number:
  US08/612,947
• Time in Patent Office: 1,412 Days
• Field of Search: 244/108, 244/109, 188/377
• US Class Current: 244/108
• CPC Class Codes: B64C 2025/005 Tail skids for fuselage tail strike protection on tricycle landing gear aircraft
• CPC Class Codes: B64C 25/52 Skis or runners
• CPC Class Codes: B64C 25/64 using rubber or like elements
• CPC Class Codes: B64D 2045/008 Devices for detecting or indicating hard landing
• CPC Class Codes: F16F 2236/06 Tension
• CPC Class Codes: F16F 7/121 the members having a cellular, e.g. honeycomb, structure
• CPC Class Codes: F16H 2035/103 with drive interruption by structural failure of overload preventing means, e.g. using shear pins

Abstract

A landing gear/tail skid having at least two pivot axes (22, 24) which are subject to relative motion in response to impact loads acting on the landing gear/tail skid (10) and a contact arm (18) disposed in combination with pivot axes (22, 24). The cartridge assembly (20) includes a housing member (30) having and internal chamber (38) and a telescoping piston assembly (40) mounting within the internal chamber (38) wherein the end portions of each are disposed in combination with one of the pivot axes (22, 24). The housing member (30) and piston assembly (40), in combination, define opposed bearing surfaces (36s, 46s) which act on an energy absorbing means (50) disposed within the internal chamber (38) and intermediate the opposed bearing surfaces (36s, 46s). The energy absorbing means (50) is operative, in response to impact loads coupled thereto by the opposed bearing surfaces (36s, 46s), to react impact loads below a threshold is value without change in its critical dimension (L_c) and is further operative to absorb and dissipate energy of impact loads at least equal to the threshold value by changes in its critical dimension (L_c). The contact arm (20) further includes an indication means (60) for visually indicating changes to the critical dimension (L_c) of the energy absorbing means (50) wherein the changes are indicative of the magnitude of the impact loads acting on the landing gear/tail skid (10).

Claims

1. A landing gear/tail skid (10) having at least two pivot axes (22, 24) subject to relative motion in response to impact loads acting on the landing gear/tail skid (10), and including:

a cartridge assembly (20) including;

a housing member (30) having an internal chamber (38) and an end portion (30e) disposed in combination with one of the pivot axes (22, or

     24);

a telescoping piston assembly (40) mounted within said internal chamber (38) of said housing member (30) and having an end portion (40e) disposed in combination with the other of the pivot axes (22, or

     24);

said housing member (30) and telescoping piston assembly (40), in combination, defining opposed bearing surfaces (36s, 46s);

the landing gear/tail skid (10) being characterized by;

energy absorbing means (50) having a critical dimension (L_c) and disposed within the internal chamber (38) intermediate the opposed bearing surfaces (36s, 46s);

said energy absorbing means (50) operative, in response to impact loads coupled thereto by said opposed bearing surfaces (36s, 46s), for reacting impact loads below a threshold value without change in said critical dimension (L_c);

said energy absorbing means (50) being further operative, in response to impact loads coupled thereto by the opposed bearing surfaces (36s, 46s), for absorbing and dissipating energy of impact loads at least equal to said threshold value by changes in said critical dimension (L_c); and

indication means (60) for visually indicating changes in said critical dimension (L_c) of said energy absorbing means (50);

said changes in said critical dimension (L_c) being indicative of the magnitude of the impact loads imposed on the landing gear/tail skid (10);

wherein the housing member (30) includes a reference surface (36rs), and wherein the housing member (30) and said energy absorbing means (50) include aligned apertures (52,

     70), and wherein said indication means (60) includes an elongate stem (62) and an integrally formed flange (64), said elongate stem (62) being disposed through said aligned apertures (52,

     70) and said flange (64) being disposed in combination with said energy absorbing means (50), said elongate stem (62) protruding beyond said reference surface (36rs) of said housing member (30) in response to said change in critical dimension (L_c) of said energy absorbing means (50).

2. The landing gear/tail skid (10) according to claim 1 wherein said changes in said critical dimension (L_c) of said energy absorbing means (50) define a maximum deformation, and wherein an indicium (80) on said elongate stem (62) is indicative of said maximum deformation to provide an indication that said threshold value has been exceeded when said indicium (80) is visible.

3. The landing gear/tail skid (10) according to claim 1 wherein said indication means (60) includes a central bore (66) formed through said elongate stem (62) and said integrally formed flange (64), wherein the housing member (30) includes an internal pilot surface (30p), and wherein the telescoping piston assembly (40) includes:

a shaft (42) extending through said central bore (66);

a centering member (44) mechanically coupled to said shaft (42) and having a peripheral surface (44p) disposed in slidable combination with said internal pilot surface (30p) of the housing member (30);

an activating sleeve (46) disposed over and coaxially aligned with respect to said shaft (42), and furthermore interposed between said centering member (44) and said indication means (60), said activating sleeve (46), furthermore, defining the opposed bearing surface (46s) of the piston assembly (40).

4. The landing gear/tail skid (10) according to claim 3 including a coil spring (48) interposed between and abutting said centering member (44) and said flange (64) for maintaining the position of said indication means (60) relative to said reference surface (36rs) of said housing member (30).

5. A landing gear/tail skid (10) for protecting and limiting the impact loads acting on the tail section of an aircraft, including:

a mounting fixture (16) for securing the landing/gear tail skid (10) to the aircraft tail section;

a contact arm (18) disposed in pivotable combination with the mounting fixture (16) about a fulcrum axis (19), the contact arm (18) rotating about the fulcrum axis (19) in response to impact loads acting on the landing gear/tail skid (10);

the mounting fixture (16) and contact arm (18) defining pivot axes (22,

     24) which are subject to relative motion in response to rotational displacement of the contact arm (18); and

a cartridge assembly (20) including;

a housing member (30) having an internal chamber (38), a reference surface (36rs), and an end portion (30e) disposed in combination with one of the pivot axes (22, or

     24);

a telescoping piston assembly (40) mounted within the internal chamber (38) of the housing member (30) and having an end portion (40e) disposed in combination with the other of the pivot axes (22, or

     24);

the housing member (30) and telescoping piston assembly (40), in combination, defining opposed bearing surfaces (36s, 46s);

the landing gear/tail skid (10) being further characterized by;

energy absorbing means (50) having a critical dimension (L_c) and disposed within the internal chamber (38) intermediate the opposed bearing surfaces (36s, 46s);

the energy absorbing means (50) operative, in response to impact loads coupled thereto by the opposed bearing surfaces (36s, 46s), for reacting impact loads below a threshold value without change in said critical dimension (L_c);

said energy absorbing means (50) being further operative, in response to impact loads coupled thereto by the opposed bearing surfaces (36s, 46s), for absorbing and dissipating energy of impact loads at least equal to said threshold value by changes in said critical dimension (L_c);

the housing member (30) and the energy absorbing means (50) including aligned apertures (52,

     70); and

indication means (60) including an elongate stem (62) and an integrally formed flange (64), said elongate stem (62) being disposed through said aligned apertures (52,

     70) and said flange (64) being disposed in combination with said energy absorbing means (50), said elongate stem (62) protruding beyond said reference surface (36rs) of the housing member (30) in response to said changes in critical dimension (L_c) of said energy absorbing means (50);

said changes in said critical dimension (L_c) being indicative of the magnitude of the impact loads imposed on the landing gear/tail skid (10).

6. A cartridge assembly (20) for use in combination with a landing gear/tail skid (10) having at least two pivot axes, (22, 24) which are subject to relative motion in response to impact loads acting on the landing gear/tail skid (10), the cartridge assembly (20) including:

a housing member (30) having an internal chamber (38) and an end portion (30e) disposed in combination with one of the pivot axes (22, or

     24);

a telescoping piston assembly (40) mounted within said internal chamber (38) of said housing member (30) and having an end portion (40e) disposed in combination with the other of the pivot axes (22, or

     24);

said housing member (30) and telescoping piston assembly (40), in combination, defining opposed bearing surfaces (36s, 46s);

the cartridge assembly (2) being characterized by;

energy absorbing means (50) having a critical dimension (L_c) and disposed within the internal chamber (38) intermediate the opposed bearing surfaces (36s, 46s);

said energy absorbing means (50) operative, in response to impact loads coupled thereto by the opposed bearing surfaces (36s, 46s), for reacting impact loads below a threshold value without change in said critical dimension (L_c);

said energy absorbing means (50) being further operative, in response to impact loads coupled thereto by the opposed bearing surfaces (36s, 46s), for absorbing and dissipating energy of impact loads at least equal to said threshold value by changes in said critical dimension (L_c); and

indication means (60) for visually indicating changes in said critical dimension (L_c) of said energy absorbing means (50);

said changes in said critical dimension (L_c) being indicative of the magnitude of the impact loads acting on the landing gear/tail skid (10)

wherein the housing member (30) includes a reference surface (36rs), and wherein the housing member (30) and said energy absorbing means (50) include aligned apertures (52,

     70), and wherein said indication means (60) includes an elongate stem (62) and an integrally formed flange (64), said elongate stem (62) being disposed through said aligned apertures (52,

     70) and said flange (64) being disposed in combination with said energy absorbing means (50), said elongate stem (62) protruding beyond said reference surface (36rs) of said housing member (30) in response to said change in critical dimension (L_c) of said energy absorbing means (50).

7. The landing gear/tail skid (10) according to claim 6 wherein said changes in said critical dimension (L_c) of said energy absorbing means (50) define a maximum deformation, wherein an indicium (80) on said elongate stem (62) is indicative of said maximum deformation to provide an indication that said threshold value has be en exceeded when said indicium (80) is visible.

8. The cartridge assembly (20) according to claim 6 wherein said indication means (60) includes a central bore (66) formed through said elongate stem (62) and said integrally formed flange (64), wherein the housing member (30) includes an internal pilot surface (30p), and wherein the telescoping piston assembly (40) includes:

a shaft (42) extending through said central bore (66);

a centering member (44) mechanically coupled to said shaft (42) and having a peripheral surface (44p) disposed in slidable combination with said internal pilot surface (30p) of the housing member (30);

an activating sleeve (46) disposed over and coaxially aligned with respect to said shaft (42), and furthermore interposed between said centering member (44) and said indication means (60), said activating sleeve (46), furthermore, defining the opposed bearing surface (46s) of the piston assembly (40).

9. The cartridge assembly (20) according to claim 7 including a coil spring (48) interposed between and abutting said centering member (44) and said flange (64) for maintaining the position of said indication means (60) relative to said reference surface (36rs) of the housing member (30).