Single use logistic glider

• US 10,040,549 B2
• Filed: 09/25/2017
• Issued: 08/07/2018
• Est. Priority Date: 09/27/2016
• Status: Active Grant

• Current Assignee: Logistic Gliders Inc.
• Original Assignee: Logistic Gliders Inc.
• Inventors: Sarigul-Klijn, Martinus M., Gionfriddo, Maurice P., Sarigul-Klijn, Nesrin
• Primary Examiner(s): Bonzell, Philip J
• Application Number:
  US15/715,016
• Publication Number:
  US 20180086449A1
• Time in Patent Office: 316 Days
• CPC Class Codes: B64C 2001/0063 from wood
• CPC Class Codes: B64C 25/52 Skis or runners
• CPC Class Codes: B64C 3/185 Spars
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 31/02 Gliders, e.g. sailplanes hang-gliders B64C31/028
• CPC Class Codes: B64D 17/80 in association with aircraft, e.g. for braking thereof

Abstract

A disposable airdropped glider. The glider body is constructed from precut panels cut from (MDO) or (HDO) plywood and assembled with pocket-screw joinery or piano hinges. A skid board forms a landing surface and a cargo deck roll-off surface. The glider has pivoting wings and struts. The glider has a triple-tail, a flat nose and honeycomb paperboard panels between the nose and the cargo. Wings are pivoted from a position overlying the fuselage to a flying position by gas springs in wing spars which are compressed by a chain attached to the fuselage through a rotating bracket such that the gas springs are compressed when the wings are folded. The airfoils are plastic extrusions with openings that hold the wing spars and co-formed jury spars which attach the upper and lower surface of the wing. A parachute uses a part of the tail structure to form a deployment drogue.

Claims

1. An expendable logistic glider comprising:

a fuselage having a nose and a tail, and a longitudinal axis extending therebetween, portions of the fuselage between the nose and the tail defining a cargo bay;

a fuselage bridging spar which is fixedly mounted to the fuselage;

a port wing spar pivotally mounted to the fuselage bridging spar, and a starboard wing spar pivotally mounted to the fuselage bridging spar, opposite the port wing spar;

wherein the port wing spar extending at least partly through a rigid airfoil to form a port wing;

wherein the starboard wing spar extending at least partly through a rigid airfoil to form a starboard wing;

a first source of stored energy mounted within the port wing to act on a first anchor attached to the fuselage to rotate the port wing from a first position at least partially over the fuselage to a second position perpendicular to the longitudinal axis of the fuselage;

a second source of stored energy mounted within the starboard wing to act on a second anchor attached to the fuselage to rotate the starboard wing from a first position at least partially over the fuselage to a second position perpendicular to the longitudinal axis of the fuselage.

2. The logistic glider of claim 1 wherein the first source of stored energy is a gas spring mounted within the port wing spar, the gas spring attached to a flexible member which is attached to the first anchor such that the gas spring is acted on by the flexible member to compress the gas spring when the port wing is in the first position at least partially over the fuselage, and the gas spring acts on the flexible member to pivot the port wing to the second position perpendicular to the longitudinal axis of the fuselage;

and wherein the second source of stored energy is a gas spring mounted within the starboard wing spar, the gas spring attached to a flexible member which is attached to the second anchor such that the gas spring is acted on by the flexible member to compress the gas spring when the starboard wing is in the first position at least partially over the fuselage, and the gas spring acts on the flexible member to pivot the starboard wing to the second position perpendicular to the longitudinal axis of the fuselage.

3. The logistic glider of claim 2 wherein the gas spring within the port wing spar is formed by two gas spring pistons having first ends connected to a bracket, wherein the flexible member is also connected to the bracket;

wherein two gas spring pistons having second ends connected to the port wing spar adjacent to portions of the port wing spar which forms an opening through the port wing spar;

a pivot bracket fixedly mounted to an exterior portion of the port wing spar adjacent to the opening through the port wing spar, the pivot bracket mounted to a pivot shaft which is mounted to the fuselage bridging spar to pivotally mount the port wing spar;

a flexible member guide mounted to the pivot bracket and extending away from the port wing spar;

wherein the flexible member extends through the opening through the port wing spar and outwardly from the port wing spar along the guide to the anchor, and

wherein the flexible member guide and the pivot bracket form an arm which applies tension to the flexible member when the port wing is moved from the second position perpendicular to the longitudinal axis of the fuselage, to the first position at least partially over the fuselage so as to compress the two gas spring pistons.

4. The logistic glider of claim 2 wherein the rigid airfoils which form the port and starboard wings have a plastic extrusion having a plurality of jury spars connecting an upper and a lower surface which form the air foil.

5. An expendable logistic glider comprising:

a fuselage having a nose and a tail, and a longitudinal axis extending therebetween, portions of the fuselage between the nose and the tail defining a cargo bay;

two wing spars pivotally mounted to the fuselage on opposite sides of the fuselage;

wherein each wing spar extends through a rigid plastic extrusion having a plurality of jury spars connecting an upper and a lower surface which form a wing;

wherein each wing has a wing strut pivotally connected to the corresponding one of the wing spars, the wing strut pivotally connected to the fuselage spaced vertically from where the wing spar is mounted to the fuselage such that the wing strut pivots with the wing;

a first source of stored energy mounted within the port wing to act on a first anchor attached to the fuselage to rotate the port wing from a first position at least partially over the fuselage to a second position perpendicular to the longitudinal axis of the fuselage;

a second source of stored energy mounted within the starboard wing to act on a second anchor attached to the fuselage to rotate the starboard wing from a first position at least partially over the fuselage to a second position perpendicular to the longitudinal axis of the fuselage.

6. The logistic glider of claim 5 further comprising;

a spring mounted within each wing to act on an anchor attached to the fuselage to rotate the wing from a first position at least partially over the fuselage to a second position perpendicular to the longitudinal axis of the fuselage.

7. The logistic glider of claim 6 wherein the spring is a gas spring mounted within each wing spar, and the gas spring is attached to a flexible member which is attached to an anchor, such that the gas spring is acted on by the flexible member to compress the gas spring when the wing is in the first position at least partially over the fuselage, and the gas spring retracts the flexible member into the wing to pivot the wing to the second position perpendicular to the longitudinal axis of the fuselage.

8. The logistic glider of claim 7 wherein the gas spring within each wing spar is formed by two gas spring pistons having first ends connected to a bracket, wherein the flexible member is also connected to the bracket;

wherein two gas spring pistons having second ends connected to the wing spar adjacent to a portion of the port wing spar which forms an opening through the wing spar;

each wing spar having a pivot bracket fixedly mounted to an exterior portion of the wing spar adjacent to the opening through the wing spar, the pivot bracket mounted to a pivot which is mounted to the fuselage;

a flexible member guide mounted to the pivot bracket and extending away from the wing spar;

wherein the flexible member extends through the opening through the wing spar and outwardly from the wing spar along the guide to the anchor, and

wherein the flexible member guide and the pivot bracket form an arm which applies tension to the flexible member when the wing is moved from the second position perpendicular to the longitudinal axis of the fuselage, to the first position at least partially over the fuselage so as to compress the two gas spring pistons.