External load stabilizer

Claim 2

An aircraft having load elevating and lowering means including: a. a winch; b. a single cable connected to said winch for either winding thereon or unwinding therefrom to thereby hoist or lower the load connected thereto; c. a load-stabilizing beam; d. means connecting said load-stabilizing beam to said single cable; e. a cargo-handling and orientating mechanism adapted to be connected to the aircraft and including: 1. a member, generally circular in plan view, shaped to define a restraining slot diametrically thereacross and to further define two substantially symmetrically opposed point sections at the farthest stations from said slot and to still further define smooth camming surfaces between said points and said slot so that any member extending beyond said generally circular member will be cammed into said slot by coaction with said camming surfaces; 2. means adapted to connect said generally circular member to the exterior of an aircraft in such a position that said slot lies in the plane of desired orientation of the load and with the member surrounding the single cable so that as the winch elevates a load, the load-stabilizing beam will engage said camming surfaces and be guided thereby into said slot.

Claim 3

means adapted to connect said generally circular member to the exterior of an aircraft in such a position that said slot lies in the plane of desired orientation of the load and with the member surrounding the single cable so that as the winch elevates a load, the load-stabilizing beam will engage said camming surfaces and be guided thereby into said slot.

Claim 4

means adapted to connect said generally circular member to the exterior of an aircraft in such a position that said slot lies in the plane of desired orientation of the load and with the member surrounding the single cable so that as the winch elevates a load, the load-stabilizing beam will engage said camming surfaces and be guided thereby into said slot.

Claim 5

Apparatus according to claim 1 and including cargo-jettisoning means.

Claim 6

a first substantially U-shaped guidance rod connected to and supported by said connecting means and projecting therefrom so that the legs of the U extend substantially perpendicular to the aircraft and lie in a plane substantially parallel to the plane of selected load orientation and wherein the closed end of the U flares outwardly from the legs of the U;

Claim 7

a first substantially U-shaped guidance rod connected to and supported by said connecting means and projecting therefrom so that the legs of the U extend substantially perpendicular to the aircraft and lie in a plane substantially parallel to the plane of selected load orientation and wherein the closed end of the U flares outwardly from the legs of the U;

Claim 8

a closed loop rod member projecting from and connected to said two rod members and shaped to flare therefrom in a direction away from the plane of selected load orientation and in a direction opposite the flare of the closed loop rod members of the first guide member.

Claim 9

a closed loop rod member projecting from and connected to said two rod members and shaped to flare therefrom in a direction away from the plane of selected load orientation and in a direction opposite the flare of the closed loop rod members of the first guide member.

Claim 10

a closed loop rod member projecting from said spaced rod members and forming a continuation thereof and shaped to flare therefrom in a direction away from said plane of selected load orientation; c. a second guide member connected to and supported by said connecting means and including:

Claim 11

a closed loop rod member projecting from said spaced rod members and forming a continuation thereof and shaped to flare therefrom in a direction away from said plane of selected load orientation; c. a second guide member connected to and supported by said connecting means and including:

Claim 12

a second substantially U-shaped rod connected to and supported by said connecting means and oriented so that the legs of the U project substantially parallel to the aircraft and are parallel to the legs of the first U-shaped rod and spaced therefrom to define a rEstraint slot therebetween extending in the direction selected load orientation and wherein the closed end of the U flares outwardly from the legs of the U in a direction opposite to the direction of the flare of the closed end of the first U-shaped rod so as to cooperate therewith in defining a continuous, enlarged area entry to said restraining slot so that as the winch elevates a load, the load-stabilizing beam will engage said U-shaped rods and be guided thereby into said restraint slot.

Claim 13

a second substantially U-shaped rod connected to and supported by said connecting means and oriented so that the legs of the U project substantially parallel to the aircraft and are parallel to the legs of the first U-shaped rod and spaced therefrom to define a rEstraint slot therebetween extending in the direction selected load orientation and wherein the closed end of the U flares outwardly from the legs of the U in a direction opposite to the direction of the flare of the closed end of the first U-shaped rod so as to cooperate therewith in defining a continuous, enlarged area entry to said restraining slot so that as the winch elevates a load, the load-stabilizing beam will engage said U-shaped rods and be guided thereby into said restraint slot.

Claim 14

a second guide member connected to and supported by said connecting means and including: A. two spaced rod members positioned to project substantially perpendicular from the aircraft and lying in a plane substantially parallel to the plane of selected load orientation and in spaced relation to said two rod members of said first guide member to form a restraint slot therebetween, B. a closed loop rod member projecting from and connected to said two rod members and shaped to flare therefrom in direction away from the plane of selected load orientation and in a direction opposite the flare of the closed loop rod members of the first guide member so that the winch elevates a load, the load stabilizing beam will engage said guide members and be guided thereby in the restraint slot.

Claim 15

a second guide member connected to and supported by said connecting means and including: A. two spaced rod members positioned to project substantially perpendicular from the aircraft and lying in a plane substantially parallel to the plane of selected load orientation and in spaced relation to said two rod members of said first guide member to form a restraint slot therebetween, B. a closed loop rod member projecting from and connected to said two rod members and shaped to flare therefrom in direction away from the plane of selected load orientation and in a direction opposite the flare of the closed loop rod members of the first guide member so that the winch elevates a load, the load stabilizing beam will engage said guide members and be guided thereby in the restraint slot.

Claim 16

Apparatus according to claim 1 and including redundant cargo-jettisoning means.

Claim 17

Cargo-handling and orientating mechanism adapted for use with an aircraft including: a. a member, generally circular in plan view, shaped to define a restraining slot diametrically thereacross and to further define two substantially symmetrically opposed point sections at the farthest stations from said slot and to still further define smooth camming surfaces between said points and said slot so that any member extending beyond said generally circular member will be cammed into said slot by coaction with said camming surfaces; b. means adapted to connect said generally circular member to the exterior of an aircraft in such a position that said slot lies in the plane of desired orientation of the member.

Claim 18

Cargo-handling and orientating mechanism adapted for use with an aircraft including: a. a member, generally circular in plan view, shaped to define a restraining slot diametrically thereacross and to further define two substantially symmetrically opposed point sections at the farthest stations from said slot and to still further define smooth camming surfaces between said points and said slot so that any member extending beyond said generally circular member will be cammed into said slot by coaction with said camming surfaces; b. means adapted to connect said generally circular member to the exterior of an aircraft in such a position that said slot lies in the plane of desired orientation of the member.

Claim 19

Apparatus according to claim 4 wherein said connecting means is of the quick connect-disconnect type.

Claim 20

A guidance cage adapted to be connected to an aircraft and to securely position a load or load-stabilizing bar in selected orientation when being carried by the aircraft and including: a. means to connect the guidance cage to the aircraft in selected oriented position; b. a first guide member connected to and supported by said connected means and including:

Claim 21

A guidance cage adapted to be connected to an aircraft and to securely position a load or load-stabilizing bar in selected orientation when being carried by the aircraft and including: a. means to connect the guidance cage to the aircraft in selected oriented position; b. a first guide member connected to and supported by said connected means and including:

Claim 22

Apparatus according to claim 1 wherein one of said guide members extends farther from said connecting means than the other so that the enlarged area entry to the restraint slot is canted, thereby necessitating that the load projection or cargo bar being raised will contact one of the guide members and commence its orientation by contact therewith during further load raising before it contacts the other guide member.

Claim 23

Apparatus according to claim 1 wherein the closed ends of said guide members culminate in a substantial tip and wherein said tips lie on opposite sides of a plane extending perpendicular to and located substantially midway between the spaced rod members of said guide members.

Claim 24

A guidance cage assembly adapted to be connected to an aircraft and to cause a load being elevated to the aircraft to be carried thereby externally during flight to achieve a selected oriented position and including: a. means adapted to connect said guidance cage assembly to said aircraft in selected oriented position; b. a first substantially U-shaped guidance rod connected to and supported by said connecting means and projecting therefrom so that the legs of the U extend substantially perpendicular to the aircraft and lie in a plane substantially parallel to the plane of selected load orientation and wherein the closed end of the U flares outwardly from the legs of the U; c. a second substantially U-shaped rod connected to and supported by said connecting means and oriented so that the legs of the U project substantially parallel to the aircraft and are parallel to the legs of the first U-shaped rod and spaced therefrom to define a restraint slot therebetween extending in the direction selected load orientation and wherein the closed end of the U flares outwardly from the legs of the U in a direction opposite to the direction of the flare of the closed end of the first U-shaped rod so as to cooperate therewith in defining a continuous, enlarged area entry to said restraining slot.

Claim 25

A guidance cage assembly adapted to be connected to an aircraft and to cause a load being elevated to the aircraft to be carried thereby externally during flight to achieve a selected oriented position and including: a. means adapted to connect said guidance cage assembly to said aircraft in selected oriented position; b. a first substantially U-shaped guidance rod connected to and supported by said connecting means and projecting therefrom so that the legs of the U extend substantially perpendicular to the aircraft and lie in a plane substantially parallel to the plane of selected load orientation and wherein the closed end of the U flares outwardly from the legs of the U; c. a second substantially U-shaped rod connected to and supported by said connecting means and oriented so that the legs of the U project substantially parallel to the aircraft and are parallel to the legs of the first U-shaped rod and spaced therefrom to define a restraint slot therebetween extending in the direction selected load orientation and wherein the closed end of the U flares outwardly from the legs of the U in a direction opposite to the direction of the flare of the closed end of the first U-shaped rod so as to cooperate therewith in defining a continuous, enlarged area entry to said restraining slot.

Claim 26

Apparatus according to claim 9 wherein one of said U-shaped rods extends farther from said connecting means than the other so that the enlarged area entry to the restraint slot is canted, thereby necessitating that the load projection or cargo bar being raised will contact the closed end of one of the U-shaped rods and commence its orientation by contact therewith during further load raising before it contacts the closed end of the other U-shaped rod.

Claim 27

Apparatus according to claim 9 wherein the closed ends of said U-shaped rods culminate in a substantial tip and wherein said tips lie on opposite sides of a plane extending perpendicular to and located substantially midway between the legs of said U-shaped rods.

Claim 28

An aircraft having load elevating and lowering means including: a. a winch; b. a single cable connected to said winch for either winding thereon or unwinding therefrom to thereby hoist or lower the load connected thereto; c. a load stabilizing beam; d. means connecting said load stabilizing beam to said single cable; e. a guidance cage assembly adapted to be connected to the aircraft and to cause a load being elevated to the aircraft to be carried thereby externally during flight to achieve a selected oriented position and including:

Claim 29

An aircraft having load elevating and lowering means including: a. a winch; b. a single cable connected to said winch for either winding thereon or unwinding therefrom to thereby hoist or lower the load connected thereto; c. a load stabilizing beam; d. means connecting said load stabilizing beam to said single cable; e. a guidance cage assembly adapted to be connected to the aircraft and to cause a load being elevated to the aircraft to be carried thereby externally during flight to achieve a selected oriented position and including:

Claim 30

Apparatus according to claim 12 wherein said connecting means between said load beam and said cable is a swiveling means.

Claim 31

Apparatus according to claim 12 wherein said connecting means between said load beam and said single cable is a releasable cargo hook.

Claim 32

Apparatus according to claim 12 and including rolling members positioned on the top of said load to claim 12 and including rolling members positioned on the top of said load beam and positioned to contact said U-shaped rods of said guidance cage assembly in rolling relation to establish minimum friction therebetween as said load beam is elevated into said restraint slot.

Claim 33

Apparatus according to claim 12 and wherein said load beam is shaped to have a rounded top side.

Claim 34

Apparatus according to claim 16 and including a layer of low friction material covering the curved top of said load beam.

Claim 35

Apparatus according to claim 12 and including bumper means positioned to be intercepted by said load beam in said restraint slot to minimize shock to the aircraft when said load beam is raised to its fully elevated restrained position in said restrained slot.

Claim 36

Apparatus according to claim 18 wherein said bumper means includes shock-absorbing means.

Claim 37

Apparatus according to claim 12 and including means to jettison said load beam.

Claim 38

Apparatus according to claim 12 and including two load cables connected to the opposite ends of said load beam and further including means to connect said load cables to the opposite end of said load beams.

Claim 39

Apparatus according to claim 21 and wherein said means connecting said load beam to said single hoist cable is a swivel connection and wherein said means connecting said two load cables to opposite ends of said beams is a releasable cargo hook.

Claim 40

Apparatus according to the claim 21 wherein said means connecting said single hoist cable to said load beam is a releasable cargo hook and wherein said means connecting said cargo cables to the opposite ends is a positive fixed connecting means.

Claim 41

Apparatus according to claim 21 wherein said means connecting said single hoist cable to said load beam is a releasable cargo hook and wherein said means connecting said two load cables to the opposite ends of said load beam are releasable cargo hooks.

Claim 42

Apparatus according to claim 12 and including means to jettison the load.

Claim 43

Apparatus according to claim 12 and including cutoff means selectively positioned with respect to said restraint slot so as to be actuated by said load-stabilizing beam to cutoff winch operation during the load-elevating process.

Claim 44

Apparatus according to claim 12 and including redundant means to jettison the load.

Claim 45

An aircraft having load elevating and lowering means including: a. a winch, b. a single cable connected to said winch for either winding thereon or unwinding therefrom to thereby hoist or lower the load connected thereto, c. a load stabilizing beam, d. means connecting said load stabilizing beam to said single cable, e. a guidance cage adapted to be connected to the aircraft and to securely position a load or load stabilizing bar in selected orientation when being carried by the aircraft and including:

Claim 46

An aircraft having load elevating and lowering means including: a. a winch, b. a single cable connected to said winch for either winding thereon or unwinding therefrom to thereby hoist or lower the load connected thereto, c. a load stabilizing beam, d. means connecting said load stabilizing beam to said single cable, e. a guidance cage adapted to be connected to the aircraft and to securely position a load or load stabilizing bar in selected orientation when being carried by the aircraft and including:

Claim 47

Apparatus according to claim 28 and including means to jettison the load.

Claim 48

Apparatus according to claim 28 and including cutoff means selectively positioned with respect to said restraint slot so as to be actuated by said load-stabilizing beam to cutoff winch operation during the load-elevating process.

Claim 49

Apparatus according to claim 28 and including redundant means to jettison the load.