Clamping connection assembly for spacecraft

Claim 2

In a spacecraft having first and second separable components joined by a tension strap V-clamp assembly so as to be held together along an axial direction while subject to both axial loads and bending moments, the improvement of a connection assembly comprising: a first flange member having a first detent on the first spacecraft component; flange members to hold them together; and a second flange member having a second detent on the second spacecraft component; a retainer member for transmitting the radial force of the tension strap to the first and second flange members to hold them together; and a shear pin mounted on the retainer member for engaging the complimentary first and second detents, the shear pin and detents cooperatively preventing relative rotational movement between flange members, the shear pin being capable of transmitting shear and torsional forces without increasing the axial load created by the tension strap or locking the connection assembly to prohibit a predetermined release.

Claim 3

The invention of claim 1 wherein the detent on each flange member extends from a respective contact surface to a camming surface along a peripheral edge of the flange member.

Claim 4

The invention of claim 2 wherein the retainer member includes first and second retention flanges each including an aperture, the shear pin being loosely journalled within the respective apertures.

Claim 5

The invention of claim 3 further including a spring member to bias the shear pin to one side of the apertures.

Claim 6

In a spacecraft having first and second separable components joined by a releasable tension strap so as to be held together along an axial direction, while subject to both axial loads and bending moments, the improvement of a connection assembly comprising: a first flange member on the first spacecraft component having a first camming surface and a second contact surface, the first surface being positioned at an acute angle to the second surface; a second flange member on the second spacecraft component, having a first camming surface and a second contact surface complimentary to the first flange member contact surface, the first surface being positioned at an acute angle to the second surface, the respective contact surfaces being smooth; a retainer member, for transmitting the radial force of the tension strap to the first and second flange members to hold them together, having a pair of complimentary camming surfaces to co-act with the first camming surfaces of the first and second flange members to create an axial force from the radial force of the tension strap, and means on the first and second flange members and retainer member for cooperatively preventing relative rotational movement between the smooth contact surfaces of the flange members, including on the retainer member at least a shear pin capable of restraining shear and torsional forces, without increasing the axial load created by the tension strap or locking the connection assembly to prohibit a predetermined release of the smooth contact surfaces and at least a pair of complimentary detents positioned on the peripheral edges of the flange members for receiving the shear pin.

Claim 7

In a spacecraft having first and second separable components joined by a releasable tension strap so as to be held together along an axial direction, while subject to both axial loads and bending moments, the improvement of a connection assembly comprising: a first flange member on the first spacecraft component having a first camming surface and a second contact surface, the first surface being positioned at an acute angle to the second surface; a second flange member on the second spacecraft component, having a first camming surface and a second contact surface complimentary to the first flange member contact surface, the first surface being positioned at an acute angle to the second surface, the respective contact surfaces being smooth; a retainer member, for transmitting the radial force of the tension strap to the first and second flange members to hold them together, having a pair of complimentary camming surfaces to co-act with the first camming surfaces of the first and second flange members to create an axial force from the radial force of the tension strap, and means on the first and second flange members and retainer member for cooperatively preventing relative rotational movement between the smooth contact surfaces of the flange members, including on the retainer member at least a shear pin capable of restraining shear and torsional forces, without increasing the axial load created by the tension strap or locking the connection assembly to prohibit a predetermined release of the smooth contact surfaces and at least a pair of complimentary detents positioned on the peripheral edges of the flange members for receiving the shear pin.

Claim 8

The invention of claim 5 wherein the retainer member includes a first and second retention flange having apertures, the shear pin being loosely journalled within the respective apertures.

Claim 9

The invention of claim 6 further including a spring member to bias the shear pin to one side of the aperture.

Claim 10

In a spacecraft having first and second separable components joined by a releasable tension strap so as to be held together along an axial direction, while subject to both axial loads and bending moments, the improvement of a connection assemblies positioned about the spacecraft, each of them comprising: a first flange member on the first spacecraft component having a first camming surface and a second contact surface, the first surface being positioned at an acute angle to the second surface; a second flange member on the second spacecraft component, having a first camming surface and a second contact surface complimentary to the first flange member contact surface, the first surface being positioned at an acute angle to the second surface, the respective contact surfaces being planar and smooth; a plurality of retainer members, for transmitting the radial force of the tension strap to the first and second flange members to hold them together, each having a pair of retention flanges with complimentary camming surfaces to co-act with the first camming surfaces of the first and second flange members to create an axial force from the radial force of the tension strap, and means on the first and second flange members and each retainer member for cooperatively preventing relative rotational movement between the smooth contact surfaces of the flange members, including on the retainer member at least a shear pin extending between the retainer member camming surfaces capable of restraining shear and torsional forces, without increasing the axial load created by the tension strap nor locking the connection assembly to prohibit a predetermined release of the smooth contact surfaces and at least and no more than a pair of complimentary detents, one on each of the outer peripheral edges of the first and second flange members for receiving the shear pin.

Claim 11

In a spacecraft having first and second separable components joined by a releasable tension strap so as to be held together along an axial direction, while subject to both axial loads and bending moments, the improvement of a connection assemblies positioned about the spacecraft, each of them comprising: a first flange member on the first spacecraft component having a first camming surface and a second contact surface, the first surface being positioned at an acute angle to the second surface; a second flange member on the second spacecraft component, having a first camming surface and a second contact surface complimentary to the first flange member contact surface, the first surface being positioned at an acute angle to the second surface, the respective contact surfaces being planar and smooth; a plurality of retainer members, for transmitting the radial force of the tension strap to the first and second flange members to hold them together, each having a pair of retention flanges with complimentary camming surfaces to co-act with the first camming surfaces of the first and second flange members to create an axial force from the radial force of the tension strap, and means on the first and second flange members and each retainer member for cooperatively preventing relative rotational movement between the smooth contact surfaces of the flange members, including on the retainer member at least a shear pin extending between the retainer member camming surfaces capable of restraining shear and torsional forces, without increasing the axial load created by the tension strap nor locking the connection assembly to prohibit a predetermined release of the smooth contact surfaces and at least and no more than a pair of complimentary detents, one on each of the outer peripheral edges of the first and second flange members for receiving the shear pin.

Claim 12

The invention of claim 8 wherein each retainer member includes a first and second retention flange having apertures, the shear pin being loosely journalled within the respective apertures.

Claim 13

The invention of claim 9 further including a spring member to bias the shear pin to one side of the aperture.