Apparatus for a vehicle

Patent metadata

Field	Value
Publication number	US-11220324-B2
Application number	US-201816478221-A
Country	US
Kind code	B2
Filing date	Feb 1, 2018
Priority date	Feb 2, 2017
Publication date	Jan 11, 2022
Grant date	Jan 11, 2022

Abstract

Apparatuses for a projectile are provided, the projectile configured for weapons band launching, examples of the apparatus comprising a body, an inflation system and external walls. The body is inflatable by the inflation system, from a deflated configuration having a first volume to an inflated configuration having a second volume, greater than the first volume. The external walls are deployable from an undeployed configuration to a deployed configuration responsive to the body being inflated. In the undeployed configuration and at an operating airspeed, the center of pressure is located at a first position with respect to the projectile. In the deployed configuration the external walls provide a deployed external surface geometry exposed to an airflow corresponding to the operating airspeed, such that the center of pressure is located at a second position with respect to the projectile, different from the first position.

First claim

The invention claimed is:

1. An apparatus for a projectile, the projectile configured to be launched from a weapons barrel, wherein in operation of the apparatus in association with the projectile under predetermined operating conditions the projectile has a center of pressure, said predetermined operating conditions including an operating airspeed for the projectile greater than a threshold airspeed, the apparatus defining a reference axis, the apparatus comprising:
a body inflatable from a deflated configuration having a first volume to an inflated configuration having a second volume, said second volume being greater than said first volume;
an inflation system for selectively inflating said body from said deflated configuration to said inflated configuration;
external walls deployable from an undeployed configuration to a deployed configuration responsive to said body being inflated from said deflated configuration to said inflated configuration;
wherein in said undeployed configuration and at said operating airspeed, said center of pressure is located at a first position with respect to the projectile along said reference axis;
and
wherein in said deployed configuration said external walls provide a deployed external surface geometry exposed to an airflow corresponding to said operating airspeed, such that said center of pressure is located at a second position with respect to the projectile along said reference axis, said second position being different from said first position.

2. The apparatus according to claim 1 , wherein in said deployed configuration said deployed external surface geometry is outwardly projecting with respect to said reference axis as compared with a nominal external surface geometry of said external walls provided in said undeployed configuration.

3. The apparatus according to claim 1 , wherein in said deployed configuration said external walls provide a deployed external surface geometry that is exposed to an airflow in operation of the apparatus and that has a first forward facing area, and wherein in said undeployed configuration said external walls provide an undeployed external surface geometry that is exposed to said airflow in operation of the apparatus and that has a second forward facing area, said first forward facing area being greater than said second forward facing area.

4. The apparatus according to claim 1 , wherein said threshold airspeed is 0.6 Mach Number or greater than 0.6 Mach Number.

5. The apparatus according to claim 1 , including at least one of the following:
wherein said reference axis is a longitudinal axis of the projectile or is coaxial with a longitudinal axis of the projectile;
wherein said second position is aft with respect to said first position along said reference axis, or, wherein said second position is forward with respect to said first position along said reference axis;
wherein said external walls are configured for deploying from said undeployed configuration to said deployed configuration in directions along more than one axis orthogonal to said reference axis;
wherein said external walls are configured for deploying from said undeployed configuration to said deployed configuration in a plurality of radial directions away from said reference axis;
wherein said body circumferentially encloses said reference axis in planes orthogonal to said reference axis;
wherein said body is generally axisymmetric with respect to said reference axis; or
wherein said apparatus is in the form of a flare module.

6. The apparatus according to claim 1 , wherein said deployed external geometry defines a generally frusto-conical form or a generally cylindrical form.

7. The apparatus according to claim 6 , wherein said frusto-conical form has an external diameter that increases in an aft direction with respect to the projectile.

8. The apparatus according to claim 2 , wherein said nominal external surface geometry defines a non-generally frusto-conical form.

9. The apparatus according to claim 1 , including one of the following:
wherein in said deflated configuration said external walls are accommodated within a cylindrical envelope having a diameter within ±10% of a baseline diameter, wherein the baseline diameter is a diameter of the projectile immediately forward of the apparatus when the apparatus is mounted to the projectile;
wherein in said deflated configuration said external walls have a generally undulating form, including a plurality of lobes;
wherein in said deflated configuration said external walls are partially folded at a plurality of fold lines, said fold line being at least partially aligned longitudinally;
wherein in said deflated configuration said external walls generally at least partially mutual overlapped in a circumferential direction with respect to said reference axis;
wherein said body has a general toroidal form; or
wherein said external walls comprise a plurality of petals, different from said body, and wherein said plurality of petals forms a flare assembly.

10. The apparatus according to claim 1 , wherein said apparatus is in the form of a fin module, and including one of the following:
wherein said body comprises a central plug portion and a plurality of fin elements;
wherein said body comprises a central plug portion and a plurality of fin elements, and, wherein said central plug portion has a circumferential periphery, and wherein said fin elements is circumferentially disposed along said circumferential periphery;
wherein said plug portion defines an internal plug chamber, and wherein each said fin element defines an internal fin chamber in fluid communication with said internal plug chamber;
wherein each said fin element has aerofoil sections in planes parallel to and radially spaced from said reference axis;
wherein each said fin element has aerofoil sections in planes parallel to and radially spaced from said reference axis, and, wherein each said aerofoil section has zero camber;
wherein each said fin element is configured for deploying from said undeployed configuration to said deployed configuration in a generally radial directions away from said reference axis;
wherein each said fin element is configured for deploying from said undeployed configuration to said deployed configuration in a generally radial directions away from said reference axis, and, wherein in said undeployed configuration each said fin is in a radially collapsed configuration;
wherein in said deflated configuration said fin elements are at least partially folded at a plurality of fin fold lines, said fin fold line being at least partially aligned longitudinally;
wherein in said undeployed configuration said fins adopt a wrap-around configuration with respect to said plug portion;
wherein in said deployed configuration said fins have a linear configuration, wherein a span of each said fin is rectilinear; or
wherein in said deployed configuration said fins have a non-linear configuration, wherein a span of each said fin is curved.

11. The apparatus according to claim 1 , wherein said body comprises any one of a balloon-type body and a bellows-type body.

12. The apparatus according to claim 1 , wherein said body is configured for providing said deployed external surface geometry to said external walls.

13. The apparatus according to claim 12 , including one of the following:
wherein said body comprises a first longitudinal end, a second longitudinal end longitudinally spaced from said first longitudinal end, an outer wall and an inner wall, wherein said first longitudinal end, said second longitudinal end, said inner wall and said outer wall define a body internal spac

Assignees

• Israel Aerospace Ind Ltd

Inventors

• Bar Hillel Shahar
• Shragai Saar

Classifications

• F42B10/20 Primary

  deployed by combustion gas pressure, or by pneumatic or hydraulic forces · CPC title

• F42B10/50

  Brake flaps {, e.g. inflatable} · CPC title

• B64C5/12 Primary

  for retraction against or within fuselage or nacelle · CPC title

• F42B10/12

  using fins longitudinally-slidable with respect to the projectile or missile · CPC title

• F42B10/06 Primary

  Tail fins · CPC title