Oct 27, 2026

US12774877 - Method for aeronautical stabilization

Launching an aeronautical system can comprise applying force or energy to the system in connection with accelerating the system. Responsive to the force or energy, an element of the system can move along a defined path within the system. The system can comprise a drive that converts motion along the defined path into rotational motion. The drive can rotate a mass within the system, which can be supported by a gas bearing. The rotating mass can comprise the moving element, a different system element, or the entire system. The rotating mass can produce angular momentum and can support gyroscopic stabilization of the aeronautical system. Rotational energy can be selectively imparted to and transferred between system elements in connection with stabilization management. System elements can moderate the system's response to impulsive stimuli associated with rotation and acceleration. A gas bearing can support an external surface of the system during launch.

Inventors: Michael L. Wach, Michael L. Wach, Jr.
Filing date: 2023-11-14

aeronauticsprojectilestabilization

The patent describes a method for gyroscopically stabilizing a projectile during launch by utilizing a helical pair of members that translate and rotate in response to propulsive forces, thereby gaining angular momentum. This angular momentum allows the projectile to achieve stabilization as it advances towards its target after launch.

Claim 1

1 . A method for gyroscopically stabilizing a projectile, the method comprising: by the projectile during a projectile launch, experiencing propulsive force, wherein the projectile comprises a helical pair comprising two members; by the projectile during the projectile launch, responsive to experiencing the propulsive force, translating one of the two members along an axis of the projectile, wherein relative axial displacement between the two members occurs; by the projectile during the projectile launch, responsive to said translating one of the two members along the axis, synchronously rotating one of the two members about the axis, wherein relative rotation between the two members occurs; by the projectile during the projectile launch, gaining angular momentum from said synchronously rotating one of the two members about the axis; by the projectile, changing from said synchronously rotating one of the two members about the axis to producing free rotation between the two members about the axis; and by the projectile after the projectile launch, advancing towards a destination while said free rotation occurs, with the gained angular momentum gyroscopically stabilizing the projectile. by the projectile during a projectile launch, experiencing propulsive force, wherein the projectile comprises a helical pair comprising two members; by the projectile during the projectile launch, responsive to experiencing the propulsive force, translating one of the two members along an axis of the projectile, wherein relative axial displacement between the two members occurs; by the projectile during the projectile launch, responsive to said translating one of the two members along the axis, synchronously rotating one of the two members about the axis, wherein relative rotation between the two members occurs; by the projectile during the projectile launch, gaining angular momentum from said synchronously rotating one of the two members about the axis; by the projectile, changing from said synchronously rotating one of the two members about the axis to producing free rotation between the two members about the axis; and by the projectile after the projectile launch, advancing towards a destination while said free rotation occurs, with the gained angular momentum gyroscopically stabilizing the projectile.

Google Patents

https://patents.google.com/patent/US12774877

USPTO PDF

https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/12774877