checkout process to design build rockets docx to see how to build design patent, Idea starts it all. execute 2 patents

• one process is done in the exo atmosphere (space vacumm)
• the second dynamic on atmospheric entry

Ongoing published archive

https://zenodo.org/records/20547536

this is DOI for provisional patent https://doi.org/10.5281/zenodo.20633570

latest DOI

https://doi.org/10.5281/zenodo.20592096 https://doi.org/10.5281/zenodo.20649201 (latest)

for provisional patent https://doi.org/10.5281/zenodo.20626092 https://doi.org/10.5281/zenodo.20633570 https://doi.org/10.5281/zenodo.20649201 (latest) This will be the sexiest engineering every pull off in 21st century nothing short of it.

ballistic-coefficient-solution

This is a rocket process or mechanism for diametrically volume collapsable structure, these are a whole new class of rockets where idea has not being seen or implemented yet. This is the first form of writing to work on a such class of rockets to solve ballistic coefficient problem.

SOLUTION

• One of the easiest method to visualize this is to sandwich two papers in between another paper.

• Now roll the papers semi-circluarly and then pull the sandwiched or center paper to cover the semi-circular gap with this

• what you see now is the cross-section of diameterically extended rocket (low ballistic coefficient - considering factors such as mass, cross sectional area etc)

• we describe the two solutions

  • of top-down twist to contract and expand from the top cone to bottom segmented body of the rocket. (inspired from the streets of India - peanut sellers)
  • diameterically increasing the size of the rocket in exo - atmosphere (in space vacuum) and performing re-entry of rocekt into any planetary body. ( one such would be the payload delivery into earth's atmospheric space )
  • here is an example (https://www.youtube.com/watch?v=nQGrYzHi-aY)

• we also describe the basic paper experiment in terms of harder shell of any material to perform the same.

• the rotational expansion & contraction of the shell radially & not push - pull

• we describe the stability and manuverability of the rocket using just the rotational concepts

Shape description

The below shows 2 aspects :-

• the first exo - atmospheric diametrically expanding rocket
• the second - irish mechanism to dynamically change the shape on descent

Note: execute two patents – one for exo – atmospheric radial expansion and the other is dynamic on fall. Check out this video [https://www.youtube.com/watch?v=RDRdsOvszN8] here we see the curved pathways transform to linear, this is great for exo-atmospheric expansion check cp,cg and tennis racket theorem effect for dynamic expansion upon entry into earths or any planetary surface we will use the green rods shaped as the same pathways this should cause rotational effect and radially contraction and expansion. Check out this video [https://www.youtube.com/watch?v=vFARO8EualU&list=PL37tY87jDKu1rBqbo0QfFEBvv5ClbCyAX] here in this video see how the blades rotate internally – we need a pivot on the outer part of the blade to have a hinge that converts this to a circular motion that would radially expand and contract the cylinder – this should work with a twist. We can design such mechanism – using the blade shape configurations or / and hinges that converts the curvilinear motion into circular motions. The most exciting part of this innovation is that its after 100 years and this open a whole new class of rocket design, physics and artificial intelligence. We need to hereby file two patents – one for exo – atmospheric expansion and the other dynamic as mentioned in the head note – the dynamic will be even more exciting as it involves such mechanic and takes time to file a patent. The easiest for me is the exo-atmospheric and landing back.

NEED TO VERIFY : while the physics checks out theoritically and with simple experiment as described above, the following needs to be verified via simulation etc.

• the integrity of the structure at high speed high altitude entry and exiting the atmosphere to any planet
• the structural description (suggested by ai) - please note this is just the bevel edges for the aerodyanmic flow of the rocket on expanded cross section

NEED TO ANALYZE

• the efficiency of using such rockets over traditional static rockets (comparetively or by itself)

WHY

• there has been no such innovation in rockets for a long time, and such ideas and solutions exists and not pursued.

PS NOTE: we havent seen any prior art on this concept - if any please feel to mail the author, otherwise this is the first of such rocket.

AI is useful

• A conversation with AI and me explaining my ideas and it giving me what my idea solves and an understanding of it.
  • basic understanding of Dzhanibekov Effect and how it effects this.
• Most of it is structural and trying to understand the structural physics

Novelty

• its embeded in the process of diameterically morphing the rocket itself radially outwards
• we use atmospheric pressure, velocity to change the rockets structure and position in space - horizontal to absorb & reduce the velocity
• in rocket science terms or aerospace engineering - we use change the center of pressure as a function of diametric morphing of the rocket segmented cylinder to change the attitude of the rocket.

Structural and its physical impact Novelty (needs better visualization / simulation and verification of such methodology - but checks out)

• this happens in the petal shaped cone aspect of the rocket
• the iris or any other shaped tiles that make up the rocket structure
• the movement radially outwards and inwards to form certain aerodynamic shape of the rocket

FUTURE

• exploring this idea for expansion and contraction [https://en.wikipedia.org/wiki/Conical_spiral] (while used for cone)

BACKGROUND Researchers have been studying "Low Ballistic Coefficient" vehicles for decades to solve the landing problem for heavy (1+ ton) payloads. [1] The Deceleration Problem: NASA and other agencies confirm that a lower ballistic coefficient is necessary to decelerate higher in the atmosphere. This provides more "altitude margin" and time to land. The "Big to Small" Concept: NASA is currently testing HIAD (Hypersonic Inflatable Aerodynamic Decelerator) technology. These are essentially "Big" inflatable heat shields that reduce the ballistic coefficient to slow a craft down. The Problem with Rigid Shells: Rigid shells (like the Viking-era 70-degree sphere-cones used by SpaceX and NASA) are limited by the launch vehicle's diameter. Your Morphing Small idea solves the "Fairing Constraint" by stowing small and growing big.

ABSTRACT: A process and method for dynamic kinetic deceleration and attitude control of an aerospace vehicle during atmospheric entry. The process utilizes a top-down rotational torque to diametrically morph a vehicle segment radially outwards within a two-dimensional cross-sectional plane, telescopically exposing a plurality of pre-curved, non-continuous internal segments along a curvilinear path to scale the vehicle's macro-radius from a stowed baseline radius ((r_{1})) to an expanded perimeter radius ((r_{2})). This transformation dynamically modifies the vehicle's cross-sectional area to slash its baseline ballistic coefficient without altering longitudinal structural length. Flight orientation is manipulated into a stable horizontal profile relative to an oncoming freestream via synchronized differential counter-rotation of outer shell segments, which neutralizes rigid-body intermediate-axis instabilities (the Dzhanibekov phenomenon) and leverages internal cryogenic liquid mass sloshing as a passive kinetic energy dissipation anchor. The counter-rotational velocities are subsequently modulated or braked within denser atmospheric layers to break the gyroscopic axis lock, allowing aerodynamic and gravitational forces to pivot the vehicle smoothly into a vertically upright orientation optimized for structural landing without requiring high-fuel attitude thrusters.

DFTC Mechanical Cross-Section (Top-Down View)

    ========================= OUTER BOUNDARY =========================
    [  ] Layer 1:  Segmented Aero-shell (Moves Radially) - this can be any metal
    [  ] Layer 2: Variable Volumetric Buffer Zone (Hollow / Pneumatic Air Void)
    ========================= CENTRAL CHASSIS ========================
    [||] Layer 3: Non-Deforming Heavy Structural Core Axis
    [##] Layer 4: Cryogenic Propellant Shell 1 (Liquid Methane Axis)
    [##] Layer 5: Cryogenic Propellant Shell 2 (Liquid Oxygen Core)
    ==================================================================


    [EXPANDED MANEUVER: HIGH DRAG STATE]
       _______________________________
      /   _________________________   \
     /   /                         \   \

    |   |      _______________      |   |
    |   |     /   #########   \     |   |
    |   |    |    ## FUEL ##   |    |   |  <-- Static Core
    |   |    |    ## SHELL #   |    |   |      Propellant Matrix
    |   |     \___#########___/     |   |
    |   |                           |   |  <-- 1-Meter Void Buffer
     \   \_________________________/   /
      \_______________________________/    <-- Morphing Outer Skin
                                               (Expanded "Big" Mode)

    [COLLAPSED MANEUVER: KINETIC NEEDLE STATE]
                 ___________
                /   _____   \
               /   / ### \   \

              |   | #FUEL#|   |            <-- Outer Skin fully
              |   | ##### |   |                compressed flush
               \   \_____/   /                 against Core
                \___________/                  (Collapsed "Small" Mode)

Please note this is part of Live Insurance Inc and retains all rights and no use of this material in any shape or form

REFERENCES [1] Guided Entry Performance of Low Ballistic Coefficient Vehicles at Mars https://arc.aiaa.org/doi/10.2514/1.A32425

Ballistic Coefficient Solution: Diametrically Volume-Collapsible Rocket Architecture

⚠️ Proprietary Notice & Restrictions (No Use License)

Copyright (c) 2026 by Author/Owner. All Rights Reserved.

THE CONTENTS OF THIS PROJECT AND DISCLOSURE ARE STRICTLY PROPRIETARY AND CONFIDENTIAL.

UNAUTHORIZED COPYING, ALTERING, REPRODUCING, MANUFACTURING, OR REPLICATING OF THE MECHANISMS, METHODS, SYSTEMS, OR DESIGN PATTERNS DESCRIBED HEREIN, VIA ANY MEDIUM (MECHANICAL, DIGITAL, OR PHYSICAL), IS STRICTLY PROHIBITED.

The public availability of this document on a public forum or repository does not convey, imply, or grant any license, right, or permission to use, modify, build, test, or distribute this technology for commercial, educational, personal, or military applications.

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Defensive Publication & Prior Art Establishment

Abstract

This disclosure introduces a novel diametrically volume-collapsible rocket architecture designed to dynamically optimize ballistic coefficients and alleviate atmospheric drag. By publishing the technical details of the radially collapsing structure and its core-isolated design, this document functions as a defensive publication to establish prior art and ensure the methodology remains in the public domain for the purpose of patent invalidation only.

1. Statement of Intent

This document serves as an open public disclosure designed to function as a Kill-Switch against future patent claims by third-party entities. By establishing the fundamental engineering concepts of a diametrically collapsing external volume variant in public records:

• Any subsequent attempt by competitors or external entities to file patent claims regarding variable-diameter structural collapses to modify ballistic parameters must be rejected by patent offices (e.g., USPTO, EPO) based on Lack of Novelty and the presence of existing Prior Art.
• This notice establishes the exact publication timestamp of the mechanical cross-section concepts (Layers 1 through 5) involving independent radial aero-skins isolated from a non-deforming heavy structural cryogenic core.

2. Challenge to Patent Examiners

We explicitly invite patent examiners worldwide to cite this public technical document as Prior Art against any future patent applications attempting to claim exclusive rights over "radially collapsing rocket bodies," "variable cross-section aerodynamic profiles," or "pneumatically/mechanically actuated external buffer zones protecting a static core axis."

Defensive Publication & Prior Art Establishment: Diametrically Morphing Rocket Architecture

Abstract

This disclosure introduces a novel, non-static class of aerospace vehicles utilizing a diametrically volume-collapsible and radially morphing rocket architecture. This process dynamically modifies the vehicle's frontal surface area to optimize ballistic coefficients ($B_C = \frac{m}{C_d A}$) in real-time, solving critical deceleration, atmospheric entry, and drag mitigation challenges. By publishing this structural process, mechanical actuation methodology, and the fundamental physics of rotational expansion, this document functions as an open defensive publication to establish prior art and permanently prevent third-party patent monopolies over this technology class.

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1. Statement of Intent & Challenge to Patent Examiners

This document serves as an open, public disclosure operating as a legal baseline against future patent claims by external entities.

• Prior Art Mandate: Any subsequent attempt by competitors or external entities to file patent claims regarding variable-diameter structural collapses, rotational shell morphing, or radial volume expansion to modify ballistic parameters must be rejected by patent offices (e.g., USPTO, EPO, JPO) based on Lack of Novelty (35 U.S.C. 102) and the presence of existing Prior Art.
• Examiner Guidance: Patent examiners worldwide are explicitly invited to cite this public technical document against any future applications attempting to claim exclusive rights over "radially morphing rocket bodies," "variable cross-section aerodynamic profiles via rotational actuation," or "iris/petal-based dynamic external buffer zones protecting a static core axis."

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2. Core Architectural Novelty & Process Description

Unlike traditional static rocket hulls or linear push-pull deployments, the novelty of this architecture is embedded in the process of continuous, radial, diametric morphing driven by rotational torque.