Flight Vehicle Tilt-Rotation Control for Payload Stability

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Solution Overview

Problem

Existing flight vehicle control and stabilization systems are inadequate in managing the orientation of non-fixed components relative to fixed components, particularly in response to perturbations caused by pilot or payload movements, leading to instability and loss of control.

Innovation Solution

A system and method that detect the orientation and perturbations of a non-fixed portion of a flight vehicle relative to a fixed portion, calculating directional adjustments to re-orient the fixed portion and maintain stability, using a combination of computer algorithms and mechanical means to adjust engines or thrusters, and anticipate subsequent perturbations.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If a non-fixed portion is added to allow pilot maneuvering, then ease of operation is improved, but stability of the flight vehicle deteriorates

Engineering Contradiction:

Improvepilot maneuvering capabilityVSAvoidflight vehicle stability

Core Design Contradiction:

Ease of operationVSStability of the object's composition

Solution Approach 1:

The system continuously detects the orientation of the non-fixed portion relative to the fixed portion using sensors, and the control algorithm automatically adjusts rotor speeds to counteract detected perturbations, creating a closed-loop feedback system that maintains stability while allowing pilot movement

Inventive Principle:

Principle #23Feedback

Solution Approach 2:

The flight vehicle's control system automatically compensates for perturbations caused by pilot movements on the non-fixed portion, eliminating the need for continuous manual correction and allowing the pilot to maneuver naturally while the system handles stabilization

Inventive Principle:

Principle #25Self-service

2Reliability

If computer stabilization algorithms are used to maintain stability, then reliability is improved, but device complexity increases

Engineering Contradiction:

Improveflight vehicle stabilityVSAvoidcontrol system complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The system replaces complex mechanical stabilization mechanisms (such as mechanical gimbals or active counterbalancing systems) with computer algorithms that process sensor data and adjust rotor speeds, achieving stabilization through software rather than additional mechanical complexity

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The control algorithm serves multiple functions: it detects perturbations, calculates corrective actions, and adjusts rotor speeds, while the same sensor system serves both for stabilization and for detecting pilot maneuvering inputs, reducing overall system complexity

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Ease of operation

If the fixed portion is re-oriented to match the non-fixed portion, then ease of operation is improved, but loss of time occurs during re-orientation

Engineering Contradiction:

Improvepilot control responsivenessVSAvoidre-orientation time

Core Design Contradiction:

Ease of operationVSLoss of time

Solution Approach 1:

The control algorithm anticipates pilot maneuvering intentions by detecting initial perturbations and begins adjusting rotor speeds before the pilot completes their maneuver, reducing the perceived re-orientation time and making the system feel more responsive

Inventive Principle:

Principle #10Preliminary action

Solution Approach 2:

The system dynamically adjusts the re-orientation speed based on the magnitude and rate of change of detected perturbations, accelerating corrections for large disturbances while using smoother, faster adjustments for minor pilot inputs, optimizing response time across different operating conditions

Inventive Principle:

Principle #15Dynamics

Data Source

PatentUS11586226B2Control and stabilization of a flight vehicle from a detected perturbation by tilt and rotation

Publication Date: 2023.02.21 RHOMAN AEROSPACE CORP

AI summary

A flight vehicle control and stabilization process detects and measures an orientation of a non-fixed portion relative to a fixed frame or portion of a flight vehicle, following a perturbation in the non-fixed portion from one or both of tilt and rotation thereof. A pilot or rider tilts or rotates the non-fixed portion, or both, to intentionally adjust the orientation and effect a change in the flight vehicle's direction. The flight vehicle control and stabilization process calculates a directional adjustment of the rest of the flight vehicle from this perturbation and induces the fixed portion to re-orient itself with the non-fixed portion to effect control and stability of the flight vehicle. The flight vehicle control and stabilization process also detects changes in speed and altitude, and includes stabilization components to adjust flight vehicle operation from unintentional payload movement on the non-fixed portion.