Electronically Actuated Rocket Catapult Nozzle for Roll Correction

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Solution Overview

Problem

Existing ejection seat systems induce unwanted roll during ejection, lacking active mechanisms to correct or prevent this, which can lead to improper orientation of the seat/user during deployment of a parachute.

Innovation Solution

Incorporation of adjustable nozzles with two linear electric actuators for multi-axis control, a control module, and sensors to monitor and correct the orientation of the ejection seat, allowing for thrust vectoring and roll correction.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Area of stationary object

If a trajectory divergence rocket motor (TDRM) is used to create clearance between seats during dual ejection, then clearance is provided, but unwanted roll is induced into the seat

Engineering Contradiction:

Improveclearance between seatsVSAvoidinduced roll

Core Design Contradiction:

Area of stationary objectVSObject-affected harmful factors

Solution Approach 1:

The system uses sensors to detect the orientation of the ejection seat during ejection and feeds this information back to the control module. The control module then activates the linear electric actuators to adjust the nozzle orientation, creating a feedback loop that actively corrects the induced roll while maintaining the clearance function of the TDRM.

Inventive Principle:

Principle #23Feedback

Solution Approach 2:

The nozzle assembly is made dynamically adjustable through the linear electric actuators, allowing the nozzle orientation to change during the ejection process. This dynamic adjustment enables the system to first provide clearance via TDRM activation, then correct the induced roll by reorienting the nozzle, resolving the contradiction between providing clearance and avoiding harmful roll.

Inventive Principle:

Principle #15Dynamics

2Reliability

If multiple motors (vernier motor, TDRM, and rocket catapult motor) are used to correct roll and provide clearance, then ejection safety is improved, but device complexity increases

Engineering Contradiction:

Improveejection safetyVSAvoidnumber of motors

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The adjustable nozzle assembly serves multiple functions: it directs thrust for clearance (working with TDRM), it enables roll correction through thrust vectoring, and it can assist in pitch control. By making the nozzle multi-functional through active adjustment, the system reduces reliance on separate dedicated motors for each function, thereby maintaining reliability while reducing overall system complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The patent merges the functions of roll correction and clearance provision into a single integrated system. The adjustable nozzle works in conjunction with the TDRM rather than requiring a separate vernier motor for roll correction. This merging of functions maintains ejection safety while reducing the total number of motors required in the system.

Inventive Principle:

Principle #5Merging (Combining)

Applied Scientific Principles

This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.

Function Achieved in This Case

Ensures proper orientation and safety of the ejection seat by actively correcting induced roll, reducing the need for multiple motors and simplifying maintenance.

Implementation Method 1

A first linear electric actuator is operably connected to the adjustable nozzle and arranged to adjust an orientation of the adjustable nozzle in a first direction and a second linear electric actuator is operably connected to the adjustable nozzle and arranged to adjust an orientation of the adjustable nozzle in a second direction

Methodology Applied

Scientific EffectLinear electric actuator: Linear Motor

Implementation Method 2

a propellant assembly mounted to the ejection seat, and a nozzle assembly having an adjustable nozzle moveably attached to the ejection seat and configured to receive propellant exhaust from the propellant assembly

Methodology Applied

Scientific EffectRocket propulsion: Rocket

Data Source

PatentUS12454361B1Electronically actuated rocket catapult system for ejection seats

Publication Date: 2025.10.28 GOODRICH CORP

AI summary

Ejection seat systems include an ejection seat and a propellant assembly mounted to the ejection seat. A nozzle assembly having an adjustable nozzle is moveably attached to the ejection seat and configured to receive propellant exhaust from the propellant assembly and exhaust through the adjustable nozzle. A first linear electric actuator is operably connected to the adjustable nozzle and arranged to adjust an orientation of the adjustable nozzle in a first direction and a second linear electric actuator is operably connected to the adjustable nozzle and arranged to adjust an orientation of the adjustable nozzle in a second direction. The second direction includes a directional component that is normal to the first direction. A control module is configured to control operation of the first linear electric actuator and the second linear electric actuator.