Emergency Thruster Layout for Controlled Flying Body Descent
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Solution Overview
Problem
Existing propulsion systems for flying bodies, such as flying cars, do not effectively mitigate the impact of a fall in emergency situations, such as engine failure, which can lead to injuries and damage.
Innovation Solution
A propulsion apparatus comprising a gas generator and multiple thrusters that generate and output combustion gas downward when an emergency condition is detected, such as engine failure, to reduce the impact of a fall.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If no emergency propulsion system is provided, then the device complexity is reduced, but the safety and reliability of the flying body deteriorates in emergency situations
Solution Approach 1:
The propulsion system is divided into separate functional modules: a gas generator unit and multiple thruster units. This segmentation allows the emergency propulsion function to be added without requiring complete system redesign, thereby improving safety while limiting the increase in overall system complexity.
Solution Approach 2:
The gas generator and thrusters are pre-positioned and pre-configured on the flying body, ready for immediate activation upon detecting an emergency condition. This preliminary preparation ensures rapid response capability without requiring complex real-time decision-making or assembly procedures during emergencies.
2Object-affected harmful factors
If a gas generator and multiple thrusters are added, then the ability to reduce fall impact is improved, but the weight of the flying body increases
Solution Approach 1:
The thrusters generate upward-directed combustion gas flow that creates a force counteracting the downward gravitational force during emergency descent. This anti-weight mechanism directly reduces the impact of fall by providing an opposing force to balance the flying body's weight.
Solution Approach 2:
The gas generator appears to be designed as a single-use or limited-use component that is activated only in emergency situations. This disposable approach allows the system to carry the necessary emergency propulsion capability without requiring complex, redundant, or permanently active systems that would add unnecessary weight.
3Force
If combustion gas is output downward continuously, then the upward thrust is maximized, but the loss of energy increases
Solution Approach 1:
The emergency propulsion system operates in periodic cycles: activated when emergency conditions are detected, maintains combustion gas output for the duration needed to reduce fall impact, then terminates when the emergency condition is resolved or fuel is depleted. This periodic operation provides maximum thrust when needed while avoiding continuous energy consumption.
Solution Approach 2:
The system applies counter-action (upward thrust) only when harmful conditions (emergency descent) are detected, rather than operating continuously. The propulsion apparatus monitors flight conditions and activates the gas generator and thrusters only when an emergency is detected, thereby providing necessary upward force while minimizing unnecessary energy loss.
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
The propulsion apparatus effectively reduces the impact of a fall by generating an upward thrust during emergencies, thereby stabilizing the flying body's descent and minimizing damage upon landing.
Implementation Method 1
a gas generator (200) that generates a combustion gas when at least a part of a flying body (1, 5) satisfies an emergency condition
Implementation Method 2
a plurality of thrusters (100) that output the combustion gas downward
Data Source
AI summary
A propulsion apparatus is provided with a gas generator and a plurality of thrusters. The gas generator generates combustion gas when a flying body satisfies an emergency condition. Herein, the plurality of thrusters output the combustion gas downward. In addition, when viewed from a direction of travel of the flying body, the plurality of thrusters may overlap the gas generator. Furthermore, the plurality of thrusters may control an attitude of the flying body. In addition, the plurality of thrusters may reduce outputs of the combustion gas to a first output based on a landing of at least a part of the flying body.