Combat Aircraft Power Management for Glide-to-Weapon Switching
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Solution Overview
Problem
Existing hybrid propulsion aircraft face a challenge in balancing the power requirements between propulsion and electrical weapon systems, leading to oversizing of electrical power sources and limiting the mass of on-board weapon systems due to the disproportionate power needs.
Innovation Solution
A management unit is implemented to selectively switch between flight and attack modes, optimizing power distribution to prioritize electrical weapon systems during attack modes by reducing propulsion system power requirements when the weapon system is in use, leveraging the aircraft's gliding capability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the electrical power source is sized to meet the maximum power demand of the electrical weapon system, then the weapon system power availability is improved, but the overall weight of the aircraft increases
Solution Approach 1:
The patent implements dynamic power management that switches between different operating modes (flight mode and attack mode) based on mission requirements. The power distribution is dynamically adjusted: in flight mode, full power is allocated to propulsion and flight systems; in attack mode, the system transitions to glide configuration and reallocates power to the electrical weapon system. This dynamic adaptation resolves the contradiction by providing high weapon power only when needed, rather than continuously sizing the power source for maximum demand.
Solution Approach 2:
The system changes operational parameters by transitioning between configured modes that alter power distribution characteristics. The management unit modifies power allocation parameters based on the selected mode, enabling the same electrical power source to serve different power demands at different times. This parameter change approach allows the aircraft to maintain lighter power sources while still meeting peak weapon system power requirements through temporal power management.
2Weight of moving object
If the electrical power source is downsized to reduce aircraft weight, then the overall weight is reduced, but the power availability for the electrical weapon system becomes insufficient
Solution Approach 1:
The patent employs periodic alternation between flight mode and attack mode operations. During flight mode, the aircraft operates with reduced power consumption optimized for propulsion. When weapon engagement is required, the system transitions to attack mode with reconfigured power distribution. This periodic switching allows the use of a lighter power source that would be insufficient for continuous maximum power output, while still providing adequate power for weapon systems during designated attack periods.
Solution Approach 2:
The system prepares for weapon system operation by pre-configuring the glide state and power management settings before weapon engagement. The management unit anticipates the power requirements and adjusts the operational mode accordingly, ensuring that when the weapon system needs power, the aircraft is already in the appropriate configuration (glide mode with optimized power allocation) to support high-power weapon operation without requiring an oversized continuous power source.
3Loss of energy
If the aircraft operates in glide mode during weapon system use, then power consumption for propulsion is reduced, but the flight control and navigation capabilities must be maintained
Solution Approach 1:
The patent applies partial action by providing just enough power to the flight control system during attack mode to maintain essential flight control and navigation functions, rather than providing full power to all systems. The management unit prioritizes power allocation to ensure minimum viable flight control capability while maximizing power available to the weapon system. This partial power provision to non-essential systems resolves the contradiction by maintaining sufficient reliability for safe operation without consuming excessive power that would be unavailable for the weapon system.
Data Source
AI summary
A fixed-wing combat aircraft including an electrical power source, a propulsion system, a low-power non-propulsion assembly including a flight control system, a high-power non-propulsion assembly including an electrical weapon system, and a management unit configured to selectively establish on command multiple operating modes including: a flight mode, in which the management unit distributes the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly, and an attack mode, in which the management unit limits the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly to the power required to allow the aircraft to glide, and reserves a majority of the available electrical power for the high-power non-propulsion assembly.