Rotorcraft Landing Guidance Using Optical-Radar Path Deviation Feedback
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Solution Overview
Problem
Rotary wing aircraft, such as helicopters and drones, face challenges in landing autonomously on unprepared terrain with poor visibility due to dust or sand, as existing systems rely on external infrastructure or ground-based guidance, leading to increased risk of accidents from sensory illusions and reduced visibility.
Innovation Solution
A landing zone landing assistance system equipped with a computer, human-machine interface (HMI), optical assembly, radar assembly, and inertial unit, which determines the relative position of the landing zone and calculates an approach path based on pilot input, allowing for autonomous guidance without external data, using optical and radar data to provide deviation feedback for precise landing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a pilot uses visual approach for landing on unprepared terrain, then the pilot can maintain freedom of choice in landing zone selection, but visibility is degraded by dust clouds and sensory illusions leading to increased accident risk
Solution Approach 1:
The patent introduces an intermediary system consisting of optical sensors, radar detectors, and inertial units that mediate between the pilot and the external environment. This system provides artificial visual markers and trajectory guidance when natural visual cues are unavailable or misleading due to dust clouds, thereby maintaining landing safety while preserving the freedom to select unprepared landing zones.
Solution Approach 2:
The patent replaces the pilot's natural visual sensing system with an artificial sensing system comprising optical sensors and radar detectors. This substitution provides reliable measurement of position and trajectory independent of external visibility conditions, eliminating the harmful effects of dust clouds and sensory illusions while maintaining the ability to operate from unprepared terrain.
2Measurement precision
If external infrastructure such as GPS or ILS is used for landing assistance, then guidance accuracy is improved, but the system becomes dependent on external data and ground equipment
Solution Approach 1:
The patent implements a self-service system where the aircraft carries its own sensing equipment (optical sensors, radar detectors, inertial units) and processes data autonomously using an embedded computer. This eliminates dependence on external infrastructure while maintaining high measurement precision through the fusion of multiple independent sensing modalities and autonomous trajectory calculation.
3Device complexity
If a pilot relies on sensory observation and experience for landing, then no external equipment is needed, but the pilot may be misled by sensory illusions especially in poor visibility conditions
Solution Approach 1:
The patent replaces the pilot's sensory observation system with an artificial sensing system based on optical sensors, radar detectors, and inertial units. This substitution provides objective, precise measurement of position and trajectory that is not subject to sensory illusions, while the embedded computer processes this data to provide accurate guidance information.
Solution Approach 2:
The patent implements a feedback system where the embedded computer continuously calculates the aircraft's position and trajectory based on sensor data, compares it with the desired approach path, and provides guidance feedback to the pilot through the HMI. This closed-loop feedback ensures high trajectory accuracy by continuously correcting deviations from the intended landing path.
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
Enables safe and precise autonomous landing on unprepared terrain by providing real-time deviation feedback, reducing reliance on external infrastructure and improving pilot accuracy in low-visibility conditions, thus mitigating the risk of accidents.
Implementation Method 1
an optical assembly (3) provided with at least one optical sensor... determining an optical image of the possible landing zone based on data supplied by the optical assembly
Implementation Method 2
a radar assembly (4) provided with at least one radar detector... determining the relative position of the landing zone... on data supplied by the radar assembly
Implementation Method 3
an inertial unit (5)... determining the relative position of the landing zone... on data supplied by the inertial unit
Data Source
AI summary
A landing zone landing assistance system for a rotary wing aircraft, the system includes a computer, an HMI for interacting with the pilot of the aircraft, an optical assembly provided with at least one optical sensor, a radar assembly provided with at least one radar detector and an inertial unit, wherein the computer is configured to implement the following steps: a first step (Step1) consisting in determining an optical image of the possible landing zone; a second step (Step2) consisting in determining the relative position of the landing zone with respect to said system in the terrestrial reference frame; a third step (Step3) consisting in determining a landing zone approach path; and a fourth step (Step4) consisting in supplying to the HMI a deviation between the position of the system and the approach path.