Flying Object Attitude Control Using Gravity Direction Separation
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Solution Overview
Problem
Flying objects like drones face challenges in accurately controlling their attitude during flight, which can lead to crashes if attitude is lost.
Innovation Solution
An attitude control device that determines the gravity direction using static acceleration components computed from both dynamic and static acceleration signals, allowing for precise attitude control by correcting these components based on correction information and angular velocity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If only a single acceleration detection signal is used to control attitude, then the device complexity is reduced, but the measurement precision of gravity direction deteriorates
Solution Approach 1:
The acceleration detection signal is segmented into dynamic acceleration components and static acceleration components through signal processing. The static acceleration components correspond to gravity direction, while dynamic components represent motion. This segmentation allows accurate gravity determination without requiring separate sensors for each component.
2Reliability
If correction information is not applied to static acceleration components, then the processing complexity is reduced, but the reliability of attitude control deteriorates
Solution Approach 1:
Correction information is applied to the static acceleration components to compensate for errors and improve accuracy. The correction process uses feedback from the relationship between dynamic and static components, adjusting the static components to achieve more reliable attitude control while maintaining reasonable processing complexity.
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 accurate and stable attitude control of flying objects, even in dynamic conditions, preventing crashes and maintaining control during intense movements or unexpected attitude losses.
Implementation Method 1
a piezoelectric first acceleration detector provided on the movable portion to output the first acceleration detection signal
Implementation Method 2
a non-piezoelectric second acceleration detector provided on the movable portion to output the second acceleration detection signal
Implementation Method 3
a movable portion movable in response to acceleration acting on the flying object
Data Source
AI summary
An attitude control device is provided and includes a control unit that determines a gravity direction in a flying object on a basis of static acceleration components computed on a basis of a first acceleration detection signal obtained by detecting dynamic acceleration components acting on the flying object and a second acceleration detection signal obtained by detecting the dynamic acceleration components and the static acceleration components acting on the flying object, and controls an attitude of the flying object on a basis of the gravity direction.