Electronic Detonator Blaster Flight Recovery After Command Transmission
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Solution Overview
Problem
Existing electronic detonator blasters face challenges such as unstable charging due to magnetic oscillation-type booster circuits, material non-uniformity issues during mass production, and difficulties in efficient wireless communication without Line of Sight, which can lead to accidents and equipment loss during recovery.
Innovation Solution
An apparatus and method for an electronic detonator blaster with an integrated flight function, where a flying vehicle is controlled to ascend to a preset altitude and land at a preset return point after completing a blasting command transmission, with features such as magnetic or busbar connection release, flight path generation for low battery scenarios, and distress notification systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If a magnetic oscillation-type booster circuit is used to charge the capacitor for detonation, then the electrical energy for detonation can be achieved, but the circuit stability deteriorates due to supply voltage changes and other conditions causing oscillation stopping or overcurrent
Solution Approach 1:
The patent changes the fundamental operating parameters of the booster circuit by transitioning from a magnetic oscillation-type circuit to a voltage reversal-type circuit. This parameter change eliminates the instability issues associated with magnetic oscillation while maintaining the capability to generate sufficient detonation energy through controlled voltage reversal and capacitor charging.
Solution Approach 2:
The patent replaces the magnetic field-based oscillation mechanism with an electrical voltage reversal mechanism. By substituting the magnetic oscillation system with a direct electrical control system using voltage reversal, the invention achieves more stable and controllable capacitor charging for detonation purposes.
2Use of energy by moving object
If a magnetic oscillation-type booster circuit is used, then the capacitor can be charged with sufficient energy, but the manufacturing precision deteriorates due to non-uniformity of core material and coil turns during mass production
Solution Approach 1:
The patent replaces the magnetic oscillation mechanism requiring precise core material and coil construction with a voltage reversal electrical control system. This substitution eliminates the manufacturing precision requirements for magnetic components while maintaining the ability to charge the capacitor with sufficient energy for detonation.
Solution Approach 2:
The invention changes the fundamental charging mechanism from magnetic oscillation to voltage reversal, thereby changing the critical parameters from magnetic component specifications (core material uniformity, coil turns) to electrical control parameters that are easier to standardize and control during mass production.
3Ease of operation
If the electronic detonator blaster approaches the blasting area for recovery, then the blaster can be retrieved, but the safety deteriorates due to unstable ground conditions, blasting vibration, or flying stone causing accidents
Solution Approach 1:
The patent introduces a flying vehicle as an intermediary carrier to transport the electronic detonator blaster. This intermediary allows the blaster to be positioned at the blasting area and recovered without human operators being physically present on the unstable ground, thereby eliminating exposure to ground instability, blasting vibration, and flying stone hazards.
Solution Approach 2:
The patent replaces the mechanical transport method (human-carrying or ground-based vehicle) with an aerial flying vehicle system. This substitution eliminates the need for physical contact with the unstable ground and hazardous blasting environment during recovery operations.
4Loss of information
If a fixed repeater is installed on the ground to improve wireless communication, then the communication efficiency improves when LoS is not established, but the device complexity increases and it is difficult to select and operate the repeater location
Solution Approach 1:
The patent transforms the static fixed repeater system into a dynamic mobile communication system using the flying vehicle. The flying vehicle can dynamically position itself to establish Line of Sight communication paths as needed, eliminating the need for fixed ground-based repeater installations and complex location selection procedures.
Solution Approach 2:
The flying vehicle serves multiple functions: it carries the electronic detonator blaster, provides aerial transport, and acts as a mobile communication relay when needed. This multi-functionality eliminates the need for separate fixed repeater infrastructure, reducing system complexity while maintaining communication efficiency.
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
This solution enhances the safety and efficiency of electronic detonator blaster operations by preventing damage from blasting impacts, improving recovery rates, and reducing the risk of accidents during recovery, while also addressing communication inefficiencies through integrated flight control and notification systems.
Implementation Method 1
a flying vehicle capable of being flown and controlled by induction of radio waves
Data Source
AI summary
Proposed are an apparatus and a method for operating an electronic detonator blaster with an integrated flight function. The apparatus includes a blasting command transmission part configured to transmit a blasting command to each of electronic detonators which are combined with a flying vehicle capable of being flown and controlled by induction of radio waves and are connected to each other, a connection control part configured to release the connection of the flying vehicle with the electronic detonators when the transmission of the blasting command is completed, and a flight control part configured to control the flying vehicle to land at a preset return point after ascending to a preset altitude when the connection of the flying vehicle with the electronic detonators is completely released.