Orbital Debris Removal Device with Timing-Controlled Braking
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Solution Overview
Problem
Current methods for removing space debris are inefficient for large debris, as they struggle to capture and slow down debris of varying shapes, sizes, and rotations, leading to difficulties in entering the atmosphere for burning and removal.
Innovation Solution
A debris removal device with an adhesion part, braking part, and timing control part that adheres to space debris and generates a braking force parallel to the orbit plane and tangential line in the opposite direction of debris circulation, allowing for controlled deceleration and alignment of the braking force through the debris' gravity center to prevent additional rotation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If conventional debris removal methods (plasma charging or foam capture) are used, then minute to relatively small debris can be removed, but relatively large space debris cannot be effectively captured or slowed down
Solution Approach 1:
The braking force application is segmented into multiple controlled impulses rather than continuous force, allowing the system to manage the complex task of decelerating large rotating debris through manageable stages while maintaining capture feasibility
Solution Approach 2:
The system dynamically adjusts the timing and direction of braking force application based on the debris' orbital position and rotation state, enabling effective deceleration of large debris without requiring complete rotation stopping before capture
2Speed
If braking force is applied continuously to slow down rotating debris, then circling speed decreases, but additional rotation is generated and complexity increases
Solution Approach 1:
The braking force is applied periodically at specific orbital positions rather than continuously, with timing controlled to coincide with favorable geometric configurations that naturally align the force through the gravity center, reducing rotational side effects while maintaining deceleration effectiveness
Solution Approach 2:
The system incorporates timing control that monitors orbital position and adjusts braking force application accordingly, using feedback from the debris' orbital state to optimize when and how braking force is applied, preventing additional rotation while achieving speed reduction
3Speed
If braking force direction is not aligned with gravity center, then circling speed decreases, but additional rotation is generated
Solution Approach 1:
The timing control system预先 determines and prepares the optimal braking moment when the force direction will naturally align with the gravity center, preventing rotational instability before it occurs by advance planning of the braking action timing and direction
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
Effectively decreases the circling speed of space debris, enabling it to enter the atmosphere for burning and removal without requiring the complex task of stopping its rotation, thus improving cost-efficiency and operational feasibility.
Implementation Method 1
an adhesion part to let the space debris adhere to the body part
Implementation Method 2
a braking part to generate braking force in a specific direction so as to act on the space debris adhering to the body part
Implementation Method 3
when the body part is located at a specific region on the orbit where a direction of the braking force is substantially parallel to an orbit plane including the orbit
Data Source
Figure 1
Figure 2~3
Figure 4~6
AI summary
Provided is a debris removal device capable of removing space debris of relatively large size effectively. A debris removal device 3 that removes space debris circling around a predetermined orbit about the earth, and includes: a body part 10; an adhesion part 20 to let the space debris adhere to the body part 10; a braking part 30 to generate braking force in a specific direction so as to act on the space debris adhering to the body part 10 via the adhesion part 20 during circling of the body part 10 around the orbit together with the space debris; and a timing control part 40 to control generation timing of the braking force. The timing control part 40 generates the braking force, during circling of the body part 10 together with the space debris around the orbit, when the body part 10 is located at a specific region on the orbit where a direction of the braking force is (i) substantially parallel to an orbit plane including the orbit and (ii) substantially parallel to a tangential line of the orbit, and (iii) in substantially an opposite direction of a circling direction of the space debris.