Abstract

The proliferation of space debris poses an escalating threat to operational satellites and future space missions. The 2007 Chinese anti-satellite missile test dramatically underscored this issue, generating thousands of pieces of debris that now orbit Earth. This paper presents the Collaborative Debris Removal And Mapping (CDRAM) mission, a novel approach to space debris mitigation. CDRAM proposes a unique debris removal methodology, incorporating a 3-axis robotic arm for capture and a reverse-acceleration technique for deorbiting. This paper details the design and construction of the CDRAM spacecraft, the proposed launch procedure, and the innovative debris removal system.

Introduction

The Growing Threat of Space Debris

Space debris, ranging from defunct satellites to minute fragments, presents a significant hazard to both manned and unmanned space activities. The sheer volume of debris, coupled with high orbital velocities, creates a dangerous environment where even small objects can cause substantial damage. The 2007 Chinese anti-satellite test exemplifies the problem, adding a substantial amount of debris to an already congested orbital environment. The challenge is further compounded by the fact that only a fraction of space debris is currently tracked, leaving countless smaller, yet still potentially damaging, objects unmonitored.

Current Debris Removal Efforts

Recognizing the escalating threat, space agencies worldwide are actively researching and developing debris removal technologies. Various approaches are being explored, including robotic capture, net deployment, and targeted deorbiting techniques. While these efforts represent progress, the scale of the debris problem necessitates innovative and efficient solutions.

The CDRAM Mission: A Novel Approach

The CDRAM mission aims to address the space debris challenge through a unique, collaborative approach. The CDRAM spacecraft is designed to not only remove debris but also map its distribution, contributing to a more comprehensive understanding of the space debris environment. This dual functionality enhances the mission's value and its potential impact on space safety.

Mission Synopsis

CDRAM is a spacecraft designed for launch into a Sun-synchronous orbit at an altitude of approximately 850 km and an inclination of 98 degrees, targeting the region populated by debris from the 2007 anti-satellite test. The spacecraft will carry a 3-axis robotic arm (GRAX3) for capturing debris and an advanced LiDAR system (ADILi) for precise debris identification and navigation. GPS will provide preliminary navigation. A primary mission objective is the removal of targeted debris. A secondary objective is the detailed mapping of the space debris field. The mission is designed for a five-year operational lifespan.

Mission Phases

Design and Construction Phase

Spacecraft Overview

The CDRAM spacecraft will utilize the Lockheed Martin LM 1000 series spacecraft bus, chosen for its adaptability and support for mid-size missions. The spacecraft will incorporate bipropellant thrusters for rapid maneuvering and ion thrusters for precise, long-term adjustments. Power will be supplied by deployable solar panels coupled with lithium-ion batteries. Telecommunications with ground control will be maintained via the TDRSS system. [Insert diagram of CDRAM spacecraft, showing key components].

Attitude Control System

Precise attitude control is critical for all phases of the mission, particularly during debris rendezvous, capture, and deorbiting. The attitude control system must compensate for changes in the spacecraft's center of mass, especially during robotic arm operations and after debris capture. The combination of bipropellant and ion thrusters will provide both the rapid response and the long-term precision needed for these maneuvers.

Telecommunications and Power Systems

Communication with ground control will be facilitated by the TDRSS system, using a main antenna on the spacecraft's top side. A secondary antenna will provide redundancy. The power system, based on deployable solar panels and lithium-ion batteries, will provide sufficient power for all spacecraft operations, including the robotic arm and LiDAR system.

Launch Phase

The CDRAM spacecraft is designed for launch aboard a Chinese Long March 4B launch vehicle from the Taiyuan Satellite Launch Center (TSLC). The spacecraft will be transported to TSLC for pre-launch testing. [Insert diagram of launch vehicle and launch site].

Operational Phase and End of Life

Following orbital insertion, the spacecraft systems will undergo a one-month testing period. Preliminary debris location will be conducted using GPS data and existing debris databases. Final rendezvous and capture will be guided by the onboard LiDAR system (ADILi). Debris removal operations will begin at lower altitudes within the target orbital region and progress to higher altitudes. The five-year mission will conclude with the spacecraft lowering its orbit for atmospheric burnup.

Payload Overview

The CDRAM payload consists of two primary components: the ADILi LiDAR system for debris identification and the GRAX3 robotic arm for debris capture and deorbiting.

Debris Identification

Database and Preliminary Navigation

CDRAM will utilize existing space debris databases from organizations like NASA and ESA, combined with GPS data, for preliminary debris location.

Advanced Debris Identification by LiDAR (ADILi)

The ADILi system, based on LiDAR technology, will provide precise debris identification and characterization for final rendezvous. [Insert diagram of ADILi system and its operational principle].

Debris Removal Instrument: GRAX3

GRAX3 Design and Operation

The GRAX3 robotic arm is a 3-axis, extendable arm designed for capturing and manipulating space debris. The arm will be constructed from lightweight carbon-fiber materials and equipped with dual grippers. The reverse-acceleration deorbiting method will involve capturing the debris, repositioning it behind the spacecraft, and then releasing it with a spring-loaded mechanism that imparts a retrograde acceleration, lowering the debris's orbit. [Insert diagram illustrating the GRAX3 robotic arm and the reverse-acceleration deorbiting process].

Debris Characterization and Limitations

CDRAM will target debris based on size, mass, structural integrity, and tumbling rate. Specific criteria will be established for each of these parameters to ensure successful capture and deorbiting.

Secondary Mission: Debris Mapping

In the event of a primary mission failure, CDRAM will transition to a secondary mission of debris mapping. The ADILi system will be used to create a detailed map of the space debris field in the target region.

Success Criteria and Conclusions

The CDRAM mission offers a novel and potentially highly effective approach to space debris mitigation. The reverse-acceleration deorbiting technique offers fuel efficiency advantages compared to traditional methods. The mission prioritizes the removal of high-risk debris, defined by their mass and collision probability. Success will be measured by the number of debris successfully deorbited and the quality of the debris map generated. The CDRAM mission has the potential to make a significant contribution to the long-term sustainability of space activities.

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