During the past few years, several research programs have assessed the current state and future evolution of the Low Earth Orbit region. These studies indicate that space debris density could reach a critical level such that there will be a continuous increase in the number of debris objects, primarily driven by debris-debris collision activity known as the Kessler effect. These studies also highlight the urgency for active debris removal. An Active Debris Removal System (ADRS) is capable of approaching the debris object through a close-range rendezvous, stabilizing its attitude, establishing physical connection, and finally de-orbiting the debris object. The de-orbiting phase could be powered by a chemical engine or an electrodynamic tether (EDT) system. The aim of this project is to model and evaluate a debris removal mission in which an adapted rocket upper stage, equipped with an electrodynamic tether (EDT) system, is employed for de-orbiting a debris object. This hybrid ADRS is assumed to be initially part of a launch vehicle on a normal satellite deployment mission, and a far-approach manoeuvre will be required to align the ADRS’ orbit with that of the target debris. We begin by selecting a suitable target debris and launch vehicle, and then proceed to modelling the entire debris removal mission from launch to de-orbiting of the target debris object using Analytical Graphic Inc.’s Systems Tool Kit (STK). Presented at the 2012 Beining Space Sustainability Conference

1. DESIGN AND EVALUATION OF AN
ACTIVE SPACE DEBRIS REMOVAL
MISSION USING CHEMICAL
PROPULSION AND
ELECTRODYNAMIC TETHERS
IN SUPPORT OF THE UNITED NATIONS
PROGRAMME ON SPACE APPLICATIONS
Matteo Emanuelli
S. Ali Nasseri
CJ Nwosa
Siddharth Raval
Andrea Turconi
SGAC Space Safety and Sustainability Working Group

2. SGAC: BEYOND A NETWORK
• Introduction
• Target Debris
• Mission Phases
• Launch Vehicle and Launch Site determination
• Mission Simulation in STK and Orbital Maneuvers
• Electrodynamic Tether
• Chemical Propulsion Analysis
• Conclusions and Future Work
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IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS 2
CONTENT
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

3. SGAC: BEYOND A NETWORK
Introduction
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3IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT
• Space Debris: Critical Level LEO
• Kessler Effect
• Idea: Integrate de-orbiting system with an
upper stage
• Each upper stage will de-orbit itself and
space debris
• We can use upper stage subsystems
during the mission, reducing mission
costs.

4. SGAC: BEYOND A NETWORK
Launch and
separation of
payloads
Maneuver
to
approach
space
debris
Grab debris
and control
attitude
Decrease
inclination
(chemical
propulsion)
Reduce
altitude
using EDT
Introduction: Flight Phases
5/16/2014
4IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

5. SGAC: BEYOND A NETWORK
Target Debris Identification
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157
33
14
19
11
10
8 27
Target Debris
Komos
Soyuz
Tsyklon-3
Zenit
Dnepr
Thor Burner 2A
Scout
Other
Kosmos 3M
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT
• Low earth orbit.
• Selected body:
Kosmos 3M

6. SGAC: BEYOND A NETWORK
Mean Motion (deg/s) 0.0573292
Eccentricity 0.002639
Inclination (deg) 82.976
Argument of Perigee (deg) 151.655
RAAN (deg) 233.421
Mean Anomaly (deg) 208.605
Target Debris Identification
5/16/2014
6IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

7. SGAC: BEYOND A NETWORK
• Analyzed all launch vehicles with
• Upper stage restartability
• Large payload mass for SSO
• High propellant capacity
• Chosen Launch Vehicles:
• Soyuz 2 with Fregat upper stage
• Proton-M with Breeze-M upper stage
• Chosen Launch site:
• Plesetsk (Russian Federation - 62°57′35″N,
40°41′2″E)
Launch Vehicle and Launch Site
5/16/2014
7IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

8. SGAC: BEYOND A NETWORK
Mission Simulation in STK
5/16/2014
8IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
Maneuver
Velocity
Increment
(km/s)
Provided by
Launch to Park Orbit - Launch Vehicle
Altitude increase 0.105 Upperstage
Hohman transfer 0.056 Upperstage
Combined change 0.849 Upperstage
Inclination change 1 (83 to 74 deg) 1.71 Upperstage
Inclination change 2 (74 to 66 deg) 1.101 Upperstage
Inclination change 3 (66 to 53 deg) 1.809 Upperstage
Inclination change 4 (53 to 43 deg) 1.402 Upperstage
Inclination change 5 (43 to 29 deg) 1.576 Upperstage
Inclination change 6 (29 to 18 deg) 2.808 Upperstage
Altitude Decrease (900 to 500 km) Depends EDT
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

9. SGAC: BEYOND A NETWORK
• EDT mass
80 kg
EDT Model
5/16/2014
9IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

10. SGAC: BEYOND A NETWORK
Soyuz upper stage
(Fregat)
Proton upper stage
(Breeze-M)
Primary payload mass (ton) 1-3 4-5
Vacuum specific impulse (s) 327 325.5
Propellant mass (ton) 5.35 19.8
Structural mass (ton) 1 2.37
EDT mass (kg) 80
Debris altitude (km) 900
Debris inclination (deg) 83
Kosmos 3M mass (kg) 1435
Target orbit (km) 500
Mass and Altitude Properties
5/16/2014
10IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

11. SGAC: BEYOND A NETWORK
(a) Propellant used versus inclination at
which EDT is turned on for the Soyuz
upper stage
(b) Propellant used versus inclination at
which EDT is turned on for the Proton
upper stage
Results: Propellant use
5/16/2014
11IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

12. SGAC: BEYOND A NETWORK
(c) Residual propellant versus inclination
at which EDT is turned on for the Soyuz
upper stage
(d) Residual propellant versus inclination
at which EDT is turned on for the Proton
upper stage
Results: Residual Propellant
5/16/2014
12IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

13. SGAC: BEYOND A NETWORK
(e) Time to de-orbit versus inclination at
which EDT is turned on for the Soyuz
upper stage
(f) Time to de-orbit versus inclination at
which EDT is turned on for the Proton
upper stage
Results: De-orbiting Time
5/16/2014
13IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

14. SGAC: BEYOND A NETWORK
• Modified Soyuz or Proton upper stage equipped
with a tether system, can deliver a primary
payload to a 900 km polar orbit and connect to a
Kosmos 3M 2nd stage to de-orbit it.
• It is clear that a hybrid solution using a chemical-
EDT system is the best choice for this particular
mission because of the short quantity of
propellant left from previous stages of the
mission.
Conclusions
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14IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

15. SGAC: BEYOND A NETWORK
• Further simulation to refine the preliminary result
• Modelling the close approach, grabbing and
stabilization of the space debris
• Simulating the EDT system using MATLAB
Future Work
5/16/2014
15IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

16. SGAC: BEYOND A NETWORK
Acknowledgement
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16IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
1. Analytical Graphics, Inc. (AGI)
2. Secure World Foundation
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT

17. SGAC: BEYOND A NETWORK
Space Safety and Sustainability Group
Sustaining space activities for future generations
Email: sidr.aero@yahoo.com
Website: www.spacegeneration.org/sss
Thank you!
5/16/2014
17IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS
DESIGN AND EVALUATION OF AN ADR MISSION USING CHEMICAL PROPULSION AND EDT