Active Debris Removal Using Modified Launch Vehicle Upper Stages

ACTIVE DEBRIS REMOVAL USING MODIFIED UPPER STAGES

IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS

Matteo EmanuelliS. Ali Nasseri

Siddharth Raval Andrea Turconi

SGAC Space Safety and Sustainability Project Group

SGAC: BEYOND A NETWORK 04/07/2023

2IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS

• ADR: Where?

• System concept

• System components

• Feasibility study

• Conclusion

• Future work

Outline

04/07/2023ADR USING MODIFIED UPPER STAGES



• Space debris density could reach a critical level.• Continuous increase in the number of debris

objects, primarily driven by debris-debris collision activity.

• Mitigation guidelines don’t apply to existing debris.• Existing debris risk is higher in low-Earth orbit

(LEO) due to a combination of high debris concentration, large number of crossings and high relative velocities.

• NASA studies: To stabilize the LEO debris environment, 5-15 large objects have to be removed per year

Space Debris Situation




• The critical region of interest for a future Active Debris Removal (ADR) missions• Altitude between 800km and 1000km, with an

inclination ranging from 60° to 110° • The larger space debris were identified as

suitable ADR targets• Higher total mass • Higher risk of cascade collisions• Easy to track • Well defined in size, mass and shape

• Focusing on rocket bodies

Suitable ADR targets




• In the selected region of interest, 141 rocket bodies are being tracked

• The majority of which are at an inclination of around 80°.

Suitable ADR targets

157

33

1419

1110 8

27

KomosSoyuzTsyklon-3ZenitDneprThor Burner 2AScoutOther

04/07/2023

Kosmos

ADR USING MODIFIED UPPER STAGES



• Kosmos-3 M debris used as case study. (SL-8 R/B

32053)

• Orbital altitude of 959 km, inclination of about 83° and

mass of 1435 kg

• Does not decay automatically within the 25 years

guideline ADR mission necessary for timely disposal

• Many studies on ADR conducted by various entities

currently focus on the Kosmos 3M

Target Debris for Test Studies




Target Debris for Test Studies




• An Active Debris Removal System (ADRS) is capable of approaching the debris object through a close-range rendezvous, establishing physical contact, stabilizing its attitude and finally de-orbiting the debris object.

• Frequent missions• Cost-effective• Initial solution: A piggyback payload with two

propulsion systems• However, upper stages are used during the launch

and they do have many subsystems which we need• Why not use them?

System Concept




• Modify launch vehicle upper stage • All de-orbiting subsystems integrated onto the

upper stage (as packages) and work in concert with upper stage subsystems during mission.

• Merits:• No new debris due to space launch. (average 70

launches per year)• One large space debris can be de-orbited per launch,

stabilizing the debris environment• Reduced cost and complexity by using upper stage

subsystems

System Concept




Concept of Operation

Phase 5Reduce inclination using chemical propulsion Deploy EDT Reduce orbital altitude to 200 km

Phase 4

Estimate motion of debris Grab object Control attitude

Phase 3

Approach debris object Identify objectPhase 2

Deliver primary payload Initiate debris removal mission

Phase 1

Launch




• Case study performed using these estimations

System Components

Subsystems Mass (kg)EDT mass [8] 80Grabbing Mechanism 100Motion Estimation 5Power System 5Misc. 10Total 200




System Components: Grabbing Mechanism

04/07/2023

Method Pros Cons

Docking through propulsive nozzle

Application for a wide range of rocket bodies. Usable also if the target is spinning.

Very precise close approach required. Not applicable to tumbling targets.

HarpoonProjectile designed to anchor safely into a wide range of materials.

Possible creation of new debris during the impact, risk of explosion, attitude modification.

Net Indifferent to target attitude.

Net’s material to be flexible and resistant. Net deployment required specialized manoeuvres.

Robotic arm

Applicable to different type of space debris. Provides the most control on the space debris.

De-tumbling procedure required. Accurate pre-inspection of the debris to chose the grabbing point. Most complex.


SGAC: BEYOND A NETWORK


• Analyzed as a possible option• Propellant-less and fully reusable• Low thrust• Collision avoidance is critical due to their length• Current model (Bombardelli, 2010)

System Components: EDT




• Criteria • Reach the target orbit with enough payload. • Restartable due to the number of maneuvers required. • Enough propellant for the mission.

• Following launchers analyzed• Soyuz 2 with the Fregat upper stage launched from the

Plesetsk and Kourou spaceports.• Proton M with the Breeze-M upper stage launched from the

Plesetsk spaceport. • DELTA 4M launched from Vandenberg air force base.• Atlas 5 401 launched from Vandenberg air force base.• Vega launched from Kourou spaceport.

• Small, medium and heavy launch systems are all represented.

Mission Analysis: Launch



15

• Simulation in AGI STK• Several manoeuvres, during which the primary payload is

released, the upper stage reaches the target orbit at an altitude of 920 km and an inclination of 83°

• The upper stage should approach and grab the debris (not modelled)

• Reduce inclination, if necessary

Mission Analysis: ΔV Required

IN SUPPORT OF THE UNITED NATIONS PROGRAMME ON SPACE APPLICATIONS

04/07/2023

Manoeuvre Δ V (km/s)Launch Vehicle Soyuz 2 Plesetsk Soyuz 2 Kourou Proton M Vega Delta 4 ATLAS 5

Altitude increase 0.105 0.164 0.105 0.181 0.177 0.186

Hohmann transfer 0.056 0.143 0.056 0.196 0.046 0.046

Combined change 0.849 2.200 0.849 2.139 0.331 0.331

Inclination change 1 (83 to 74 deg) 1.710 1.101 1.71 1.101 1.100 1.100

Inclination change 2 (74 to 66 deg) 1.101 0.600 1.101 0.501 0.501 0.501

Inclination change 3 (66 to 53 deg) 1.809 1.908 1.809 - 2.093 2.107







Mission Analysis: Propellant Available

04/07/2023

ATLAS V DELTA IV M





Soyuz from Plesetsk Soyuz from Korou





Proton M Vega




• At least a velocity increment of 0.5 km/s is needed• Propellant used in grabbing manoeuvre not included

Mission Analysis: Direct De-orbit

04/07/2023

InclinationΔV (km/s)

ATLAS V DELTA IV M Proton Soyuz from Kourou

Soyuz from Plesetsk

83 7.618 7.672 4.043 0 1.82074 6.518 6.572 2.333 0 0.11066 6.016 6.071 1.232 0 053 3.909 3.978 0 0 043 2.689 2.774 0 0 029 0.787 0.873 0 0 018 0 0 0 0 0




Mission Analysis: Time to De-orbit with EDT

04/07/2023

Reduce altitude to 200 km




• The launch cost for the system ranges from $390 k to $1689 k, averaging at $848k.

• As the upper stage removes itself and a rocket body, it seems reasonable that the removal cost per kg of debris will be lower than costs per kg using this concept, which is important in choosing ADR methods [9].

• May be implemented as a service provided by the launch service provider.

Costs and Implementation




• The proposed solution can remove large space

debris from high altitude high inclination LEO

orbits in a timely manner using medium to heavy

launchers.

• Heavy launchers could carry out the mission

without an EDT or on several objects, but medium

upper stages require an EDT system.

Conclusions




• Finalize choice of grabbing mechanism

• Model the close approach, grabbing and

stabilization of the space debris

• Re-entry safety analysis

• Cost estimation

• Simulate mission for more launchers and several

target debris for comparison

Future Work




Acknowledgement

1. Analytical Graphics, Inc. (AGI)

2. International Association for the Advancement of Space Safety




Space Safety and Sustainability Project Group

Sustaining space activities for future generations

Email: [email protected]: www.spacegeneration.org/sss

Thank you!


http://www.spacegeneration.org/sss

Active Debris Removal Using Modified Launch Vehicle Upper Stages

Engineering

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