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Do not command a maneuver solely because a conjunction alert arrived. Treat the alert as a predicted close approach, then have the authorized flight-dynamics and mission-control team validate the current data, calculate collision probability and consequences, compare maneuver and no-maneuver trajectories, coordinate with any other operator, and obtain formal approval. Execute only the maneuver that passes the mission’s current screening and command process.
What a satellite collision alert actually means
A conjunction screening or Conjunction Data Message (CDM) identifies two cataloged objects whose predicted positions may enter a defined screening volume. It is an alert to analyze an encounter, not proof that a collision will occur. A CDM normally carries the objects’ state vectors and covariances at the time of closest approach (TCA), conjunction parameters, and information about the orbit determination used to produce the prediction.
NASA’s Step 1 guidance is explicit: “It is important to recognize that CDMs are not collision warnings—no actual assessment of collision risk has been performed in generating them.” The prediction can change as tracking observations improve, so an early alert is neither a final risk verdict nor a maneuver command.
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NASA describes screenings performed by the U.S. Space Force 18th Space Defense Squadron three times a day on its conjunction-assessment page. That cadence is context for the NASA service, not a guarantee that every mission receives an alert or update at the same time. Your mission’s data feed, update schedule and contractual notifications control operations.
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First response: stabilize the decision process
The first objective is to prevent an uncoordinated command while preserving enough time for analysis. Put the alert into the mission’s established conjunction-response workflow and identify who has authority to make the mitigation decision.
- Acknowledge and time-stamp the event. Record the CDM identifier, creation time, TCA, source, object identifiers, and the latest tracking or orbit-determination version. Preserve the original message so later updates can be compared.
- Freeze assumptions, not the spacecraft. Do not improvise a burn, attitude change or “safe” radial move. Place any pending maneuver that could alter the encounter into the mission’s review queue until flight dynamics assesses it.
- Confirm the two objects. Check that the primary spacecraft, the secondary object and their covariance data correspond to the current catalog records. Resolve duplicate object IDs, stale ephemerides or unexpected orbit-determination sources before calculating risk.
- Assign the analysis team. Flight dynamics should own trajectory and covariance analysis; mission control should manage command readiness and constraints; the project manager or equivalent mission authority should own the decision under the approved plan.
- Set the next review time. Record when the next tracking update, screening cycle or scheduled status meeting is expected. A conjunction assessment is a moving process, not a one-time reading of the first CDM.
How collision risk is assessed
A useful decision separates the predicted geometry from the uncertainty around that geometry and from the consequences of an impact. No single number is sufficient.
Probability of collision (Pc)
Pc estimates the likelihood that the objects’ actual miss distance will be smaller than their combined effective size, using uncertain predicted trajectories. It is a statistical result based on the state and covariance data; it is not a measured percentage of certainty and does not mean that the objects occupy every point in the uncertainty region with equal likelihood.
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Predicted miss distance
Miss distance is the nominal separation at TCA. A small value can be concerning even when Pc is not yet high, particularly when the covariance is poorly characterized or the object sizes are large. A larger nominal separation does not automatically make the event harmless if uncertainty is broad or the encounter geometry changes in later updates.
Encounter geometry
Relative velocity, the orientation of the encounter plane and the direction of the uncertainty ellipse affect how a separation maps to Pc. Two encounters with the same nominal miss distance can have different risk because their geometry and covariance are different.
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Uncertainty and data quality
Orbit-determination errors, tracking gaps, measurement age and covariance realism determine how much confidence to place in the prediction. Recalculate after each meaningful tracking update; do not carry an old Pc forward as though it were a permanent property of the event.
Consequences
Operational risk includes more than collision likelihood. Consider spacecraft loss, debris generation, interruption of a critical service, crew or human-spaceflight exposure, regulatory obligations, recovery options and the propellant or control margin consumed by a maneuver. A lower-probability event may warrant action when the consequences are severe, while a higher numerical Pc may be managed differently for a spacecraft with unusual control or mission constraints.
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Use the mission’s approved conjunction-response plan, not a generic internet threshold. NASA NPR 8079.1 (2023) states that “The project manager makes the conjunction mitigation decision,” based on risk-analysis recommendations and mission procedures. Other organizations may assign that authority to a flight director, spacecraft owner, operations director or another named role.
For NASA’s Earth-orbit procedure, the baseline at the mitigation commitment point is either a Pc greater than 1E-04 (one in 10,000) or a Euclidean miss distance smaller than the combined hard-body radius. This is a NASA procedural baseline, not a universal rule for commercial, civil, military or international missions. Your approved threshold may differ by orbit regime, spacecraft class, mission phase, consequence model or regulator.
- Verify the exact commitment point in the mission plan: the time by which a mitigation decision must be made to remain executable.
- Confirm whether the threshold applies to the latest CDM, a propagated state at commitment time, or a defined screening product.
- Document the recommendation, the data version used, the decision authority, dissenting views and the rationale for maneuvering or not maneuvering.
Build and screen a maneuver plan
A maneuver is acceptable only if it reduces the target encounter risk without creating a more serious problem elsewhere. Analyze the maneuver and the unmodified trajectory using the same catalog and comparable assumptions.
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Prepare the maneuver ephemeris
Generate a proposed post-maneuver ephemeris with covariance that covers the spacecraft through and beyond TCA. Include the maneuver execution time, burn or control profile, attitude assumptions, dispersions, thrust or delta-v uncertainty and any planned follow-up correction. If the spacecraft uses a different control mode, model the resulting attitude and orbit-estimation effects rather than treating the burn as an ideal impulse.
Screen against the full catalog
Screen the proposed ephemeris against the mission’s complete conjunction catalog, not only the original secondary. NASA best practices call for checking that the mitigation does not create another conjunction above the mission’s mitigation threshold. Compare the maneuvered and unmodified trajectories so the team can identify the risk reduction attributable to the plan.
Check mission constraints
- Available propellant or remaining delta-v and the minimum reserve required for station keeping, deorbiting or contingency recovery.
- Attitude-control authority, wheel or thruster limits, power, thermal and communications constraints during the burn.
- Payload pointing, imaging, navigation, formation-flying or service commitments that could be disrupted.
- Ground-station visibility, command latency, orbit-determination quality and the time needed to verify burn execution.
- Post-maneuver re-acquisition, navigation update and return-to-mission procedures.
Compare more than one candidate
When time and control authority permit, evaluate multiple geometrically different options rather than selecting the first trajectory that lowers Pc. The preferred option is the one that provides adequate risk reduction while preserving future operational margin and avoiding new high-risk encounters.
| Decision dimension | What to compare | Why it matters |
|---|---|---|
| Residual Pc | Post-maneuver probability versus the unmodified case and the mission threshold | Shows whether the plan meets the approved risk criterion |
| Miss distance and geometry | Separation at TCA, relative velocity and encounter-plane orientation | Reveals whether a nominally larger miss distance is robust to uncertainty |
| Covariance quality | Data age, tracking support and sensitivity to state or covariance changes | Indicates how stable the assessment is likely to be |
| Catalog-wide effects | New conjunctions created by each candidate | Prevents moving the risk to another object |
| Spacecraft cost | Delta-v, propellant reserve, attitude and control limits | Protects later mission phases and recovery capability |
| Execution feasibility | Command lead time, communications, burn reliability and verification | A mathematically attractive plan is unsafe if it cannot be executed and confirmed |
| Mission consequence | Service interruption, payload impact, crew or regulatory implications | Balances collision likelihood against what could be lost |
Coordinate with the other operator
If the secondary is an active, maneuverable spacecraft, contact its owner or operator through the channels defined in the conjunction data-sharing agreement. NASA best practices call for agreeing on a way forward and freezing the other spacecraft’s planned trajectory through TCA while the event is resolved. The purpose is to avoid two independent maneuvers that interact unpredictably or recreate the conjunction.
Share the minimum operational data needed for a common assessment: the relevant ephemeris and covariance versions, intended maneuver window, expected post-maneuver state, screening results and a point of contact for rapid updates. Do not assume that silence means consent. If contact cannot be established, escalate according to the mission plan and treat the other object’s trajectory as an uncertainty in the risk analysis.
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Timing, submission and execution controls
NASA NPR 8079.1 (2023) calls for proposed maneuver plans, including ephemerides with covariance, to be submitted to the NASA Conjunction Assessment Risk Analysis (CARA) team or Johnson Space Center Flight Operations Directorate at least 24 hours before intended execution for screening. That lead time belongs to the NASA procedure; another operator may specify a different deadline or screening service.
- Plan: Generate the maneuver candidate and its covariance, then run internal dynamics, constraints and catalog-wide screening.
- Submit: Deliver the agreed ephemeris package through the mission’s designated data exchange, with version, time system, maneuver assumptions and contact information clearly identified.
- Review: Resolve screening findings, compare updated tracking data and obtain the named decision authority’s approval.
- Commit: Enter the approved maneuver into the command plan only after confirming that no newer CDM or operator coordination changes the assessment.
- Execute and verify: Conduct the burn through the normal command authorization process, confirm spacecraft telemetry and obtain a post-burn orbit determination.
- Close the event: Propagate the verified post-maneuver state, screen the catalog again and retain the decision and execution record for mission assurance.
The reviewed guidance does not provide a universal command sequence or a safe maneuver vector for an unknown spacecraft. A valid burn depends on propulsion, attitude and orbit-control capabilities, current ephemerides, mission constraints and operational authority. Only the responsible flight-dynamics and mission-control teams can translate an approved trajectory into spacecraft commands.
When the right decision is to wait
Not every alert crosses the mission’s mitigation threshold. If the current analysis shows acceptable risk, continue surveillance under the approved plan rather than maneuvering reflexively. Waiting is an active decision: define the next data update, the trigger for reconsideration, the latest time a maneuver remains feasible and the person responsible for reviewing it.
A no-maneuver decision should still include a catalog-wide check, a record of Pc, miss distance, geometry and covariance quality, and a contingency plan if subsequent tracking raises the risk. The assessment must be refreshed whenever new observations materially change the encounter.
Common failure modes and recovery actions
“The CDM says collision, so burn now.”
Problem: A proximity alert is mistaken for a completed risk assessment. Recovery: Reclassify the message as a screening input, obtain current state and covariance data, and calculate Pc and consequences before any command.
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Using a stale orbit or covariance
Problem: The team bases a decision on an earlier message after new tracking data are available. Recovery: Re-run the encounter with the latest accepted orbit determination and retain the prior result only for trend analysis.
Optimizing only the original conjunction
Problem: A burn lowers the target Pc but creates a new high-risk event with another catalog object. Recovery: Screen the complete catalog with the maneuvered ephemeris and compare it with the unmodified trajectory.
Two operators maneuver independently
Problem: Both spacecraft change trajectory without coordination, producing an unexpected encounter. Recovery: Use the designated operator-to-operator channel, agree on a trajectory freeze through TCA where possible, and escalate unresponsive contacts through mission and regulatory procedures.
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Problem: The candidate requires unavailable delta-v, an unsupported attitude, insufficient communications or an unrealistic command lead time. Recovery: Re-plan within propulsion, guidance, communications and reserve limits; document the trade-off rather than hiding it in an idealized simulation.
Failing to verify the post-burn state
Problem: The mission assumes the burn occurred as modeled. Recovery: Check telemetry, obtain a new orbit determination, and perform a fresh conjunction screening before declaring the event closed.
What a complete event record should contain
- Every received CDM and the orbit-determination or tracking version associated with it.
- Pc, miss distance, encounter geometry, covariance quality and consequence assessment at each decision point.
- The approved threshold and the role authorized to decide.
- Unmodified and candidate maneuver ephemerides with covariance, including assumptions and dispersions.
- Full-catalog screening results and evidence that no unacceptable conjunction was created.
- Operator coordination messages, trajectory-freeze agreements and escalation attempts.
- Approval, command authorization, execution telemetry, post-burn orbit determination and closure screening.
This record supports later safety review and makes clear which facts were known when the decision was made. It also prevents a preliminary alert, an analysis recommendation and an executed command from being conflated in mission reporting.
Bottom line
A satellite collision alert is a trigger for disciplined analysis, not an instruction to fire thrusters. Validate the current encounter data, assess Pc and consequences, apply your mission’s approved authority and threshold, screen every candidate against the full catalog, coordinate with an active secondary operator, meet the required data lead time, and execute only through the authorized command process. Reassess after every significant tracking update and verify the post-maneuver orbit before closing the event.
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