Euclid - VII. Structural-thermal-optical performance

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Table 6

Estimated correlations based on the analysis of the in-orbit data.

Relation	In orbit	STOP prediction	Comment
ΔT_BP/ΔSAA (mK deg⁻¹)	5–15	2.6	SAA >90° for STOP
$Δ R_{norm}^{2} / Δ T_{B P} (% K^{- 1})$ $Mathematical equation: $\[\Delta R_{\text {norm }}^{2} / \Delta T_{\mathrm{BP}}\left(\% \mathrm{~K}^{-1}\right)\]$$	3–6	3.7	In-orbit value from peak on mission day 533 Estimated 30% uncertainty in R² due to colour
$Δ R_{norm}^{2} / Δ S A A (% \deg^{- 1})$ $Mathematical equation: $\[\Delta R_{\text {norm}}^{2} / \Delta \mathrm{SAA}\left(\% \operatorname{deg}^{-1}\right)\]$$	0.03–0.05	0.01	SAA >90°; in-orbit peak on mission day 533 Estimated 30% uncertainty in R² due to colour
Δe_norm/ΔT_BP (% K⁻¹)	50–70	70	Variation of mean normalised ellipticity \|e\|
Δe₁/ΔT_BP (K⁻¹)	0.01	−	Estimated from Fig. 11b
Δe₂/ΔT_BP (K⁻¹)	−0.013	−	Estimated from Fig. 11c
Δe_norm/ΔSAA (% deg⁻¹)	0.5–0.7	0.2	SAA >90° for STOP;
Baseplate thermal time constant (h)	20	12–15	The larger STOP value was derived from System parameters updated close to launch
M1 thermal time constant (h)	33	33–35

Notes. In-orbit R² and e were extracted from data obtained in the period September to December 2024, averaged over intervals of 12 h. Temperature sensor THM05 was used for T_BP.

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