Platform

The Analytics
Platform

From raw DAQ telemetry to a complete diagnostic report package — automated, reproducible, and designed for liquid rocket engine development.

Automated Analytics Pipeline

Five stages from test execution to complete deliverable package — with no manual data preparation in between.

01
RAW DATA
Test Execution

Hot fire test runs on the Thrust.kz stand. DAQ system captures telemetry at high frequency. Video synchronized to data stream via LED beacon.

02
CSV
Telemetry Ingestion

Raw CSV files and video clips are ingested. Column normalization, unit conversion, and channel alias mapping are applied automatically.

03
L1
L1 Descriptive Report

Automated generation of the L1 HTML report: 15+ parameter tabs, statistical summaries, outlier detection, atmospheric corrections, embedded video.

04
L2
L2 Diagnostic Report

Derived performance parameters (c*, CF, Isp, O/F), combustion quality assessment, ignition event classification, and anomaly flagging.

05
CAMPAIGN
Campaign Package

Campaign HUB aggregates all tests. COMP Comparative report overlays metrics across tests. Full DOCX deliverables generated for program review.

Four Analytical Views

Each report type addresses a different level of analysis — from raw channel visualization to multi-campaign trend tracking.

LRE_L1_Descriptive.html
Overview
Thrust
Pressure
Temp
Perf.
Peak Thrust
413
Duration
13.3
Avg Pc
1.43
L1 · Descriptive
Time-Series Analytics

Comprehensive per-channel time-series visualization with statistical summaries, burn window detection, outlier clipping, and synchronized video playback across 15+ parameter channels.

ThrustPressureTemperatureMass FlowVideo
LRE_L2_Diagnostic.html
Summary
Ignition
Combustion
Perf.
c*
1510
Isp
243
O/F
1.41
L2 · Diagnostic
Combustion Quality Assessment

Derived performance parameters — c*, CF, Isp, O/F — computed from measured thrust and mass flow. Ignition event classification, transient analysis, and combustion stability metrics.

c*IspCFO/FIgnitionJANNAF
HUB_Campaign_Master.html
Overview
Test A
Test B
Test C
Channels
50+
Max Thrust
413
Max Burn
13.3
Test A Test B Test C
HUB · Campaign
Campaign Master Dashboard

Unified campaign overview aggregating all test results. Individual test cards with key metrics, status badges, and links to L1/L2 reports. Program-level KPI summary for stakeholder review.

Multi-testKPI SummaryNavigation Hub
LRE_COMP_Comparative.html
Thrust Compare
Performance
Conditions
Parameters
40+
Δ Pc
0.4
Δ O/F
0.18
Thrust Isp
COMP · Comparative
Cross-Test Comparison

Side-by-side overlay of performance metrics across all campaign tests. Identify trends, regressions, and improvements across engine development iterations with normalized parameter comparisons.

Trend AnalysisOverlay ChartsPerformance Delta
Platform-Measured
Performance Data

All metrics derived by the Aexion platform from live telemetry. The test with propellant mass flow instrumentation produced the campaign's most complete performance dataset.

Peak Thrust
413
kgf · 4.05 kN
LOX/IPA engine
Chamber Pressure
1.43
MPa · Avg Pc
Measured · LOX/IPA
O/F Ratio
1.41
LOX / IPA
Measured mass flow
Max Burn Duration
13.27
seconds
LOX/IPA engine
Test Stand — Thrust.kz
LocationAlmaty Region, Kazakhstan
Elevation~870 m ASL
PropellantLOX / IPA
Engine Geometry
Throat Area (A*)1.66 × 10⁻³ m²
Throat Diameter (d*)45.98 mm
Expansion Ratio (ε)4.38
Contraction Ratio (CR)5.00
Standards
Report FrameworkJANNAF GL-2012-01
Output FormatsHTML · DOCX
Atm. CorrectionsApplied (UAAA ref.)
See the Platform
in Action

Request a demo and we'll walk you through a complete report package — from raw telemetry to the full analytics suite.