Propulsion & Hot-Fire

Rocket Propulsion Testing & Ground Validation

High-frequency transient DAQ, turbopump hot-fire telemetry, and acoustic vibration analysis for ISRO (LPSC/IPRC Mahendragiri) and SpaceX (McGregor Test Stand, Texas).

HIGH-FREQUENCY HOT-FIRE DAQ

Microsecond Hot-Fire Transient Capture & Rocket Engine DAQ

Ingest tens of thousands of combustion chamber pressure transducers, turbopump vibration accelerometers, and cryogenic flow sensors up to 100kHz. Capture ignition pressure spikes, acoustic resonances, and LOX/LH2 chill-down transients across ISRO LPSC, IPRC Mahendragiri, and SpaceX McGregor test stands.

Combustion & Transients
100kHz chamber pressure spike capture with microsecond PTP sync
Turbopump & Cryo DAQ
LOX/LH2 chill-down, HAT vacuum ignition & gimbal TVC response
Rocket Engine Hot-Fire DAQ Stand
IPRC MAHENDARAGIRI & MCGREGOR DAQ ONLINE100,000 Hz Ingest
PLATFORM CAPABILITIES

Designed for Mission-Critical Fidelity

1. ISRO LPSC / IPRC Mahendragiri HAT & Cryogenic Test Stand

High Altitude Test (HAT) facility vacuum ignition simulation for CE-7.5 and CE-20 cryogenic upper stage engines. Monitor LOX/LH2 chill-down, turbopump cold flow, and CUS integrated stage static firing in real time.

1. ISRO LPSC / IPRC Mahendragiri HAT & Cryogenic Test Stand

One telemetry platform from component cold-flow to pad static fire

ISRO LPSC & MAHENDARAGIRI

Solid motor static test firing at SHAR STEX complex & S200 segment testing.
High Altitude Test (HAT) facility vacuum ignition simulation for CE-7.5 & CE-20 cryo engines.
Gas generator, turbopump cold/hot flow, injector head & stage static tests (L110, C25).

SPACEX MCGREGOR & STARBASE

Static fire test stand firings at McGregor development facility for Merlin & Raptor.
Component acceptance hot-fire testing for every engine prior to stage assembly.
Full duration static fire burns, Wet Dress Rehearsals (WDR), and Starship LN2 cryo proof.

PAD STATIC FIRE & HOPS

Low-altitude flight testing (Starhopper, SN5/SN6 Starship vehicle hops).
Thrust Vector Control (TVC) hydraulic & electric gimbal actuator validation.
Pre-launch pad static fire operations and zero-packet-drop microsecond DAQ archival.
Rocket engine hot-fire

From Mahendragiri HAT Chambers to McGregor Test Stands. Zero Data Loss.

ISRO (LPSC/IPRC MAHENDARAGIRI) & SPACEX (MCGREGOR STAND) PIPELINE

Rocket Propulsion Ground Testing & Validation Flow

Standard rocket engine & stage testing workflow using ISRO (LPSC / IPRC Mahendragiri) & SpaceX (McGregor Test Facility, Texas) industry terminology.

STEX SDSC-SHAR

ISRO 1. Solid Motor Testing (SHAR STEX Complex)

Static Test firing at SHAR

Static Test and Evaluation Complex (STEX) firing at SDSC SHAR

Sub-scale motor testing

Propellant grain burn rate & acoustic sub-scale motor validation

Full-scale segment testing

Segmented booster static test firing (S200 solid rocket booster)

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ISRO 1. Solid Motor Testing (SHAR STEX Complex)
STEX SDSC-SHAR
IPRC / MCGREGOR READY
PLATFORM CAPABILITIES

Engineered for High-Fidelity Domain Telemetry

100 kHz Ingest Rate

Native C++ edge buffer handles extreme data bursts without backpressure.

Nanosecond Sync

PTP IEEE 1588 synchronization across distributed test stands.

Air-Gapped Security

Deploy on isolated local subnets with zero internet dependency.

LabVIEW & MATLAB Integration

Pre-built connectors for industry standard test bench software.

Parquet & HDF5 Export

Instant export into open columnar data formats for post-test analysis.

Real-time FFT Graphs

Sub-10ms web UI graph updates for vibration and acoustic signatures.

MEASURABLE IMPACT

Proven Results in Mission-Critical Facilities

10x
Faster Hot-Fire Analysis

Engineers diagnose combustion instability in seconds rather than hours.

0 Packets
Lost During Ignition

Zero data drop recorded during high vibration propulsion runs.

100%
Test Audit Compliance

Fully reproducible telemetry sessions with immutable timestamps.

PILOT PROGRAM

Ready to transform your rocket engine hot-fire test stand?

YOUR HARDWARE & DATASETUP IN DAYSNO LOCK IN
arush@xpectraflow.com

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