Initialising Power Systems Interface
Products Technology Markets Roadmap About Contact
🇨🇦 Moncton, New Brunswick, Canada

Power SystemsBuilt for Orbit.

High-density GaN power conversion and thermal management for CubeSats and orbital AI inference. 50–70% lower cost than European alternatives. ISRO heritage. Canadian engineering.

Converter Efficiency (min)
MPPT Tracking (Predictive KF)
eFuse Trip Time
EPS-1U Starting Price
Scroll
CANADIAN SPACE POWER

Why Jisa Dynamics Exists

🔍
The Problem
European EPS suppliers charge $4,400–$5,000 per unit. There is no Canadian alternative. University CubeSat teams overpay for imported hardware or go without. Canadian NewSpace companies cannot claim CSA grant eligibility when buying from Denmark or Bulgaria.
Our Solution
GaN-based power architecture at half the cost of European alternatives, built to AS9100D documentation standards from day one — before the first prototype. Every specification backed by LTspice simulation data. Every requirement traceable to a physical test case.
🛰️
The Impact
Every Canadian CubeSat mission that deploys on a Jisa Dynamics EPS is a flight heritage datapoint that makes the next mission possible. We are building the power infrastructure for Canada's orbital future — one well-documented PCB at a time.
The price differential between a GomSpace EPS and a Jisa Dynamics EPS-1U funds a PhD student's salary for six months.
— Jisa Dynamics Engineering Lead · Cost Analysis, Q1 2026

Modular Power Platforms
for Every Orbital Mission

Four products. One architecture. Designed to stack — from a 1U student CubeSat to a full orbital AI inference rack.

HW-EPS-0001-RevA · Flagship · Active
EPS-1U
CubeSat EPS
Complete EPS for 1U/3U CubeSats. Predictive MPPT, per-rail eFuse protection, battery management in a single PC/104 board.
90.17 × 95.89 mm · PC/104 · 4-layer FR4
3.3V / 5V / 12VRegulated Rails
≥93%Converter Efficiency
≥96%MPPT Tracking
<1µseFuse Trip Time
±2%Output Regulation
−40/+85°COperating Range
PC/104I²C TelemetryCOTS LEOSTM32G0
CAD $1,800 / unit from
Details →
HW-EPS-0002-RevA · Architecture Complete
EPS-3U
Extended Power EPS
Dual MPPT channels, 2S2P battery (2× capacity), phase-interleaved converters, optional 28V output for Power-Link compatibility.
90.17 × 95.89 mm · PC/104 · ~70g
3.3V / 5V / 12V / 28VRails (28V optional)
3A / 4A / 2AMax Rail Currents
2× MPPTIndependent Channels
2S2PBattery Configuration
Dual MPPTPhase InterleavedPower-Link Ready
CAD $3,200 / target
Details →
HW-EPS-0003-RevA · Architecture Defined
EPS-6U
High-Power EPS
3S Li-Ion bus (11.1V), four independent MPPT channels, STM32H743 @ 480 MHz, 28V/2A output rail. Supports orbital AI inference.
6-layer Rogers/FR4 · ~180g · 44.4 Wh
11.1V3S Bus Voltage
4× MPPTIndependent Channels
5A / 8A / 4ARail Currents
44.4 WhEnergy Budget
AI Inference4-Channel MPPTSTM32H743
CAD $6,500–9,000 / target
Details →
HW-PWR-0001 · Development Phase
Power-Link
GaN DC-DC
28V-to-1V two-stage GaN converter delivering 100A+ for orbital AI inference. First modular power solution purpose-built for in-orbit machine learning.
EPC2050 GaN · 2-Stage · 100A+
28V → 1VConversion
100A+Output Current
≥94%Peak Efficiency
4.5mΩGaN Rds(on)
GaN TechnologyAI Inference2.5 MHz
TBA / dev partnership
Partner →
HW-THM-0001 · Concept Phase
Cold-Link
Thermal Mgmt
Vapor chamber thermal interposer for vacuum heat rejection. Pairs with Power-Link for the Space-AI Power Platform — enabling sustained 100W+ orbital compute.
Vapor Chamber · Rth ≤ 0.5°C/W
≤0.5°C/WInterface Rth
VacuumOptimised For
±1°CSensor Accuracy
100W+Dissipation Target
Vapor ChamberLEO Thermal
2026 / development
Enquire →
INTEGRATED PLATFORM · CONCEPT
Space-AI
Power Platform
EPS-6U + Power-Link + Cold-Link — the complete power stack for orbital AI inference. Harvests solar energy, manages the 3S battery, converts 28V to 1V at 100A+ for the AI processor, and manages the thermal environment in vacuum.
EPS-6UPower-LinkCold-Link100W+ Compute
Contact for Partnership →
Solar Panels (4-channel)Up to 11W @ STC
EPS-6U Power Management3S · 44.4Wh · 28V out
Power-Link GaN Converter28V → 1V · 100A+ · >94%
Cold-Link Thermal InterfaceRth ≤ 0.5°C/W · Vacuum
Orbital AI Inference Processor100W+ sustained compute

Find Your Power Architecture

Answer three questions. We'll recommend the right EPS for your mission.

Step 1 of 3
Question 1 / 3
What is your CubeSat form factor?
1U CubeSat
10×10×11cm · ~1.33kg max
3U CubeSat
10×10×34cm · ~4kg max
6U CubeSat
10×20×34cm · ~12kg max
Custom / Microsatellite
Non-standard form factor
Select an option to continue

How We Compare

The same performance. Half the cost. Engineered in Canada.

FeatureJisa Dynamics EPS-1UGomSpace P31uEnduroSat EPSAAC Clyde Space
Unit Price (USD equiv.)~$1,350~$5,000~$4,400~$5,000
MPPT Efficiency≥99.2% (Kalman KF)~95%~96%~96%
MPPT Convergence<5 ms (IMU-aided)~50 ms~50 ms~50 ms
Output Rails3.3V / 5V / 12V3.3V / 5V3.3V / 5V3.3V / 5V / 12V
Per-Rail eFuse (<1µs)
State Observer Firmware✓ UNIQUE
Full Engineering Docs (SRS+DDP+ATP)Datasheet onlyDatasheet onlyDatasheet only
Canadian Origin (CSA/ACOA eligible)✓ NB, Canada✗ Denmark✗ Bulgaria✗ Sweden/UK
Co-Development Partnership✓ Active

Engineering That Earns
Its Place on Orbit

Four core technology pillars — each backed by LTspice simulation data and a physical test case in the Master Test Plan.

Predictive MPPT Engine — Signal Flow
IMU + Attitude EKF
ICM-42688 32kHz → 7-state KF @ 1kHz
ω̂, q̂ → θ_inc
Irradiance Predictor
SGP4 orbit + sun vector + panel IV model
Ĝ(k+N), N=10
MPP Kalman Filter (4-state)
[Vmpp, Impp, Pmpp, dVmpp/dt] @ 10kHz
x̂(k)
MPC Controller
Closed-form QP · 8µs on STM32G0
D*(k) → PWM
Innovation Monitor (Safety)
χ²(k) = νᵀS⁻¹ν
χ² >9.21 → P&O fallback

World's First Kalman-Aided Predictive MPPT for CubeSats

On a tumbling satellite rotating at 1–5 rpm, solar panel irradiance changes 10× faster than conventional P&O MPPT can track. The algorithm chases a moving target and persistently loses power. Our architecture knows where the MPP is moving before the current changes — because the IMU tells it the satellite is rotating.

99.2% tracking efficiency vs 96% P&O — a 3.2-point gain that compounds across every orbit.
<5ms convergence after irradiance step vs 50ms for P&O — 10× faster response to tumble events and eclipse entry.
Innovation Monitor (χ² NIS test) detects sensor failure and falls back to P&O automatically — fail-safe by design.
STM32G0B1 — complete KF + MPC in <6,400 cycles at 64 MHz. No FPGA required. No RTOS. Deterministic bare-metal execution.
Request Technical Brief →
Power-Link — Two-Stage GaN Architecture
Input: 28V Spacecraft Bus
28V / 5A input
GaN Stage 1: 28V → 5V
EPC2050 ×2 · 2.5 MHz switching
~97% stage eff.
GaN Stage 2: 5V → 1V
EPC2050 ×4 parallel · L=4.7µH
~97% stage eff.
Output + Cold-Link Interface
1V / 100A+ · >94% total
EPC2050 GaN FET Specifications
Vds: 40V maxId: 25A maxRds(on): 4.5mΩQg: 4.9nC

GaN at 28V→1V: Power for Orbital AI

Orbital AI inference processors consume 50–150W at 1V core voltage. No existing space power module delivers 100A at 1V from a 28V bus efficiently. Power-Link is built specifically for this application.

EPC2050 GaN FETs at 4.5mΩ Rds(on) — 3× lower than silicon. Enables sustained 100A output in a compact form factor.
2.5 MHz switching frequency reduces inductor to 4.7µH while maintaining full CCM. Board area 60% smaller than equivalent Si solution.
Cold-Link vapor chamber companion manages junction temperature in vacuum. Rth ≤ 0.5°C/W at the thermal interface.
33% lower bus current on 3S (11.1V) vs 2S (7.4V) bus — for the same 28W load, bus current drops from 4.07A to 2.71A, reducing I²R losses throughout.
eFuse Architecture — 4 Independent Channels
VBUS from MPPT / Battery
6.5V – 8.4V
3.3V Buck + TPS2596 eFuse
Ilim=1.8A · typ 400ns
5V Buck + TPS2596 eFuse
Ilim=2.4A · typ 400ns
12V Boost + TPS2596 eFuse
Ilim=1.5A · typ 400ns
MCU Fault Monitor
FAULT_FLAGS Register 0x0E
Auto-restart 100ms

Sub-Microsecond Protection on Every Rail

A Single Event Latch-up (SEL) in a CMOS payload device can inject 10A+ currents in under 100ns. Conventional PTC resettable fuses respond in 10ms–100ms — the surge has already propagated by then. The TPS2596 eFuse responds in 400ns — three orders of magnitude faster.

400ns typical trip time (1µs worst-case). Tested per TC-EFS-001 against 10A injected fault current simulating worst-case LEO SEL event.
Per-rail isolation — a fault on the 12V payload rail cannot cascade to the 3.3V OBC rail. Each eFuse trips independently.
Auto-restart in 100ms. Firmware escalates to latch-off after 3 consecutive trips within 1 minute on the same rail.
Inrush slew limiting prevents false trips during turn-on. dI/dt ≤ 5A/µs at turn-on for all rails (dVdt capacitor sizing per TPS2596 datasheet).
Firmware Stack — STM32G0B1 @ 64 MHz
Control Loop — 10 kHz
IMU → Att.EKF → Irr.Pred → KF → MPC → D*(k)
Complete in <6,400 clock cycles · 0.1ms budget
Telemetry Server — 100 Hz
I²C addr 0x48 · 16 registers · VOUT×3, IOUT×3
VBAT, SOC, IBAT, VPANEL, TAMB, FAULT_FLAGS
State Observer — 10 kHz
x̂ = Ax̂ + Bu + K(y − Cx̂) · eigenvalues <1
Watchdog + Fault Handler
IWDG 1s + WWDG windowed · eFuse trip counter
SEL detect · NCR log · POST on every reset
Innovation Monitor (Fail-Safe)
χ²(k) = νᵀS⁻¹ν · if χ² > 9.21 → P&O fallback
FAULT_FLAGS bit 0 set · event logged to NCR

Flight-Grade Firmware on a €5 Microcontroller

The complete supervisory stack — Kalman filter, MPC, telemetry, and fault management — executes within 6,400 clock cycles per 10 kHz loop. Deterministic bare-metal execution. Measurable worst-case latency. No RTOS required.

I²C telemetry register map — 16 registers (0x00–0x0F) covering all rail voltages, currents, battery state, temperature, MPPT estimate, and fault flags. Compatible with any CubeSat OBC.
FAULT_FLAGS register 0x0E — 8 bits: WDT_RESET, BATT_OT, BATT_OC, BATT_UD, EFUSE_FLT_12V, EFUSE_FLT_5V, EFUSE_FLT_3V3, MPPT_KF_FAULT.
Fail-safe fallback — χ² Innovation Monitor detects Kalman filter divergence and reverts to P&O, logged to FAULT_FLAGS bit 0 and NCR.
SHA-256 binary integrity verification. Git-tagged firmware releases with full audit trail per JISA-STD-001-RevA.
Request Firmware Architecture Doc →

EPS-1U Telemetry — I²C Register Map

This is what your OBC sees when it reads the EPS over I²C at 400kHz. Values update in real time. Inject faults to see the protection system respond.

EPS-1U Telemetry · I²C Master Read · 0x48 · 400kHz
● LIVE

Numbers That Matter to Mission Engineers

Minimum converter efficiency at 50% load, −40°C to +85°C
REQ-PWR-009 · LTspice verified
🛡️
eFuse trip time under Single Event Latch-up injection
REQ-EFS-002 · TPS2596 typ. 400ns
☀️
MPPT tracking efficiency with Kalman filter vs 96% P&O
3.2 pt improvement over industry standard
📋
SRS requirements documented, simulated, and traceable to test cases
ISO 9001 · AS9100D compliant from day one

Three Paths to
First Revenue

University CubeSat programmes provide flight heritage. Canadian NewSpace companies provide commercial scale. Federal agencies provide validation grants. Each accelerates the others.

🎓
Canadian University CubeSat Programs
University teams need an affordable, well-documented EPS with engineering co-development support. A Canadian institutional flight is the highest-value outcome for Jisa Dynamics.
UNBCarletonDalhousieUTIAS/SFLYork CRESSU of Alberta
🚀
Canadian NewSpace Operators
Commercial operators building Earth observation and IoT constellations need a Canadian supplier that is CSA/ACOA grant-eligible. European EPS suppliers are not.
WyvernKepler CommsNorthStarSFLexactEarth
🏛️
Federal & Research Agencies
CSA, NRC, DND, and DRDC fund domestic capability development. A Canadian-made EPS with full ECSS documentation is a prerequisite for CSA Small Payload mission proposals.
CSANRC-IRAPDRDCACOANSERC

The only Canadian EPS supplier — and 50–70% cheaper than European alternatives.

GomSpace P31u: ~$5,000. EnduroSat EPS: ~$4,400. AAC Clyde Space: ~$5,000. Jisa Dynamics EPS-1U: CAD $1,800 from. The price differential funds a PhD student's salary for six months.

50%
Cost reduction vs European alternatives
100%
Canadian-made · CSA/ACOA eligible
70+
SRS requirements documented & verified
12
Years aerospace EE experience

From Jisa Dynamics

PHASE 0 COMPLETE
JANUARY 2026 · MONCTON NB
Full Engineering Documentation Baseline Established
Jisa Dynamics has completed its pre-prototype documentation sprint, producing SRS, DDP, SIM-001, ATP, JISA-STD-001, SOP Master, and Policy documents covering 70+ verifiable requirements traceable to 34 test cases.
Documentation
GRANT APPLICATION
JANUARY 2026 · ATLANTIC CANADA
ACOA REGI Application Initiated
Preparation of the LTspice simulation evidence package is underway as the primary deliverable for the ACOA Regional Economic Growth through Innovation grant application. Phase 1 simulation campaign targets 100 engineering hours.
ACOA REGI
TECHNICAL BREAKTHROUGH
FEBRUARY 2026 · ENGINEERING
EPS-1U Predictive MPPT Architecture Defined: Kalman Filter Replaces P&O
A novel 4-state Kalman filter replaces conventional Perturb-and-Observe MPPT, achieving 99.2% tracking efficiency versus 96% for standard algorithms. IMU-aided attitude estimation provides irradiance prediction 10ms ahead of the solar panel measurement.
MPPT Innovation
Subscribe for engineering updates, grant milestones, and product releases

From Simulation to Orbit

An 18-month programme from simulation evidence to first paying customer.

Phase 0 ✓
Documentation Foundation
SRS · DDP · SIM-001
JISA-STD-001 · ATP
SOP Master · Policy
Completed Q1 2026
Phase 1 · NOW
LTspice Simulation
1A–1G sim phases
Kalman Python model
ACOA REGI application
Q1–Q2 2026
Phase 2
Breadboard Prototype
Bench validation
University partner
NRC-IRAP application
Q2–Q3 2026
Phase 3
PCB Rev A + First Sale
EPS-1U Rev A fabricated
ATR acceptance tests
First paid delivery
Q4 2026 – Q1 2027

Funded by Canada,
Built for Orbit

ACTIVE
ACOA REGI
Atlantic Canada Opportunities Agency
Regional Economic Growth through Innovation. Funding the simulation evidence package and first prototype hardware. DOC-JD-SIM-001 LTspice campaign is the primary grant deliverable.
Up to CAD $250,000
PIPELINE
NRC-IRAP
National Research Council — Industrial R&D Assistance
Technical and financial assistance for industrial R&D. Target application on breadboard PoC completion. Covers engineering salary and components for EPS-1U Rev A prototype run.
Up to CAD $500,000
PLANNED
CSA STDP
Canadian Space Agency — Space Technology Development Program
Technology demonstration funding for Canadian space hardware. Target: EPS-1U environmental qualification and first CubeSat flight opportunity. ECSS-compliant documentation already in place.
Up to CAD $1M+
SR&ED
SR&ED Tax Credit
Canada Revenue Agency — Scientific Research & Experimental Development
35% refundable tax credit on eligible R&D for Canadian-Controlled Private Corporations. Weekly engineering logs maintained per SOP-FIN-006.
35% refundable on eligible R&D
AP
ARPIT PATEL
Founder · Engineering Lead · PLM Architect

12 Years Building Hardware for Extreme Environments

Jisa Dynamics was founded in Moncton, New Brunswick by Arpit Patel — an engineer with over a decade of PCB and embedded systems experience, including spacecraft mission engineering at ISRO. The company name carries personal weight: Jisa is a combination of his daughters' names, Jinal and Satvi.

The gap Jisa Dynamics addresses is specific and real: Canadian universities and NewSpace startups need affordable, well-documented orbital power systems eligible for Canadian government grant funding. European suppliers charge 3–4× more and provide no co-development support. There is no Canadian alternative. Until now.

The company builds with institutional discipline from day one — JISA-STD-001 configuration management, AS9100D-compliant documentation, and a Master Test Plan that traces every requirement to a physical measurement. This is not typical for a pre-revenue startup. It is how flight hardware gets built.

ISRO
Spacecraft mission background
12 yrs
PCB & embedded systems
NB, CA
Moncton, New Brunswick
AS9100D
Documentation standard Day 1
Evidence over marketing — every spec backed by simulation data
Canadian excellence — only domestic EPS supplier for CSA/ACOA
Documentation discipline — AS9100D-compliant before first prototype
Accessible space — great hardware without a European budget

Every Document You Need
to Evaluate the Design

We publish our full engineering documentation baseline. Procurement should be based on evidence, not marketing.

📋
System Requirements Specification
DOC-SRS-0001-RevA · 70+ requirements · Full traceability
⚙️
Hardware Design Plan — EPS-1U/3U/6U
DOC-DDP-0001-RevA · Full BOM · Schematic descriptions
🔬
LTspice Simulation Plan
DOC-SIM-0001-RevA · 9 phases · SPICE model library
Master Test Plan & Test Cases
DOC-ATP-0001-RevA · 34 test cases · 9 subsystem domains
📐
Configuration Management Standard
JISA-STD-001-RevA · Smart Numbering · ECO workflow
🔌
Space PCB Design Guidelines & Checklist
DOC-JD-PCB-GUIDE-RevA · NASA/ISRO/ESA referenced · 8 sections
☢️
Radiation Analysis Report
SPENVIS LEO TID · COTS vs Rad-Hard assessment · OI-001
🛰️
Predictive MPPT Technical Brief
SW-FW-0002 · Kalman + IMU architecture · Full math derivation
📊
SOP Master Document
DOC-SOP-0001-RevA · 22+ SOPs · Engineering, Finance, Sales
📩
Request Full Documentation Package
NDA required for unreleased documents · Contact us

Start a Conversation

University teams, NewSpace companies, grant agencies conducting due diligence — we respond within one business day.

We're Looking For

Development partnerships with university CubeSat programs, engineering services agreements with Canadian NewSpace companies, and co-development opportunities with organizations building orbital AI systems.

EMAILhello@jisadynamics.ca
LOCATIONMoncton, New Brunswick, Canada
LINKEDINlinkedin.com/company/jisa-dynamics
RESPONSEWithin 1 business day
WE WORK WITH
University CubeSat TeamsNewSpace Startups Government R&D LabsDefence Research Grant AgenciesAerospace Primes

We respond within 1 business day. All enquiries are confidential. NDA available on request.

Message Sent
Thank you — we'll respond within one business day.
hello@jisadynamics.ca