HELIX ROTORCRAFT // TECHNICAL DOCUMENTATION

TECHNICAL
LIBRARY

Engineering documentation for the Apex Series rotorcraft family. All documents are current revision as of March 2026. Documents are available to qualified partners, investors, and government evaluators under NDA.

5
Documents
3
Aircraft
Mar 2026
Current as of
HR-TPD-001Rev DCURRENT15 Mar 2026
APEX PELICAN

Apex Pelican — Technical Performance Document

Full aerodynamic, propulsion, and systems performance specification for the Apex Pelican heavy-lift tilt-rotor. Covers momentum theory derivation, rotor blade analysis, powertrain architecture, weight statement, and mission performance at MTOW 21,500 lb.

TABLE OF CONTENTS
1. System Overview
2. Weight Statement
3. Rotor Aerodynamics (Momentum Theory)
4. Hover Performance
5. Cruise Performance
6. Propulsion Architecture
7. Emergency Systems
8. Mission Profiles
KEY FIGURES
MTOW21,500 lb
Max Payload8,786 lb
Sling Load9,000 lb
Cruise230 KTAS
Range666 NM
Engines3× Nelson LS427 TT
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HR-TPD-002Rev DCURRENT15 Mar 2026
APEX PEREGRINE

Apex Peregrine — Technical Performance Document

Full performance specification for the Apex Peregrine hybrid-electric tilt-rotor. Covers 15-ft swept-tip rotor analysis, single Nelson LS427 TT genset architecture, emergency power system (EPS), ballistic recovery parachute (BRP), and corrected CT/σ derivation.

TABLE OF CONTENTS
1. System Overview
2. Weight Statement
3. Rotor Aerodynamics — Swept-Tip Analysis
4. Hover Performance
5. Cruise Performance
6. Propulsion Architecture
7. Emergency Power System (EPS)
8. Ballistic Recovery Parachute (BRP)
KEY FIGURES
MTOW5,891 lb
Payload2,000 lb
Cruise200 KTAS
Range611 NM
Rotor15-ft swept-tip
Engine1× Nelson LS427 TT
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HR-TPD-003Rev BCURRENT15 Mar 2026
PEREGRINE-E

Apex Peregrine-E — Technical Performance Document

Performance specification for the Apex Peregrine-E pure-electric tilt-rotor. Covers Amprius SiNx 233 kWh battery pack sizing, YASA 400 motor selection, acoustic signature analysis, 250 KTAS cruise performance, and military/MEDEVAC dual-use configuration.

TABLE OF CONTENTS
1. System Overview
2. Weight Statement
3. Battery Pack Sizing
4. Motor Selection — YASA 400
5. Hover Performance
6. Cruise Performance
7. Acoustic Signature Analysis
8. Military Configuration
9. MEDEVAC Configuration
KEY FIGURES
MTOW5,285 lb
Payload1,400 lb
Cruise250 KTAS
Range100 NM one-way / 200 NM round-trip
Battery233 kWh
Acoustic~62 dB @ 300 m
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HR-ESS-001Rev ACURRENT15 Mar 2026
APEX PEREGRINE

Peregrine Emergency Systems Specification

Specification for the Peregrine's dual-layer emergency systems: the LiFePO4 Emergency Power System (EPS) providing 90-second assisted descent, and the Magnum BRS M-8000 ballistic recovery parachute. Covers activation logic, energy budget, deployment envelope, and placard limits.

TABLE OF CONTENTS
1. System Overview
2. Emergency Power System (EPS)
3. EPS Energy Budget
4. Ballistic Recovery Parachute (BRP)
5. BRP Deployment Envelope
6. Activation Logic
7. GCS Interface Placards
8. Certification Basis
KEY FIGURES
EPS Capacity3.79 kWh
EPS Duration90 sec
EPS Power126 kW
BRP Canopy82 ft
BRP Landing≤35 ft/s
BRP Min Alt400 ft AGL
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HR-PKG-001Rev ACURRENT15 Mar 2026
PEREGRINE-E

Peregrine-E Rapid-Deployment Container System

Design specification for the HR-PKG-001 Rapid-Deployment Container System (RDCS) enabling the Apex Pelican to sling-load a fully mission-ready Peregrine-E to a forward staging point. Covers folded dimensions, weight statement, rotor fold procedure, pyrotechnic release, sling attach points, and certification basis.

TABLE OF CONTENTS
1. Purpose and Scope
2. System Overview
3. Dimensional Envelope
4. Weight Statement
5. Rotor Folding Procedure
6. Container Release and Deployment
7. Sling Load Attach Points
8. Environmental Limits
9. Ground Handling
10. Certification Basis
KEY FIGURES
Packaged Weight4,000 lb
Pack Time5 min (2-person ground crew)
Deploy Time3 min (autonomous)
Sling Rating18,000 lb
Max Transit130 KTAS
ISO Footprint20-ft container
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Qualified investors and government partners can request the complete technical package including BOMs, weight statements, and propulsion analysis under NDA.

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