Composite Materials Engineering for the UAE’s First Hybrid Sounding Rocket

The composite material strategy, manufacturing innovation, and cross-center collaboration behind a national aerospace milestone

Abstract

On 13 February 2026, the Technology Innovation Institute (TII) launched the UAE’s first hybrid sounding rocket from a domestic launch site, reaching an apogee of 3.3km before recovering safely via parachute. The mission was a milestone for the nation’s sovereign aerospace ambitions — and behind it was a body of composite materials work that made the mission structurally possible. 

This whitepaper, authored by TII’s Advanced Materials Research Center (AMRC), presents the composite engineering program that underpinned the launch: the selection criteria and trade-offs across the rocket’s structural components, the function role of different fiber and reinforcement selection and architectures, the thermal protection strategy, and the advanced automated manufacturing processes employed (for the first time in the UAE and the wider region) to produce flight-ready composite structures at the required tolerances. 

The work represents more than a single rocket mission. It establishes a domestic composite manufacturing capability for aerospace applications, demonstrates multi-disciplinary integration between materials science and propulsion engineering, and sets a replicable technical baseline for future, higher-altitude vehicles.

Mission at a glance

Launch date: 13 February 2026 | Apogee: 3.3km | Recovery: parachute (full vehicle)
Propulsion: Nitrous oxide / high-density polyethylene (N20-HDPE) hybrid motor
Composite components: Motor casing / upper and lower fuselage / nose cone / fins / interface sleeve
Weight reduction vs. metallic equivalent: up to 40% at scale
Manufacturing: Fully automated composite processing — a regional first

1.  The Materials Challenge in Hybrid Rocket Design

Composite materials — fiber-reinforced polymers (FRPs) and related hybrid systems — have become the structural backbone of modern launch vehicles. Where metallic alloys once dominated rocket airframes, advanced composites now enable the combination of low mass, high specific strength, and tailored functional properties that performance-critical aerospace structures demand. The global space carbon fiber composites market reflects this shift: valued at approximately USD 451 million in 2024, it is growing rapidly as more launch programs worldwide shift from aluminium and titanium to carbon-fiber-reinforced polymers (CFRPs). 
For the UAE’s hybrid rocket program, the materials challenge was particularly significant. 

A sounding rocket operating within the lower atmosphere faces a demanding and simultaneous set of structural and functional requirements. The material system must:

Metallic solutions, whether aluminium alloy airframes or steel motor casings, can address the structural requirements but fail on mass. Research shows that carbon-fiber composites achieve 30 to 50 percent weight reduction compared to conventional aluminium and titanium alloys, while maintaining or exceeding their mechanical and thermal performance. For a small sounding rocket with a fixed propellant load, every kilogram saved from the structure directly translates to increased altitude capability. 

At the same time, a single material cannot satisfy all of the requirements simultaneously. Carbon-fiber composites exhibit high electromagnetic shielding capability — an effect that varies with frequency — making them incompatible with nosecone applications where RF transparency is essential. Selecting the right fiber-matrix system for each component location and then integrating these different systems into a coherent vehicle was the core challenge to address.

2. Component-Level Material Strategy

The approach to material selection was function-led: each component’s primary loading environment and functional requirements drove the choice of fiber reinforcement, matrix resin, and fiber architecture. The rocket’s composite structure was developed across five principal component families.

Motor casing

The motor casing is the structurally and thermally most demanding component in a hybrid rocket. During combustion, the N2O oxidizer is pressurized and the HDPE fuel grain burns within the casing wall. The casing must contain this combustion pressure without yielding, while simultaneously conducting as little heat outward as possible. The temperature of the combustion chamber gases in hybrid and solid rocket motors typically ranges between 2,000 and 3,000 C. 

A high-performance carbon-fiber-reinforced polymer architecture was selected for the casing outer structure, providing the hoop and axial strength to contain chamber pressure at minimal wall thickness and mass. An internal thermal insulation system was integrated to protect the composite wall from the combustion environment. This dual-layer strategy, combining structural composite on the exterior with compliant insulation on the interior, is consistent with established practice in hybrid and solid rocket motor design, where elastomeric ablative systems protect the substrate while the composite structure carries load. 

Fuselage and structural body

The rocket’s fuselage — both the upper stage (housing the recovery bay and avionics) and the lower stage (surrounding the propulsion module) — required a structural shell capable of resisting combined bending, axial compression and torsion under aerodynamic and thrust loads, while adding minimal mass. 

CFRP was the primary material for both fuselage sections. The tailored fiber orientations within each laminate were selected to optimize the structure against its dominant load case: primarily axial and hoop for the lower stage and bending for the upper stage where parachute ejection loads are also present. Components produced for the lower stage included the fuselage body, propellant feed structures, and interface sleeves that join the two stages with the precision required for flight. 

The fuselage also housed the parachute recovery system. The parachute bay section required sufficient structural stiffness to withstand ejection impulse loads while remaining intact for aerodynamic deceleration post-apogee. Recovered post-flight parts confirmed the structural integrity of these components through the full mission envelope. 

Nose cone

The nose cone presented a fundamentally different design driver from the structural airframe components. Its primary function is not purely mechanical: it must also serve as a radome, a structural enclosure that is simultaneously weatherproof, aerodynamically shaped, and electromagnetically transparent to the GPS and radar signals used for navigation and range safety. 

Carbon fiber is electrically conductive and essentially opaque to RF signals, making it entirely unsuitable for a radome application. A glass-fiber-reinforced composite system was chosen for the nose cone, exploiting glass fiber’s intrinsic dielectric properties. Glass-fiber and E-glass reinforcement systems are widely used in aerospace radome applications because their dielectric constant can be engineered to minimize signal attenuation across the relevant frequency bands, allowing radar and GPS signals to pass through with minimal loss or distortion. 

The nose cone design required careful balance between structural performance and electromagnetic properties. Increasing wall thickness improves structural margins but can introduce unacceptable signal insertion loss. It also represented a challenge from a geometrical point of view due to the double-curvature nature of the design. The material selection, laminate design and the selected manufacturing process addressed this trade-off to meet both the mechanical load cases of flight and the signal transparency requirements of the navigation system. 

Fins

The rocket fins provide aerodynamic stability throughout the flight trajectory and must withstand significant aerodynamic loading, particularly during the high-dynamic-pressure phase of the ascent. Fin panels are typically thin, and the stiffness-to-mass ratio of the material system is the dominant design driver: A low-stiffness fin will flutter or diverge aerodynamically before the structural strength limit is reached. 

High-performance CFRP was selected for the fins, with fiber orientations chosen to maximize in-plane stiffness and resist flutter. The density of carbon fiber at approximately 1.75g/cm3 allowed the fins to be designed with adequate stiffness at panel thicknesses that did not add excessive mass outboard of the rocket’s center of gravity, preserving the stability margin. 

Thermal protection strategy

The thermal environment of a hybrid rocket is complex. The combustion chamber sustains extreme internal temperatures during the burn, but external aerodynamic heating (while less severe at the altitudes and velocities of this sounding mission) also acts on the vehicle surface. The composite structure must be protected from both. 

The design approach to integrate the thermal protection solution applied sufficient insulation material inside the motor casing to protect the composite structure from combustion-generated heat, while the composite casing itself provided the required structural performance. This was a joint design problem: the insulation thickness and properties influenced the structural wall design, and the composite material properties in turn influenced the thermal model. The level of integration required between materials science and propulsion engineering was a direct function of this thermal coupling.  

This kind of coordinated thermal-structural design, where the insulation and the structure form a system rather than independent elements, reflects established best practice in rocket motor design. At the temperatures involved in hybrid combustion, even brief exposure of the composite wall to untreated combustion gases would lead to rapid fiber-matrix interface degradation and structural failure.

3. Advanced Manufacturing: A Regional First 

Material selection is only half the challenge. For composite components to perform as designed and maintain the required tolerances, the manufacturing process must faithfully reproduce the target fiber orientation, volume fraction and void content — to dimensional tolerances tight enough that the assembled vehicle integrates correctly. For a sounding rocket, the integration requirement is particularly stringent: any mismatch between composite sub-assemblies at the stage interfaces can introduce structural eccentricities that affect trajectory. 

For this program, fully automated composite manufacturing technologies were deployed in a first for this application in the UAE and across the wider region. Automated processes offer two critical advantages over manual lamination: precision in fiber placement and repeatability between parts while ensuring a higher manufacturing throughput. 

Automated composite processing

Automated Fiber Placement (AFP) deposit composite tapes/towpregs using precise software control, achieving fiber placement accuracy that is not attainable through manual layup. Unlike manual processes, software-controlled deposition does not allow unintended gaps or overlaps between tapes, both of which introduce stress concentrations and reduce the structural efficiency of the laminate. Modern AFP systems can also incorporate real-time inspection, detecting defects in the laid material in-situ. With an 8-axis AFP robotic cell, capable of processing high-temperature thermoplastic tapes, TII stands at the forefront of advanced manufacturing technologies, not just in the region but worldwide.

Filament winding, in which continuous fiber tows or towpregs are wound onto a rotating mandrel under tension, was used for the cylindrical fuselage and casing geometries. Winding angle control governs the fiber orientation in the finished part: circumferential winding produces high hoop strength for pressure containment, while helical winding provides balanced axial and hoop properties appropriate for structural tubes. The precision of the winding angle, tension and resin content directly determines the structural performance of the finished part. 

For this program, these automated manufacturing approaches were employed to produce multiple flight-qualified composite components to the tolerances required for vehicle integration. This represented the first application of these manufacturing techniques to aerospace composite structures within the UAE. 

Dimensional accuracy and integration

One of the most technically demanding aspects of the program was achieving the level of dimensional accuracy needed to integrate the independently manufactured composite sub-assemblies into a single coherent flight vehicle. Each component — motor casing, fuselage sections, nose cone, fins, interface sleeve — was produced separately and then integrated mechanically.

Composite parts can be sensitive to process variability: temperature during cure, applied pressure, mandrel release and post-processing all affect final dimensions. The manufacturing protocol was developed iteratively through collaboration with local industrial partners, refining the process on each successive production batch until consistent dimensional accuracy at the required tolerance level was achieved.

4. Cross-Center Collaboration: Materials Meets Propulsion

The composite engineering program did not operate in isolation. The structural and thermal performance requirements for each component were determined by the propulsion system design and these requirements were communicated directly between the PSRC and AMRC teams throughout the development cycle. 

This proximity had practical consequences. When the propulsion team refined the motor design, the materials team could respond rapidly to the changed requirements, whether that meant updating the motor casing lamination schedule, adjusting insulation thickness, or re-evaluating the fin planform. Conversely, when the AMRC identified a manufacturing constraint, like a geometry that was difficult to de-mold cleanly at the required tolerance, for example, the propulsion design could be adapted early in the program before that constraint became a late-stage integration problem. 

Collaboration meant that materials decisions were never made in isolation from their system context. Each choice — fiber type, matrix, lamination schedule, insulation system — was understood in terms of its effect on the vehicle as a whole.

5. Outcomes and Performance Validation

The composite structure performed successfully across all flight phases. Key outcomes validated by the mission: 

Post-flight recovery of both rocket sections was a program requirement specifically because it allowed the materials team to inspect actual component condition after flight loading. The recovered hardware confirmed that the composite structure had experienced no delamination, no thermal damage at the casing, and no visible degradation to the different components. This physical evidence, alongside the flight telemetry data, constitutes the primary validation of the composite engineering approach. 

6. Building a Sovereign Advanced Materials Capability

Beyond the immediate technical achievement, the composite program established something of durable strategic value: a domestic capability for the design, manufacture, testing, and qualification of aerospace-grade composite structures in the UAE. 

That capability was built through an iterative process of technical collaboration with local industrial partners. Components were not purchased off the shelf; they were developed through repeated production cycles in which manufacturing processes were progressively refined until the required precision and quality levels were consistently achievable. 

The result is that the UAE now possesses, for the first time, a tested and validated pipeline for composite aerospace structures: from material selection and laminate design through automated manufacturing, dimensional inspection, and flight qualification. Future vehicles will be built on the same design, manufacturing, and qualification foundations established for this program. 

Future directions

The composite architecture developed for this program was designed with scalability in mind. As TII’s hybrid rocket roadmap progresses toward higher-altitude missions (with the next vehicle targeting approximately 20km, with a thrust-class motor approximately four times more powerful), the structural and thermal demands on the composite airframe will increase substantially. 

The AMRC forward program will address this through development in several areas:

As the propulsion roadmap scales toward sounding rocket apogees of 20km and beyond — and ultimately toward small satellite launch capability — the composite engineering program will scale in parallel.

7. Conclusion

The UAE’s first hybrid rocket launch was enabled by a carefully engineered composite material strategy that spanned the full vehicle. Carbon-fiber composites provided the structural and mass performance of the motor casing, fuselage and fins. Glass-fiber composites delivered the electromagnetic transparency required at the nose cone. A jointly designed thermal protection system protected the composite structure at the propulsion-materials interface. And fully automated manufacturing processes, deployed for the first time in the UAE for this class of application, produced the dimensional accuracy needed to integrate an all-composite rocket vehicle. 

The success of the launch is a validation of both the technical choices and the collaborative model that produced them. 

The composite materials capability established for this program is a lasting contribution to the UAE’s aerospace industrial base and is the foundation on which the next vehicles will be built.