Landing Gear Actuator Brackets

Name: Actuator Brackets & Landing Gear Retraction Mount Assemblies – Frigate
Price: 249.00 USD
Availability: InStock

Landing gear actuator brackets serve as critical structural links, transferring hydraulic actuator force to the airframe. Poor force path distribution can cause stress concentrations and localized yielding.

Material Specification

Titanium 6Al-4V (Grade 5), Aluminum 7075-T7351, or Steel AISI 4340 (AMS 6414)

Actuator Interface Design

Lug-and-clevis (MS21250), Flanged (NAS/AN bolt pattern), or Spline-coupled (SAE J498)

Aircraft Structure Mounting Points/Hole Pattern

4–12 bolt holes (NAS/AN/MS), PCD 50–200mm, Threaded inserts (Helicoil/Keensert)

Load Capacity

Ultimate Tensile – 900–1,400 MPa, Shear Load – 75–250 kN, Compression – 100–300 kN (FEA-validated)

Deflection Limits

≤0.15mm deflection @ limit load, Natural frequency >80 Hz

Product Description

To prevent this, the brackets are engineered using finite element-based load path optimization. This ensures smooth axial and torsional load transfer into the trunnion or support beam, reducing peak stress gradients and promoting uniform strain distribution throughout all flight phases.

Fatigue Life

10⁶ cycles @ 30% UTS (ASTM E466), S-N curve provided

Surface Treatment

Anodizing (Aluminum), Passivation (Titanium), Cadmium Plating (Steel, per AMS-QQ-P-416)

Dimensional Tolerances

±0.05mm (Hole positions), ±0.025mm (Bore diameters), Flatness ≤0.1mm/m

Non-Destructive Testing Requirements

Fluorescent Penetrant (FPI), Ultrasonic (UT), X-ray (RT for welds)

Certification Standards

AMS 4911 (Ti-6Al-4V), BMS 7-260 (Aluminum), FAA 14 CFR §25.571, AS9100

Technical Advantages

Kinematic mismatches between actuator rod ends and mounting bores introduce angular misalignment and degrade stroke linearity. Landing Gear Actuator Brackets assemblies are machined with bore coaxiality tolerances within ±0.01 mm and flatness within 0.02 mm over the mounting face. This level of precision ensures concentric alignment of actuator pins and consistent extension/retraction symmetry, critical for synchronized landing gear operation and actuator seal longevity.

Design criteria prioritize low-cycle fatigue endurance and resistance to micro-crack propagation under cyclic high-load conditions. Material selection favors 7075-T6 aluminum and Ti-6Al-4V alloys based on their endurance limits, fracture toughness (K_IC), and crack growth rate (da/dN) under spectrum loading. All brackets meet minimum fatigue lives exceeding 10⁵ cycles under spectrum loading conditions representative of commercial landing gear duty profiles.

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Industry Applications

Commercial Aircraft Gear Deployment

Used in commercial aircraft to transfer actuator force during landing gear extension and retraction under high axial and lateral load conditions.

Military Jet Alignment Systems

Applied in military jets where precision-machined brackets align hydraulic actuators to prevent asymmetric deployment of high-speed retractable landing assemblies.

UAV Compact Gear Interfaces

Integrated in unmanned aerial vehicles to provide structural support for lightweight retractable gear systems requiring compact actuator interface geometry.

Cargo Aircraft Load Stability

Utilized in cargo aircraft to ensure actuator motion fidelity under high-mass loading cycles during frequent ground contact and taxi operations.

Business Jet Vibration Isolation

Essential in business jets to isolate vibrational loads between actuator housing and fuselage hardpoints during rapid gear transitions.

Rotary-Wing Landing Support

Deployed in rotary-wing aircraft skid systems with actuated gear extensions for operations requiring varying ground clearance during deployment.

Surface Integrity and Debris Resistance

Failure initiation from foreign object damage or surface abrasion necessitates robust surface treatment. Landing Gear Actuator Brackets surfaces undergo shot peening to induce compressive residual stresses, delaying fatigue crack initiation. Hard anodizing or passivation coatings are applied to resist hydraulic fluid corrosion, fretting wear, and galvanic interaction with adjacent stainless actuator fittings. Surface roughness values are maintained below Ra 0.8 µm to reduce nucleation sites.

All actuator bracket geometries and material properties conform to MIL-STD-810G environmental performance and FAA FAR 25.735 load-bearing requirements. Static and dynamic load testing is conducted with strain gauges and digital image correlation (DIC) systems to capture displacement and stress wave propagation during simulated landing impacts. Design validation includes shear-out, bearing load, and bending moment testing to 1.5x operational limits with full instrumentation.

Having Doubts? Our FAQ

Check all our Frequently Asked Question

How does Frigate ensure bracket fatigue life under variable spectrum loading?

Frigate uses FEA simulations combined with spectrum fatigue testing based on real flight load profiles. Landing Gear Actuator Brackets are evaluated for crack initiation and propagation under random cyclic loads using NASGRO and ASTM E647 methods. Material behavior is verified under both low- and high-cycle fatigue regimes. This ensures minimum 10⁵ operational cycles without structural degradation.

What techniques does Frigate use to maintain bore alignment during high-volume production?

Frigate applies high-precision CNC machining with in-process coordinate measurement verification. Bore concentricity and perpendicularity are held within ±10 microns across multiple production runs. Custom jigs and tool paths ensure minimal thermal distortion during finishing. This guarantees uniform actuator pin alignment across large-lot manufacturing.

How does Frigate validate landing gear actuator brackets for real-world operating conditions?

Brackets undergo full-scale load testing using strain-gauge instrumentation and DIC (digital image correlation) systems. Simulated axial, shear, and bending loads replicate landing gear dynamics across extreme conditions. All validation follows FAR 25.735 and MIL-STD-810G criteria. Data from testing is correlated back to FEA results for model accuracy.

How does Frigate handle galvanic compatibility between actuator brackets and mating components?

Frigate performs galvanic series analysis to pair materials with minimal electrochemical potential difference. Protective coatings like hard anodizing or PTFE sealants are applied to prevent current flow at contact interfaces. Bracket hardware is also matched with corrosion-resistant alloys. This reduces the risk of accelerated pitting in mixed-metal assemblies.

What steps does Frigate take to ensure thermal stability of actuator bracket assemblies?

Frigate selects bracket materials with controlled coefficients of thermal expansion closely matching actuator housing alloys. Thermal cycling tests from -55°C to +85°C verify mechanical stability and dimensional retention. Interface gaps, seal zones, and bolt preloads are tested post-cycle. These measures prevent thermal distortion and misalignment during extreme operating environments.

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LOCATIONS

Registered Office

10-A, First Floor, V.V Complex, Prakash Nagar, Thiruverumbur, Trichy-620013, Tamil Nadu, India.

Operations Office

9/1, Poonthottam Nagar, Ramanandha Nagar, Saravanampatti, Coimbatore-641035, Tamil Nadu, India. ㅤ

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