Sampie Booysen
Co-founder and CTO
We deeply value their personalized service. From facilitating valuable connections within the global space industry, to providing valuable market insight reports, working with satsearch has significantly influenced our sales processes.
The platform allows us to present our communication systems to the right audiences at the right time. We are especially grateful for how the program has accelerated our business growth.
Astrid Kjeldal
Sales Manager & Team Lead
When working on the commercialization of space, it is essential to make the procurement process as easy and uncomplicated as possible, and this is where satsearch offers an excellent marketplace for the space industry and helps give a great overview for the customer of what the market has to offer.
As a satellite supplier and a satsearch partner, we have had many sales inquiries through satsearch, many of whom are our customers today.
Alberto Ordaz Acero
BD Manager
Satsearch is a must for satellite products and services suppliers to showcase their catalogue effectively, resulting in increased visibility and sales opportunities.
The great team behind satsearch also helps connecting with a global network of potential customers and bringing great monthly reports.
Thomas Yen
CEO
We have worked with satsearch since the early days of Tensor Tech and it has always been an important partner for us.
Unlike how sales traditionally works in the space industry, satsearch provides a transparent way for buyers to look for suitable suppliers and products.
I believe they have truly fostered the growth of the industry.
Tensor Tech, as a user, has also enjoyed the way we update our information, monitor the traffic for data analysis, and attract more international clients.
Ronnie Nader
Chief Designer and Director of Space Operations
Ever since we signed up for satsearch back in 2019 it was an immediate hit and it has been a game changer for us.
The people involved really want their users to succeed, they do understand the industry and the market and not only that, but for providers, the relationship has been a constant feedback about what works and what does not, who is who in the landscape and all that knowledge serves to improve the platform and the quality of the leads.
We also have other leads providers, so we can compare, and none gets to the level of satsearch. In short, satsearch works, period.
Struan Johnston
Director
It has become a well known supply chain platform for the industry and a great place to find and compare different suppliers in a fraction of the time.
As a manufacturer of satellite components, we have grown our reach and audience using satsearch as a marketing channel, and met many of our customers via satsearch for the first time.
Sampie Booysen
Co-founder and CTO
We deeply value their personalized service. From facilitating valuable connections within the global space industry, to providing valuable market insight reports, working with satsearch has significantly influenced our sales processes.
The platform allows us to present our communication systems to the right audiences at the right time. We are especially grateful for how the program has accelerated our business growth.
Astrid Kjeldal
Sales Manager & Team Lead
When working on the commercialization of space, it is essential to make the procurement process as easy and uncomplicated as possible, and this is where satsearch offers an excellent marketplace for the space industry and helps give a great overview for the customer of what the market has to offer.
As a satellite supplier and a satsearch partner, we have had many sales inquiries through satsearch, many of whom are our customers today.
Alberto Ordaz Acero
BD Manager
Satsearch is a must for satellite products and services suppliers to showcase their catalogue effectively, resulting in increased visibility and sales opportunities.
The great team behind satsearch also helps connecting with a global network of potential customers and bringing great monthly reports.
Thomas Yen
CEO
We have worked with satsearch since the early days of Tensor Tech and it has always been an important partner for us.
Unlike how sales traditionally works in the space industry, satsearch provides a transparent way for buyers to look for suitable suppliers and products.
I believe they have truly fostered the growth of the industry.
Tensor Tech, as a user, has also enjoyed the way we update our information, monitor the traffic for data analysis, and attract more international clients.
Ronnie Nader
Chief Designer and Director of Space Operations
Ever since we signed up for satsearch back in 2019 it was an immediate hit and it has been a game changer for us.
The people involved really want their users to succeed, they do understand the industry and the market and not only that, but for providers, the relationship has been a constant feedback about what works and what does not, who is who in the landscape and all that knowledge serves to improve the platform and the quality of the leads.
We also have other leads providers, so we can compare, and none gets to the level of satsearch. In short, satsearch works, period.
Struan Johnston
Director
It has become a well known supply chain platform for the industry and a great place to find and compare different suppliers in a fraction of the time.
As a manufacturer of satellite components, we have grown our reach and audience using satsearch as a marketing channel, and met many of our customers via satsearch for the first time.
Browse the latest capabilities that qualified buyers
are looking for on satsearch right now
Minimum Technical Requirements:
Feed assembly suitable for operation on a 3.8 metre Cassegrain/parabolic SATCOM antenna.
Receive Frequency Range: 3.4 GHz to 4.2 GHz.
Transmit Frequency Range: 5.850 GHz to 6.425 GHz.
Polarisation: Circular, supporting both:
- Left Hand Circular Polarisation (LHCP)
- Right Hand Circular Polarisation (RHCP)
- Orthogonal/reversible operation.
Transmit Axial Ratio: ≤ 0.75 dB.
Cross-Polarisation Performance: Compliant with Intelsat IESS-207 requirements.
Regulatory Compliance: FCC and Intelsat compliant.
Minimum Antenna G/T: 22.5 dB/K at 25° elevation angle with receive out-of-band filtering.
Equivalent Isotropically Radiated Power (EIRP): Support antenna system performance of 63 dBW (single carrier, mid-band).
Feed assembly shall be supplied complete with all required:
Waveguide interfaces
Orthomode transducer (OMT) or equivalent
Mounting hardware
Polarisation switching components
Environmental sealing suitable for outdoor deployment
Vendor Response Requirements
Tenderers shall provide:
1. Detailed feedhorn datasheet.
2. Mechanical drawings including dimensions and mounting interfaces.
3. Waveguide flange standards and interface details.
4. Gain and illumination pattern plots.
5. Cross-polarisation performance data.
6. Environmental specifications.
7. Mean Time Between Failure (MTBF), if available.
8. Country of manufacture and delivery lead time.
9. Confirmation of compatibility with existing 3.8 m tactical SATCOM antenna systems.
We're looking for a complete 3p PocketQube platform — structure, OBC, EPS, and UHF comms — compatible with the Alba Orbital AlbaPod deployer.
The satellite is a fixed payload with no moving parts and no camera — it carries visual markers on its exterior panels for testing proximity/detection sensors, plus a small onboard circuit that measures solar cell performance and sends data down over radio.
We need to deliver the finished satellite to our launch provider within 3 to 5 months, so lead time is critical for us.
To save time on both sides, please include everything in your first response — quotation, lead time, flight heritage, ICD, CAD model, and datasheet — rather than a partial reply, so we can evaluate your offer in one pass without needing follow-up requests. Also let us know if staged or deposit payment is available, as we're an early-stage company working with a limited budget right now.
| Req ID | Category | Parameter Name | Guidance & Reference Range | Buyer Target Specification (Input Required) | Unit | Criticality | Verification Method |
| 1. MISSION PROFILE & ENVIRONMENTAL LEVELS | |||||||
| M-01 | Mission Profile | Target Orbit / Trajectory | LEO, MEO, GEO, Deep Space | LEO | - | Critical | Analysis / Design Review |
| M-02 | Mission Profile | Design Operational Lifetime | 1 to 15 | 3-5 year | Years | High | Reliability Analysis |
| M-03 | Radiation Tolerance | Total Ionizing Dose (TID) | 10 to 100+ radiation tolerance | 20 krad | krad(Si) | Critical | Radiation Test Report |
| M-04 | Radiation Tolerance | SEE / SEL Immunity Threshold | Single Event Latch-up immunity | 43 MeV/cm2/mg | MeV-cm²/mg | Critical | Heavy Ion Test Report |
| 2. COMPUTING ARCHITECTURE & PERFORMANCE | |||||||
| C-01 | Processor | CPU Processor Architecture | ARM, RISC-V, LEON4, x86 | ARM or RISC-V | - | High | Manufacturer Datasheet |
| C-02 | Processor | Core Count / Frequency | Dual/Quad Core @ >400MHz | 100 | MHz | Medium | Benchmarking Data |
| C-03 | Memory | RAM Capacity (with ECC) | Error-correcting volatile memory | < 1 GB | GB | Critical | Architecture Review |
| C-04 | Storage | Non-Volatile Flash Storage | High-capacity fault-tolerant storage | < 1 GB | GB | High | Architecture Review |
| C-05 | Accelerator | Hardware AI/ML Acceleration | Optional (FPGA/NPU capability) | None | TOPS | Medium | Performance Simulation |
| 3. SIZE, WEIGHT, POWER & THERMAL (SWaP) | |||||||
| S-01 | Physical | Maximum Permissible Mass | Strict structural mass allocation | 150 | grams | Critical | Physical Measurement |
| S-02 | Physical | Enclosure Dimensions (Max) | Max envelope (X, Y, Z layout) | 100 x 100 x 30 | mm | Critical | CAD Model Inspection |
| S-03 | Power | Average Power Consumption | Continuous operational power limit | 0.5 | Watts | Critical | Electrical Power Analysis |
| S-04 | Power | Peak Power Consumption | Maximum transient power limit | 1 | Watts | High | Power Benchmarking |
| S-05 | Thermal | Thermal Dissipation Interface | Conduction to spacecraft cold plate | Conduction | - | High | Thermal Simulation / TVAC |
| 4. ELECTRICAL & DATA INTERFACES | |||||||
| I-01 | Data Bus | Primary High-Speed Data Bus | SpaceWire / Gigabit Ethernet / PCIe | Nil | - | Critical | Interface Control Doc (ICD) |
| I-02 | Command Bus | Secondary Command Interface | CAN bus / RS-422 / I2C | 1x CAN, 1x RS-422 minimum | - | Critical | Interface Control Doc (ICD) |
| I-03 | Power Input | Input Voltage Range | 28V Nominal standard satellite bus | 10. May | V DC | Critical | Power Board Testing |
| I-04 | Electrical | Galvanic Power Isolation | Required to protect main bus | - | High | Circuit Schematic Review | |
| 5. QUALITY ASSURANCE & QUALIFICATION | |||||||
| Q-01 | Heritage | Target Technology Readiness Level | TRL 6+ preferred (flight proven) | 6+ | TRL Score | High | Flight Heritage Doc |
| Q-02 | Screening | EEE Component Screening Level | COTS+ / NASA Level 2 / ECSS Grade | COTS+ | - | Critical | Parts Selection List |
| Q-03 | Environment | Operational Temperature Range | Thermal vacuum qualified limits | °C | Critical | Thermal Chamber Test | |
| Q-04 | Testing | Vibration & Shock Standard | MIL-STD-810H / SMC-S-016 compliant | - | High | Qualification Test Report | |
| Hardware Deliverable Class | Required Units | Target Delivery Date | Deliverable Scope Description | ||||
| Engineering Model (EM EPS) | 1 | Oct 26 | Form-factor fit check model with commercial grade micro-components. | ||||
| Qualification Model (EQM EPS) | To undergo full structural, dynamic vibration, and TVAC cycle overstress profiles. | ||||||
| Flight Model (FM EPS) | 1 | 26. Nov | Primary flight system integrated directly onto the flight spacecraft structure. | ||||
| Flight Spare (FS EPS) | Fully certified ground spare retained to mitigate integrated AIT system failures. | ||||||
We require an S-band transceiver for our 3U CubeSat project, operating in the 2025–2100 MHz receive (uplink) band and the 2200–2290 MHz transmit (downlink) band. The transceiver should support a minimum data rate of 4 Mbps and provide a minimum transmit output power of 30 dBm. The module should preferably be compatible with the PC/104 mounting hole standard for ease of integration into our spacecraft.
In addition, we are looking to procure a deployable UHF antenna operating in the 401–402 MHz frequency range. The antenna should be mountable on a 1U CubeSat face and be rated to support a 30 dBm transmit output power.
Our current avionics architecture uses SMA connectors for RF interfaces and Harwin Gecko and Molex Pico-Lock connectors for board-level interfacing. We also use RS-485, USB, and Ethernet as our primary communication interfaces. While compatibility with these connectors and interfaces would be preferred to simplify system integration, it is not a strict requirement.
Please let us know if you require any additional technical or mission-specific information to assess the suitability of your solution for our application.
We are developing an Electrical Power System (EPS) for a CubeSat and are looking for qualified suppliers to provide Battery Management System (BMS) hardware or related solutions. The requested system should support a 4-series (4S) lithium-ion battery configuration suitable for CubeSat applications, including battery protection, cell balancing, voltage and current monitoring, temperature monitoring, state-of-charge estimation, and fault detection. The solution should be compatible with spacecraft power systems and operate reliably in low-power, high-reliability environments. We request detailed datasheets, CAD models, user manuals, lead time, quotation, and any available flight heritage information. If available, please include interface documentation (ICD), electrical specifications, reference designs, and integration guidelines for CubeSat EPS applications.
| Category | Parameter / Requirement | Typical Example (Buyer Guide) | Buyer Target / Required Spec | Notes / Justification |
| SUPPLY CHAIN & COMMERCIAL | ||||
| Target Unit Cost (USD) | $5,000 - $15,000 based on moment | Supplier quotation required | Request separate EM and FM pricing, NRE for any customisation, harness/options and validity period. | |
| Minimum Order Quantity (MOQ) | 1 (Engineering) / 3 (Flight) | 3 flight rods; quote 1 EM and 1 flight spare as options | One rod per independent spacecraft axis. EM supports driver and flatsat integration. | |
| Lead Time (Weeks) | 12 to 24 Weeks | EM: 4 months; FM: 6 months for standard design | Based on supplier email. Custom rod lead time may be longer and must be separately identified. | |
| Export Control Classification | EAR99 Preferred (Avoid ITAR if possible) | Supplier to confirm export classification and licensing requirements | Preference is the least-restrictive lawful classification; do not assume EAR99. | |
| Flight Heritage / TRL | TRL 7 or higher | Standard qualified, flight-proven design preferred; provide TRL and heritage | Provide missions, quantities delivered/on orbit, anomalies and similarity to a five-year LEO mission. | |
| Quality Management Standard | AS9100 or ISO 9001 | ISO 9001 / AS9100 or equivalent; provide certificates | Supplier to identify applicable QMS, configuration control and traceability arrangements. | |
| Warranty Period | 12 Months Post-Delivery | Supplier standard warranty; state commencement and exclusions | Request warranty for workmanship and conformance, plus non-conformance/remedy process. | |
| ELECTRICAL & PERFORMANCE | ||||
| Nominal Magnetic Dipole Moment (Am²) | 15 Am² for MicroSat, 0.2 Am² for CubeSat | 1.6 A·m² nominal per rod baseline; quote nearest higher standard option and supplier recommendation | Preliminary quote baseline only. Final moment depends on deployed inertia, disturbance torques, tip-off and unloading time. | |
| Linearity Range | < 5% deviation up to nominal moment | Provide current-to-dipole curve and maximum non-linearity over operating range | Needed for closed-loop current control and accurate commanded dipole allocation. | |
| Residual Magnetic Moment (Am²) | < 0.05 Am² (crucial to avoid permanent drag) | State maximum residual magnetic moment and switch-off settling time | Critical because magnetometer measurements are taken with rods de-energised; low remanence is preferred. | |
| Nominal Supply Voltage (V) | 5V DC or 28V DC | 5 V preferred where standard; alternatives acceptable if technically advantageous | Final choice must trade current, harness loss, driver losses, power architecture and standard-product availability. | |
| Max Power Consumption (W) | < 2.5 W at nominal moment | Target ≤1.5 W per rod at rated 1.6 A·m²; state power for higher-moment option | Preliminary EPS allocation. Supplier should identify continuous/intermittent limits and duty-cycle constraints. | |
| Resistance (Ohms) @ 20°C | 25 - 50 Ohms (varies by design) | Supplier to provide resistance and inductance for each winding at 20°C | Required to size H-bridge MOSFETs, current sensing, transient suppression, PWM and settling time. | |
| Electrical Interface / Connector | Micro-D 9-pin, Flying Leads | Independent leads/pins for each bifilar winding; supplier-standard connector or flying leads acceptable | Provide pinout, mating connector, harness recommendations and derating limits. | |
| Polarity Reversal Tolerance | Must support continuous reversal via H-bridge | Continuous bidirectional operation via ImplementSpace H-bridge driver | Supplier to provide current-control method, PWM limits, flyback/transient requirements and prohibited conditions. | |
| MECHANICAL & PHYSICAL | ||||
| Maximum Mass (kg) | < 0.45 kg per rod | Preferred ≤0.075 kg per rod; up to ~0.100 kg may be considered | A preference, not a frozen hard limit. Correct dipole, thermal performance and standard qualification take priority. | |
| Dimensions - Length (mm) | 300 mm (X/Y axis), shorter for Z-axis | Preferred ≤120 mm; up to ~150 mm may be considered subject to layout review | Final axis-specific mounting envelopes will come from spacecraft CAD. | |
| Dimensions - Diameter (mm) | < 20 mm | Minimise cross-section; provide full envelope including mounts and connector clearance | No justified hard diameter limit is frozen yet. | |
| Core Material | Permenorm, HyMu-80, or similar high-permeability | Supplier-standard low-remanence high-permeability core | Provide core material, saturation behaviour, remanence characteristics and any magnetic cleanliness limitations. | |
| Mounting Mechanism | 2x M3 threaded holes per bracket | Supplier-standard robust mounting; provide CAD/STEP, fastener and torque requirements | Mount must survive launch loads and preserve rod-axis alignment. Include bracket mass in quoted envelope. | |
| ENVIRONMENTAL & RELIABILITY | ||||
| Operating Temperature Range (°C) | -40°C to +80°C (standard LEO) | Minimum operational capability: -24°C to +61°C | Preliminary mission acceptance envelope; final range must also cover spacecraft thermal-model MPT values. | |
| Survival Temperature Range (°C) | -50°C to +90°C | Preferred design qualification capability: at least -34°C to +71°C | Corresponds to current SpaceX qualification margin around the minimum acceptance range. | |
| Thermal Vacuum (TVAC) Tested? | Minimum 4 cycles required at limits | Protoflight baseline: -29°C to +66°C, 20 cycles total; at least 4 TVAC cycles preferred | Supplier to provide standard component qualification/acceptance profile and identify any delta to mission requirements. | |
| Radiation Tolerance (TID, krad) | > 20 krad (Si) for standard LEO | No active-electronics TID requirement; all insulation, adhesives and materials must suit 5-year LEO plus EOL operations | Provide radiation/material suitability evidence and any life-limiting degradation mechanisms. | |
| Random Vibration (grms) | NASA GEVS (14.1 grms) compliance | Protoflight: SpaceX MPE +3 dB ≈ 7.88 gRMS, 1 min/axis, 3 axes | Prefer existing design qualification evidence at MPE +6 dB ≈ 11.14 gRMS, 2 min/axis, 3 axes. | |
| Shock Tolerance (g) | > 1000g SRS at 1000Hz | Protoflight advised: MPE +3 dB, Q=10; ~42 g @100 Hz and ~1,414 g @1,000-10,000 Hz; 2/axis | Prefer design qualification evidence at MPE +6 dB: ~60 g @100 Hz and ~2,000 g @1,000-10,000 Hz; 3/axis. | |
| Outgassing (TML / CVCM) | < 1.0% TML / < 0.1% CVCM per ASTM E595 | TML/RML <1.0% and CVCM <0.1%; provide material declarations/test data | All vacuum-exposed non-metallic materials must be acceptable for launch and five-year LEO operation. | |
We are requesting detailed technical information and a rough-order-of-magnitude quotation for a fully managed hosted-payload mission. This is an initial planning inquiry, not a purchase commitment.
The proposed student-led payload is a custom PCB intended to provide publicly documented in-orbit performance data for a commercially available STT-MRAM device with limited public flight heritage. The preliminary design includes one STT-MRAM device under test, an STM32L4-series MCU, a local temperature sensor, supporting power/interface circuitry, and firmware for memory testing, health monitoring, data logging, and host communication.
The payload will write known data patterns, immediately read and verify them, reread verified locations after defined intervals, and log mismatches, failed accesses, communication errors, temperature, resets, boot count, and uptime. We may also test retention across commanded payload or memory-device power cycles.
Preliminary information:
Preferred orbit: LEO, approximately 500–600 km; altitude and inclination flexible
Operating period: please quote 1-, 3-, and 6-month options
Expected data volume: below 1 MB/day
Interface: provider-recommended digital interface
Current maturity: requirements definition and early prototype development
Schedule: please identify the earliest realistic delivery and launch opportunities
Please confirm whether this mission is compatible with your service and provide:
1. Customer responsibilities and maturity
A complete list of everything the customer must design, build, program, test, qualify, document, license, operate, or support. State the required maturity or TRL at initial engagement, contract signing, design reviews, delivery, and flight acceptance. Identify all required flight, engineering, qualification, flat-sat, or spare units; required documentation; required payload-level testing; and which activities are performed by the customer, performed by the provider, or included in the quoted price.
2. Responsibility handoff
Identify the exact milestone at which the provider accepts the payload and assumes responsibility for remaining routine mission activities. If responsibility never transfers completely, list every customer task remaining after acceptance, integration, launch, commissioning, and during operations.
We seek an option in which the provider handles spacecraft provision, payload integration, spacecraft-level testing, launch procurement and integration, applicable mission-level licensing and regulatory coordination, launch and early-orbit operations, payload commissioning, routine commanding and power cycling, ground communications, data downlink/storage/delivery, health monitoring, anomaly response, and end-of-life/deorbit compliance. Our preferred post-acceptance role is limited to payload-specific clarification and anomaly support.
Please state whether the host provides UTC or mission time, data buffering, scheduled commands, switchable payload power, reset information, and optional firmware updates.
3. Pricing and schedule
Provide the total estimated cost for the most fully managed option, assuming no or minimal customer responsibilities after payload delivery. If customer involvement remains, identify the exact tasks. Break out costs where applicable for engineering studies, nonrecurring engineering, integration, testing/qualification, launch, licensing, commissioning, operations, ground service, data delivery, additional operating time/data, development support, and insurance or reflight protection. State assumptions, lead time, payment milestones, and whether pricing is budgetary or fixed.
4. Reliability and flight heritage
Provide data for the exact spacecraft bus and hosted-payload interface proposed, including spacecraft launched and successfully commissioned, hosted payloads launched and successfully operated, missions completing their contracted duration, typical duration and availability, data-delivery performance if tracked, significant failures or anomalies and corrective actions, and whether the proposed configuration has flown. Please distinguish company heritage from heritage of the exact bus and interface.
5. Failure remedies and insurance
Explain the standard remedy for launch delay or failure, failure to commission, loss of payload power or communications, inability to retrieve data, early spacecraft failure, or delivery of less than the contracted operating period. State whether each may result in a refund, partial refund, service credit, replacement flight, discounted reflight, insurance claim, or no remedy. Describe available launch or in-orbit insurance, reflight protection, or service guarantees, including coverage, exclusions, deductibles, and who arranges coverage.
| # | Parameter | Requirement | Response |
| 1 | Physical Properties | Payload Mass (kg) | < 15 kg |
| 2 | Payload Volume (U or m3) | 200 x 300 x 200 mm | |
| 3 | General | Payload type e.g. RF, EO (RGB, HS, MS IR) | Optical Payload |
| 4 | Desired orbits e.g. SSO, near-equatorial | SSO | |
| 5 | Desired altitudes e.g. 550 km | 500 km | |
| 6 | EPS | Payload continuous power (W) | < 25 W |
| 7 | Payload peak power (W) | < 50 W | |
| 8 | Payload duty cycle per orbit (%) | 70 | |
| 9 | Payload voltage supply e.g. 3V3, 5V, 12V | 12 V | |
| 10 | RF | High-speed downlink required e.g. > 5 Mbps? | < 15 Mbps |
| 11 | Daily data budget (Mb or Gb) | < 5 Gb | |
| 12 | Encryption required on TTC or payload data e.g. AES-256? | no | |
| 13 | Interfaces | Bus to payload interfaces required e.g. CAN, I2C, SPI, UART, RS422, RS485, PPS | CAN |
| 14 | On-board data storage requirements? | yes | |
| 15 | ADCS | Payload Pointing Modes when active e.g. Nadir | Nadir |
| 16 | Pointing Accuracy | No requirements | |
| 17 | Pointing Knowledge | No requirements | |
| 18 | Slew Rate (°/s) requirements? | No requirements | |
| 19 | GPS required for position, velocity knowledge? | No requirements | |
| 20 | Propulsion | Propulsion Required? | Yes |
| 21 | Propulsion type requirement e.g. electric, chemical? | Electric. Which type of electric propulsion is used and what are the parameters? We need to understand the impact on the optical system. | |
| 22 | Propulsion system use e.g. orbit maintenance | Orbit maintenance, De-orbit | |
| 23 | Propulsion thrust or delta V requirements? | 3-5 mN | |
| 24 | Operations | Operations duration e.g. 6 months, 12 months | 3-4 years |
| 25 | Summary of payload operations or CONOPS? | 26 months | |
| 26 | Other | Any other comments or notes? E.g. ITAR restrictions, ground station requirements. | No ITAR restrictions |
| 27 | Other | Anything else? E.g. budgetary or lead time requirements. | Lead time: 12 months |
