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
We are looking for a set of attitude determination and control subsystem (ADCS) actuators and sensors for a 6U CubeSat mission. Details below:
1. Magnetorquers (3-axis)
- Configuration: 3 orthogonal axes (integrated assembly or 3 individual single-axis units)
- Target magnetic dipole moment: [e.g., ≥0.2 A·m² per axis — specify based on your detumbling analysis]
- Interface: I2C/UART digital driver preferred (or analog/PWM — specify per your OBC)
- Supply voltage: [e.g., 3.3V/5V]
- Quantity: 3 flight units + 1 spare (recommended)
- Application: detumbling after deployment and momentum dumping/coarse pointing alongside reaction wheels
2. Reaction wheels (3-axis)
- Configuration: 3 orthogonal single-axis wheels (or an integrated 3-axis reaction wheel assembly, if available)
- Target angular momentum storage: [e.g., ≥10-25 mNms per wheel — specify based on your pointing/slew requirements]
- Target max torque: [e.g., ≥1 mNm per wheel — specify]
- Interface: I2C/UART/CAN digital control preferred (specify per your OBC)
- Supply voltage: [e.g., 5V/12V]
- Quantity: 3 flight units + 1 spare (recommended)
- Application: fine pointing and slew maneuvers for a 6U platform
3. Sun sensors (coarse)
- Type: analog coarse sun sensor (e.g., single-axis photodiode-based, similar to Tensor Tech CSS-10 or equivalent)
- FOV: ±60° or better per unit
- Interface: analog output, to be read via external ADC (MAX11131)
- Quantity: 6 units (one per CubeSat face, for full 4π sky coverage)
- Application: coarse sun vector determination for detumbling safe-mode and eclipse detection
Please include in your quote for each item: unit pricing per quantity break, power consumption (peak/average), mass, dimensions, lead time, flight heritage, and export control classification (ECCN/ITAR status, as we are based in Brazil).
| PROJECT INFORMATION | |||
| Project Type | Earth Obervation | E.g., Earth Observation Constellation | |
| Target Orbit | Transporter SSO 500km | LEO, MEO, GEO, or Sub-orbital | |
| SUPPLY CHAIN & LOGISTICS | |||
| Quantity Required (Flight) | 1 | Number of flight units | |
| Quantity Required (Eng/Qual) | 0 | Number of engineering/qual models (EM/QM) | |
| Target Lead Time (ARO) | None (First Flight) | [Months] Time from Order to Delivery | |
| Export Control Classification | MTCR Cat II | ITAR, EAR99, ECCN (Note: GNSS often ITAR/EAR restricted) | |
| Technology Readiness Level (TRL) | 7+ | TRL 1-9 (Prefer TRL 7+ for flight) | |
| GNSS PERFORMANCE & RF SPECS | |||
| Supported Constellations | GPS L1 | GPS (L1/L2/L5), Galileo, GLONASS, Beidou | |
| Number of Channels | Total tracking channels available | ||
| Position Accuracy (3D RMS) | 10 | [Meters] Expected accuracy in orbit | |
| Velocity Accuracy (3D RMS) | 0.2 | [m/s] Expected velocity accuracy | |
| Time to First Fix (Cold Start) | 15min | [Seconds] TTFF without prior almanac/ephemeris | |
| Time to First Fix (Warm/Hot) | 5min | [Seconds] TTFF with current almanac | |
| Tracking Sensitivity | [dBm] Minimum signal level for continuous tracking | ||
| Update Rate | 1 | [Hz] Position/Velocity output frequency (e.g., 1Hz, 10Hz) | |
| COCOM Limits Disabled | Yes | Crucial for Space! (Must exceed 18km/515m/s) | |
| Category | Parameter | Input Value / Target | Unit / Notes |
| PROJECT INFORMATION | |||
| Project / Mission Name | GEO | E.g., GEO Commsat, Deep Space Probe | |
| Attitude Determination Role | Primary IRU (Inertial Reference Unit) | Primary IRU, Backup Rate Sensor, Safe Mode | |
| SUPPLY CHAIN & LOGISTICS | |||
| Quantity Required (Flight) | 2 | Number of flight units per spacecraft | |
| Quantity Required (Eng/Qual) | 1 | Number of EM/QM units for testing | |
| Target Lead Time (ARO) | 12 | [Months] Time from Order to Delivery (often 12-24m for space gyros) | |
| Export Control Classification | None | ITAR, EAR (Specify ECCN), None | |
| Technology Readiness Level (TRL) | TRL 9 (Flight Proven) | TRL 1-9 (Prefer 8+ for GEO) | |
| ARCHITECTURE & INTERFACES | |||
| Gyroscope Technology Type | Select... | FOG, HRG, RLG, Space-grade MEMS | |
| Number of Axes | 3-Axis Orthogonal | 1-Axis, 3-Axis Orthogonal, 4-Axis (Tetrad/Skewed) | |
| Internal Redundancy | Cold Redundant Electronics | None, Cold Redundant Electronics, Fully Redundant | |
| Data Interface (Output) | Select... | RS-422, SpaceWire, MIL-STD-1553, SPI | |
| Data Update Rate | [Hz] Rate of angular rate output (e.g., 10Hz, 100Hz) | ||
| Supply Voltage | Select... | 5V, 12V, 28V, 50V (Regulated vs Unregulated) | |
| GYROSCOPIC PERFORMANCE | |||
| Measurement Range (Max Rate) | ± 499 | [deg/sec] Maximum measurable angular rate (e.g., 10 deg/s) | |
| Bias Instability (Allan Variance) | ≤ 1.5 | [deg/hr] Critical for GEO pointing (e.g., < 0.005 deg/hr) | |
| Angle Random Walk (ARW) | ≤ 0.08 | [deg/√hr] High-frequency noise metric (e.g., < 0.0005 deg/√hr) | |
| Scale Factor Accuracy | ≤ | [ppm] Accuracy over temp/life (e.g., < 100 ppm) | |
| Axis Alignment Error | ≤ | [mrad] Orthogonality/Misalignment (for multi-axis units) | |
| Bandwidth (-3dB) | ≥ | [Hz] Dynamic response capability | |
| PHYSICAL & ELECTRICAL CONSTRAINTS | |||
| Maximum Mass | 10 | [kg] Constraint for the sensor head + electronics | |
| Envelope / Dimensions | [mm] Max Length x Width x Height | ||
| Power Consumption (Steady State) | [W] Average power draw in tracking mode | ||
| Power Consumption (Peak / Warm-up) | [W] Peak power drawn immediately after turn-on | ||
| Initialization / Warm-up Time | ≤ | [Minutes] Time until full accuracy is achieved | |
| GEO ENVIRONMENT & SURVIVABILITY | |||
| Design Life (Orbit) | 5 | [Years] Typical GEO mission life is 10-15+ years | |
| Radiation Tolerance (TID) | ≥ 100 | [krad (Si)] GEO requires high TID shielding/tolerance | |
| Single Event Effects (SEE) Limit | Immune to SEL (LET > 75) | Immune up to X MeV-cm2/mg (Latch-up/Upset) | |
| Operating Temp Range (Baseplate) | [°C] Temperature limits for guaranteed performance | ||
| Non-Operating Survival Temp | [°C] Survival extremes during transfer or safe-mode | ||
| Random Vibration Tolerance | [gRMS] Launch vibration survival | ||
| ID | Parameter Name | Specification Guideline / Instructions | Required Value (To Fill) | Unit / Options |
| 1. MISSION PROFILE & PROGRAMMATICS | ||||
| PM-01 | Target Orbit Type | Determines radiation environment and link distance geometry. | LEO (<2000 km) | [Select Dropdown] |
| PM-02 | Design Life | Required operational duration in space environment. | 1 | Years |
| PM-03 | Flight Model (FM) Qty | Number of flight units required for spacecraft integration. | 2 | Units |
| PM-04 | Engineering Model (EM) Qty | Number of qualification/test units required for ground beds. | 6 | Units |
| PM-05 | Target Delivery Date | Required on-dock date for the first flight unit. | 2027-08-01 | Date (YYYY-MM-DD) |
| 2. RADIO FREQUENCY (RF) PERFORMANCE | ||||
| RF-01 | Uplink (Rx) Frequency Band | Frequency band for receiving commands from ground/relay. | S-Band (2-4 GHz) | [Select Dropdown] |
| RF-02 | Uplink Center Frequency | Specific operating frequency if allocated by ITU/SFCG. | 2021 | MHz |
| RF-03 | Downlink (Tx) Frequency Band | Frequency band for transmitting telemetry and mission data. | S-Band (2-4 GHz) | [Select Dropdown] |
| RF-04 | Downlink Center Frequency | Specific operating frequency if allocated by ITU/SFCG. | 2101 | MHz |
| RF-05 | Min Downlink Data Rate | Minimum required throughput for science/telemetry data transmission. | 3 (Max) | Mbps |
| RF-06 | Min Uplink Data Rate | Minimum required throughput for command uploads. | 100 (max) | kbps |
| RF-07 | Min RF Output Power | Minimum RF power output at transceiver antenna port. | 10 or 20 | Watts |
| RF-08 | Ranging Support | Indicate if coherent turn-around ranging is required for navigation. | Yes | [Select Dropdown] |
| 3. SIZE, WEIGHT, AND POWER (SWaP) | ||||
| SW-01 | Maximum Allowable Mass | Strict allocation from the spacecraft mass budget. | - | kg |
| SW-02 | Envelope Dimensions (Max) | Maximum envelope allocation (Width x Length x Height). | - | mm x mm x mm |
| SW-03 | Primary Input Voltage | Spacecraft power bus nominal voltage standard. | 28 VDC (Standard) | [Select Dropdown] |
| SW-04 | Max Power Consumption (Tx Mode) | Power draw when transmitting at maximum RF power. | 10 or 20 | Watts |
| SW-05 | Max Power Consumption (Rx Mode) | Power draw when in quiet listening/receive mode. | 10 or 20 | Watts |
| 4. ELECTRICAL & DATA INTERFACES | ||||
| IF-01 | Command & Telemetry Interface | Data bus protocol for standard spacecraft C&DH communications. | SpaceWire | [Select Dropdown] |
| IF-02 | High-Speed Data Interface | Separate high-speed bus if required for payload data downlink. | SpaceWire | [Select Dropdown] |
| IF-03 | RF Output (Tx) Connector | Physical RF connector type for the transmit line. | SMA | [Select Dropdown] |
| IF-04 | RF Input (Rx) Connector | Physical RF connector type for the receive line. | SMA | [Select Dropdown] |
| 5. ENVIRONMENTAL, RADIATION & QUALITY | ||||
| EQ-01 | Total Ionizing Dose (TID) | Minimum radiation dose hardness the component must withstand. | 30 krad (Standard LEO) | [Select Dropdown] |
| EQ-02 | SEE Immunity (LET Threshold) | Single Event Effect immunity threshold without destructive latch-up. | MeV·cm²/mg | |
| EQ-03 | Operational Temp Range (Min) | Minimum qualification operating temperature limit. | -40 | °C |
| EQ-04 | Operational Temp Range (Max) | Maximum qualification operating temperature limit. | 85 | °C |
| EQ-05 | Component Quality Level | Required manufacturing, inspection, and component screening standard. | COTS+ / Rad-Tolerant | [Select Dropdown] |
| Category | Parameter | Mission Requirement | Expected Unit / Format |
| Volume | Number of units | 2–5 cells (research evaluation) | |
| Electrical (AM0) | BOL Efficiency | Manufacturer recommendation / datasheet value requested | % |
| EOL Efficiency | Not applicable (terrestrial research use) | % | |
| Max Power Voltage (Vmp) | Manufacturer datasheet requested | V | |
| Max Power Current (Imp) | Manufacturer datasheet requested | mA/cm² or A | |
| Open-Circuit Voltage (Voc) | Manufacturer datasheet requested | V | |
| Short-Circuit Current (Isc) | Manufacturer datasheet requested | mA/cm² or A | |
| Mechanical | Cell Architecture | Triple-junction (InGaP/GaAs/Ge) preferred | Text |
| Cell Dimensions | 40mm × 80 mm preferred ( or available options) | mm x mm | |
| CIC Assembly | Coverglass Thickness | Manufacturer recommendation | µm or mils |
| Coverglass Coatings | AR coating preferred | Text | |
| Interconnect Design | Manufacturer recommendation | Text | |
| Bypass Diode Type | Manufacturer recommendation | Text | |
| Contact Layout | Manufacturer recommendation | Text | |
| Heritage & QA | Flight Heritage | Not required for terrestrial research | Orbit / Mission List |
| Space Standard Auth. | Not required | Text | |
| LAT Documentation | Preferred if available | Yes/No |
| SOLAR ARRAY DRIVE ASSEMBLY (SADA) - PROCUREMENT SPECIFICATION | |||
| Category | Parameter | Input Value / Target | Unit / Notes |
| PROJECT INFORMATION | |||
| Project / Mission Name | GEO | E.g., Earth Obs Constellation, GEO Commsat | |
| Target Orbit | GEO | LEO, MEO, GEO, Deep Space | |
| SUPPLY CHAIN & LOGISTICS | |||
| Quantity Required (Flight) | 2 | Number of flight units (per spacecraft) | |
| Quantity Required (Eng/Qual) | 1 | Number of EM/QM/STM units | |
| Target Lead Time (ARO) | 12 | [Months] Time from Order to Delivery | |
| Export Control Classification | None | ITAR, EAR, or ECCN code | |
| Technology Readiness Level (TRL) | TRL 9 (Flight Proven) | TRL 1-9 (Prefer TRL 8+ for mechanisms) | |
| SLIP RING & POWER TRANSFER | |||
| Power Transfer Architecture | Slip Ring (Continuous 360) | Continuous Slip Ring vs. Cable Wrap/Twist Capsule | |
| Maximum Bus Voltage | 42 | [Vdc] E.g., 28V, 50V, 100V | |
| Total Power Transfer Required | 400 | [W or kW] Total solar array power passing through SADA | |
| KINEMATICS & MOTOR CONTROL | |||
| Drive Motor Type | Stepper Motor | Stepper Motor, Brushless DC (BLDC) | |
| Rotation Range | Continuous 360 Degrees | Continuous 360°, Limited Angle (e.g., ±180°) | |
| MECHANICAL & LOAD CAPACITIES | |||
| Maximum Mass | 7 | [kg] Mass of SADA (Motor + Slip Ring + Housing) | |
| ENVIRONMENTAL & SURVIVABILITY | |||
| Required Operational Life | 5 | [Years] Mission duration | |
| PROCESSING & MEMORY ARCHITECTURE | |||
| Primary Processor Type | Hybrid SoC + FPGA | FPGA, SoC, CPU, GPU, DSP, or Hybrid | |
| Processor Architecture / Core | ARM Cortex-A53/A72 + FPGA fabric | E.g., ARM Cortex-A53, RISC-V, Xilinx Zynq Ultrascale+ | |
| Computing Performance | >100 GOPS (preferably TOPS-class) | [GOPS/TOPS] Giga/Tera Operations Per Second (or DMIPS/MFLOPS) | |
| Volatile Memory (RAM) | >=16 GB ECC DDR4/DDR5 | [GB] Total accessible DDR/SRAM for processing (Specify ECC in notes) | |
| Non-Volatile Storage (Flash/SSD) | Gigabit Ethernet | [GB/TB] On-board mass storage for payload data | |
| Hardware Acceleration | AI/ML Accelerator | AI/ML Accelerator (NPU), VPU, Vision Processing, None | |
| Supported Operating System | Linux + RTOS support | RTOS (FreeRTOS, VxWorks, RTEMS) or Linux (Ubuntu, Yocto) | |
| DATA INTERFACES & CONNECTIVITY | |||
| High-Speed Payload Data IN | SpaceFibre / PCIe / Ethernet | SpaceWire, SpaceFibre, PCIe, Gigabit Ethernet, LVDS | |
| High-Speed Data Bandwidth IN | >10 Gbps | [Gbps] Required ingestion rate from sensors | |
| Spacecraft Bus Interface | CAN, SpaceWire, RS-422 | CAN bus, RS-422, I2C, SPI, MIL-STD-1553 | |
| Mass Memory / Downlink Interface | SerDes / PCIe / Ethernet | Direct to Tx via LVDS, JESD204B, SerDes | |
| PHYSICAL & ELECTRICAL CONSTRAINTS | |||
| Maximum Mass | <5 kg | [kg] Constraint for the processing unit | |
| Dimensions / Form Factor | Custom Box or VPX | PC/104, 3U VPX, Custom Box, PCle Card | |
| Power Consumption (Nominal Processing) | <100 W | [W] Average power during heavy data crunching | |
| Power Consumption (Idle/Standby) | <20 W | [W] Power draw when payload is inactive | |
| Supply Voltage | 28 V | 5V, 12V, 28V (Specify regulated/unregulated) | |
| Thermal Dissipation Strategy | Conduction to baseplate | Conduction to baseplate, Radiation, Heat pipes | |
| ENVIRONMENTAL & RELIABILITY | |||
| Operating Temp Range | -20°C to +70°C | [°C] Baseplate or ambient temperature range | |
| Radiation Tolerance (TID) | >50 krad(Si) | [krad (Si)] Total Ionizing Dose over mission lifetime | |
| Single Event Effects (SEE) Mitigation | TMR + ECC + Watchdog | TMR (Triple Modular Redundancy), EDAC/ECC, Watchdog, Rad-Hard Chip | |
| Design Life | 10-15 years | [Years] Required operational lifetime in orbit | |
