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12U spacecraft
12U Deep-Space Astronomy CubeSat Bus, Integration, and Verification Services
Status:
Open
Deployable Helical Antenna
We're currently looking for a COTS solution for a deployable Helical Antenna for the lower UHF band Around 402/468 MHz.
Status:
Open
ADCS actuators and sensors
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).
Status:
Open
GNSS receiver
| 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) | |
Status:
Open
Gyroscope
| 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 | ||
Status:
Open
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