Satellite Solution

Contact Us

INTRODUCTION

Lockheed Martin Space encourages payload providers and mission planners to create missions optimized for—or at least compatible with—our versatile and highly capable LM 2100 geosynchronous-orbiting (GEO) platform. The table below provides a summary of typical interfaces and performance capabilities provided by the LM 2100 platform. These specifications serve only as a guide to those interested in flying on this bus. An actual compatibility assessment is best done through an exchange of detailed information and interface requirements. In many cases, specific interface adaptations can be easily created.

Likewise, Figures 1 and 2 provide notional examples of payloads and where they might be accommodated on an LM 2100-based satellite. Figures 3 and 4 provide specific definition of the volumes available for payload mounting based on typical launch vehicle fairing constraints.

LM 2100
LM 2100 Images

Table 1. LM 2100 Hosted Payload Accommodation

Typical1 Payload Resource Allocations, Performance Characteristics and Interface Requirements

Nominal Payload Resource Allocations

Payload Mass Limit 1000 kg
Payload Power 12000 W
Payload Thermal Dissipation 6000 W
Payload Volume (contiguous) 3.5 m3
Payload Volume (contiguous) 3.5 m3

Key Platform Performance Characteristics

Attitude Control (Including Stationkeeping Maneuvers)
Attitude Control System 3-axis stabilized, zero momentum bias
Pointing Knowledge, 3σ 0.02° Roll/Yaw/Pitch
Total Pointing Accuracy, 3σ 0.10° Roll/Yaw/Pitch (optional 0.03° per axis)
Acceleration Environment (Jitter) <20 milli-g with optional vibration isolation
Mission Parameters
Orbit GEO: 35786 km circular, longitude/inclination maintained ± 0.05°
Duration 15 years
Probability of Success >0.80 for 15 year mission
Nominal Program Schedule >18-36 mo

Key Platform Interface Characteristics

Command and Data Handling Interfaces
Main Data bus MIL-STD-1553B data bus
Alternate Serial Bus Interface RS-422 derived bi-directional serial bus
Pulse Commands -32 V, 28V
Telemetry Types available Active analog, passive analog, discrete, serial (bidirectional serial bus), serial (1553), software 16 Bit / 32 Bit words, and memory dumps
Payload Downlink No specific constraints. Data rates 10 kbps to 100 Mbps and above are readily accommodated.
Power
Main Bus Voltage (Standard) 70 V Regulated to 68 V to 71 V
Secondary Bus Voltage (Optional) 28 V Regulated to ± 2V
Vibration
Standard Component Random Vibration 0.2 G2/Hz        20-1000 Hz
Environment -6 dB/Oct        1000-2000 Hz
Standard Component Sine Vibration Environment 0.5″ D.A.        10-24 Hz
15.0 G        24-35 Hz
20.0 G         36-55 Hz
7.0 G         56-100 Hz

Thermal
Internal Temperature Environments In-Orbit Temperature Range -24°C and +61°C
Transfer Orbit Temperature Range -24°C and +30°C
Component Thermal Design Criteria Maximum average baseplate temperature 45°C; ±15°C max diurnalswing.
Reliability / Survivability / Electromagnetic Compatibility
Radiation Tolerance 20-100 kRad(Si) Total Dose
Single Event Effects <1 critical upset per box per 1000 yr
Payload Module Shielding Effectiveness >20 dB (200 MHz to 40 GHz)


Figure 1. External view of typical LM 2100 showing a variety of potential payload mounting locations


Figure 2. Typical LM 2100 showing size constraints when mounted in typical launch vehicle fairings. Falcon 9 also available


Figure 3. Volume available for payload mounting on LM 2100


Figure 4. Volume available for payload mounting on LM 2100 with dimensions in inches