Atlas
Payload Accommodations
Ariane 5 | Ariane 6 | |
Payload Compartment | ||
Maximum Payload Diameter | 4570 mm (180 in.) | 4570 mm (180 in.) |
Maximum Cylinder Length | Single payload (assume 2624 mm interface) | Single payload (assume 2624 mm interface) |
Multipayload (assume 2624 mm interface) | Multipayload (assume 2624 mm interface) | |
Maximum Cone Length | Fairing: 6030 mm (237.4 in.) | Fairing: 6030 mm (237.4 in.) |
Payload Adapter Interface Diameter | 937 mm (36.9 in.); 1194 mm (47.0 in.); 1666 mm (65.6 in.); 2624 mm (105.3 in.) | 937 mm (36.9 in.); 1194 mm (47.0 in.); 1666 mm (65.6 in.); 2624 mm (105.3 in.) |
Payload Integration | ||
Nominal Mission Schedule Begins | T–10 to 40 months | T–10 to 40 months |
Launch Window | Spacecraft launch window at least 3 hours | |
Last Countdown Hold Not Requiring Recycling | T–5 min, 40 s | T–5 min, 40 s |
On Pad Storage Capability | 60 days after fueling EPS | 60 days after fueling EPS |
Last Access to Payload | T–2 days through access doors | T–2 days through access doors |
Environment | ||
Maximum Axial Load | +4.25 g | +2.2g, -4.6 g |
Maximum Lateral Load | ±0.25 g | ±2.0 g |
Minimum Lateral/Longitudinal Payload Frequency | 9 Hz/payload dependent | ≥ 6 Hz lateral, ≥ 20 Hz longitudinal |
Maximum Acoustic Level | 139 dB at 2000–4500 Hz | 136 dB at 90-180 Hz |
Overall Sound Pressure Level | 142 dB (one third octave) | 142 dB (one third octave) |
Maximum Flight Shock | 5000 g at 2–10 kHz on spacecraft interface | 1000g at 1–10 kHz on spacecraft interface |
Maximum Dynamic Pressure on Fairing | 40 kPa (835 lbf/ft2) | 100 kPa (2089 lbf/ft2) |
Maximum Aeroheating Rate at Fairing Separation | 1135 W/m2 (0.1 BTU/ft2/s) | 1135 W/m2 (0.1 BTU/ft2/s) |
Maximum Pressure Change in Fairing | 3.2 kPa/s (0.5 psi/s) | 4.0 kPa/s (0.58 psi/s) |
Cleanliness Level in Fairing | Class 100,000 | Class 100,000 |
Payload Delivery | ||
Standard Orbit Injection Accuracy (3 sigma) | GTO: Semimajor axis ±78 km (42 nmi); Eccentricity ±0.0009; Inclination ± 0.06 deg SSO 800 km (430 nmi): Semimajor axis ±12 km (6.5 nmi) Inclination ±0.12 deg | GTO: Semimajor axis ±40 km (21.6 nmi); Eccentricity ±0.00045; Inclination ± 0.02 deg SSO 800 km (430 nmi): Semimajor axis ±2.5 km (1.35 nmi) Inclination ±0.04 deg |
Attitude Accuracy (99%) | ±1 deg; ±1 deg/s | ±1 deg; ±1 deg/s |
Nominal Payload Separation Rate | 0.5 m/s (1.6 ft/s) | 0.5 m/s (1.6 ft/s) |
Deployment Rotation Rate Available | 0–5 rpm | 0–5 rpm |
Loiter Duration in Orbit | ? h | ? h |
Maneuvers (Thermal/Collision Avoidance) | Yes | Yes |
Multiple/Auxiliary Payloads | ||
Dual or Multiple Manifest | Ariane 5 is designed to carry up to three independent primary payloads or multiple satellites for constellations. | dd |
Auxiliary Payloads | The ASAP5 structure carries auxiliary payloads on the Ariane 5 adapter. Up to eight 100-kg microsatellites or four 300-kg minisatellites, or a combination thereof, can be carried. Microsatellites must be no more than 600x600 mm square and 800 mm high (23.6x23.6x31.5 in.). Minisatellites must fit in the volume of a cylinder 1500 mm high and 1500 mm in diameter (59x59 in.). Auxiliary payloads may be carried on missions to either LEO or GTO. | |