Payload Accommodations


Proton M/Breeze M

Payload Compartment


Maximum Payload Diameter (Note: Cross section of available volume is not quite circular. Available diameter is approximate.)

3864 mm (152.1 in.)

Maximum Cylinder Length

BR-1160: 4112 mm (161.9 in.)
BR-13305: 4116 mm (162.0 in.)
BR-15255: 6064 mm (238.8 in.)

Maximum Cone Length

3800 mm (149.6 in.)

Payload Adapter Interface Diameter

Both separation nut (truss type) and Marmon clamp (shell type) adapters available in standard diameters, including 937 mm (37 in.), 1194 mm (47 in.), and 1666 mm (66 in.)

Payload Integration


Nominal Mission Schedule Begins

New spacecraft: T–18 to 24 months
Reflight: T–6 months

Launch Window


Last Countdown Hold Not Requiring Recycling

T–70 min

On-Pad Storage Capability

48 h for a fueled vehicle

Last Access to Payload

T–1.5 h through access doors



Maximum Axial Load

+4.3 g

Maximum Lateral Load

±1.35 g g

Minimum Lateral/Longitudinal Payload Frequency

10 Hz/25 Hz

Maximum Acoustic Level

132.4 dB at 100 Hz

Overall Sound Pressure Level

141.4 dB

Maximum Flight Shock

4000–8000 g at 10 kHz, depending on separation system

Maximum Dynamic Pressure on Fairing

3890 Pa (800 lbf/ft2)

Maximum Aeroheating Rate at Fairing Separatii

on 130 W/m2 (0.01 BTU/ft2/s) for late fairing separation or 9600 W/m2 (0.85 BTU/ft2/s) for early fairing separation; optimum jettison at 1135 W/m2 planned with use of additional jettison zone

Maximum Pressure Change in Fairing

1.5 kPa/s (0.2 psi/s)

Cleanliness Level in Fairing

Class 100,000 (no air conditioning during 4-h erection period onto pad and 70 min before launch)

Payload Delivery


Standard Orbit Injection Accuracy (3 sigma)

LEO at 200 km (108 nm) circular at 51.6 deg
Apogee: ±4.0 km (2.5 nmi)
Perigee: ±2.0 km (1.0 nmi)
Inclination: ±0.03 deg
Apogee: ±100 km (62.5 nmi)


Inclination: ±0.15 deg

Attitude Accuracy (3 sigma)

±5 deg, ±0.7–1.8 deg/s

Nominal Payload Separation Rate

0.15–0.5 m/s (0.5–1.5 ft/s)

Deployment Rotation Rate Available

6 deg/sec

Loiter Duration in Orbit

More than 24 h

Maneuvers (Thermal/Collision Avoidance)


Multiple/Auxiliary Payloads



Proton has carried multiple spacecraft on mission unique dispensers. For example, seven spacecraft per flight were carried for Iridium. Proton has not carried comanifested payloads for separate customers in the past, but a dual-payload fairing structure has been considered as an option for future missions.

Auxiliary Payloads

Proton has not generally carried auxiliary payloads in the past. Availability of secondary payload opportunities is unknown. Contact ILS for more information.