SSL Payload Orbital Delivery System (PODS)

“FedEx to GTO/GEO”

May 28th, 2014

For more information, contact:

Al Tadros, SSL

Email: alfred.tadros@sslmda.com

Tel: (650) 714-0439

2 28 May 2014

The Payload Orbital Delivery System (PODS) enables low-cost, high-tempo access to GTO or GEO for small payloads – “FedEx to GEO”

≤ 90 kg for standard form factor, ≤ 150 kg for extended form factor

~6-8 satellite launch opportunities per year with SSL

Standardization of interfaces and form factor enables quick turnaround

No need to coordinate with other payloads

Launch vehicle independent – payload interface does not change if the launch vehicle changes

Cost-Effective, Frequent, Quick Access to GTO/GEO for Small Payloads

3 28 May 2014

Concept for Resupply of Servicing Infrastructure in GEO

4 28 May 2014

Deep Space Microsatellite Missions - GTO Drop-Off

5 28 May 2014

MicroSatellites Are Integrated and Dispensed from the ComSat

Typical pre-release views for different launch locations are shown

Launch location depends on microsatellite volume and ComSat configuration

Payload sizing can go as small as CubeSat

Unused Battery Compartments

On East/West Faces

Anti-Nadir Side of

North/South Panels

Antenna Tower

Mid East/West Faces

If No E/W OMUX

6 28 May 2014

Launch Frequency to GTO/GEO is Forecasted to Remain High

7 28 May 2014

User’s Guide Summary Table

MicroSatellite Parameter Typical Value User Value

Launch Frequency 6-8 SSL Launch Opportunities per year

Maximum Volume 1m x 0.5m x 0.4m (Standard Sizing)

1m x 1m x 0.6m (Extended Sizing)

Maximum Mass 90 kg (Standard Sizing)

150 kg (Extended Sizing)

Center of Mass Within 15 cm of MicroSatellite geometric center in any axis

Available power 150W average, 300W peak; 28-31 V

State During Launch Off

Data Connection MIL-STD-1553 (optional)

Thermal Environment -35°C to + 60°C non-operating + aero-thermal heating during

launch

Launch Dynamics Acoustic, static, vibration, shock envelope of common launch

vehicles (Ariane 5, Proton, Falcon 9, Sea Launch)

Ejection Speed ~0.25 m/s

Maximum Tumble Rate 0.5 deg/sec/ axis

Dispensing Orbits Available GTO (at apogee), near GEO (100-300 km sub or super)

Range Accuracy of Drop-Off 100 m

In-track accuracy 2 km

Release pointing accuracy 5 degrees per axis

Deployment Video Available Yes

8 28 May 2014

Payload Orbital Delivery System (PODS) Design Concept

PODS Baseplate

(stays with Host)

Standard PODS (1m x 0.5m x 0.4m) (L x W x H)

Launch

Locks

Low Separation

Force Electrical

Connector

Low Tumble Rate

Ejection

Mechanism

Insert

Microsatellite of Choice

Extended Size

Baseplate for Larger

Payloads

9 28 May 2014

MicroSatellite Mechanical Interface to GEO ComSat

Launch

Locks

PODS Ejection

Mechanism Fittings

The MicroSatellite interfaces mechanically to the GEO ComSat via the PODS Ejection Mechanism (PEM) Baseplate.

Primary structural interface to the MicroSatellite is the launch locks (Redundant Release Devices)

Fittings on MicroSatellite will interface to the PODS Ejection Mechanism for deployment

10 28 May 2014

MicroSatellite Ejection from Host

The MicroSatellite can be dropped off at GTO or GEO (sub or super)

The ejection will be set up such that it is passively safe from the satellites recontacting each other (i.e., neither spacecraft is required to perform a maneuver to avoid recontact after ejection)

The Host spacecraft will command/control the ejection

0.25 m/s ejection speed

0.5 deg/sec/axis maximum tumble rate

< 5 degrees pointing error on ejection

Upon ejection, data will be provided to the MicroSatellite owner/operator to determine the location of the MicroSatellite

100 m range accuracy

2 km track accuracy

The release sequence will be monitored by video equipment on Host

11 28 May 2014

Sample Orbit Parameters for Various Launch Vehicles

12 28 May 2014

Sample Orbit Parameters for Various Launch Vehicles (cont’d)

13 28 May 2014

Power & Data

Power (optional)

Power can be provided to the MicroSatellite on the ground and after launch for heaters, battery charging, etc.

Available power: nominally 150W average, 300W peak; 28-31 V

More power can be made available if needed

MicroSatellite State

On as needed during AI&T

Off during Host launch, LV-separation and Orbit Raising

On prior to ejection for health monitoring, battery top-off, etc.

Off ~10 seconds before MicroSatellite ejection

No electric current flowing at IFD Interface at Separation/PODS Ejection

Data Interface (optional):

MIL-STD-1553 preferred; low volume for sporadic health data only

Other options available

14 28 May 2014

Thermal Environment

The thermal environment that the MicroSatellite will see while hosted depends on the hosting location

-35°C to + 60°C is a range that will envelope most cases

The MicroSatellite should be designed to survive this temperature range during launch and orbit-raising

Power is provided for heaters if necessary

Aero-thermal heating during launch must also be considered

Temperatures can be as high as 145°C per launch vehicle’s thermal analysis, however duration is short.

15 28 May 2014

Dynamic Environment

The MicroSatellite will need to be tested to meet the dynamic environment typical of commercial satellite launch vehicles:

Design Load: 13g in each of three axes

Frequency: Minimum 50 Hz lateral and axial in the S/C coordinate system

Sine Vibration: Sweep rate: 4 octave/min, all three axes: • 5 to 20.2 Hz: 0.25 inches

• 20.2 to 50 Hz: 13 g

• 50 to 100 Hz: 5.2 g

Random Vibration: Normal to mounting surface. Test duration: 60 seconds/axis: • 20 to 50 Hz: 6.0 dB/oct

• 50 to 600 Hz: 0.2g2/Hz

• 600 to 2000 Hz: -4.5 dB/oct

• Overall: 14.4 g-rms

Random Vibration: In-plane. Test duration: 60 seconds/axis: • TBS

Shock Level from Launch Vehicle via the Host S/C to the MicroSatellite: Frequency SRS Acceleration - Qualification, g (Q=10) (Hz) In Plane Out-of-Plane

200 52 100

850 - 600

4000 4200 4200

16 28 May 2014

RF Environment

RF environment generated by the Host spacecraft should be considered in MicroSatellite CONOPS and comm design

May govern when MicroSatellite comm can be turned on after release and separation

RF field strength vs distance estimates provided for release during pre-operational maneuvers

17 28 May 2014

Typical ComSat launch

is 24-30 months from

signing of ComSat

contract

Integration and Test (I&T) Flow

Initial Spacecraft

Level Test

(includes Power and Data

compatibility testing)

Pre-Thermal

Vacuum Interface

Validation

Thermal

Vacuum

Testing

Post-Thermal

Vacuum

Checks

Mechanical and

Electrical Operations

Packaging

& Shipment

Test

Operations

Final Launch

Operations

Combined

Operations

Communications

Panel Level

Spacecraft

Assembly

Propulsion/Bus

Subsystem (SSM)

Dynamics

Build

Dynamics

Testing & Mass

Properties

Post-Dynamics

Mechanical

Verification

Compact

Antenna

Test Range

Spacecraft

Testing

Antenna/

Tower

Solar Array

Solar Array

Batteries

Solar Array

INITIAL REFERENCE PERFORMANCE PHASE

THERMAL VACUUM PHASE

DYNAMICS PHASE FINAL PERFORMANCE PHASE

FINAL OPERATIONS PHASE LAUNCH SITE PHASE

PIM,

EMI/EMC

Test

MicroSatellite Final

Performance & Health

Dispenser Integral to Spacecraft

MicroSatellite Ground Segment Interface Testing

Launch

MicroSatellite Ground Segment

I/F Verific. Opportunity

Alternate (Recurring) Integration Path – requires a high-fidelity simulator for earlier spacecraft test flow

MicroSatellite

MicroSatellite Integration & Test

Required Integration Path for first-time implementation in a particular location

18 28 May 2014

Summary

The Payload Orbital Delivery System (PODS) enables cost-effective, high-tempo access to GTO or GEO for SmallSats

6-8 launch opportunities per year with SSL

Cost-effective access to GTO & GEO combined with recent advances in SmallSat technology enables many potential future missions

SSL welcomes input from Users:

In developing and co-proposing mission concepts that can take advantage of this unique platform

Working with SmallSat providers to address mission-specific needs