NASA/CP--1999-209482

Proceedings of the First Annual

NRO-OSL/GSFC-ATS Rideshare Conference

William Cutlip, Ed.

National Aeronautics and

Space Administration

Goddard Space Flight Center

Greenbelt, Maryland 20771

October 1999

https://ntrs.nasa.gov/search.jsp?R=20010084928 2018-05-15T10:41:35+00:00Z
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Proceedings of the

i st Annual

NRO-OSL/GSFC-ATS

Rideshare Conference

April 15-16, 1999
FIRST ANNUAL

GODDARD SPACE FLIGHT CENTER - ACCESS TO SPACE GROUP

NATIONAL RECONNAISSANCE OFFICE - OFFICE OF SPACE LAUNCH

RIDESHARE CONFERENCE

Mr. William Cutlip and Mr. Jim Liller

Co-Chairmen

LI-I-I-ON/TASC FACILITY

DULLES, VIRGINIA

April 15-I 6, 1999
FIRST ANNUAL GSFC-ATS/NRO-OSL

RIDESHARE CONFERENCE

15 Apr 99

8:00

8:10

8:20

8:30

8:35

8:50

9:05

9:25

10:10

10:20

10:40

11:00

11:20

12:30

12:50

1:00

1:20

1:40

2:00

2:10

2:20

2:35

2:55

3:15

3:30

3:45

4:05

Security

Opening Remarks

Administrative

Agenda

RideShare Catalog

Access To Space Program

Rapid S/C Development Office {QuickRide)

Spartan Project Office

Break

Shuttle Small Payloads Project

MightSat Program

Spectrum Astro Buses

Lunch

Integrated Space Systems Buses

Athena

Orbital Buses

Ball Aerospace Buses

Lockheed Martin Buses

Break

Orbiting Tech Testbed Initiative

Swales Bus

TRW Buses

FAISA_ M

GEO Bus

Stanford MicroSat

Space Transportation Program

United Space Alliance

Chip Harbaugh/TASC

Lt Col Arey/NRO/OSL/APD

Jim Liller/NRO

Jim Liller/NRO

Jim Liller/NRO

Bill Cutlip/GSFCIATS

Jim Adams/GSFC

Dave Shrewsberry/GSFC

Chris Dunker/GSFC

Pete Thomas/AFRL

Scott Yeakel/Spectrum Astro

Phil Smith/ISS

Trip Carter/LMA

Regan Howard/Orbital

Terry Schrepel/Ball Aerospace

Ed McNamara/LMMS

Jim Ritter/NRL

Mike Cully/Swales

Donald Marshall/TRW

Jason O'Neil/Final Analysis

Paul Regeon/ONR

Bob Twiggs/Stanford University

Dennis Smith/MSFC

Therese Thrift/USA

16Apr

8:00

8:05

8:20

8:40

8:55

9:15

10:00

10:15

10:30

11:15

11:30

12:30

1:00

1:15

1:30

1:50

2:10

2:30

Agenda

Universities Space Research Assoc

SpaceHab

Na noSat Deployment Concepts

SERB/STP

EELV Secondary P/L Adapter

Break

PuckSat

Space Maneuver Vehicle

Coleman Aerospace Vehicle Systems

Lunch

Orbital Sub-Orbital Program

Sat Threat Warning/Attack Rpt Prog

NASA ELV Program/Policy

Pegasus/Taurus

Boeing Delta II & EELV

Lockheed Martin EELV

Secondary Payload Broker Discussion

Jim Liller/NRO

Jack Sevier/USRA

Truss Bardos/SpaceHab

Steve Huybrechts/AFRL

Maj Ward/AQSL

Capt. Scott Haskett/SMC-TELO

Joe Young/Swales

Lt Col Verderame/AFRL

Frank Krens/Coteman Aerospace

Maj BuckleylSMC-TEB

Lt. Col HilIand/AFRL

Albert Sierra/NASA HQ

Ed MorrislOrbital

Bill Files/Boeing

Mike RagolelLockheed Martin

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V V V
EELV Secondary Payload

Adapter (ESPA)

Capt Scott A, Haskett.

USAF Space Test Program

SMC/TELO

(sos)846-8s70

Overview

• ESPA Motivation

-Small Satellite (SmallSat) Uses

- US SmallSat Launch Capabilities

• ESPA Program

- Characteristics and Capabilities

- Current Activities/Far-Term Plan

- ESPA Customers

• Conclusion
Small Satellites (<200 kg)

• Space Experiments

- Inexpensive Way to Demonstrate New

Space Technology

-Perform Space Experiments

-Test Operational Prototype Hardware

• AFSPC Researching Operational

Missions for Smallsats

-Space-Based Radar, Space Support

US SmallSat Launch Capabilities

I

• US Medium/Heavy ELVs Have No Buittin Secondary Payload Capabilities

- Secondary launches are "custom" missions

• Cheapest US Booster: OSP

-Orbital/Suborbital Program (OSP) uses

Minuteman II, Pegasus XL stages

- Dual-Satellite launch on OSP costs N$14M

• Least Expensive SmallSat Launch Today

Costs $7M
EELV

[] EELV Launchers Are Very Capable

- At least 58% of manifested DoD EELV

Medium Missions have >20001bs margin

[] EELV Has No Requirement for

Secondary Payloads

[] ESPA Uses EELV Margin to Launch up to

Six SmallSats in Addition to the Primary

Payload

ESPA Characteristics

[] Cylindrical Structure, 24" tall

[] Est. Empty Mass: 114 kg (250 Ibs)

[] Holds Six SmalISats + Primary Payload

-SmalISats: 30-inch cube, up to 220 Ibs

-ESPA projected maximum: 910 kg (2000

Ibs) "fully loaded"

[] Design Allows Secondary Separation

Before Primary Separation (if needed)
|

|

f

Primary

spacecraft

Large secondary

Standard

0 62.01"

interface

_ Secondary spacecraft support structure

Secondary spacecraft interface plate

4
ESPA Impacts to Primary

[] Negative:

-Raises Primary Payload 24"

[] Reduces Usable Volume in Fairing

[] Raises CG

- Effects can be Minimized by Optimizing

Primary Payload Adapter

• Neutral:

-Design Replicates EELV Standard Interface

Plane to Primary

5
ESPA Impacts (continued)

III

• Neutral (continued):

- Minimum Interaction between Primary and

Secondaries

-Shockless/Non-Pyro Separation Systems

for Secondaries

m Positive:

- Greater Payload Mass Reduces Vibration of

Payload Stack

"_Vibration Isolation (Soft Ride) _:

Vibration Isolation

I

• Reduces Dynamic Response of

Secondary Equipment by at Least a

Factor of 2

-Secondaries have separate isolation

systems also

• Proven Technology

-Taurus: GFO (N60% isolation)

-Taurus: STEX (N85% isolation)

-OSP Flight 1 (Scheduled September 99)

6

m
Isolation on

ii IIIII

GFO

ESPA Program Details

II III

• Joint STP-AFRL/VSD Program

-Estimated Non-Recurring Cost: $4.41Vl

• ESPA Special Study Initiated by EELV

SPO April 99

• AFRL Will Build One Qualification Model,

One Flight Model

- PDR June 99, CDR June 00

• IOC FY02; Hoping for Launch in FY 03

- DMSP, GPS, SBR
ESPA Flight I

[] STP Budgeting for First Flight

Integration Costs

- Cost-sharing anticipated for any non-STP

payloads

• Mission Guidelines

- Secondary Manifest Managed by STP

- Secondaries delivered on time or don't fly

-Primary Drives Umbilical Connections

- Secondaries "Dead" Until Release

Far-Term ESPA Plan

I I

• STP Researching Cooperative

Agreement with EELV Prime Contractors

- Primes procure ESPA, making it optional on

any DoD EELV Medium mission

- ESPAavailable to commercial market

• Secondary Manifest Managed by

Primary ESPA Customer (e.g. NASA,

STP) or Third Party (e.g. USRA)
Estimated Recurring Costs

I II

• ESPA Cost: $700,000 to $900,000

- $600,000 for ESPA cylinder & primary

isolation system

- $50,000 per secondary isolation system

[] Estimated Integration Costs: $1.0M

[] ESPA Goal: Keep Cost per Satellite

(fully-loaded ESPA) Less Than $500K

[] Potential Customers Excited by LowCost Launch Prospects

I I

ESPA Customers

I III

• "Road Show" Briefing Given to Potential

ESPA Customers

• AFSPC/NASA/NRO Partnership Council

-General Myers, Mr. Goldin, Mr. Hall

ISMC

- EELV SPO/Boeing/Lockheed-Martin

- Action-Officers atGPS, DMSP, DSCS

- PresentationsPIanneclforPMs

• HQ AFSPC DR/DOY/XPX
ESPA Customers (cont.)

• Naval Research Lab

• NASA

- Goddard SFC

- Jet Propulsion Laboratory

-Assistant Administrators, KSC (scheduled)

• Industry/Academia

- University Space Research Association

- Bali Aerospace

- A::[AAConferences (scheduled)

Conclusion

Illll

• Small Satellites are Useful, But US Lacks

SmaliSat Launch Infrastructure

- Hard to fulfill STP mission

- Potential impact to future AFSPC missions

• ESPA Carries Up to Six SmalISats and

Offers "Soft Ride" to Primary and

Secondary Payloads

• Launch Cost Per Satellite Drops from

$7M-$10M to $320k to $850k

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_0'98£066
Shared Payload Launch Opportunities

To date, Orbital has successfully placed 52 payloads into

orbit on 13 Pegasus and Taurus shared launches.

Presently, Orbital has launch opportunities available on

our launch systems. These launches have capacity

available for co-passenger payloads matching the orbit,

schedule, mass, and volume parameters, shown in the

TableA below. Payloads that can accept these mission

parameters shou Id contact Orbital to verify technical

compatibility and obtain a launch agreement. In

addition, Orbital maintains a listing of known missions

that are searching for complementary payloads to share a

launch. These missions are listed in Table B.

If any of these payload parameters match your specific

needs, you are invited to contact OrbitaPs Launch

Systems Group business development to further assess

mission compatibility and a possible launch assignment

on Pegasus or Taurus.

° Check our Orbital launch opportunities on our

web site (www.Orbital.com)

• Look for compatible ride share partners

• Register your mission to be considered

Mission Orbit Launch Mass Available

Date Volume Available

Pegasus 0-5"

LV-P010 550-700 km

Taurus Sun-Synchronous

LV-T01 [ 470 km

10:50 a,m,

Pegasus 0-10 °

LV-P012 550-650 krn

Circular

OSP

LV-013

Pegasus

LV-P014

Pegasus

LV-015

Sun-Synchronous

12:00 p,m. +_2hrs

or 50-95 °,

500-600 km

45° Inclination

825 km

45° Inclinalion

825 km

Early !.20-75 kg

2OO0

Mid • 300 kg

2000 o110cmDiax153cm

Hei,qht

2001 .100 kg Estimate

Early ,150kg+

2000 • 66 crn dia x TBD Length

Mid • 140 kg

2000 o Cone, 100 cra at Base, 75 cm

at Top

o 95 cm Height (23" Interface

Assumed)

Late .140 kg

2000 ,, Cone, 100 cm al Base, 75 cm

at Top

• 95 cm Height (23" Interface

Assumed)

Primary Payload

- Separation System

Available,

_/'/_Primary/ Seconda_

V//,payload/ i Payload,

_//-z__ _._i_,:Envelopei

i

_L 7

I

7

Pegasus Shared Launch Configuration

(Drawings Not

to Scale)

_"_ Primary _/

/ _" Payload

///_ Primary

/ - Payload

/

,,%

?

Separation

System

Taurus Shared Launch Configuration

m

Mission

P-107

P-108

lnc|ination Altitude Launch "l'aunch Mass &

Nodal Crossing Date Volume Available

Sun-Synchronous Mid 2000 • 100 Kg

550-650 km ° 111,7 cm dia, x

6 a.m, ± 2 hrs .. 55.6 cm heiflht

Sun-Synchronous 2002 ° 110 - 275 Kg

613 km Circular o 109,2 cm dia. x

177.8 cm height

For further information contact the New Business office at (703) 404-7400

@1999 Orbital Sciences Corporation

www.orbita l.com
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I Form Approved

REPORT DOCUMENTATION PAGE OMB No. 0704-0188

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1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED

October 1999 Conference Publication

4. TITLE AND SUBTITLE 5. FUNDING NUMBERS

Proceedings of the First Annual NRO-OSL/GSFC-ATS Rideshare

Conference--April 15-16, 1999 740.2

6. AUTHOR(S)

W. Cutlip, Ed.

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS (ES)

Mission Integration and Planning Division

Project Formulation Office

Goddard Space Flight Center

Greenbelt, Maryland 20771

9. SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS (ES)

National Aeronautics and Space Administration

Washington, DC 20546-0001

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99A01867

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CP--1999-209482

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13. ABSTRACT (Maximum 200 words)

This document contains the proceedings of the First Annual NRO-OSL/GSFC-ATS Rideshare Conference. The conference was held April 15-16, 1999, at the Litton/TASC Facility, Dulles, Virginia. and

was co-chaired by William Cutlip, Goddard Space Flight Center Access to Space Group, and Jim

Liller, National Reconnaissance Office, Office of Space Launch.

14. SUBJECT TERMS

Rideshare; space transportation; buses; Get Away Special (GAS), launch

vehicle.

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550

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