Attachment 05 Launch Service Capabilities Specs and Envs.docx

ATTACHMENT 05

LAUNCH SERVICES CAPABILITIES, SPECIFICATIONS AND ENVIRONMENTS

FOR

Venture-Class Acquisition of Dedicated and Rideshare (VADR) Launch Services

LAUNCH SERVICES CAPABILITIES, SPECIFICATIONS AND ENVIRONMENTS

This attachment represents the capabilities, specifications, and environments of the Contractor’s launch services, including all standard and non-standard commercial launch services with a clear delineation between each service. The contractor shall update the attachment annually, if applicable, or notify NASA if no changes have occurred. The purpose of this document is to understand the launch vehicle capabilities for spacecraft planning purposes; this information will not be shared publicly but will used for Government purposes.

If there are known and planned updates to each common launch vehicle configuration that would impact the values provided in this document, please describe these changes.

The document shall address, at a minimum:

Launch Vehicle(s)

a. Define in Table A5-1 the launch vehicle (LV) first stage, upper stage, payload adapter (PA), and payload fairing (PLF) configuration options available for each proposed common launch vehicle configuration. These configurations shall include all standard electrical systems, mechanical systems, propulsion systems, ordnance devices, and flight instrumentation. In addition, include any non-core propulsive stage(s) for the vehicle configuration that are part of each proposed launch service. Thrust and propellant mass shall be included for each stage.

Table A5-1: Vehicle Configurations (Example Only – Contractor to Specify Format and Data)

Common Launch Vehicle Configuration

LV First Stage

LV Upper Stage(s)

LV Payload Adapter(s)

LV Payload Fairing(s)

Non-Core Propulsive Stage(s)

b. For each vehicle configuration in table A5-1, provide a separate diagram showing the maximum payload static envelope and the associated dynamic envelope for a rigid payload hard mounted to the PA.

c. Provide a separate detailed drawing for each PA, which includes dimensions, mounting provisions, and interfaces.

d. Describe, in detail, the payload electrical interfaces for the proposed vehicle configuration(s).

e. Provide the maximum payload capability, where applicable, in Tables A5-2 through A5-5, from each launch site with associated ground rules for each vehicle configuration defined in Table A5-1. Table entries corresponding to orbits to which the Contractor is not offering may be left blank. Additional rows or columns may be added to applicable tables by the Contractor to show specific capabilities.

Performance shall be expressed in terms of separated payload mass (assuming standard PAs as outlined in paragraph a.) and shall assume a 3-sigma performance reserve for the following orbits:

Low Earth Orbits (LEO): Data shall be provided for circular orbit altitudes from 200 to 1000 km (in increments of 100 km) for inclinations of 0, 28.5, 38, 70, and 90 degrees

Sun-Synchronous Orbits: Data shall be provided for circular orbit altitudes from 200 to 1000 km.

High Energy Missions: Data shall be provided as a function of C3 from –10 km2/sec2 to 30 km2/sec2.

Elliptical Orbits: Data shall be provided as a function of apogee altitude and inclination using the launch vehicle’s standard ground rules.

Table A5-2: Maximum LEO Payload Capability for TBP Vehicle Configuration, Launch Site, and Ground Rules (Data TBP)

Inclination (deg)

Table A5-3: Maximum Sun-Synchronous Payload Capability for TBP Vehicle Configuration, Launch Site, and Ground Rules (Data TBP)

Vehicle Configuration

Table A5-4: High Energy Mission Payload Capability for TBP Vehicle Configuration, Launch Site, and Ground Rules (Data TBP)

Vehicle Configuration

-10

-5

Table A5-5: Maximum Elliptical Orbit Payload Capability with Optimized Perigee for TBP Vehicle Configuration, Launch Site, and Ground Rules (Data TBP)

Inclination (deg)

50,000

40,000

35,788

30,000

20,000

10,000

5,000

f. Provide standard insertion accuracies for each vehicle configuration defined in Table A5-1 for each of the maximum and minimum mission profiles defined in Tables A5-2 through A5-5. Table A5-6 lists example orbital parameters that should be considered.

Table A5-6: Standard Insertion Accuracy Requirements (Example Only – Contractor to Specify Format and Data)

Required 3-Sigma Insertion Error Limit Magnitude

Inclination

Argument of Periapsis

Right Ascension of Ascending Node

Apogee

Perigee

Right Ascension of Launch Asymptote

Declination of Launch Asymptote

C3

g. Provide the standard payload deployment capability in Table A5-7. Values provided reflect the generic capabilities of the launch vehicle (e.g. spin stabilization, three-axis stabilization, etc), and all assumptions made with respect to payload mass properties shall be stated. Errors are defined for each vehicle configuration and consist of all known dispersion sources (guidance, navigation, ACS limitations, etc.).

Table A5-7: Standard Payload Deployment Rates/Attitudes (TBP)

Spin-stabilization

Three-axis Stabilization

Lateral LV rate at separation

h. Provide the environments during ground processing, transport, and pad operations, including static loads, vibration, acoustics, thermal, electromagnetic interference (EMI)/ Electromagnetic Compatibility (EMC), and shock environments.

i. The Contractor shall provide data for the maximum payload EMI/ EMC, acoustic, vibration, shock, acceleration, and thermal environment levels during launch and ascent. The contractor shall provide these environments through payload separation.

The maximum electromagnetic radiated emissions levels encountered by the payload and susceptibility levels of the launch system shall be depicted in Figures A5-1 and A5-2, respectively.

The Contractor shall illustrate the pressure profiles and depressurization rates for each PLF in Figure A5-3. The maximum expected payload flight environments due to acoustics (spatially averaged within the PLF and 50% fill), random vibration (measured at the top of the LV payload adaptor), and shock (measured at the top of the LV payload adaptor) shall be shown in Tables A5-8, A5-9, and A5-10, respectively, and defined at a P95/50 statistical level.

The maximum expected total acceleration (limit load factors), including uncertainty factors, shall be shown in Table A5-11 (key dynamic events may be broken out as appropriate). The maximum expected sinusoidal vibrations at the base of the PA shall be shown in Table A5-12. The maximum quasi-steady acceleration as a function of payload separated mass shall be shown in Figure A5-4.

The Contractor shall provide the maximum thermal environment during ascent for every launch component (e.g. upper stage, unblanketed skin, thermal/acoustic blankets, etc.) inside the fairing with a view factor to the payload in Figure A5-5.

Where the expected payload environments exceed the range of environments described in the NASA Goddard General Environmental Verification Standard (GEVS), GSFC-STD-7000 Rev A guidelines and/or the Space and Missile Systems Center Standard: Test Requirements for Launch, Upper-Stage and Space Vehicles (SMC-S-016), the Contractor shall identify mitigation options. Some missions may require specific limits to launch environments.

Figure TBP

Figure A5-1: Maximum Electromagnetic Radiated Emissions Levels Encountered by the Payload

Figure TBP

Figure A5-2: Maximum Electromagnetic Radiated Susceptibility Levels of the Launch System

Figure TBP

Figure A5-3: PLF Pressure Profiles and Depressurization Rates

Table A5-8: Maximum Flight-Level Payload Acoustic Environment

Table TBP

Table A5-9: Maximum Flight-Level Payload Interface Random Vibration Environment (If Applicable)

Table TBP

Table A5-10: Maximum Flight-Level Payload Interface Shock Response Spectrum

Table TBP

Table A5-11: Payload Design CG Limit Load Factors

Notes: (1) Sign convention: positive axial acceleration produces compression

(2) Axial and lateral accelerations are simultaneous

Table A5-12: Maximum Expected Sinusoidal Vibrations at the Base of the PA (If Applicable)

Table TBP

Figure TBP

Figure A5-4: Maximum Quasi-Steady Acceleration as a Function of Payload Separated Mass

Figure TBP

Figure A5-5: Maximum Thermal Environment During Ascent

Rideshare Payload Adapter System(s)

Describe the commercial rideshare payload adapter and separation system(s), including physical and electrical characteristics provided by the Offeror for each proposed vehicle configuration. Include a graphical description for separating and non-separating payloads and state associated ground rules that apply to the rideshare payload accommodations, including any CubeSat dispenser offerings.

Launch Site Integration

a. Describe the physical attributes, the capabilities, and the limitations (e.g. fueling, transportation, airlock, lifting, office space, GSE accommodation) of any payload processing facilities (PPF) to be available for any launch service being proposed including PPF occupancy duration(s). Specify the contamination environments achievable in the PPF and within the payload fairing. In addition, specify the temperature and humidity environments to which the PPF and PLF can be controlled (TBP to TBP°C (TBP to TBP°F) and TBP% to TBP%, respectively).

b. Describe the services, equipment, support, and limitations provided at the launch site(s) for the integration and launch of each payload.

Additional Information

Describe any unique capabilities of the proposed launch service. This should include anything that the Contractor wishes to emphasize as unique to their launch service.