A2_TRD_4Nov14.pdf

ATTACHMENT 2

TO

FA8818-15-R-0003

Operationally Responsive Space - 5 (ORS-5)

LAUNCH SERVICE

TECHNICAL REQUIREMENTS DOCUMENT

(TRD)

4 November 2014

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ACRONYM LIST

AFI Air Force Instruction C/CAM Collision/Contamination Avoidance Maneuver GSE Ground Support Equipment EMI Electromagnetic Interference ICD Interface Control Document LV Launch Vehicle LSC Launch Service Contractor MPE Maximum Predicted Environment OASPL Overall Sound Pressure Level ORS Operationally Responsive Space RF Radio Frequency SV Space Vehicle TRD Technical Requirements Document

TABLE OF CONTENTS

ACRONYM LIST

1.0 SCOPE

2.0 REQUIREMENTS

2.1 System Description

2.1.1 Launch Vehicle

2.1.2 Ground Segment

2.2 Characteristics

2.2.1 Performance

2.2.2 Payload Accommodation Requirements

2.2.3 Telemetry and Instrumentation

2.2.4 EMI/EMC

3.0 ORS-5 Range Requirements

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1.0 SCOPE

a. The Government’s objective is to commercially procure a single launch service to place the ORS-5 space vehicle (SV) into the required orbit.

b. The Launch Service Contractor (LSC) is encouraged to propose an innovative and cost effective launch service which meets the requirements of this TRD.

c. This document defines top level system performance requirements for the launch service required to place the ORS-5 space vehicle into the specified orbit. Detailed interface requirements will be defined in the LV/SV Interface Control Document (ICD).

2.0 REQUIREMENTS

2.1 System Description

a. The ORS-5 launch service requirements apply to both the LV and associated Ground Segment.

2.1.1 Launch Vehicle

a. The LSC shall provide hardware and software to accomplish all mission functions.

2.1.2 Ground Segment

a. The ground segment consists of:

1. Support Equipment consisting of all equipment required to process, integrate, handle, check-out, and launch the LV.

2. Launch Facilities

3. Contractor provided launch vehicle contamination control system for sites without environmental control.

b. The baseline launch location shall be defined by the LSC.

2.2 Characteristics

2.2.1 Performance

2.2.1.1 Throw-Weight to Orbit

a. The system shall be capable of placing 120 kg SV into the required orbit. The SV separation system is included in this mass requirement.

b. Sufficient performance margins shall be included to provide a 0.997 (3-Sigma) probability of achieving the required orbit accuracy when all potential sources of dispersions are accounted.

2.2.1.2 Orbit

a. The launch vehicle shall place the ORS-5 SV in an orbit inclined at 2º with a maximum error of +/-0.2º

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b. The launch vehicle shall place the ORS-5 SV into an orbit with an apogee and perigee between 600 km and 700 km.

2.2.1.3 Insertion Accuracy (3-Sigma)

Reserved

2.2.1.4 Attitude Control (3-Sigma)

The LV shall control its attitude at the time of SV deployment to ±1º of the desired attitude with drift rates ≤ 1 º/sec about each axis

2.2.1.5 Collision/Contamination Avoidance Maneuver

The LV shall perform C/CAM as necessary to minimize SV contamination and preclude re-contact between the ORS-5 SV and the launch vehicle.

2.2.1.6 Orbital Debris

The LV and associated components shall re-enter the earth’s atmosphere within 25 years after end of mission or enter an acceptable disposal orbit, as specified in AFI 91-217 Space Safety and Mishap Prevention Program.

2.2.2 Payload Accommodation Requirements

2.2.2.1 Mechanical

2.2.2.1.1 Dynamic Envelope

The LV shall accommodate the ORS-5 space vehicle size as defined in Figure 1.

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Figure 1 Required SV Dynamic Envelope

2.2.2.1.2 Access

a. The LV shall provide 1 access door in the fairing to provide access to the ORS-5 SV after fairing encapsulation without removing the fairing or breaking electrical connections.

b. The opening shall be a minimum of 8.5” x 13” in size.

2.2.2.1.3 Interface

a. The LV shall provide a non-separating structural interface on which to mount the ORS-5.

b. The LV shall provide a 15 inch diameter bolted interface ring bolt-circle. The bolt pattern consists of 24 - 1/4” x 28 holes that are spaced every 15 degrees.

c. The flatness of the mating plane shall be less than 0.004”.

2.2.2.1.4 Mass Properties

The SV center of gravity shall be less than 35 inches from the 15” bolted interface plane and less than 1.5” from the SV centerline.

2.2.2.2 Electrical

2.2.2.2.1 Command, Control, and Monitor

a. The LV shall provide a separating umbilical connector(s) with a minimum of 60 pins total to the SV until launch.

b. The circuits shall be 20 AWG twisted shielded pairs unless otherwise specified.

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c. The ground umbilical circuits shall include at least six pairs of twisted shielded cable that is suitable for RS-422 serial communications. In addition the umbilical shall provide the capability to remotely control and monitor the SV and charge batteries using GSE furnished by the SV contractor. Circuits will be defined in the LV/SV ICD.

2.2.2.2.2 SV Separation Signals

The LV shall provide primary and redundant separation signals to actuate the ORS-5 provided Motorized Lightband Mark II separation system. The LV shall detect a positive indication of SV separation through a minimum of two loopbacks.

2.2.2.3 Environments

2.2.2.3.1 Quasi-Static Loads

The launch vehicle shall impart acceleration load factors less than 8.5 g’s in the launch vehicle axial direction and 8.5 g’s in the launch vehicle lateral direction. These loads can be applied simultaneously and at the ORS-5 center of mass.

2.2.2.3.2 Random Vibration

The LV maximum predicted random vibration environment as applied at the non-separating 15” interface shall not exceed the levels specified in Table 1.

Frequency (Hz) PSD (g2/Hz) 20 0.005 50 0.012 800 0.012 2000 0.005 Overall (grms) 4.27 Table 1 LV Random Vibration Limitations

2.2.2.3.3 Shock

The launch vehicle shock environment as applied at the 15” bolted interface, shall not exceed the values in Table 2

Frequency (Hz) Shock (g’s) 51 51 1850 1000 10,000 1000 Table 2 Shock Limitations

2.2.2.3.4 Acoustics

The launch vehicle shall ensure the acoustic levels inside the fairing do not exceed the levels shown in Table 3.

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Frequency (Hz) MPE (dB)

31.5 128 63 131 125 135.2 250 133.6 500 130.3 1000 126.0 2000 120.0 4000 116.0

OASPL 139.6

Table 3 Acoustic Environment

2.2.2.3.5 Thermal

a. Thermal environment and relative humidity control shall be provided to the SV during ground processing and up to launch.

b. During ground processing prior to launch, the fairing temperature shall be maintained within 65 to 85 ºF; neglecting internal heating sources from the SV.

c. Relative humidity shall be controlled to ensure that condensation does not form on any LV or internal fairing surface.

d. The LV shall provide aero-thermal protection to the SV prior to launch and during ascent.

e. Conductive insulation shall be grounded and interconnected to prevent electrical discharge.

f. The internal wall temperature of the fairing shall be limited to 200 ºF in the cylindrical portion during ascent.

g. The fairing shall be retained until aero-heating rates are below 0.1 BTU/sq-ft/sec.

2.2.2.3.6 Contamination

a. The LSC shall maintain the SV in a Class 10,000 environment at all times with no condensation forming on payload surfaces, as defined in ISO Standard 14644.

b. Inner surfaces of the fairing and payload deck shall be cleaned so that they are Visibly Clean, Level II, as defined in ISO Standard 14644.

c. After payload encapsulation, all air supplied to the fairing volume shall be Class 10,000.

Relative humidity shall be maintained between 35 to 60 %.

d. The LSC shall provide a continuous clean dry nitrogen purge to a point on the ORS-5 SV from mating to the launch vehicle through liftoff. The GN2 shall be 99.999% pure, with <3 ppm water content and <0.5 ppm total hydrocarbon content. Required flow rate and location on the SV will be defined in the LV/SV ICD.

2.2.2.3.7 Plume Effects

The LV shall minimize plume effects from all propulsion sources in terms of forces and moments applied to the SV after deployment and contamination prior to and after deployment.

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2.2.3 Telemetry and Instrumentation

The LSC shall collect and transmit (RF) sufficient data during prelaunch and in-flight to assess LV and SV status, performance, environments, meet all Range Safety requirements and to provide diagnostics in the event of anomalous performance.

2.2.4 EMI/EMC

2.2.4.1 Emissions

The Launch System shall minimize radiated and conducted emissions that could affect the ORS- 5 space vehicle. Specific levels shall be documented in the LV/SV ICD.

2.2.4.2 Susceptibility

a. The LV shall be capable of operating at the identified launch site without adverse effects from the electromagnetic environments.

b. The LV shall be capable of withstanding EMI radiated and conducted emissions from the ORS-5 space vehicle. Specific limitations shall be documented in the LV/SV ICD.

3.0 ORS-5 RANGE REQUIREMENTS

The LSC shall provide the following accommodations for the ORS-5 SV at the integration and launch site for 20 days prior to mating operations to the launch vehicle.

a. Class 10,000 clean room, minimum 25 ft x 25 ft with power as specified in the LV/SV ICD and a crane capable of lifting the SV.

b. Additional non-flight hardware room 20 ft by 20 ft.

c. Office accommodations for 4 MIT Lincoln Lab personnel and 3 government program office personnel.

d. A minimum of 1000sq ft of storage space, with protection from the elements, for shipping containers and other non-flight hardware

e. Use of a forklift to off-load the space vehicle and GSE from the transport plane.

f. Console positions for a total of 10 government and contractor personal during launch operations. At least 3 of these positions shall be in the Launch Operations Center.

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3.0 ORS-5 Range Requirements