A2_-_ORS-5_TRD_V1.pdf

ATTACHMENT 2

To

FA8818-15-R-0003

Operationally Responsive Space - 5 (ORS-5)

LAUNCH SERVICE

TECHNICAL REQUIREMENTS DOCUMENT

(TRD)

24 April 2015

ORS-5 TRD – 3 March 2015 Page 1 of 9

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 Service

2.1.2 Ground Segment

2.2 Characteristics

2.2.1 Performance

2.2.2 Payload Accommodation Requirements

2.2.3 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 space vehicle consists of the spacecraft bus, the sensor, a Mark II Motorized Lightband and a MOOG Softride system. All the space vehicle components are accounted for in the mass and volume allocations specified below.

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 LS/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 Service

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 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 160 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 service shall place the ORS-5 SV in an orbit inclined at -1.0º to +1.0° with a preferred inclination of 0°.

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b. The launch service shall place the ORS-5 SV into an orbit at an altitude between 520 km – 670 km.

c. The LSC shall work with the ORS Office to optimize the orbit within the required inclination and altitude ranges to maximum ground communication contact time while meeting the requirements for SV de-orbit lifetime.

2.2.1.3 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 ≤ 1.5 º/sec about each axis

2.2.1.4 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.

2.2.1.5 Orbital Debris

The LV upper stage and associated components shall be designed to minimize debris released during normal operations; shall minimize debris generated by accidental explosion by demonstrating by analysis that there is no credible failure mode for accidental explosions and by depleting or safing all sources of stored energy; estimate and limit the probability of collision with known objects during orbital lifetime; and re-enter the earth’s atmosphere within 25 years after end of mission with a Casualty Expectation (Ec) of less than 1x10-4 or plan for a controlled reentry or enter an acceptable disposal orbit. These requirements are as specified in USG Orbital Debris Mitigation Standard Practices (USGODMSP).

2.2.2 Payload Accommodation Requirements

2.2.2.1 Mechanical

2.2.2.1.1 Dynamic Envelope

The LS shall accommodate the ORS-5 space vehicle size as defined in Figure 1.The SV +X axis is shown for reference.

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Figure 1 Required SV Dynamic Envelope

2.2.2.1.2 Access

a. The LS shall provide 1 access door in the fairing to provide access to the ORS-5 SV from fairing encapsulation until L-12 hrs without removing the fairing or breaking electrical connections. Details of the location of the door will be negotiated and documented in the SV-

LS ICD.

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

2.2.2.1.3 Interface

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

b. The LS shall provide a 15 inch diameter bolted interface ring bolt-circle. The bolt pattern consists of 24 holes that are spaced every 15 degrees. Details of the interface will be documented in the SV-LS ICD.

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

2.2.2.1.4 Mass Properties

The Launch Service shall be capable of accommodating a SV center of gravity that is less than 35 inches from the 15” bolted interface plane and less than 1.5” from the bolted interface plane centerline.

+Xsv

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2.2.2.2 Electrical

2.2.2.2.1 Command, Control, and Monitor

a. The LS 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.

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, until launch. Circuits will be defined in the SV-LS ICD.

2.2.2.2.2 SV Separation Signals

The LS shall provide primary and redundant separation signals to actuate the ORS-5 provided Motorized Lightband Mark II separation system. The LS 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 axial acceleration load factors less than 10 g’s in the space vehicle compression, and less than 5g’s in the SV –X direction. The launch vehicle shall impart lateral acceleration load factors of less than 8.5g’s. Additionally, combined loads, root sum square (RSS), at the SV center of gravity shall not exceed 11 g’s.

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 1000 0.012 2000 0.005 Overall (grms) 4.39 Table 1 LV Random Vibration Limitations

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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 51 900 1750 10,000 1750 Table 2 Shock Response Spectrum Limitations (Q=10)

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.

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°F 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 as defined in ISO Standard 14644.

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.

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2.2.2.3.6 Contamination

a. The LSC shall maintain the SV in a Class 10,000 environment at all times, except for short (15-30 min) periods during mating and encapsulation operations. The LSC shall support the ability for the SVC to bag and purge the spacecraft during excursions from class 10,000 environments.

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 LS/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.

2.2.3 EMI/EMC

2.2.3.1 Emissions

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

2.2.3.2 Susceptibility

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

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

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

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

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

d. Office accommodations for 4 MIT Lincoln Lab personnel and 3 government program office personnel with desks, chairs and internet access.

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e. Use of a forklift capable of off-loading the space vehicle and GSE from the transport vehicle.

f. Console positions for a total of 10 government and contractor personnel during launch operations. At least 3 of these positions shall be in the Launch Operations Center. Two of the positions will require connectivity to SV Battery Charging and monitoring EGSE (provided by the SV contractor).

g. A location at the termination of the LV Umbilical to support 2 racks of SV EGSE for Battery Charging and Monitoring equipment.

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3.0 ORS-5 Range Requirements