08.05.2022_RFI 1_Appendix 1_Rev. 0.docx

Appendix 1

Appendix 1 Draft System Performance Specifications (SPS) In the below table Key Performance Parameters (KPP) and Key System Attributes (KSA) have been identified as follows:

· KPPs are considered essential for successful mission accomplishment and are mandatory requirements. KPPs are indicated with bold text.

· KSAs are attributes considered critical or essential for an effective capability but were not selected as KPPs. KSAs provide the Coast Guard with an additional level of capability prioritization below the KPP. A KSA does not have to be related to a KPP and there is no implication that multiple KSAs equal a KPP. KSAs are indicated with italicized text.

Unless otherwise noted herein, the threshold requirements in this SPS are mandatory. The objective requirements in this SPS are desired capabilities.

Performance characteristics not listed in the SPS (e.g., sense and avoid, surface search, etc.) may be noted by including the capability in the vendor’s written response.

Unmanned Aircraft (UA) Performance Specifications The UA with full fuel and payload shall be capable of takeoff, operation, and recovery while operating in the environmental conditions described below.

Service Ceiling[footnoteRef:2] [2: Service ceiling is the altitude at which the AV’s vertical rate of climb performance is equal to 100 feet/minute.]

Same as Threshold

The UA shall be capable of launch and recovery from the host cutter flight deck [KPP]. The nominal dimensions for the host cutter flight deck is 48 feet wide by 80 feet long (reference drawing in Appendix 2). Ship-motion parameters for launch and recovery are based on Sea State 4 (4.1-8.2’ seas, Bretschneider scale) with calculated parameters given below.

Ship Motion Parameter[footnoteRef:4] [4: The ship-motion parameter is relative to the center of the flight-deck where applicable.]

The UA shall also have the following capabilities.

The UA shall have an alternate means of controlling the UA to return to the host cutter for recovery when the primary link for UA control becomes unavailable or degraded to the point of no longer controlling the UA.

The UA shall have a pilot-actuated flight termination mode.

The UA shall have a pre-flight programmable flight termination routine that will be executed if UA flight control cannot be regained. The pre-flight programmable flight termination routine shall include (1) parameters to initiate the routine and (2) the flight termination routine to subsequently implement.

The UA shall provide a non-visible, near-IR marker or FDA approved illuminator.

The UA shall have a real time EO moving video sensor to provide uninterrupted video imaging, capable of continuously capturing maritime surface targets around the UA from no less than the horizon to directly below the UA.

The UA shall have a real time IR moving video sensor to provide uninterrupted video imaging, capable of continuously capturing maritime surface targets 360 degrees around the UA from no less than the horizon to directly below the UA.

The UA shall be capable of accepting modular payloads. Modular payloads are defined as payloads that can be replaced or interchanged with the previously-installed EO or IR payload(s) within one to two hours (elapsed time). Modular payloads may be government provided.

At an operating altitude of 3,000 feet directly overhead of the target of interest (no slant range), the UA shall incorporate low-visibility, counter-shaded paint scheme consisting of FED-STD-595C FS 36320 (or similar) matte gray upper surfaces and FED-STD-595C FS 36375 (or similar) matte gray lower surfaces. Markings shall be painted in the respective contrasting gray as depicted in MIL-STD-2161 (series).

System Footprint/Mobility and Transportation Requirements Physical space for the UAS system and ancillary support equipment is extremely limited. The flight deck of the host cutter is available for launch and recovery of the UA; however, the flight deck must be able to be cleared and made available for helicopter operations with a 15-minute notification.

The UAS System cutter-based antenna system shall be within the space, weight, and power allocated within the UAS A-Kit infrastructure aboard the host cutter (see Appendix 2).

The UAS GCS shall not exceed the space, weight, and power reservations allocated within the UAS A-Kit infrastructure aboard the host cutter's combat information center (see Appendix 2).

The GCS (including required rack-mounted components) shall be designed to allow for upgrade and integration of future capabilities.

The UAS(s), launch/recovery system, maintenance/support equipment, and spares shall be stored, secured, and maintained in the hangar space designated for UAS.

The UA, UAS support kit, and launch/recovery system(s) shall be capable of being loaded onto the cutter while pier side.

LRE shall not interfere with flight-operations per the USCG Air Operations (AIROPS) Manual COMDINST M3710.1 (series). LRE shall be maintained and operated by Contractor embarked resources, including optional use of the Contractor provided equipment.

All flight-deck operated launch and recovery equipment shall be capable of traverse and setup within 30 minutes in sea conditions of up to and including +/- 3 degrees pitch / +/- 5 degrees roll.

All flight-deck operated launch and recovery equipment shall be capable of clearing the flight deck within fifteen minutes in conditions up to and including +/- 3 degrees pitch / +/- 5 degrees roll.

The UA shall launch and recover while a static MH-65 is spotted with blades unfolded on the flight deck. [KSA]

Ground Control Station (GCS) Requirements

Positive Control[footnoteRef:5] [KSA] [5: A UAS with an autopilot or programmable mode capability can be considered under control with such mode engaged provided the responsible and qualified operator maintains continuous situational awareness, and can alter the UAV’s airspeed, altitude and heading by their specific actions.]

The GCS shall provide for a qualified operator to be in positive control of the UA, at any time that intent-for-flight exists.[footnoteRef:6] [6: Intent-for-flight shall be as defined in the respective UAS’ operating manual / Standard Operating Procedures (SOP).]

The UAS flight parameters (altitude, direction, airspeed, navigation route) shall be controllable during flight.

The GCS shall provide the ability to maintain simultaneous positive control of both the UA and the UA’s payloads (sensors, voice communications, and transponder).

The UA shall be capable of accurately adapting to dynamic, in-flight re-tasking instructions.

The GCS shall provide the ability to create, store, select, and modify routes and waypoints.

The GCS shall have the capability of directing in-flight re-tasking and controlling payload sensors.

The GCS shall operate all payloads simultaneously and independently, based on pilot selection.

The GCS shall display the UA's position, navigation route and AIS data simultaneously on a geographic map/chart display.

The GCS EO and IR displays shall include metadata of no less than UA tail number, UA position, UA altitude, UA heading, north seeking arrow, calculated target position, range to target, date/time, and sensor heading and orientation relative to UA.

The UAS shall provide the capability of “GCS-to-GCS” handoff of the airborne UA to another compatible GCS.

The UAS shall be operated by a single pilot seated at a single-person GCS, who will control the UA and its payload.

From the GCS position, the UAS pilot shall communicate internally on the cutter’s internal communication system. The cutter’s internal communications system shall not be integrated into the GCS.

Recorded and stored horizontal position accuracy shall be within 20 meters of actual UA position.

The GCS's stored flight parameter and payload data shall be exportable to media outside the GCS compatible with the Coast Guard standard image.

The GCS operator shall be capable of expeditiously responding to system malfunctions, emergencies and Air Directional Controller (ADC) direction.

GCS/OPCEN; One 440VAC 60Hz electrical circuit is provided and stepped down to 110VAC 60Hz to facilitate power for the GCS racks. These circuits are fed by 15Amp circuit breakers.

LRE/Flight Deck; Two 440VAC, 60 Hz single electrical receptacles are installed at the launching area. These receptacles are each fed by 20Amp circuit breakers.] [9: No electrical power provided by the ship to the UAS will be from Vital Circuits. A vital circuit is defined in the Code of Federal Regulations (CFR) 111.60-9 as "...a branch circuit that supplies equipment vital to the propulsion, control, or safety of the vessel", and generally provides higher reliability/quality than do other shipboard circuits. Therefore, the ship-based UAS components will be subject to frequent interruptions of electrical power. In the event of an interruption of ship-provided power, the Contractor shall be responsible for recovery of AV from maximum operational radius.]

The GCS shall have an independent, uninterrupted back-up power supply to allow full operations for a minimum of 10 minutes.

Sensor, Communication, Navigation, and Identification Systems (CNI) Requirements The UAS shall be an unclassified system. UAS servicing and maintenance shall be performed at the unclassified level.

Communications (Datalinks / Operation) [KSA]

Communications (Spectrum)

The UA and topside and flight deck positioned GCS subsystems shall be compatible with its external radio- frequency (RF) EME, during both shipboard and off-ship operations (inter-system EMC).

CNI equipment shall be compatible with its shipboard external RF EME or shipboard internal EME, as applicable.

The GCS Operator Work Station and all other GCS subsystems mounted internal to ship’s hull shall be compatible with the shipboard internal EME.

The UA shall not present an electromagnetic radiation hazard to personnel, ordnance, or fuel.

The UA shall not present an electrostatic discharge hazard to personnel, ordnance, fuel, electronics or the proper operation of radio receivers.

ISR Data Product Requirements

During night with no visible moisture or particulates, the IR sensor shall track the following surface targets from altitude 3,000 feet and slant range 4,242 feet: a 20 foot outboard boat traveling at 25 knots; and a 25 foot sailboat with sails deployed, making way.

The GCS may connect to any CG enterprise system. However, all data shall be exportable from the GCS to external media, in industry-standard file formats that can be read by CG systems.

All data shall be available for export within 10 minutes of live capture.

The system shall be able to autonomously maintain uninterrupted tracking of a stationary or moving object, while in visual contact.

If standard definition motion imagery is used then it shall be Motion Imagery System Matrix (MISM) Level 3-compliant to MISP Recommended Practice 9720d.

If high definition motion imagery is used then it shall be MISM Level 9-compliant to MISP Recommended Practice 9720b.

The EO sensor shall display a National Image Interpretability Rating Scale (NIIRS) image quality rating of seven or better from altitude 3,000 feet and slant range 4,242 feet during daylight with no visible moisture or particulates.

The Contractor shall provide IR still images in NITF 2.1 format, captured from the FMV stream.

The IR sensor shall display a NIIRS image quality rating of seven or better from altitude 3,000 feet and slant range 4,242 feet at night with no visible moisture or particulates.

The EO and IR sensors shall have multiple fields of view or zoom feature to include a wide area mode for searching.

The GCS shall display the AIS data on a geographic map/chart display.

The UA AIS system shall receive LE encrypted signals.

The UA shall possess an AIS with a minimum effective range of 60 NM from the AV to cooperative ships.

Certification/Qualification Requirements

The UAS shall not degrade the host cutter’s E3 envelope beyond normal operating parameters, except for limitations that may be declared for specific phases of UAS operations.

The UAS national security and systems information processing equipment design, modification, installation and integrity shall adhere to TEMPEST requirements contained within the Aeronautical Engineering Maintenance Management Process Guide, CGTO PG-85-00-110, and Control of Compromising Emanations, COMDTINST M2241.6 (series).

The UAS shall not invalidate the host cutter’s TEMPEST certification or information assurance authority to operate (ATO).

All UAS electromagnetic equipment shall conform to technical parameters identified in the National Telecommunications and Information Administration’s (NTIA), Manual of Regulations & Procedures for Federal Frequency Management (Red Book) and be designed to operate in spectrum authorized for use by federal agencies.

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