ASAP_Performance_Specs_28_Nov_2016.pdf

MIS-PRF-60989 Rev 2

CAGE 18876

28 Nov 2016

PERFORMANCE SPECIFICATION

FOR THE ARMY’S

ADVANCED SUBSCALE AERIAL PLATFORM (ASAP)

28 November 2016

Prepared by:

Targets Management Office

Project Manager for Instrumentation, Targets and Threat Simulators

Program Executive Office for Simulation, Training and Instrumentation

Building 3203, Hercules Road

Redstone Arsenal, Alabama 35898-7458

SFAE-STRI-ITTS-Q

Performance Specification for the Army’s Advanced Subscale Aerial Platform

MIS-PRF 60689 Rev2 28 Nov 2016

CHANGE RECORD

This sheet is a record of each issue of this document.

When the revised document is issued, the previous issue is automatically superseded.

Version Date Configuration

Management Pages Changed

Reason for Change

Original

Rev 1

Rev 2

25 Mar 2016

22 Sep 2016

28 Nov 2016

Jim Schwierling

N/A

9,13,16

9,13,15,21

N/A

Add Payload part numbers; Add Visibility Req’ts; better define payload area.

Removed Camera Requirement;

Removed duplicate Visibility Req’ts; Revised the Verification Matrix

PERFORMANCE SPECIFICATION FOR THE ADVANCED

SUBSCALE AERIAL PLATFORM TARGET SYSTEM

Document Number:

MIS-PRF-60689

Approval Page

This document provides the Performance Specification for an enhanced capability high altitude, Advanced Subscale Aerial Platform (ASAP) System.

CONCURRENCE BY:

12/1/2016

X James Schwierling James Schwierling Lead Project Director, Targets Mgmt Office Signed by: SCHWIERLING.JAMES.E.1230232756

12/1/2016

X Steve Moore Steve Moore

Chief, Aerial Targets Operations, Targets Mgmt Of...

Signed by: MOORE.STEPHEN.H.1230750587 12/1/2016

X Brian P. Nalley for Tony Still Chief, Engineering Division, Targets Mgmt Office Signed by: NALLEY.BRIAN.P.1229834700

12/1/2016

X BE Truog Bruce Truog Deputy Director, Targets Management Office Signed by: TRUOG.BRUCE.E.1139511944

12/1/2016

X Alvin V. Brown Alvin V. Brown Director, Targets Management Office PM ITTS Signed by: BROWN.ALVIN.VAN.1114473673

Contents

1 SCOPE

1.1 General Description

1.2 Mission Objective

1.3 Characteristics

2 APPLICABLE DOCUMENTS

2.1 General

2.2 Government Documents

2.2.1 Specifications, Standards, and Handbooks

2.2.2 Other Government documents, drawings, and publications

2.2.3 Non-Government standards and other publications

2.3 Order of Precedence

3 REQUIREMENTS

3.1 Ground Control Station (GCS)

3.2 ASAP Target

3.3 Special Test Equipment and Tools

3.4 6DOF Simulation

3.5 ASAP System Performance Requirements

3.5.1 Control Frequency

3.5.2 Control Range

3.5.3 Payload Control

3.5.4 Simultaneous Control of Aerial Targets

3.5.5 Formation Flights of Two, Three and Four Aerial Targets

3.5.6 Data Link

3.5.7 Set-up Time

3.5.8 Launch Sequence

3.5.9 Maintenance Turn Time

3.5.10 Flight Termination System

3.5.11 Reliability, Availability, and Maintainability (RAM)

3.5.12 Interchangeability

3.6 ASAP System Environmental Requirements

3.6.1 High Temperature - Operating

3.6.2 High Temperature - Storage

3.6.3 Low Temperature - Operating

3.6.4 Low Temperature - Storage

3.6.5 Altitude

3.6.6 Transportation

3.6.7 Shock

3.7 Aerial Target Performance Requirements

3.7.1 Visual Acquisition

3.7.2 Recovery

3.7.3 Flight Termination

3.7.4 Electrical System

3.7.5 Airspeed

3.7.6 Maximum Flight Altitude

3.7.7 Minimum Flight Altitude

3.7.8 Low Altitude Threat Simulation (LATS)

3.7.9 Low Altitude Endurance

3.7.10 High Altitude Endurance

3.7.11 Built-In-Test

3.7.12 Day/Night Operations/ Visual Acquisition

3.7.13 Launch Envelope

3.7.14 Controllability

3.7.15 Storage/Shelf Life

3.7.16 Payloads

3.7.17 Heading Hold

3.7.18 Maneuverability

3.8 Waypoint Navigation

4 VERIFICATION

4.1 Methods of Verification

4.2 Class of Verification

4.3 Conformance Inspection

4.4 Qualification by Similarity

4.5 Verification Matrix

5 Packaging 6 ACRONYMS/abreviations

Appendix A Waypoint Navigation

1 SCOPE

This specification establishes the performance requirements for the acquisition of an Advanced Subscale Aerial Platform (ASAP) and related equipment. The Targets Management Office (TMO) has a requirement to provide high altitude, high-speed aerial targets to the United States Army Air and Missile Defense (AMD) community, other Department of Defense (DoD) services, and Foreign Military Sales (FMS) customers, to support Research, Development, Test and Evaluation (RDT&E) and training missions at DoD ranges and other military/non-military installations worldwide.

1.1 General Description

The ASAP target system consists of a remote controlled, jet engine powered air vehicle with payload equipment and associated support equipment as defined herein. The ASAP target system incorporates all equipment necessary to meet the requirements of this ASAP system performance specification. The ASAP target system consists of these basic elements:

• ASAP Aerial Target

• Ground Support Equipment

• Six Degrees of Freedom (6DOF) Simulation

1.2 Mission Objective

The ASAP System shall provide aerial target threat presentations for detection/tracking and live fire testing and training. The addition of payload equipment supports various test and training requirements. TMO has no plans to integrate the ASAP into Table of Distribution and Allocation (TDA) or Table of Organization and Equipment (TOE) organizations.

1.3 Characteristics

The ASAP system performance characteristics delineated in Section 3 represent the performance characteristics of the system.

2 APPLICABLE DOCUMENTS

2.1 General

Sections 3, 4 and 5 reference documents listed in this section. This section does not include documents cited in other sections of this specification or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, the contractor must meet all requirements listed in sections 3 and 4.

2.2 Government Documents

2.2.1 Specifications, Standards, and Handbooks

MIL-STD-129

Marking for Shipment and Storage

MIL-STD-130

Identification Marking of U.S. Military Property

MIL-STD-464 Electromagnetic, Environmental Effects Requirements for Systems

MIL-STD-810 Environmental Engineering Considerations and Laboratory Tests

MIL-STD-882 System Safety Program for Systems and Associated, Subsystems and Equipment, Requirements for the identification, classification, and mitigation of hazards.

MIL-STD-1472 Human Engineering Design Criteria for Military Systems, Equipment and Facilities

2.2.2 Other Government documents, drawings, and publications

Department of Defense Instruction (DoDI) 8320.04 Subject:

Item Unique Identification (IUID) Standard for Tangible Personal Property

DFARS 252.211-7003 Item Identification and Valuation (current edition)

2.2.3 Non-Government standards and other publications

None

2.3 Order of Precedence

In the event of a conflict between the text of this specification and the references cited herein, the text of this document takes precedence. Nothing in this document supersedes applicable standards and regulations unless a specific exemption has been obtained.

3 REQUIREMENTS

All threshold and objective values are specifically identified within the body of this specification. The terms “threshold” and “objective” are in bold type immediately preceding/following the stated requirement. Threshold is the minimum capability required of the system. Objective reflects the desired capability goal. Requirements not specifically identified as “threshold” or “objective” are threshold requirements and identify the minimum acceptable system/subsystem performance. Key performance parameters (KPPs) are identified by term “KPP” in bold type immediately following the stated requirement. The ASAP shall meet or exceed all threshold requirements.

3.1 Ground Control Station (GCS)

The ASAP shall operate with the Government owned, Army Ground Aerial Target Control System (AGATCS) using manual control, pre-programmed maneuvers and semi-autonomous Waypoint Navigation (threshold) (KPP). The Government shall have full data rights to any software developed at Government expense (threshold).

3.2 ASAP Target

The ASAP target shall be a remote-controlled, reusable, jet engine powered air vehicle capable of carrying internal and external payloads (threshold) (KPP). The target shall be modular in construction to facilitate maintenance and repair (threshold). The target shall support the addition of internal and external payloads to enhance and extend the capabilities of the baseline target (threshold).

3.3 Special Test Equipment and Tools

The ASAP shall be compatible with the Army’s Model 59 Test Set (threshold). The following items shall be considered part of the total system: Special Test Equipment and Tools including electronic and mechanical test equipment and special tools required to verify the target system is functioning properly and ready for launch/flight/recovery shall be considered part of the total system.

3.4 6DOF Simulation The ASAP target 6DOF simulation shall be integrated into and operate with the Government-owned AGATCS simulation capability (threshold) (KPP). The 6DOF simulation shall support mission rehearsal and operator training requirements (threshold). The Government shall have full data rights to simulation software developed using Government funds (threshold).

3.5 ASAP System Performance Requirements

The ASAP System shall have the following performance characteristics: (unless otherwise specified, performance is based on a “clean” baseline target without internal and external payloads).

3.5.1 Control Frequency

The system shall operate within an adjustable frequency range between 358 – 380 MHz using Micro Systems radio P/N AY12950-3 or form, fit and function equivalent (threshold). The system shall operate with Micro Systems, Inc. radios currently approved for use at Fort Bliss and White Sands Missile Range (WSMR) (threshold) (KPP). The system shall operate on a single, selectable frequency to allow flexibility when operating on DoD test ranges (threshold). The system shall support modification to operate with alternate transponders and frequencies to support planned flight operations in both continental United States (CONUS) and outside continental United States (OCONUS) test ranges (threshold).

3.5.2 Control Range

The system shall have a direct line of site control range of at least 150 kilometers (threshold), at least 200 kilometers (objective), in an environment with unobscured line of sight and without the use of a radio relay. The ASAP shall be able to operate beyond radio frequency (RF) line of sight with the addition of a radio relay (threshold).

3.5.3 Payload Control

The system shall have a minimum of three (3) discrete and one (1) proportional control signal outputs from the GCS for payload control and a minimum of two (2) discrete and one (1) proportional control signal inputs to the GCS for payload monitoring (threshold). The ASAP shall have a minimum of four (4) discrete and two (2) proportional control signal outputs from the GCS for payload control and a minimum of three (3) discrete and two (2) proportional control signal inputs to the GCS (objective).

The ASAP shall support the following GFE payloads with associated cables and antennas where applicable (threshold):

• Internal Payload Bay

• Scoring Devices

• Meggitt Defense Systems ProTrak scoring system with RF and DSP Modules

• Meggitt Defense Systems CMDI-118 Microdops

• Emhiser Research, Inc. Telemetry Transmitter, 5 Watts Model No.

ETTT-06D1A502-TMO0

• IFF Transponder

• Sagetech Corp. XPC-TR mode 3C

• Sagetech Corp. XPS-TR mode S

• Sagetech Corp. XPG-TR mode S

• Data Logger

• Dynetics 10006813 Data Logger 1 GB with IMU and GPS antenna

• Low Altitude Threat Simulator (LATS) kit to allow for low altitude flights.

• Internal – Other

• Nose Lens MIS39698-1, -2

• External

• APC – 4 Wing Tip Pod Part number 999E250038-1

• TOW Target Launcher Assembly Part Number 13216270

• JCHAAT TOW Target MPN 757300-1 (Meggitt Defense Systems)

3.5.4 Simultaneous Control of Aerial Targets

The system shall be capable of simultaneous operation with a second target (threshold). The ASAP system shall be capable of simultaneous operation with up to four targets (objective). The ASAP system shall be capable of simultaneous operation with a second ASAP on a single control frequency (objective).

3.5.5 Formation Flights of Two, Three and Four Aerial Targets The system shall be capable of formation flight with a second target (threshold). The system shall be capable of formation flight with up to four targets (objective).

3.5.6 Data Link

The system shall provide a 10 Hz data link connectivity (one target per frequency) between the GCS and the target during a mission (threshold). With 2 targets per frequency, a 5 Hz data link shall be maintained (threshold). This data link shall provide control information to the target as well as status information from the target (threshold). The system shall follow a pre-programmed response for safe flight termination if the data link loses connectivity (threshold).

3.5.7 Set-up Time

The ASAP target system shall be set up and “ready for operation” in no more than 72 duty hours (threshold) or 24 duty hours (objective) after arrival at the Test Range designated launch site.

Note: “Ready for Operation” means the target has successfully completed all electrical and engine tests, the recovery system and all payloads are installed; target is fueled and has completed weight and balance.

3.5.8 Launch Sequence

The system shall have the capability to launch two targets for a single mission (threshold); or four targets for a single mission (objective). The launch window between two target launches shall not exceed 45 seconds (threshold), 30 seconds (objective).

3.5.9 Maintenance Turn Time

The ASAP target shall be set up and “ready for operation” after retrieval in no more than five (5) duty days (including the replacement of the chute pack) (threshold), or no more than three (3) duty days (objective).

3.5.10 Flight Termination System

The system shall provide a method(s) to allow the RCS operator, via the AGATCS, to terminate the flight in the event of an emergency (threshold) (KPP). In addition, the system shall incorporate a flight termination system that is compliant with the applicable range safety guidelines. The ASAP target shall enter an auto-recovery mode in response to a loss of command data link or if commanded to do so from the GCS (threshold).

3.5.10.1 Pre-programmed Delay

The ASAP shall have a programmable delay between 0 and 30 seconds before executing an auto-recovery. The delay time shall be capable of being programmed from the AGATCS control console by the Remote Control Operator. If the command data link is lost for a period less than the pre-programmed delay the ASAP target shall remain on its current heading and speed (threshold). If the loss of the carrier situation continues for more than the pre-programmed delay, the target shall enter its auto-recovery mode (threshold).

3.5.10.2 Fuel Shut-Off

The flight termination system shall have a redundant fuel shut-off system that can be commanded from the GCS (threshold). This redundant fuel shut-off shall not require a separate radio for transmission (objective).

3.5.11 Reliability, Availability, and Maintainability (RAM)

3.5.11.1 Reliability

Reliability is defined as the probability the system will perform correctly through the Launch, Mission Flight Profile, and Recovery phases of each target mission as planned.

The system shall have a reliability of 95% with only a primary target prepared and 98% with a primary and backup target prepared prior to launch (threshold).

3.5.11.1.1 Flight Reliability.

Flight reliability is the probability that the ASAP (given a successful launch) will successfully perform all functions required during the target’s flight. The flight portion of a target is defined as that period of time from completion of the launch phase to the time the flight terminates as follows:

• Weapon System Kill

• Command Recovery

• Un-commanded Recovery due to loss of command data link

Minimum flight reliability shall be 91% (threshold), 95% (objective).

3.5.11.1.2 Recovery

Recovery reliability is the probability that the recovery system will deploy upon command resulting in little or no damage to the ASAP. The recovery phase is initiated by command or is automatically initiated (un-commanded) as noted above. The recovery phase lasts until the target touches the ground (or water). Minimum recovery reliability shall be 97% (threshold), 99% (objective).

3.5.11.2 Availability

System availability shall meet the satisfactory flight rate of 95% for all missions (threshold), 98% (objective). A satisfactory flight is defined as a flight that successfully takes-off on schedule, meets all of the requirements for the scheduled task, and successfully follows the prescribed flight path/profile for the designated mission. The satisfactory flight rate definition is the ratio of the number of satisfactory flights to the number of total flights attempted.

3.5.11.3 Maintainability

The ASAP System shall have modular system architecture for ease of assembly and repair. The ASAP system shall incorporate built-in-test and diagnostic capabilities. The ASAP system shall have a Mean Time to Repair (MTTR) of four (4) hours (threshold).

The ASAP system shall have a Mean Time Between Failure (MTBF) (non-consumable parts) of 10 flights (threshold).

3.5.12 Interchangeability

All items with the same manufacturer’s part number, which can be removed and replaced during operation and maintenance of the system, shall be capable of being readily installed, removed, or replaced without alteration, misalignment, or damage to items being installed or to adjoining items or structure (threshold).

3.6 ASAP System Environmental Requirements

3.6.1 High Temperature - Operating

The ASAP system shall be capable of operating when exposed to surface temperatures defined by MIL-STD-810G, Method 501.5, Hot-Dry (32ºC to 49ºC) (90˚F to 120˚F) (threshold).

3.6.2 High Temperature - Storage

The ASAP system shall not be damaged after exposure to induced conditions as defined by MIL-STD-810G, Method 501.5, Hot Dry (33ºC to 71ºC) (91˚F to 160˚F) (threshold).

3.6.3 Low Temperature - Operating

The ASAP system shall be capable of operating when exposed to surface temperatures defined by MIL-STD-810G, Method 502.5, Basic Cold (-21ºC to -31ºC) (-6˚F to -24˚F) (threshold).

3.6.4 Low Temperature - Storage

The ASAP system shall not be damaged after exposure to induced conditions as defined by MIL-STD-810G, Method 502.5, Basic Cold (-25ºC to -33ºC) (-13˚F to -27˚F) (threshold).

3.6.5 Altitude

The ASAP shall be capable of operating when exposed to the combined temperature, humidity, vibration and altitude environments as defined by MIL-STD-810G, Method 520.3, Hot Atmosphere Model up to 40,000 feet (threshold).

3.6.6 Transportation

The ASAP system shall be transportable on a truck or trailer on improved and unimproved/ range roads, as well as shipboard and air transport (threshold). The ASAP system when packaged in shipping containers shall not be damaged when subjected to transportation vibration as defined by MIL-STD-810G, Method 514.6, Annex C: Category 4 – Truck/Trailer - Secured Cargo; Category 7 – Aircraft – Jet and Category 8 – Aircraft – Propeller (threshold).

3.6.7 Shock

The ASAP system components, when packaged in shipping containers shall not be damaged when subjected to a transit drop as defined by MIL-STD-810G, Method 516.6, Procedure IV (threshold).

3.7 Aerial Target Performance Requirements

3.7.1 Visual Acquisition

The ASAP shall be designed to be visually acquired at a distance of 8 kilometers (threshold). A high visibility paint scheme shall be provided and a smoke oil system with a usable capacity of 7 us gallons shall be installed (threshold). A smoke oil system shall be included as part of the basic ASAP design and shall provide a minimum of 7 minutes of continuous smoke for smoke generation. The ASAP smoke oil system shall have the capability for continuous or intermittent smoke by command from the Ground Control System (GCS) (threshold).

3.7.2 Recovery

The ASAP shall be recoverable, by parachute, over the speed and altitude ranges of the target (threshold) (KPP). The recovery system shall minimize target damage during land or water operations, and allow for 5 duty days turnaround (threshold). The ASAP shall be capable, with an optional kit, of water recovery (threshold). With an optional water recovery kit, the ASAP shall remain afloat in salt water for a period of at least 2 hours (threshold).

The ASAP shall be recoverable by land (threshold). With the addition of optional hardware, the ASAP shall be recoverable by helicopter (threshold).

3.7.3 Flight Termination

The ASAP target, when in flight, shall enter a recovery mode under any of the following conditions (threshold):

• Remote control operator (RCO) command;

• Automatically upon loss of UHF command;

• Automatically upon loss of vehicle power; and

• Automatically upon failure of the avionics/ flight control system.

The flight termination system shall have a redundant fuel shut-off system that can be commanded from the control panel (threshold). This redundant shut-off does not require a separate radio for transmission (objective).

3.7.4 Electrical System

The ASAP electrical system shall provide 28 volt direct current (VDC) primary power (threshold) (KPP). The ASAP shall provide a separate twelve (12) VDC battery to operate the recovery system (threshold) (KPP). The ASAP shall have redundant power for the recovery system coupled to the vehicle primary power source (threshold)

(KPP).

The ASAP shall supply a minimum of 83 Amperes at 28 VDC (2.324 Kilowatts) for operating internal and external payloads (threshold) (KPP). The target shall provide payload power on a separate electrical bus and shall be in addition to that required to operate and recover the target vehicle (threshold).

3.7.5 Airspeed

The aerial target shall operate and sustain airspeeds up to 450 knots indicated air speed (KIAS) for four (4) minutes in level flight at an altitude of 10,000 feet mean sea level (MSL) (threshold), or 600 KIAS for 3.5 minutes in level flight at an altitude of 10,000 feet MSL (objective). The ASAP shall provide the necessary information to be able to display ground speed on the AGATCS (threshold).

3.7.6 Maximum Flight Altitude

The aerial target shall operate for 2 minutes at a maximum altitude of 40000 feet MSL (threshold), 50,000 feet MSL (objective).

3.7.7 Minimum Flight Altitude

The ASAP, when equipped with optional hardware, shall operate over land for a minimum of one minute at 50 feet AGL across the entire speed range of the ASAP (threshold) (KPP), 25 feet AGL (objective). The ASAP, when equipped with optional hardware, shall operate over water for a minimum of one minute at 50 feet AGL across the entire speed range of the ASAP (threshold) (KPP), 25 feet AGL (objective). The ASAP, when equipped with optional hardware, shall be capable of stepping up or down in altitude in 5 feet increments (threshold). The ASAP shall provide for an automatic climb escape mode if, (1) the controller desires to end the presentation, (2) the altimeter malfunctions, or (3) command link to the vehicle is lost (threshold) (KPP).

3.7.8 Low Altitude Threat Simulation (LATS)

The ASAP, when equipped with optional hardware, shall be able to transition to a programmable low altitude with a single command from the AGATCS (threshold). The transition from 2000 feet AGL to the programmed flight altitude shall take no more than 30 seconds (threshold (KPP), 25 seconds (objective). During this transition, the target shall not overshoot the desired altitude by more than 25% of the desired altitude

(threshold) (KPP). An ASAP diving from 2000 feet to 100 feet can have a maximum overshoot of 25 feet.

3.7.9 Low Altitude Endurance

For altitudes at or below 15,000 feet MSL, the ASAP target shall have an endurance of 60 minutes of which 3 minutes are at 0.8 mach (threshold) (KPP). At altitudes at or below 15,000 feet MSL, the aerial target shall have an endurance of 90 minutes of which 5 minutes are at 0.8 mach (objective).

3.7.10 High Altitude Endurance

At altitudes at or above 25,000 feet MSL, the aerial target shall have an endurance of 90 minutes 45 minutes of which should be at 0.8 mach (threshold) (KPP). At altitudes at or above 25,000 feet MSL, the aerial target shall have an endurance of 120 minutes at 0.8 mach (objective).

3.7.11 Built-In-Test

The ASAP system shall have a built-in-test capability that reports the health status of the system components during pre-flight testing and at the launch pad/blockhouse prior to launch (threshold). The ASAP shall transmit health and status information to the AGATCS system prior to launch and during operation (objective).

3.7.12 Day/Night Operations/ Visual Acquisition

The ASAP system shall perform in accordance with the requirements of this specification at any time during a 24-hour period over land or bodies of water (threshold).

3.7.12.1 Strobe Light

The ASAP shall be capable of incorporating a strobe light as required for night operations (threshold).

3.7.13 Launch Envelope

The ASAP target shall be capable of launching under the following wind conditions (threshold): 50 KTAS Head (nose) Winds, 20 KTAS Cross Winds and 25 KTAS Tail Winds. The ASAP target shall be capable of launching under the following wind conditions (objective): 60 KTAS Head Winds, 35 KTAS Cross Winds and 30 KTAS Tail Winds. Wind conditions shall be measured at the launch site.

3.7.14 Controllability

During straight and level flight, at a specified altitude and airspeed, under crosswind conditions of 60 knots (at altitudes from 30,000 to 10,000 feet), or 40 knots (at altitudes from 10,000 to 300 feet), the ASAP shall be controlled, using the AGATCS, within a 650 foot wide corridor +/-300 feet off the centerline for not less than 12 miles (threshold).

The ASAP shall be capable of maintaining the desired heading, altitude and speed under asymmetrical load conditions, such as when pulling tow targets (threshold).

3.7.15 Storage/Shelf Life

The ASAP shall have a minimum shelf life of 5 years (threshold) or 8 years (objective) when stored in the storage and shipping container in the Basic Hot environment as defined by AR 70-38.

3.7.16 Payloads

3.7.16.1 Internal Payloads

The ASAP shall provide a minimum of 4.7 cubic feet of space in the fuselage to accommodate payloads up to 100 lbs (threshold) (KPP), 300 lbs. (objective). The payload area shall have a minimum continuous mounting plane of 20 inches in length and be able to accommodate a payload that is 10 inches along the payload mounting surface and 4.6 inches perpendicular to the mounting surface (dark outlined box) or

6.25 inches along the mounting surface and 6 inches perpendicular to the mounting surface (dotted outline box). Figure 3.1 is an example based on a 15 inch diameter payload area with a mounting shelf in the middle. The purpose is to show minimum dimensions for the payload area, not to drive the target design to any particular shape.

Figure 3-1 Sample Payload Bay

3.7.16.2 External Payloads

The ASAP shall support a 50 lbs. load on each wingtip (threshold). The ASAP shall support a 100 lbs. minimum mounted payload under each wing (threshold) (KPP). The ASAP shall support a 100 lb. payload under each wing and an additional 50 lb. wingtip payload (objective).

6.25” Height Minimum

10.00” Width Minimum

Notional Mounting Surface

4.6 “

6 “

20.00” Depth Minimum

3.7.16.3 Transponder Payload

The ASAP shall include provision for the installation of an optional GFE Sagetech Corp.

XPC-TR Mode 3C transponder and either a Sagetech Corp. XPS-TR or XPG-TR Mode S Transponder. The installation shall include the associated antennas for the selected transponder (threshold). The transponder integration with ASAP shall be modular in design allowing for installation and removal with a minimum number of tools. The ASAP shall provide power to the transponder (threshold), have a battery backup (objective).

The ASAP ground support equipment shall be able to program transponder identification codes (threshold). The integration shall allow ground personnel to turn the transponder on/off in the target (threshold) and from the ground control system (objective).

3.7.16.4 Towed Target Payload Capability

The ASAP shall be pre-wired and capable of carrying and operating GFE tow targets (threshold) (KPP). The ASAP shall support installation and operation of two wing mounted tow targets without modification of the GFE TOW launcher (threshold). The ASAP shall deploy towed targets when commanded from the GCS (threshold). The ASAP shall release the tow line and towed target when commanded from the GCS (threshold).

3.7.17 Heading Hold

The ASAP Avionics/Control system shall provide a control mode to hold the heading constant when turns or maneuvers are not being commanded (threshold). This mode shall be activated whenever the mode is not overridden by remote command (threshold).

3.7.18 Maneuverability

The ASAP, in the basic configuration, shall be capable of performing maneuvers at the speed, altitude, and load factor ranges defined below.

3.7.18.1 Load Factor Control

The ASAP shall be capable of constant load factor maneuvers up to 6g (threshold).

The g level shall be set by remote command and may be increased by two during a maneuver by discrete command. The ASAP shall be capable of performing the following advanced high g maneuvers: g-turn, weave, barrel roll, slice, pitch-back, dive, and climb maneuvers.

3.7.18.2 G Turns

The ASAP shall be capable of executing a sustained 180-degree, 6g turn at 10,000 feet MSL while maintaining altitude +/- 200 feet (threshold); executing a sustained 180-degree greater than 6g turn at 10,000 feet MSL while maintaining altitude +/- 200 feet (objective).

3.7.18.3 Weaves

The ASAP shall be capable of a executing a 6g-weave maneuver at 10,000 feet MSL (threshold); greater than 6g weave maneuver at 10,000 feet MSL (objective).

3.7.18.4 Rolls

The ASAP shall be capable of performing a Barrel Roll at 10,000 feet MSL (threshold).

3.7.18.5 Pitch Back

The ASAP shall be capable of performing a Pitch Back maneuver at 10,000 feet MSL (threshold).

3.7.18.6 Slice

The ASAP shall be capable of performing a Slice maneuver at 10,000 feet MSL (threshold).

3.7.18.7 Dive

The ASAP shall be capable of executing and recovering after a high speed (> 400 knots-indicated airspeed (KIAS)) 30 degree dive (threshold). The ASAP shall be capable of a executing and recovering after a high speed (> 400 KIAS) 45 degree dive (objective).

3.7.18.8 Climb

The ASAP shall be capable of executing a 15 degree climb (threshold), 20 degree climb (objective).

3.8 Waypoint Navigation

The ASAP shall be capable of Waypoint Navigation as defined in Appendix A.

Waypoint navigation shall be consistent with the parameters listed in the sub-paragraphs of 3.7 above.

4 VERIFICATION

Section 4 establishes the verifications of section 3 requirements. The methods of verification are included in the Verification Cross Reference Matrix (VCRM) Table I.

Performance requirements that are optional in the Statement of Work, will only be verified if option is exercised.

4.1 Methods of Verification

The following methods shall be utilized to accomplish the verification of requirements:

Analysis (A) Demonstration (D) Examination (E) Test (T) Not Applicable (N/A)

4.2 Class of Verification

The ASAP system components shall be subject to a final verification inspection as shown in Table I, Verification Cross Reference Matrix (VCRM).

4.3 Conformance Inspection

Conformance inspection shall include the analyses, examinations and demonstrations as outlined in Table I, VCRM.

4.4 Qualification by Similarity

Upon Government approval, the system may be verified by the use of “qualification by similarity” for requirements with analysis as a test method. The contractor shall provide the following information at the time of request. The Government will review the requests and provide written acceptance/rejection within 60 days after receiving the request.

1. Describe the target component and the proposed similar component.

2. Describe the qualification process used for the proposed component and provide a summary of the test results.

3. Describe the differences between the target component and the proposed similar component.

4. Describe how these differences do not affect the qualification results.

4.5 Verification Matrix

Verification Matrix

Paragraph Section 3 Requirements Verification Method

Verification Class

3 Requirements N/A Inspection

3.1 Ground Control Station D Inspection

3.2 ASAP Target E Inspection

3.3 Ground Support Equipment D Inspection

3.4 Six Degrees of Freedom (6DOF)

Simulation D Inspection

3.5 ASAP System Performance

Requirements

N/A Inspection

3.5.1 Control Frequency D Inspection

3.5.2 Control Range D Inspection

3.5.3 Payload Control D Inspection

3.5.4 Simultaneous Control of Aerial

Targets T Inspection

3.5.5 Formation Flights of Two, Three

and Four Aerial Targets

T Inspection

3.5.6 Data Link T Inspection

3.5.7 Set-up Time D Inspection

3.5.8 Launch Sequence D Inspection

3.5.9 Maintenance Turn Time D Inspection

3.5.10 Flight Termination System D Inspection

3.5.10.1 Pre-programmed Delay D Inspection

3.5.10.2 Fuel Shut Off D Inspection

3.5.11 Reliability, Availability and

Maintainability (RAM) N/A Inspection

3.5.11.1 Reliability A Inspection

3.5.11.1.1 Flight Reliability D Inspection

3.5.11.1.2 Recovery A Inspection

3.5.11.2 Availability A Inspection

3.5.11.3 Maintainability D Inspection

3.5.12 Interchangeability D Inspection

3.6 ASAP System Environmental

Requirements N/A Inspection

3.6.1 High Temperature – Operating T Inspection

3.6.2 High Temperature – Storage T Inspection

3.6.3 Low Temperature – Operating T Inspection

3.6.4 Low Temperature – Storage T Inspection

3.6.5 Altitude T Inspection

3.6.6 Transportation T Inspection

3.6.7 Shock T Inspection

3.7 Aerial Target Performance

Requirements N/A N/A

3.7.1 Visual Acquisition D Inspection

3.7.2 Recovery D Inspection

3.7.3 Flight Termination D Inspection

3.7.4 Electrical System D Inspection

3.7.5 Airspeed T Inspection

3.7.6 Maximum Flight Altitude T Inspection

3.7.7 Minimum Flight Altitude T Inspection

3.7.8 Low Altitude Threat Simulation

(LATS)

T Inspection

3.7.9 Low Altitude Endurance T Inspection

3.7.10 High Altitude Endurance T Inspection

3.7.11 Built-In Test D Inspection

3.7.12 Day/Night Operations/ Visual

Acquisition D Inspection

3.7.12.1 Strobe Light T Inspection

3.7.13 Launch Envelope A Inspection

3.7.14 Controllability T Inspection

3.7.15 Storage/Shelf Life A Inspection

3.7.16 Payloads N/A Inspection

3.7.16.1 Internal Payloads D Inspection

3.7.16.2 External Payloads D Inspection

3.7.16.3 Transponder Payload D Inspection

3.7.16.4 Towed Target Payload Capability D Inspection

3.7.17 Heading Hold D Inspection

3.7.18 Maneuverability N/A Inspection

3.7.18.1 Load Factor Control D Inspection

3.7.18.2 G Turns T Inspection

3.7.18.3 Weaves D Inspection

3.7.18.4 Rolls D Inspection

3.7.18.5 Pitch Back D Inspection

3.7.18.6 Slice D Inspection

3.7.18.7 Dive D Inspection

3.7.18.8 Climb D Inspection

3.8 Waypoint Navigation D Inspection

5 PACKAGING

Preservation, packaging, packing, and markings shall be in accordance with the AMCOM approved packaging data sheet(s) specified in the procurement document.

6 ACRONYMS/ABREVIATIONS

6 DOF Six Degrees of Freedom A Analysis AGATCS Army Ground Aerial Target Control System AGL Above Ground Level AMD Air and Missile Defense APM Army Part Number AR Army Regulation ASAP Advanced Subscale Aerial Platform C Celsius CONUS Continental United States COTS Commercial Off-The-Shelf D Demonstration DoD Department of Defense DOF Degrees of Freedom DTED Digital Terrain and Elevation Data E Evaluation EA Electronic Attack EFTS Enhanced Flight Termination System EMI Electromagnetic Interference F Fahrenheit FMC Fully Mission Capable FMS Foreign Military Sales FTS Flight Termination System g Gravity (Unit of Force) GCS Ground Control Station GFE Government Furnished Equipment Hz Hertz IAS Indicated Air Speed IAW In accordance with IUID Item Unique Identification km kilometer KIAS Knots – Indicate Air Speed KPP Key Performance Parameter

LATS Low Altitude Threat Simulation lb Pound LOC Loss of Carrier m Meter MHz Megahertz MIL-STD Military Standard MPS Mission Planning Software MSL Mean Sea Level MTBF Mean Time Between Failures MTTR Mean Time to Repair N/A Not Applicable NDI Non-developmental Item OCONUS Outside the Continental United States RAM Reliability, Availability and Maintainability RCC Range Commanders Council RCO Remote Control Operator RDT&E Research, Development, Test and Evaluation RF Radio Frequency STD Standard T Test TDA Table of Distribution and Allowances TMO Targets Management Office TOE Table of Organization and Equipment VCRM Verification Cross Reference Matrix VDC Volts Direct Current WSMR White Sands Missile Range

Appendix A Waypoint Navigation

Commercial Waypoint Navigation for Aerial Targets (Unless otherwise specified all requirements are Threshold)

Assumptions:

a. In order to minimize latency and take advantage of each target’s unique flight capabilities, the waypoint engine/interpreter shall be installed on the target and not reside on the ground station. (Objective)Remote Control Operator (RCO) has manual control of target during launch.(Objective)

b. RCO manually initiates waypoint navigation in flight and can override waypoint navigation at any time.

c. If a Loss of Carrier occurs, Targets will search for the signal for a preprogrammed number of seconds and then initiate recovery. If the signal is regained prior to the preprogrammed number of seconds, the RCO will manually fly the target to either the recovery location or a predetermined waypoint resume point and re-engage waypoint navigation.

d. Mission planner software interfaces accurately with the simulator

Mission Planning Software Requirements:

1. The mission planner software (MPS) shall be capable of importing digital terrain and elevation data (DTED).

2. The MPS shall have a simplified ‘point and click’ interface.

3. The MPS shall allow a user to create a flight plan which takes into account terrain, aircraft performance/capability and target configuration.

a. The MPS shall have the capability to display, add, delete and modify no-fly zones.

b. The MPS shall allow waypoints to be placed/plotted onto a map.

c. The MPS shall allow the insertion of waypoints by typing in latitude and longitude coordinates.

d. The MPS shall allow functions and maneuvers to be assigned to waypoints.

e. The MPS shall allow arrival time to be assigned to waypoints

4. The MPS shall have the capability to record, store, recall and playback mission planning files through the target simulator.

5. The MPS shall generate data file(s) for upload into the target for execution.

6. The MPS shall be capable of generating mission files for single, dual targets, triple and quadruple target missions.

7. The MPS shall allow the following events to be assigned to a waypoint.

a. Heading changes (G Turns, etc…)

b. Altitude and Attitude changes (climb, dive)

c. Payload commands (smoke, scoring, tow deploy, tow release, etc…)

d. Complex maneuvers (Weaves, Low Altitude Threat Simulation, etc…)

e. Airspeed/Throttle Commands including Speed Hold on Throttle

f. Loitering

g. Recovery

h. Limits associated with pitch, roll, airspeed can be set in the MP.

i. Ground Speed

j. Arrival time

k. Starting waypoint

l. Repeating waypoint

m. Low Altitude Reference

8. The MPS shall interface with the target simulator to verify the planned mission profile is achievable and within the target’s performance envelope.

9. The number of waypoints allowed for a mission is a minimum of 1 up to and including the number required to have a waypoint flight approach a path-following flight. (Minimum of 250 waypoints per flight)

10. The MPS shall not plan a flight path that exceeds the targets capabilities or flight envelope.

11. The MPS shall identify and notify the user of any potential problem areas during mission planning.

12. The MPS shall allow the user to repeat the path or loiter at the end of waypoint flight.

Ground Control Station/Mission Planner Software Requirements

1. The MPS/Ground Control System interface shall allow the RCO to add, change or delete a waypoint during flight.

2. The RCO shall have the capability to manually control payloads in waypoint flight.

3. The GCS shall have the ability to simultaneously display multiple targets operating in waypoint mode and manual mode.

4. The RCO shall have the capability to enter or exit waypoint flight mode at any time during the flight.

5. The RCO shall have the capability of commanding recovery or emergency recovery at any time during the waypoint flight.

6. The GCS display shall highlight the next waypoint(s) in the target path

7. The RCO shall have the capability to specify the next waypoint when engaging or restarting waypoint flight.

8. The RCO shall have the capability to command the target to repeat the path.

Aerial Target Requirements:

1. The Target shall receive and execute a waypoint file upon command.

2. The target shall be capable of swapping between manual control and waypoint navigation mode during flight. A RCO may command control of the target while in waypoint navigation mode and at any time during the flight the RCO may reenter waypoint navigation mode. Once waypoint navigation mode is engaged the target will take the shortest path back to the next defined waypoint, within target capability.

3. The Target shall adjust heading, speed and altitude in order to achieve the programmed flight path.

4. The Target shall fly to specific waypoint, at a defined heading, speed and altitude at a synchronized arrival time.

5. Target payloads shall be controllable by passing through a waypoint.

(For example: At location xyz, smoke is engaged)

6. Target maneuvers (Dives, LATS, Climbs, Weave, G-Turns, etc…) shall be capable of initiation at predefined waypoints.

7. In the event of a Loss of Carrier, the target will follow the predefined LOC routine.

8. When the RCO commands waypoint flight, the target will maneuver to the next waypoint along the path.

9. If the last waypoint is reached, and the next waypoint is not defined or assigned, the target will enter a loiter mode around the last waypoint.

10. Self- Preservation: The target shall limit any waypoint commanded instructions or maneuvers which exceed the capability of the airframe. For Example: If for any reason, Waypoint Navigation cannot maintain positive aircraft control and the target is no longer able to maintain stable flight to achieve the next waypoint, positive aircraft control will take precedence and the GCS will be notified.

11. Waypoint Navigation shall be capable of controlling the target at all altitudes within the target’s flight envelope and capability, including low altitude flight when the target is equipped with a Radar Altimeter.

2.3 Order of Precedence

3.5.12 Interchangeability

3.8 Waypoint Navigation