ASTM F3002-22

This document is not an ASTM standard and is intended only to provide the user of an ASTM standard an indication of what changes have been made to the previous version. Because
it may not be technically possible to adequately depict all changes accurately, ASTM recommends that users consult prior editions as appropriate. In all cases only the current version
of the standard as published by ASTM is to be considered the official document.
Designation: F3002 − 14a F3002 − 22
Standard Specification for
Design of the Command and Control System for Small
Unmanned Aircraft Systems (sUAS)
This standard is issued under the fixed designation F3002; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope
1.1 This specification is provided as a consensus standard in support of an application to a nation’s governing aviation authority
(GAA) for a permit to operate a small unmanned aircraft system (sUAS) for commercial or public use purposes.
1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility
of the user of this standard to establish appropriate safety safety, health, and healthenvironmental practices and determine the
applicability of regulatory limitations prior to use.
1.3 This international standard was developed in accordance with internationally recognized principles on standardization
established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued
by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
2. Referenced Documents
2.1 ASTM Standards:
F2910 Specification for Design, Construction, Design and TestConstruction of a Small Unmanned Aircraft System (sUAS)
F2911 Practice for Production Acceptance of a Small Unmanned Aircraft System (sUAS)
F3003 Specification for Quality Assurance of a Small Unmanned Aircraft System (sUAS)
F3060 Terminology for Aircraft
F3341/F3341M Terminology for Unmanned Aircraft Systems
2.2 EN Standard:
EN 62262 Degrees of protection provided by enclosures for electrical equipment against external mechanical impacts (IK code)
2.3 IEC Standard:
IEC 60529 Degrees of protection provided by enclosures (IP Code)
3. Terminology
3.1 Definitions:Unique and Common Terminology—Terminology used in multiple standards is defined in F3341/F3341M, UAS
Terminology Standard and F3060, Aircraft Terminology Standard. Terminology that is unique to this specification is defined in this
section.
3.1.1 bit error rate detection, BER, n—rate at which errors occur in a transmission system; applicable to any system that transmits
data over a network of some form in which noise, interference, and phase jitter may cause degradation of the digital signal.
This specification is under the jurisdiction of ASTM Committee F38 on Unmanned Aircraft Systems and is the direct responsibility of Subcommittee F38.01 on
Airworthiness.
Current edition approved June 1, 2014Oct. 1, 2022. Published July 2014December 2022. Originally approved in 2014. Last previous edition approved in 2014 as
F3002 – 14.F3002 – 14a. DOI: 10.1520/F3002-14A.10.1520/F3002-22.
For referenced ASTM standards, visit the ASTM website, www.astm.org, or contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM Standards
volume information, refer to the standard’sstandard’s Document Summary page on the ASTM website.
Available from American National Standards Institute (ANSI), 25 W. 43rd St., 4th Floor, New York, NY 10036, http://www.ansi.org.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
F3002 − 22
3.1.2 command and control (C2) link(s), n—safety-critical radio-frequency (RF) link(s) between the ground control station (GCS)
and the unmanned aircraft (UA).
3.1.3 C2 range, n—distance between GCS and UA at which positive control of the UA can be maintained.
3.1.4 downlink, n—any RF link from UA to GCS.
3.1.5 flight control system, FCS, n—composed of system components intended to take GCS commands via a C2 link and control
flight control surfaces and propulsion systems.
3.1.5.1 Discussion—
The FCS may include autopilot functions, lost-link functions, fly-away protection functions, payload functions, and navigation
functions. The FCS may be contained in one discrete component or multiple discrete components.
3.1.6 fly away, n—unintended flight outside of operational boundaries (altitude/airspeed/lateral) as the result of a failure of the
control element or onboard systems, or both.
3.1.7 fly-away protection system, n—a system that will return the UA safely to the surface, or keep the UA within the intended
operational area, when the C2 link between the pilot and the UA is lost.
3.1.8 ground control station, GCS, n—a land- or sea-based control center that provides the facilities for human control of UA.
3.1.9 licensed band, n—any frequency or range of frequencies in which transmission requires permission from a governing body
(for example, the Federal Communications Commission [FCC]).
3.1.10 link error, n—degradation of the digital signal between the GCS and the UA that can be monitored by techniques including
BER detection.
3.1.11 link integrity, n—acceptable rate of transactions completed with undetected error.
3.1.12 link timeout, n—time between the actual lost-link event being validated and the system initiating the lost-link procedure.
3.1.13 lost link, n—occurrence in which the pilot in command (PIC) has lost the ability to control positively the sUAS because
of degradation, loss or interruption of the necessary control or monitoring link(s), or both.
3.1.14 manufacturer, n—entity responsible for assembly and integration of components and subsystems to create a safe operating
sUAS.
3.1.15 pilot in command, PIC, n—the pilot responsible for the operation and safety of the UA during flight time.
3.1.16 positive control, n—a condition in which commanded changes in the UA flight path result in the expected maneuver(s)
within an expected period of time.
3.1.17 small unmanned aircraft system, sUAS, n—composed of the small unmanned aircraft (sUA) and all required on-board
subsystems, payload, control station, other required off-board subsystems, any required launch and recovery equipment, and C2
links between the sUA and the control station.
3.1.18 unmanned aircraft, UA, n—airborne portion of the sUAS.
3.1.19 uplink, n—any RF link from GCS to UA.
3.2 Acronyms:
3.2.1 BER—Bit Error Rate
F3002 − 22
3.2.2 C2—Command and Control
3.2.3 FCC—Federal Communications Commission
3.2.4 FCS—Flight Control Station
3.2.5 GAA—Governing Aviation Authority
3.2.6 GCS—Ground Control Station
3.2.7 GPS—Global Positioning System
3.2.8 HMI—Human/Machine Interface
3.2.9 PIC—Pilot in Command
3.2.10 RF—Radio Frequency
3.2.11 RFI—Radio Frequency Interference
3.2.12 RX—Receiver
3.2.13 sUA—Small Unmanned Aircraft
3.2.14 sUAS—Small Unmanned Aircraft System
3.2.15 TX—Transmitter
3.2.16 UA—Unmanned Aircraft
4. Applicability
4.1 This standard is written for all sUAS that are permitted to operate over a defined area and in airspace authorized by a
nation’snation’s GAA. It is assumed that one or more visual observers will provide for the sense and avoid requirement to avoid
collisions with other aircraft and that the maximum range and altitude at which the sUAS can be flown will be specified by the
nation’s GAA. Unless otherwise specified by a nation’s GAA, this standard applies only to UA that have a maximum gross takeoff
weight of 25 kg (55 lb) or less.
5. Functional Architecture
5.1 A high-level functional block diagram of the C2 system is presented in Fig. 1.
6. General Requirements
6.1 The following are general C2 requirements involving the system components listed below:
6.1.1 All C2 system and UA components shall minimize RFI so as not to degrade C2 link performance below acceptable levels.
6.1.2 All C2 system and UA components shall minimize RFI so as not to corrupt data transmitted or received over the C2 link.
6.1.3 All C2 system electronic components shall be protected from impacts that may occur during normal operation (an impact
rating of EN 62262 IK06 is recommended).
F3002 − 22
FIG. 1 High-Level Functional Block Diagram of the C2 System
6.1.4 All C2 system electronic components shall be protected from environmental conditions that may occur during normal
operation.
6.1.5 All C2 electronic devices shall be labeled with power requirements.
6.1.6 The C2 system’s antenna, associated RF connections and System Acceptance Test Report shall be furnished as part of the
C2 system.
F3002 − 22
6.1.7 Signal and power connectors for C2 electronic devices shall provide self-locking or positive locking connectors to ensure
continuity of power and signal transmission during normal operation.
6.1.8 The C2 system shall provide for mounting to a fixed surface using rigid or semi-rigid fasteners. (Non-rigid fasteners, such
as strings, rubber bands, and glue, are not permitted for this purpose.)
7. C2 System Spectrum Requirements
7.1 Small UAS operations using unlicensed bands shall be conducted in accordance with applicable regulations.
7.2 Small UA
...