ASTM F3002-2014a Standard Specification for Design of the Command and Control System for Small Unmanned Aircraft Systems &40 sUAS&41 《小型无人机系统(sUAS)指挥和控制系统设计的标准规格》.pdf

《ASTM F3002-2014a Standard Specification for Design of the Command and Control System for Small Unmanned Aircraft Systems &40 sUAS&41 《小型无人机系统(sUAS)指挥和控制系统设计的标准规格》.pdf》由会员分享，可在线阅读，更多相关《ASTM F3002-2014a Standard Specification for Design of the Command and Control System for Small Unmanned Aircraft Systems &40 sUAS&41 《小型无人机系统(sUAS)指挥和控制系统设计的标准规格》.pdf（6页珍藏版）》请在麦多课文档分享上搜索。

1、Designation: F3002 14F3002 14aStandard Specification forDesign of the Command and Control System for SmallUnmanned Aircraft Systems (sUAS)1This standard is issued under the fixed designation F3002; the number immediately following the designation indicates the year oforiginal adoption or, in the cas

2、e of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification is provided as a consensus standard in support of an application to a na

3、tions 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 responsibilityof the user of this standar

4、d to establish appropriate safety and health practices and determine the applicability of regulatorylimitations prior to use.2. Referenced Documents2.1 ASTM Standards:2F2910 Specification for Design, Construction, and Test of a Small Unmanned Aircraft System (sUAS)F2911 Practice for Production Accep

5、tance of a Small Unmanned Aircraft System (sUAS)F3003 Specification for Quality Assurance of a Small Unmanned Aircraft System (sUAS)2.2 EN Standard:3EN 62262 Degrees of protection provided by enclosures for electrical equipment against external mechanical impacts (IK code)2.3 IEC Standard:3IEC 60529

6、 Degrees of protection provided by enclosures (IP Code)3. Terminology3.1 Definitions:3.1.1 bit error rate detection, BER, nrate at which errors occur in a transmission system; applicable to any system thattransmits data over a network of some form in which noise, interference, and phase jitter may c

7、ause degradation of the digitalsignal.3.1.2 command and control (C2) link(s), nsafety-critical radio-frequency (RF) link(s) between the ground control station(GCS) and the unmanned aircraft (UA).3.1.3 C2 range, ndistance between GCS and UA at which positive control of the UA can be maintained.3.1.4

8、downlink, nany RF link from UA to GCS.3.1.5 flight control system, FCS, ncomposed of system components intended to take GCS commands via a C2 link and controlflight control surfaces and propulsion systems.3.1.5.1 DiscussionThe FCS may include autopilot functions, lost-link functions, fly-away protec

9、tion functions, payload functions, and navigationfunctions. The FCS may be contained in one discrete component or multiple discrete components.1 This test method specification is under the jurisdiction ofASTM Committee F38 on UnmannedAircraft Systems and is the direct responsibility of Subcommittee

10、F38.01on Airworthiness.Current edition approved Jan. 15, 2014June 1, 2014. Published January 2014July 2014. Originally approved in 2014. Last previous edition approved in 2014 as F3002 14.DOI: 10.1520/F3002-14.10.1520/F3002-14A.2 For referencedASTM standards, visit theASTM website, www.astm.org, or

11、contactASTM Customer Service at serviceastm.org. For Annual Book of ASTM Standardsvolume information, refer to the standards Document Summary page on the ASTM website.3 Available from American National Standards Institute (ANSI), 25 W. 43rd St., 4th Floor, New York, NY 10036, http:/www.ansi.org.This

12、 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. Becauseit may not be technically possible to adequately depict all changes accurately, ASTM recommends that users consult prior edition

13、s as appropriate. In all cases only the current versionof the standard as published by ASTM is to be considered the official document.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States13.1.6 fly away, nunintended flight outside of operat

14、ional boundaries (altitude/airspeed/lateral) as the result of a failure of thecontrol element or onboard systems, or both.3.1.7 fly-away protection system, na system that will return the UA safely to the surface, or keep the UA within the intendedoperational area, when the C2 link between the pilot

15、and the UA is lost.3.1.8 ground control station, GCS, na land- or sea-based control center that provides the facilities for human control of UA.3.1.9 licensed band, nany frequency or range of frequencies in which transmission requires permission from a governing body(for example, the Federal Communi

16、cations Commission FCC).3.1.10 link error, ndegradation of the digital signal between the GCS and the UA that can be monitored by techniquesincluding BER detection.3.1.11 link integrity, nacceptable rate of transactions completed with undetected error.3.1.12 link timeout, ntime between the actual lo

17、st-link event being validated and the system initiating the lost-link procedure.3.1.13 lost link, noccurrence in which the pilot in command (PIC) has lost the ability to control positively the sUAS becauseof degradation, loss or interruption of the necessary control or monitoring link(s), or both.3.

18、1.14 manufacturer, nentity responsible for assembly and integration of components and subsystems to create a safeoperating sUAS.3.1.15 pilot in command, PIC, nthe pilot responsible for the operation and safety of the UA during flight time.3.1.16 positive control, na condition in which commanded chan

19、ges 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, ncomposed of the small unmanned aircraft (sUA) and all required on-boardsubsystems, payload, control station, other required off-board subsystems, any required l

20、aunch and recovery equipment, and C2links between the sUA and the control station.3.1.18 unmanned aircraft, UA, nairborne portion of the sUAS.3.1.19 uplink, nany RF link from GCS to UA.3.2 Acronyms:3.2.1 BERBit Error Rate3.2.2 C2Command and Control3.2.3 FCCFederal Communications Commission3.2.4 FCSF

21、light Control Station3.2.5 GAAGoverning Aviation Authority3.2.6 GCSGround Control Station3.2.7 GPSGlobal Positioning System3.2.8 HMIHuman/Machine Interface3.2.9 PICPilot in Command3.2.10 RFRadio Frequency3.2.11 RFIRadio Frequency Interference3.2.12 RXReceiver3.2.13 sUASmall Unmanned Aircraft3.2.14 s

22、UASSmall Unmanned Aircraft System3.2.15 TXTransmitter3.2.16 UAUnmanned Aircraft4. Applicability4.1 This standard is written for all sUAS that are permitted to operate over a defined area and in airspace authorized by anations GAA. It is assumed that one or more visual observers will provide for the

23、sense and avoid requirement to avoid collisionswith other aircraft and that the maximum range and altitude at which the sUAS can be flown will be specified by the nations GAA.Unless otherwise specified by a nations GAA, this standard applies only to UA that have a maximum gross takeoff weight of 25k

24、g (55 lb) or less.5. Functional Architecture5.1 A high-level functional block diagram of the C2 system is presented in Fig. 1.F3002 14a26. General Requirements6.1 The following are general C2 requirements involving the system components listed below:6.1.1 All C2 system and UAcomponents shall minimiz

25、e 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 op

26、eration (an impactrating of EN 62262 IK06 is recommended).FIG. 1 High-Level Functional Block Diagram of the C2 SystemF3002 14a36.1.4 All C2 system electronic components shall be protected from environmental conditions that may occur during normaloperation.6.1.5 All C2 electronic devices shall be lab

27、eled with power requirements.6.1.6 The C2 systems antenna, associated RF connections and SystemAcceptance Test Report shall be furnished as part of theC2 system.6.1.7 Signal and power connectors for C2 electronic devices shall provide self-locking or positive locking connectors to ensurecontinuity o

28、f 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, suchas strings, rubber bands, and glue, are not permitted for this purpose.)7. C2 System Spectrum Requirements7.1 Small

29、 UAS operations using unlicensed bands shall be conducted in accordance with applicable regulations.7.2 Small UAS operations using a licensed band shall obtain approval to use that band from the appropriate governing agency.8. C2 Link8.1 Functional RequirementsThe C2 link shall provide C2 link statu

30、s to the UAFCS to allow the UAFCS to initiate lost-linklogic when C2 link connectivity is lost.8.2 Performance Requirements:8.2.1 The rate of C2 link transactions completed with undetected error shall not exceed 0.001 %.8.2.2 The C2 link shall be capable of transmitting the minimum set of data requi

31、red by the GAA.8.2.3 The C2 link shall be capable of receiving the minimum set of data required by the GAA.8.2.4 The C2 link shall transmit all data that are safety critical as established by the manufacturer.8.2.5 Aloss of connectivity for longer than a maximum duration to be established by the cou

32、ntrys GAAshall trigger a lost-linkcondition.8.2.6 The C2 link shall prevent unauthorized ground control stations from pairing with or controlling the UA.8.2.7 The C2 link shall be rated by the manufacturer with maximum range.8.2.8 C2 radios shall be labeled with operating frequency and channel infor

33、mation.8.3 Design RequirementsThe C2 link(s) shall be encrypted.8.3 Testing RequirementsIf a C2 downlink is required by the manufacturer for safety-of-flight or operational requirements, orboth, the C2 link data integrity shall be monitored while C2 system elements are emitting RF and the GCS transm

34、itter is operatingat maximum transmission power.9. GCS9.1 Operational Requirements:9.1.1 There shall be a means for verifying before flight that the fly-away protection system is capable of functioning properlyduring flight.9.2 Functional Requirements:9.2.1 If a C2 downlink is required by the manufa

35、cturer for safety-of-flight or operational requirements, or both, the GCS shallbe capable of providing position and altitude data to the PIC.9.2.2 If a C2 downlink is required by the manufacturer for safety-of-flight or operational requirements, or both, the GCS shallprovide the capability to monito

36、r the C2 uplink bit error rate.9.2.3 If a C2 downlink is required by the manufacturer for safety-of-flight or operational requirements, or both, the GCS shallprovide the capability to monitor the C2 downlink bit error rate.9.2.4 If a C2 downlink is required by the manufacturer for safety-of-flight o

37、r operational requirements, or both, the GCS shallprovide the capability to monitor link status.9.2.5 If a C2 downlink is required by the manufacturer for safety-of-flight or operational requirements, or both, the GCS shallprovide an alert to the PIC when a lost-link condition is entered.9.2.6 If a

38、C2 downlink is required by the manufacturer for safety-of-flight or operational requirements, or both, the GCS shallprovide an alert to the PIC if the uplink or downlink message error rate exceeds 0.001.9.2.7 If a C2 downlink is required by the manufacturer for safety-of-flight or operational requir

39、ements, or both, the GCS shallprovide an alert to the PIC when an incompatibility is detected between the GCS and the systems with which it communicates.9.2.8 If a C2 downlink is required by the manufacturer for safety-of-flight or operational requirements, or both, the GCS shallprovide a lost-link

40、condition status to the PIC.9.2.9 A backup power supply capable of lasting long enough for a safe UA recovery shall be provided.9.2.10 If warning lights are used, red shall signify a warning, yellow shall signify caution, and green shall signify satisfactorystatus.F3002 14a49.2.11 If warning lights

41、are used, a unique audible alarm tone consistent with the warning lights shall sound for a maximumof two seconds.9.2.12 If a C2 downlink is required by the manufacturer for safety-of-flight or operational requirements, or both, displays offlight-critical information, including fuel level, battery st

42、atus, and conformance with restrictions on airspeed, altitude, and lateraldistance from the GCS, shall be made readily available to the PIC.9.2.13 The GCS shall provide the capability of performing a reduced-range test to test link capability in situ.9.3 Interoperability Requirements:9.3.1 The GCS s

43、hall verify that it is configured to control the intended UA before flight.9.4 Design Requirements:9.4.1 If a C2 downlink is required by the manufacturer for safety-of-flight or operational requirements, or both, the GCS shallprovide a visible indication of link status.9.4.2 The GCS shall provide a

44、manual or automatic means of interfacing a C2 link reduced-range attenuator between the C2RF source and the link antenna.9.4.3 The GCS shall provide a capability to test and measure the maximum RF output of the C2 link to and from the UA ata specified line-of-sight distance.9.4.4 The GCS shall provi

45、de the operator an interface for interpreting the results of the C2 link reduced-range test.9.4.5 The GCS shall prevent the PIC from launching the UA while the C2 link reduced-range attenuator is in use.9.5 Testing:9.5.1 The GCS transmitter maximum range value shall be tested.9.5.2 The GCS receiver

46、maximum range value shall be tested.10. Unmanned Aircraft10.1 Operational Requirements:10.1.1 The responses to a lost-link condition shall include a combination of one or more of the following actions:10.1.1.1 Landing the UA after the expiration of the C2 link timeout counter,10.1.1.2 Returning the

47、UA to the UA launch/takeoff location or some other previously designated location within the operationarea,10.1.1.3 Termination of the flight in a predictable manner after confirmation of lost link and the expiration of the C2 link timeoutcounter, or10.1.1.4 Loitering within the operational area for

48、 a specified period of time before initiating one of the above three techniques.10.2 Functional Requirements:10.2.1 If a C2 downlink is required by the manufacturer for safety-of-flight or operational requirements, or both, the UA shalltransmit position and altitude data to the PIC.10.2.2 The UA sha

49、ll record any occurrence of a lost-link condition.10.2.3 The UA shall execute lost-link logic upon occurrence of a lost-link condition.10.3 Performance Requirements:10.3.1 The UA shall be capable of remaining in a contained area if one has been specified by the PIC.10.4 Interoperability Requirements:10.4.1 A C2 lost link shall not cause UA system failures.10.4.2 The lost-link function shall be capable of executing after the C2 uplink capability fails.10.4.3 The lost-link function shall be capable of executing after the C2 downlin