Micro and Mini UAV Airworthiness, European and NATO Activities

Transcription

1 Recent Development in Unmanned Aircraft Systems Micro and Mini UAV Airworthiness, European and NATO Activities iti Fulvia Quagliotti Politecnico di Torino Department of Aerospace Engineering Torino, Italy 1

2 Index Review of the state-of-the-art the art Politecnico di Torino experiences: Quadrotor,MH600, MH2000, MH850 Certification and flight 2

3 Review of the state-of-the-art Review of state-of-the-art t th t Politecnico di Torino experiences: Quad-rotor, MH600, MH2000, MH850 Certification and flight 3

4 Micro Aerial Vehicles Fixed Wing Configurations Flapping Wing Configurations Rotary Wing Configurations 4

5 Characteristics of Fixed Wing Inability of hovering flight High stall speed Good performances in windy conditions Traditional aerodynamic control devices Large wing surface to accommodate systems and payloads 5

6 Fixed Wing UAV (IV) MicroHawk (POLITECNICO DI TORINO Dept. of Aerospace Engineering) Project EU IST/FET: MARVEL (Micro Air Vehicles for Multi-purpose Remote Monitoring and Sensing) Engine: electric DC Maximum dimension: 150 mm Gross weight: 70 g Stall speed: 7 m/s Patent n. TO2003A PCT/IB2004/ Politecnico di Torino 6

7 Fixed Wing UAV (V) Pointer Predator Global Hawk LARGE Pioneer Hunter MEDIUM MH600 MH150 MH2000 SMALL Black Widow MICRO 7

8 Characteristics of Flapping Wing Critical mathematical modeling of motion mechanism Very limited endurance Strong limitation of payload weight Critical performances in windy condition 8

9 Characteristics of Rotary Wing Construction complexity Control complexity Capability of hovering flight Limitation of payload weight 9

10 Advantages and drawbacks of rotary wing REQUIREMENTS: Adequate payload (digital it camera and/or sensors) Good stability performances ADVANTAGES: Good maneuvrability and agility performances Capability to hover on a targett and fly vertically Ability to fly in confined areas DRAWBACKS: Complexity of the control system Adequate endurance values 10

11 Politecnico di Torino experiences: Quad-rotor, MH600, MH2000, MH850 Review of state-of-the-art Politecnico di Torino experiences: Quad-rotor, MH600, MH2000, MH850 Certification and flight 11

12 Quad-Rotor UAV Quad-Rotor (POLITECNICO DI TORINO Department of Aerospace Engineering) Engine: DC motor External dimension: 80 cm Weight: 1.6 kg Endurance: minutes Payload: 350 g 12

13 MicroHawk Research Program (I) 13

14 MicroHawk Research Program (II) MARVEL Project MicroHawk 150 PNRA Piano Nazionale Ricerca in Antartide (MicroHawk 2000) Regione Piemonte Research Program (MicroHawk 2000) ITHACA Program (MicroHawk 2000) 14

15 MicroHawk Research Program (III) Research activity: Politecnico di Torino Aerospace Engineering Department Production, simulation, flight test activities: MAVTech (Micro Aerial Vehicles Technology), a Spin-off of Politecnico di Torino 15

16 MicroHawk platforms (I) Project started within EU MARVEL program Fixed wing Tail-less ill configuration Double vertical fin Electric propulsion system Five models having different dimensions (MH150, MH300, MH600, MH1000, MH2000) 16

17 MicroHawk platforms (II) Advantages: adequate aerodynamic efficiency concentrated masses and small weight absence of severe aeroelastic problems configuration spin resistant and stable Disadvantages: difficulty to apply high lift devices limited payloads 17

18 MicroHawk platforms (III) MH150: wingspan 150 mm weight 35 g very short range remotely piloted MH300: wingspan 337 mm weight 105 g basic reconnaissance mission remote monitoring by micro camera remotely piloted 18

19 MH600 platform wingspan gp 600 mm wing area m 2 mass 620 g static margin > 0.08 wing load < 3.5 kg/ m 2 flight envelope range: 8-20 m/s at sea level flight endurance: 30 min (flight speed: 15 m/s) On board camera 19

20 MH2000 platform wingspan 2000 mm wing area m 2 electric (LiPo batteries) or ICE mass 8/9 kg with autopilot payload 2 kg flight endurance: 40 min at 15 m/s (electric engine version) 75 min at 15 m/s (ICE version) Adopted by ITHACA (Information Technology for Humanitarian Assistance, Cooperation and Action) Program 20

21 MH 850 Concept UAV for alpine surveillance missions Constraints High altitude Low temperature Adverse weather Strong winds Lack of infrastructures Requirements Light weight Simple operations High power Endurance and speed Hand/catapult launch Rugged structure 21

22 MH 850 Possible missions Environmental monitoring Protected area monitoring Cartographic surveys Support in case of natural disasters Fire prevention Floods 22

23 MH Characteristics Flexible Light / Low cost Man portable / Hand launched RC /Autonomous flight Electric propulsion Long endurance Wing Span 85 cm Weight 1000 g Payload g Cruising speed 45 km/h Endurance 1 h 15 min 23

24 MH 850 Structural project (I) Aims of the structural project: Easy and cheap manufacturing process User friendly to assembly Easy access to all internal components Crashableh structure t (no damage to third parties) 24

25 MH 850 Structural project (II) Wing EPP (Expanded PolyPropylene) Low weight Easy/low cost manufacturing Easy to repair in case of crash damage Good quality of superficial finish 25

26 Typical mission profile take-off procedure in flight-operations ti autonomous or remote control landing procedure 26

27 MH Support equipment Catapult and Bag Safe launch Easy deployment Packable Easy transportation 27

28 MH850 - Flight test Performance and flight qualities Take-off and landing In flight behaviour Performance Different payloads, CG position, batteries type, propeller characteristics Payload and position link integration Video quality Range of transmission Position link accuracy Autopilot integration Gains tuning Mission demo 28

29 MH850 - Flight test results Performance and flight qualities Performances match the expectations Flight qualities are very satisfactory No anomalous behaviour is noticed in flight Catapult launch and landings are always satisfactory Payload and position link integration Optical payload integrated with good results Position link integration ti in progress Autopilot integration Hardware integration and ground test completed Waiting for civil aviation authority clearance for flight test 29

30 Pilot Training Training on airfield Simulation platform 30

31 Example of monitoring mission Images taken from an altitude li of f120 m 31

32 Certification and flight Review of state-of-the-art Politecnico i di Torino experiences: Quadrotor, MH600, MH2000, MH850 Certification and flight 32

33 Open issues for civil UAS The main open issues for civil UAS are: operations safety level (mission type) collision avoidance technology communications reliability power p and propulsion p system reliability launch and recovery systems certification need to provide a Flight Data Recorder-like system 33

34 Civil UAS airworthiness (I) () Two regulatory development approaches 1. Safety approach: evaluation of the level of risks by third parties*. Its value depends both on UAS platform and mission type and duration Advantages: the approach allows to fly the UAS without full compliance of requirements (level of risks evaluation) Drawback: the level of risks is evaluated case by case for each UAS and mission (limitations to fly in restricted/controlled airspace) 2. Conventional approach with airworthiness codes: definition of a code of requirements, in form of standards, for the UAS and its subsystems Advantages: certification process performed once; changes are accepted in the mission profile and in the subsystems (type certification procedures similar to the manned aircraft ones) Drawback: to receive the certification UAS must comply all the requirements, if not it cannot fly at all * number of fatalities and/or injuries per hour of flight 34

35 Civil UAS airworthiness (II) For commercial applications the second approach is more convenient, similar to manned aircraft certification and it is the guideline for all the regulatory bodies which are developing airworthiness and certificate requirements for UAS. But 30% of current manned aviation regulation applies to UAS without modifications* 54% could be applied with some revisions* 16% do not apply* Manned regulations can be used as guideline but different approaches are needed for UASs * source: FAA Center of excellence for General Aviation Research (CGAR) 35

36 European regulation In Europe: Article 4.4 of EC Regulation 216/2008 Certification and operational requirements for UAS with a MTOM below 150kg Certification and operational requirements UAS with a MTOM above 150kg European National Aviation Authorities i (NAA) In Italy issued according to the ENAC Circular for UAS with MTOM <150 kg or designed for research activities, under development. Currently, UAS can fly in non-segregated airspaces only with a Permit to Fly issued according to ENAC Circular NAV 32C European Aviation Safety Agency (EASA) - E.Y UAS Policy Statement Airworthiness Certification of UAS, based on EASA Part 21 36

37 Open issues for mini and micro UAS In order to achieve the complete integration in the National Airspace System (NAS), UAS should have the same level of safety as manned aircraft Mini and micro UAS can operate only in Visual Line-of-Sight (VLOS) operations, limited, if necessary, in endurance, range, max height, max speed, minimum distance from an airport Mini and micro UAS require a single pilot, due to VLOS limitation, single-task missions with aforementioned limitations 37

38 UAS classification (I) Military bodies are forth with respect to civil regulatory bodies in developing UAS airworthiness requirements due to: 1. the lesson-learned with operational use of UAS 2. civil stakeholders does not have a unique regulatory body for mini and micro UAS whereas European and US military have the NATO. A definitive classification for UAS does not exist either for military or civil bodies DGAA Classification table (AER P2) 38

39 UAS classification (II) NATO JCGUAV (Joint Capability Group on UAV) Classification table 39

40 STANAG 4703 The most complete (and almost definitive) regulation for mini and micro UAS is the NATO STANAG 4703 STANAG Light UAV Systems Airworthiness Requirements (USAR-LIGHT) for North Atlantic Treaty Organization (NATO) Military UAV Systems This document contains the minimum set of technical airworthiness requirements intended primarily for the airworthiness certification of fixed-wing UAV Systems with a maximum take-off weight of 150 kg or less that intend to regularly operate in non- segregated airspace. Developed on the basis of: STANAG 4671 (UAV Systems Airworthiness Requirements for North Atlantic Treaty Organization Military UAV Systems) CS-VLA (Certification Specifications for Very Light Aeroplanes) CS-22 Amendment 1 (Certification Specifications for Sailplanes And Powered Sailplanes) l ASTM F (Standard Specification for Design and Performance of a Light Sport Airplane) DEF STAN (Safety Management Requirements for Defence Systems) 40

41 An example: the case of MH850 Regulation of UAVs with mass below 150 Kg has still not been implemented by European authority (EASA). Regulation of small UAVs is responsibility of national authorities. In June 2009, the Italian civil aviation authority (ENAC, Ente Nazionale per l Aviazione Civile) issued a draft document giving guidelines for small UAVs certification. The first step is the request for a Permit to Fly. April, Von Karman Institute for Fluid Dynamics 41

42 Permit to fly Main requirements to obtain a permit to fly for an UAV are: Aircraft Identification Purpose and type of operations Flight area identification General Airworthiness Review Flight envelope Structure Flight and ground loads Flight minimum requirements Safety assessment 42

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