国 上游夏大学 SHANGHAI JIAO TONG UNIVERSITY HALE UAV DESIGN 上游充通大 SHANGHAI JIAO TONG UNIVERSITY SHANGHAI JIAO TONG UNIVERSTT CONCEPTUAL DES IGNOF A HIGH ALTITUDE LONG ENDURANCE UAV Team members: 胡向嘉5124139009 程晨 5124139007 赵诗鸿5124139025 邱展 5124139026 赖生智5124139028 Adviser:Prof.Song -1-
HALE UAV DESIGN - 1 - SHANGHAI JIAO TONG UNIVERSITY CONCEPTUAL DESIGNOF A HIGH ALTITUDE LONG ENDURANCE UAV Team members: 胡向嘉 5124139009 程晨 5124139007 赵诗鸿 5124139025 邱展 5124139026 赖生智 5124139028 Adviser: Prof.Song
国 上游夏大学 SHANGHAI JIAO TONG UNIVERSITY HALE UAV DESIGN CONCEPTUAL DESIGNOF A HIGH ALTITUDE LONG ENDURANCE UAV ABSTRACT This paper presents the conceptual design process of a high altitude long endura nce unmanned aerial vehicle (HALE UAV).The HALE UAV is mainly used to carry out high reconnaissance,besides it can be used in airborne early warning, communications relay,electronic jamming and head off theater ballistic missiles etc.However,China's army have no such a high altitude,long endurance UAV which can beats US RQ4A.Therefore,we brought up this program.Following t he principles of aircraft conceptual designing,the authors complete configuratio n design,weight estimation,aerodynamic design,power plant design,performa nce analysis and economy analysis step by step.All in all,we try to present to re liable,economic and efficient UAV. Keyword:HALE,UAV,conceptual design -2-
HALE UAV DESIGN - 2 - CONCEPTUAL DESIGNOF A HIGH ALTITUDE LONG ENDURANCE UAV ABSTRACT This paper presents the conceptual design process of a high altitude long endura nce unmanned aerial vehicle (HALE UAV). The HALE UAV is mainly used to carry out high reconnaissance, besides it can be used in airborne early warning, communications relay, electronic jamming and head off theater ballistic missiles , etc. However, China’s army have no such a high altitude, long endurance UAV which can beats US RQ4A. Therefore, we brought up this program. Following t he principles of aircraft conceptual designing, the authors complete configuratio n design, weight estimation, aerodynamic design, power plant design, performa nce analysis and economy analysis step by step. All in all, we try to present to re liable, economic and efficient UAV. Keyword: HALE, UAV, conceptual design
国 上海文夏大学 SHANGHAI JIAO TONG UNIVERSITY HALE UAV DESIGN CONTENT ABSTRACT. -2- 1.Introduction.… -6- 1.1. Introduction of UAV.… -6- 1.1.1. Brief history of UAV........ 6- 1.1.2.Classification of UAV............... 7- 1.2. Introduction of HALE UAV. -8- 1.3. Marketing on China's HALE... -10- 2.Design requirements............ -11- 2.1. Main goal.… …-11- 2.2. Target design parameters............ -11- 3.Payload Analysis.… .-12- 3.1. Integrated sensor system -12- 3.2. Navigation system......... -12- 3.3. Airborne communication system-13- 3.4. Assistance defense system........................... -13- 3.5. System decision......... -13- 4. Primary weight estimation. -15- 4.1. Take-off weight analysis............. .-15- 4.2. Take-off weight estimation method .-15- 4.2.1. Calculate WPL.… .-16- 4.2.2. Initial Wro. .-16- 4.2.3. Calculate Wr/Wro.… …-16- 4.2.4. Calculate Wog/Wro..... -18- 4.2.5. Iteration progress.......... -19- 4.3. 5.Primary aerodynamic performance estimation...-21- 5.1. Maximum lift coefficient estimation.-21- 5.2. Zero-lift drag coefficient estimation.............. -21- 6. Thrust-to weight ratio and wing loading................. .-25- 6.1.1. Definition of thrust-to-weight ratio.......... .-25- 6.1.2. Experience statistics. .-25- 6.1.3. Empirical formula using maximum Mach number...........................-.25- 6.1.4. T/W from climb performance........... …-26- 6.1.5. The value of T/W obtained above26 6.2. Wing loading… .-26- 6.2.1. Definition of wing loading. -26- 6.2.2. Experience statistics. -27- 6.2.3. Determined from range... .-27- 6.2.4. Determined from maximum lift coefficient and maximum speed............-27- 6.2.5. The value of wing loading obtained above...-29- -3-
HALE UAV DESIGN - 3 - CONTENT ABSTRACT..................................................................................................................................- 2 - 1. Introduction ..........................................................................................................................- 6 - 1.1. Introduction of UAV...............................................................................................- 6 - 1.1.1. Brief history of UAV.......................................................................................- 6 - 1.1.2. Classification of UAV......................................................................................- 7 - 1.2. Introduction of HALE UAV .....................................................................................- 8 - 1.3. Marketing on China’s HALE ................................................................................ - 10 - 2. Design requirements.......................................................................................................... - 11 - 2.1. Main goal............................................................................................................ - 11 - 2.2. Target design parameters................................................................................... - 11 - 3. Payload Analysis................................................................................................................. - 12 - 3.1. Integrated sensor system ................................................................................... - 12 - 3.2. Navigation system .............................................................................................. - 12 - 3.3. Airborne communication system ....................................................................... - 13 - 3.4. Assistance defense system................................................................................. - 13 - 3.5. System decision.................................................................................................. - 13 - 4. Primary weight estimation................................................................................................. - 15 - 4.1. Take-off weight analysis..................................................................................... - 15 - 4.2. Take-off weight estimation method................................................................... - 15 - 4.2.1. Calculate WPL .............................................................................................. - 16 - 4.2.2. Initial WTO ................................................................................................... - 16 - 4.2.3. Calculate WF/WTO ....................................................................................... - 16 - 4.2.4. Calculate WOE/WTO ..................................................................................... - 18 - 4.2.5. Iteration progress....................................................................................... - 19 - 4.3. Estimation result ................................................................................................ - 19 - 5. Primary aerodynamic performance estimation ................................................................. - 21 - 5.1. Maximum lift coefficient estimation.................................................................. - 21 - 5.2. Zero-lift drag coefficient estimation................................................................... - 21 - 6. Thrust-to weight ratio and wing loading............................................................................ - 25 - 6.1.1. Definition of thrust-to-weight ratio............................................................ - 25 - 6.1.2. Experience statistics................................................................................... - 25 - 6.1.3. Empirical formula using maximum Mach number..................................... - 25 - 6.1.4. T/W from climb performance..................................................................... - 26 - 6.1.5. The value of T/W obtained above .............................................................. - 26 - 6.2. Wing loading ...................................................................................................... - 26 - 6.2.1. Definition of wing loading .......................................................................... - 26 - 6.2.2. Experience statistics................................................................................... - 27 - 6.2.3. Determined from range.............................................................................. - 27 - 6.2.4. Determined from maximum lift coefficient and maximum speed............. - 27 - 6.2.5. The value of wing loading obtained above ................................................ - 29 -
上海文夏大学 SHANGHAI JIAO TONG UNIVERSITY HALE UAV DESIGN 6.3. Constrain analysis......... .-29- 6.3.1. Determine the relationship of T/W and W/S at cruise requirements........-29- 6.3.2. Determine the relationship of T/W and W/S at takeoff condition.............-30- 6.3.3. Constrain analysis curve-32- 7.Aerodynamic configuration design........-34- 7.1.Joined wing design...................... -34 7.1.1. Joined wing introduction..-34- 7.1.2. Joined wing selection....... -36- 7.2. Airfoil selection-36 7.3. Wing span...... -39- 7.4. Taper rati0… .-39 7.5. Sweepback angle.......... .-40- 7.6. Mean aerodynamic chord... .-41- 8.Fuselage design and empennage design.... .-43- 8.1. Fuselage design.... …-43- 8.2. Empennage design.............. -45- 8.2.1.Airfoil selection....... …-46- 8.2.2.Tail size calculation................ -47- 9. Structure load design................. -49- 10. Powerplant-50- 10.1. Selection of engine.… -50- 10.1.1.Calculation of thrust at cruise....... …-50- 10.1.2.Calculation of maximum thrust....... …-50- 10.1.3.Choose an engine............ .-50- 10.2.Design of inlet.... …-51- 10.2.1.Working condition of inlet............. .-51- 10.2.2.Design of subsonic inlet.-52- 10.3. Design of nozzle.… -53- 10.3.1.The function and requirements of nozzle. -54- 10.3.2.The selection of nozzle's fundamental form. …-54- 10.3.3.The calculation of nozzle area........ .-54- 10.4.3D Model …-54- 11. Refine weight .-56- 11.1. Fuselage mass-56- 11.2. Nacelle mass... -57- 11.3. Tail 11.4. Landing gear,control surface and fixed equipment mass............... .-57- 11.5. Fuel mass.-57- 11.6. Ving mass...… -57- 11.7. Iteration of takeoff weight............. -58- 11.8. Estimation of center of gravity.......... -60- 12.Landing gear system. .-62- 12.1. Landing gear composition............ .-62- 12.2. The size of landing gear tire............ .-63- -4-
HALE UAV DESIGN - 4 - 6.3. Constrain analysis............................................................................................... - 29 - 6.3.1. Determine the relationship of T/W and W/S at cruise requirements........ - 29 - 6.3.2. Determine the relationship of T/W and W/S at takeoff condition............. - 30 - 6.3.3. Constrain analysis curve............................................................................. - 32 - 7. Aerodynamic configuration design .................................................................................... - 34 - 7.1. Joined wing design ............................................................................................. - 34 - 7.1.1. Joined wing introduction............................................................................ - 34 - 7.1.2. Joined wing selection ................................................................................. - 36 - 7.2. Airfoil selection .................................................................................................. - 36 - 7.3. Wing span........................................................................................................... - 39 - 7.4. Taper ratio .......................................................................................................... - 39 - 7.5. Sweepback angle................................................................................................ - 40 - 7.6. Mean aerodynamic chord .................................................................................. - 41 - 8. Fuselage design and empennage design............................................................................ - 43 - 8.1. Fuselage design .................................................................................................. - 43 - 8.2. Empennage design ............................................................................................. - 45 - 8.2.1. Airfoil selection........................................................................................... - 46 - 8.2.2. Tail size calculation ..................................................................................... - 47 - 9. Structure load design ......................................................................................................... - 49 - 10. Powerplant................................................................................................................. - 50 - 10.1. Selection of engine............................................................................................. - 50 - 10.1.1. Calculation of thrust at cruise .................................................................... - 50 - 10.1.2. Calculation of maximum thrust.................................................................. - 50 - 10.1.3. Choose an engine....................................................................................... - 50 - 10.2. Design of inlet .................................................................................................... - 51 - 10.2.1. Working condition of inlet.......................................................................... - 51 - 10.2.2. Design of subsonic inlet. ............................................................................ - 52 - 10.3. Design of nozzle ................................................................................................. - 53 - 10.3.1. The function and requirements of nozzle .................................................. - 54 - 10.3.2. The selection of nozzle’s fundamental form .............................................. - 54 - 10.3.3. The calculation of nozzle area.................................................................... - 54 - 10.4. 3D Model............................................................................................................ - 54 - 11. Refine weight ............................................................................................................. - 56 - 11.1. Fuselage mass .................................................................................................... - 56 - 11.2. Nacelle mass....................................................................................................... - 57 - 11.3. Tail mass............................................................................................................. - 57 - 11.4. Landing gear, control surface and fixed equipment mass.................................. - 57 - 11.5. Fuel mass............................................................................................................ - 57 - 11.6. Wing mass.......................................................................................................... - 57 - 11.7. Iteration of takeoff weight ................................................................................. - 58 - 11.8. Estimation of center of gravity........................................................................... - 60 - 12. Landing gear system................................................................................................... - 62 - 12.1. Landing gear composition.................................................................................. - 62 - 12.2. The size of landing gear tire ............................................................................... - 63 -
上海文夏大学 SHANGHAI JIAO TONG UNIVERSITY HALE UAV DESIGN 12.3. Detail parameter of landing gear ...-64- 12.4. Full-aircraft center of gravity-6- 13. Aerodynamic performance (Raymer's book).......-68- 13.1. 13.1.1.Lift curve slope. -68- 13.1.2. Maximum lift(clean)… .-69- 13.1.3.Angle of attack for maximum lift.... -69- 13.2.Drag. .-71- 13.2.1.Parasite (ero-lift)drag.-71- 13.2.2.Drag due to lift (induced drag).......... -74- 13.2.3.The total drag-75- 13.3. Lift drag ratio… -76- 13.4.Summary of aerodynamic characteristic. .-76- 14. Flight performance......... .-77- 14.1.Field performance........................ …-77- 14.2. Cruise performance...-79- 14.3. Static ceiling… …-80- 14.4. Summary of flight performance-81- 15. -82- 15.1. The method for analyzing Lcc and calculation.-82- 15.2. The composition of working time and cost in LAND DAPCA IV model...............-83- 15.3. Total operating cost -85- 15.3.1.Fuel c0st........ -86- 15.3.2.Maintenance cost.... …-86- 16. Conclusion and acknowledge...... .-88- 16.1. Conclusion .-88- 16.2. Acknowledge............. .-88- 17. Reference......... .-89- -5-
HALE UAV DESIGN - 5 - 12.3. Detail parameter of landing gear ....................................................................... - 64 - 12.4. Full-aircraft center of gravity.............................................................................. - 66 - 13. Aerodynamic performance (Raymer’s book) ............................................................. - 68 - 13.1. Lift ...................................................................................................................... - 68 - 13.1.1. Lift curve slope ........................................................................................... - 68 - 13.1.2. Maximum lift (clean).................................................................................. - 69 - 13.1.3. Angle of attack for maximum lift................................................................ - 69 - 13.2. Drag .................................................................................................................... - 71 - 13.2.1. Parasite (zero-lift) drag............................................................................... - 71 - 13.2.2. Drag due to lift (induced drag) ................................................................... - 74 - 13.2.3. The total drag ............................................................................................. - 75 - 13.3. Lift drag ratio...................................................................................................... - 76 - 13.4. Summary of aerodynamic characteristic............................................................ - 76 - 14. Flight performance..................................................................................................... - 77 - 14.1. Field performance.............................................................................................. - 77 - 14.2. Cruise performance............................................................................................ - 79 - 14.3. Static ceiling ....................................................................................................... - 80 - 14.4. Summary of flight performance......................................................................... - 81 - 15. Economics .................................................................................................................. - 82 - 15.1. The method for analyzing LCC and calculation .................................................. - 82 - 15.2. The composition of working time and cost in LAND DAPCA IV model............... - 83 - 15.3. Total operating cost............................................................................................ - 85 - 15.3.1. Fuel cost ..................................................................................................... - 86 - 15.3.2. Maintenance cost....................................................................................... - 86 - 16. Conclusion and acknowledge..................................................................................... - 88 - 16.1. Conclusion.......................................................................................................... - 88 - 16.2. Acknowledge...................................................................................................... - 88 - 17. Reference ................................................................................................................... - 89 -
上海文夏大学 SHANGHAI JIAO TONG UNIVERSITY HALE UAV DESIGN 1.Introduction 1.1.Introduction of UAV What is a UAV?UAV is an abbreviation of unmanned aerial vehicle.UAV is an aircraft without a human pilot aboard.Its flight is controlled either autonomously by onboard computers or by the remote control of a pilot on the ground or in another vehicle. A UAV equipped with mating systems of controlling,communication,data link and other supportive equipment is called a UAS,which is short for unmanned aircraft system.So we can know a typical UAS consists of the following: unmanned aircraft(UA) control system,such as ground control station(GCS) control link,a specialized datalink other related support equipment 1.1.1.Brief history of UAV We all know that most modern technologies were developed during wars.UAV is not an exception.Its history is also the history of wars in twentieth century. The earliest attempt at a powered unmanned aerial vehicle was A.M.Low's "Aerial Target"of 1916.Later,in November 1917,the Automatic Airplane was flown for representatives of the US Army.This led the army commission a project to build an "aerial torpedo",resulting in the Kettering Bug which first flew in 1918. While the Bug's revolutionary technology was successful,it was not in time to fight in the war,which ended before it could be fully developed and deployed. Nazi Germany produced and used various UAV aircraft during the course of WWII.Jet engines were applied after World War II. In 1959 the U.S.Air Force,concerned about losing pilots over hostile territory, began planning for the use of unmanned aircraft. In 1973 the U.S.military officially confirmed that they had been using UAVs in Southeast Asia(Vietnam).Over 5,000 U.S.airmen had been killed and over 1,000 more were missing or captured. During the 1973 Yom Kippur War,Soviet-supplied surface-to-air missile batteries in Egypt and Syria caused heavy damage to Israeli fighter jets.As a result,Israel developed the first UAV with real-time surveillance.With the maturing and miniaturization of applicable technologies as seen in the 1980s -6-
HALE UAV DESIGN - 6 - 1. Introduction 1.1. Introduction of UAV What is a UAV? UAV is an abbreviation of unmanned aerial vehicle. UAV is an aircraft without a human pilot aboard. Its flight is controlled either autonomously by onboard computers or by the remote control of a pilot on the ground or in another vehicle. A UAV equipped with mating systems of controlling, communication, data link and other supportive equipment is called a UAS, which is short for unmanned aircraft system. So we can know a typical UAS consists of the following: unmanned aircraft (UA) control system, such as ground control station (GCS) control link, a specialized datalink other related support equipment 1.1.1.Brief history of UAV We all know that most modern technologies were developed during wars. UAV is not an exception. Its history is also the history of wars in twentieth century. The earliest attempt at a powered unmanned aerial vehicle was A. M. Low's "Aerial Target" of 1916.Later, in November 1917, the Automatic Airplane was flown for representatives of the US Army. This led the army commission a project to build an "aerial torpedo", resulting in the Kettering Bug which first flew in 1918. While the Bug's revolutionary technology was successful, it was not in time to fight in the war, which ended before it could be fully developed and deployed. Nazi Germany produced and used various UAV aircraft during the course of WWII. Jet engines were applied after World War II. In 1959 the U.S. Air Force, concerned about losing pilots over hostile territory, began planning for the use of unmanned aircraft. In 1973 the U.S. military officially confirmed that they had been using UAVs in Southeast Asia (Vietnam). Over 5,000 U.S. airmen had been killed and over 1,000 more were missing or captured. During the 1973 Yom Kippur War, Soviet-supplied surface-to-air missile batteries in Egypt and Syria caused heavy damage to Israeli fighter jets. As a result, Israel developed the first UAV with real-time surveillance. With the maturing and miniaturization of applicable technologies as seen in the 1980s
上泽发通大学 SHANGHAI JIAO TONG UNIVERSITY HALE UAV DESIGN and 1990s,interest in UAVs grew within the higher echelons of the U.S. military. In the 1990s,the U.S.Department of Defense gave a contract to AAI Corporation along with Israeli company Malat.The U.S.Navy bought the AAI Pioneer UAV that was jointly developed by AAI and Malat.Many of these Pioneer and newly developed U.S.UAVs were used in the 1991 Gulf War. UAVs were seen to offer the possibility of cheaper,more capable fighting machines that could be used without risk to aircrews.As of 2012,the United States Air Force employed 7,494 UAVs-almost 1 in 3 USAF aircraft.The CIA has also operated UAVs. In 2013 it was reported that UAVs were used by at least 50 countries,several of which made their own:for example,Iran,Israel and China. 1.1.2.Classification of UAV UAVs typically fall into one of six functional categories: Target and decoy-providing ground and aerial gunnery a target that simulates an enemy aircraft or missile ● Reconnaissance-providing battlefield intelligence Combat-providing attack capability for high-risk missions Logistics-UAVs specifically designed for cargo and logistics operation Research and development-used to further develop UAV technologies to be integrated into field deployed UAV aircraft Civil and Commercial UAVs-UAVs specifically designed for civil and commercial applications They can also be categorized in terms of range/altitude and the following has been advanced as relevant at such industry events as ParcAberporth Unmanned Systems forum: Hand-held 2,000 ft(600 m)altitude,about 2 km range Close 5,000 ft(1,500 m)altitude,up to 10 km range NATO type 10,000 ft(3,000 m)altitude,up to 50 km range ● Tactical 18,000 ft(5,500 m)altitude,about 160 km range MALE (medium altitude,long endurance)up to 30,000 ft(9,000 m)and range over 200 km HALE(high altitude,long endurance)over 30,000 ft(9,100 m)and indefinite range HYPERSONIC high-speed,supersonic(Mach 1-5)or hypersonic (Mach 5+)50,000 ft(15,200 m)or suborbital altitude,range over 200 km ORBITAL low earth orbit (Mach 25+) CIS Lunar Earth-Moon transfer CACGS Computer Assisted Carrier Guidance System for UAVs -7-
HALE UAV DESIGN - 7 - and 1990s, interest in UAVs grew within the higher echelons of the U.S. military. In the 1990s, the U.S. Department of Defense gave a contract to AAI Corporation along with Israeli company Malat. The U.S. Navy bought the AAI Pioneer UAV that was jointly developed by AAI and Malat. Many of these Pioneer and newly developed U.S. UAVs were used in the 1991 Gulf War. UAVs were seen to offer the possibility of cheaper, more capable fighting machines that could be used without risk to aircrews. As of 2012, the United States Air Force employed 7,494 UAVs - almost 1 in 3 USAF aircraft. The CIA has also operated UAVs. In 2013 it was reported that UAVs were used by at least 50 countries, several of which made their own: for example, Iran, Israel and China. 1.1.2.Classification of UAV UAVs typically fall into one of six functional categories: Target and decoy – providing ground and aerial gunnery a target that simulates an enemy aircraft or missile Reconnaissance – providing battlefield intelligence Combat – providing attack capability for high-risk missions Logistics – UAVs specifically designed for cargo and logistics operation Research and development – used to further develop UAV technologies to be integrated into field deployed UAV aircraft Civil and Commercial UAVs – UAVs specifically designed for civil and commercial applications They can also be categorized in terms of range/altitude and the following has been advanced as relevant at such industry events as ParcAberporth Unmanned Systems forum: Hand-held 2,000 ft (600 m) altitude, about 2 km range Close 5,000 ft (1,500 m) altitude, up to 10 km range NATO type 10,000 ft (3,000 m) altitude, up to 50 km range Tactical 18,000 ft (5,500 m) altitude, about 160 km range MALE (medium altitude, long endurance) up to 30,000 ft (9,000 m) and range over 200 km HALE (high altitude, long endurance) over 30,000 ft (9,100 m) and indefinite range HYPERSONIC high-speed, supersonic (Mach 1–5) or hypersonic (Mach 5+) 50,000 ft (15,200 m) or suborbital altitude, range over 200 km ORBITAL low earth orbit (Mach 25+) CIS Lunar Earth-Moon transfer CACGS Computer Assisted Carrier Guidance System for UAVs
国上泽文通大学 SHANGHAI JIAO TONG UNIVERSITY HALE UAV DESIGN Our design is a conceptual design of HALE i.e.high altitude,long endurance UAV. 12. Introduction of HALE UAV From last section,we have known some basics of UAV.Since our project is to design a HALE UAV,here we will give several examples of world's famous large UAVs to give a overall view of the world's advanced level in UAV field. 1.IAI Heron Figure 1-1 IAl Heron UAV The IAI Heron (Machatz-1)is a medium-altitude long-endurance unmanned aerial vehicle(UAV)developed by the Malat(UAV)division of Israel Aerospace Industries.It is capable of Medium Altitude Long Endurance(MALE)operations of up to 52 hours'duration at up to 10.5 km(35,000 ft).It has demonstrated 52 hours of continuous flight,but the effective operational maximal flight duration is less,according to payload and flight profile.There is a new version,Heron TP,also known as IAI Eitan.On 11 September 2005,it was announced that the Israel Defense Forces purchased US$50 million worth of Heron systems.Figure 1-1 shows IAI Heron UAV. 2.MQ-9 Reaper -8-
HALE UAV DESIGN - 8 - Our design is a conceptual design of HALE i.e. high altitude, long endurance UAV. 1.2. Introduction of HALE UAV From last section, we have known some basics of UAV. Since our project is to design a HALE UAV, here we will give several examples of world’s famous large UAVs to give a overall view of the world’s advanced level in UAV field. 1. IAI Heron Figure 1 - 1 IAI Heron UAV The IAI Heron (Machatz-1) is a medium-altitude long-endurance unmanned aerial vehicle (UAV) developed by the Malat (UAV) division of Israel Aerospace Industries. It is capable of Medium Altitude Long Endurance (MALE) operations of up to 52 hours' duration at up to 10.5 km (35,000 ft). It has demonstrated 52 hours of continuous flight, but the effective operational maximal flight duration is less, according to payload and flight profile. There is a new version, Heron TP, also known as IAI Eitan. On 11 September 2005, it was announced that the Israel Defense Forces purchased US$50 million worth of Heron systems. Figure 1 – 1 shows IAI Heron UAV. 2. MQ-9 Reaper
SHANGHAI JIAO TONG UNIVERSITY HALE UAV DESIGN Figure 1-2 MQ-9 Reaper The General Atomics MQ-9 Reaper(formerly named Predator B)is an unmanned aerial vehicle(UAV)capable of remote controlled or autonomous flight operations,developed by General Atomics Aeronautical Systems(GA- ASI)primarily for the United States Air Force.UAVs are also commonly referred to as drones by the media.The MQ-9 and other UAVs are referred to as Remotely Piloted Vehicles/Aircraft(RPV/RPA)by the U.S.Air Force to indicate their human ground controllers.The MQ-9 is the first hunter-killer UAV designed for long-endurance,high-altitude surveillance.Figure 1-2 shows MQ-9 Reaper 3.RQ-4A Global Hawk Figure 1-3 RQ-4A Global Hawk The Northrop Grumman RQ-4A Global Hawk is an unmanned(UAV) surveillance aircraft.It was initially designed by Ryan Aeronautical(now part of -9-
HALE UAV DESIGN - 9 - Figure 1 - 2 MQ-9 Reaper The General Atomics MQ-9 Reaper (formerly named Predator B) is an unmanned aerial vehicle (UAV) capable of remote controlled or autonomous flight operations, developed by General Atomics Aeronautical Systems (GAASI) primarily for the United States Air Force. UAVs are also commonly referred to as drones by the media. The MQ-9 and other UAVs are referred to as Remotely Piloted Vehicles/Aircraft (RPV/RPA) by the U.S. Air Force to indicate their human ground controllers. The MQ-9 is the first hunter-killer UAV designed for long-endurance, high-altitude surveillance. Figure 1 - 2 shows MQ-9 Reaper 3. RQ-4A Global Hawk Figure 1 - 3 RQ-4A Global Hawk The Northrop Grumman RQ-4A Global Hawk is an unmanned (UAV) surveillance aircraft. It was initially designed by Ryan Aeronautical (now part of
上游夏大学 SHANGHAI JIAO TONG UNIVERSITY HALE UAV DESIGN Northrop Grumman),and known as Tier II+during development.In role and operational design,the Global Hawk is similar to the Lockheed U-2.The Global Hawk is operated by the United States Air Force and U.S.Navy.It is used as a high-altitude platform covering the spectrum of intelligence collection capability to support forces in worldwide military operations.According to the United States Air Force,the superior surveillance capabilities of the aircraft allow more precise weapons targeting and better protection of friendly forces. The global hawk is also our referring standard.Figure 1-3 shows RQ-4A Global Hawk. 1.3.Marketing on China's HALE From above we can see the world's technique in UAV is quite mature and advanced.As for in China,large UAV is also developing.Here we take Pterosauria(Yi Long)as an example to show china's UAV technique level. 海 Figure 1-4 YI IONG UAV The Pterosauria is a dual-use MALE(medium altitude,long endurance)UAV developed by 611 institution,equipped with a 100HP piston engine.It is qualified for full-autonomously flat-wheel landing and cruising.Its appearance is quite similar to MQ-9 while weight similar to MQ-1.Its weighs 1100 kg and the length is 9 m,the span is 14m.The ceiling of Pterosauria is about 5300m and it is capable for a range of 4000km. Though the Pterosauria is a sufficient piece of work I China's manufacturer industry,there is still a gap between the world's advanced level and China's.It is necessary to design a real HALE for China.This is where our design idea generates. -10-
HALE UAV DESIGN - 10 - Northrop Grumman), and known as Tier II+ during development. In role and operational design, the Global Hawk is similar to the Lockheed U-2. The Global Hawk is operated by the United States Air Force and U.S. Navy. It is used as a high-altitude platform covering the spectrum of intelligence collection capability to support forces in worldwide military operations. According to the United States Air Force, the superior surveillance capabilities of the aircraft allow more precise weapons targeting and better protection of friendly forces. The global hawk is also our referring standard. Figure 1 - 3 shows RQ-4A Global Hawk. 1.3. Marketing on China’s HALE From above we can see the world’s technique in UAV is quite mature and advanced. As for in China, large UAV is also developing. Here we take Pterosauria (Yi Long) as an example to show china’s UAV technique level. Figure 1 - 4 YI lONG UAV The Pterosauria is a dual-use MALE (medium altitude, long endurance) UAV developed by 611 institution, equipped with a 100HP piston engine. It is qualified for full-autonomously flat-wheel landing and cruising. Its appearance is quite similar to MQ-9 while weight similar to MQ-1. Its weighs 1100 kg and the length is 9 m, the span is 14m. The ceiling of Pterosauria is about 5300m and it is capable for a range of 4000km. Though the Pterosauria is a sufficient piece of work I China’s manufacturer industry, there is still a gap between the world’s advanced level and China’s. It is necessary to design a real HALE for China. This is where our design idea generates
