Hindustan Aeronautics Ltd

Bangalore, India

Hindustan Aeronautics Ltd

Bangalore, India
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Global Military Helicopters market competition by top manufacturers, with production, price, revenue (value) and market share for each manufacturer; the top players including Geographically, this report is segmented into several key Regions, with production, consumption, revenue (million USD), market share and growth rate of Military Helicopters in these regions, from 2012 to 2022 (forecast), covering North America Europe China Japan Southeast Asia India On the basis of product, this report displays the production, revenue, price, market share and growth rate of each type, primarily split into Attack Helicopters Transport Helicopters Observation Helicopters Maritime Helicopters Multi-mission and Rescue Helicopters Training Helicopters On the basis on the end users/applications, this report focuses on the status and outlook for major applications/end users, consumption (sales), market share and growth rate of Military Helicopters for each application, including Fighting Transportion Detection Other Global Military Helicopters Market Research Report 2017 1 Military Helicopters Market Overview 1.1 Product Overview and Scope of Military Helicopters 1.2 Military Helicopters Segment by Type (Product Category) 1.2.1 Global Military Helicopters Production and CAGR (%) Comparison by Type (Product Category) (2012-2022) 1.2.2 Global Military Helicopters Production Market Share by Type (Product Category) in 2016 1.2.3 Attack Helicopters 1.2.4 Transport Helicopters 1.2.5 Observation Helicopters 1.2.6 Maritime Helicopters 1.2.7 Multi-mission and Rescue Helicopters 1.2.8 Training Helicopters 1.2.4 Type II 1.3 Global Military Helicopters Segment by Application 1.3.1 Military Helicopters Consumption (Sales) Comparison by Application (2012-2022) 1.3.2 Fighting 1.3.3 Transportion 1.3.4 Detection 1.3.5 Other 1.4 Global Military Helicopters Market by Region (2012-2022) 1.4.1 Global Military Helicopters Market Size (Value) and CAGR (%) Comparison by Region (2012-2022) 1.4.2 North America Status and Prospect (2012-2022) 1.4.3 Europe Status and Prospect (2012-2022) 1.4.4 China Status and Prospect (2012-2022) 1.4.5 Japan Status and Prospect (2012-2022) 1.4.6 Southeast Asia Status and Prospect (2012-2022) 1.4.7 India Status and Prospect (2012-2022) 1.5 Global Market Size (Value) of Military Helicopters (2012-2022) 1.5.1 Global Military Helicopters Revenue Status and Outlook (2012-2022) 1.5.2 Global Military Helicopters Capacity, Production Status and Outlook (2012-2022) 7 Global Military Helicopters Manufacturers Profiles/Analysis 7.1 Boeing 7.1.1 Company Basic Information, Manufacturing Base, Sales Area and Its Competitors 7.1.2 Military Helicopters Product Category, Application and Specification 7.1.2.1 Product A 7.1.2.2 Product B 7.1.3 Boeing Military Helicopters Capacity, Production, Revenue, Price and Gross Margin (2012-2017) 7.1.4 Main Business/Business Overview 7.2 Sikorsky Aircraft 7.2.1 Company Basic Information, Manufacturing Base, Sales Area and Its Competitors 7.2.2 Military Helicopters Product Category, Application and Specification 7.2.2.1 Product A 7.2.2.2 Product B 7.2.3 Sikorsky Aircraft Military Helicopters Capacity, Production, Revenue, Price and Gross Margin (2012-2017) 7.2.4 Main Business/Business Overview 7.3 AgustaWestland 7.3.1 Company Basic Information, Manufacturing Base, Sales Area and Its Competitors 7.3.2 Military Helicopters Product Category, Application and Specification 7.3.2.1 Product A 7.3.2.2 Product B 7.3.3 AgustaWestland Military Helicopters Capacity, Production, Revenue, Price and Gross Margin (2012-2017) 7.3.4 Main Business/Business Overview 7.4 Bell Helicopter 7.4.1 Company Basic Information, Manufacturing Base, Sales Area and Its Competitors 7.4.2 Military Helicopters Product Category, Application and Specification 7.4.2.1 Product A 7.4.2.2 Product B 7.4.3 Bell Helicopter Military Helicopters Capacity, Production, Revenue, Price and Gross Margin (2012-2017) 7.4.4 Main Business/Business Overview 7.5 Eurocopter 7.5.1 Company Basic Information, Manufacturing Base, Sales Area and Its Competitors 7.5.2 Military Helicopters Product Category, Application and Specification 7.5.2.1 Product A 7.5.2.2 Product B 7.5.3 Eurocopter Military Helicopters Capacity, Production, Revenue, Price and Gross Margin (2012-2017) 7.5.4 Main Business/Business Overview 7.6 Lockheed Corporation 7.6.1 Company Basic Information, Manufacturing Base, Sales Area and Its Competitors 7.6.2 Military Helicopters Product Category, Application and Specification 7.6.2.1 Product A 7.6.2.2 Product B 7.6.3 Lockheed Corporation Military Helicopters Capacity, Production, Revenue, Price and Gross Margin (2012-2017) 7.6.4 Main Business/Business Overview 7.7 Hindustan Aeronautics Limited (HAL) 7.7.1 Company Basic Information, Manufacturing Base, Sales Area and Its Competitors 7.7.2 Military Helicopters Product Category, Application and Specification 7.7.2.1 Product A 7.7.2.2 Product B 7.7.3 Hindustan Aeronautics Limited (HAL) Military Helicopters Capacity, Production, Revenue, Price and Gross Margin (2012-2017) 7.7.4 Main Business/Business Overview 7.8 Kamov Design Bureau 7.8.1 Company Basic Information, Manufacturing Base, Sales Area and Its Competitors 7.8.2 Military Helicopters Product Category, Application and Specification 7.8.2.1 Product A 7.8.2.2 Product B 7.8.3 Kamov Design Bureau Military Helicopters Capacity, Production, Revenue, Price and Gross Margin (2012-2017) 7.8.4 Main Business/Business Overview 7.9 Kawasaki Heavy Industries 7.9.1 Company Basic Information, Manufacturing Base, Sales Area and Its Competitors 7.9.2 Military Helicopters Product Category, Application and Specification 7.9.2.1 Product A 7.9.2.2 Product B 7.9.3 Kawasaki Heavy Industries Military Helicopters Capacity, Production, Revenue, Price and Gross Margin (2012-2017) 7.9.4 Main Business/Business Overview 7.10 Korea Aerospace Industries (KAI) 7.10.1 Company Basic Information, Manufacturing Base, Sales Area and Its Competitors 7.10.2 Military Helicopters Product Category, Application and Specification 7.10.2.1 Product A 7.10.2.2 Product B 7.10.3 Korea Aerospace Industries (KAI) Military Helicopters Capacity, Production, Revenue, Price and Gross Margin (2012-2017) 7.10.4 Main Business/Business Overview 7.11 Mil Moscow Helicopter Plant 7.12 Mitsubishi Heavy Industries 7.13 NHIndustries (NHI) 7.14 Hughes Aircraft 7.15 Piasecki Helicopter For more information, please visit https://www.wiseguyreports.com/sample-request/1142899-global-military-helicopters-market-research-report-2017


Raj S.P.,Hindustan Aeronautics Ltd
ARF 2015 - 4th Asian-Australian Rotorcraft Forum | Year: 2015

The AFCS (Automatic Flight Control System) provides stability and improves the handling qualities by controlling the motion of the aircraft while in flight thus reducing the pilot workload. The flight control laws acquire inputs from various onboard sensors and drive the actuators which in turn command the control surfaces to move the aircraft in desired direction. Techniques like classical control and Eigen structure assignment have been used since decades for design of flight control laws and proven across various fixed and rotary wing platforms. Dynamics of a helicopter is very complex compared to a fixed wing aircraft because of high level of coupling between the output states. The feedback controller used in this paper is based on optimal LQR (Linear Quadratic Controller). LQR is a powerful tool to control Multiple Input Multiple Output (MIMO) systems with minimum control effort & it has many advantages over conventional controllers. It provides a global optimized solution by creating a balance between all the inputs and output states in form of a well defined quadratic cost function. A trade off is done between the control effort and error tolerances of the output states based on design criteria. Stability Augmentation System (SAS) is designed to meet the criteria as specified in standards like DEFSTAN-00970, AC-27 & ADS-33E. Linearized model of a helicopter having four bladed hingeless main rotor and four bladed tail rotor with conventional mechanical controls is used for the simulation studies. The model based design and closed loop simulations to evaluate the performance of the control law have been done on MATLAB Simulink®.


Abdul Kalam S.,PVP Siddhartha Institute of Technology | Vijaya Kumar R.,Hindustan Aeronautics Ltd | Ranga Janardhana G.,Jawaharlal Nehru Technological University Kakinada
Materials Today: Proceedings | Year: 2017

Bird impact usually occurs during taking off or landing of flights. The aircraft structures should absorb impact energy generated due to ingested birds, ice balls or hail stone and hard body objects. etc. This paper deals with a sensitivity study of hydrodynamic bird models which is performed by numerical simulation. The analysis is carried out by using an explicit Finite Element Analysis (FEA) code AUTODYNE for impact of substitute birds on square plate of rigid Aluminum. The bird body is modeled as a porous water-air material in the shape of a Cylindrical, Cylindrical with Hemispherical ends, Ellipsoidal and Spherical. The finite element bird modeling was carried out by the use of Smooth Particle Hydrodynamics (SPH) method for materials of 10% porosity. The Stagnation and Hugoniot Pressures with time were achieved from four bird models are presented and theoretical results were compared with simulation results. © 2017 Elsevier Ltd. All rights reserved.


Mark C.P.,Karunya University | Selwyn A.,Hindustan Aeronautics Ltd.
Propulsion and Power Research | Year: 2016

The design of an annular combustion chamber in a gas turbine engine is the backbone of this paper. It is specifically designed for a low bypass turbofan engine in a jet trainer aircraft. The combustion chamber is positioned in between the compressor and turbine. It has to be designed based on the constant pressure, enthalpy addition process. The present methodology deals with the computation of the initial design parameters from benchmarking of real-time industry standards and arriving at optimized values. It is then studied for feasibility and finalized. Then the various dimensions of the combustor are calculated based on different empirical formulas. The air mass flow is then distributed across the zones of the combustor. The cooling requirement is met using the cooling holes. Finally the variations of parameters at different points are calculated. The whole combustion chamber is modeled using Siemens NX 8.0, a modeling software and presented. The model is then analyzed using various parameters at various stages and levels to determine the optimized design. The aerodynamic flow characteristics is simulated numerically by means of ANSYS 14.5 software suite. The air-fuel mixture, combustion-turbulence, thermal and cooling analysis is carried out. The analysis is performed at various scenarios and compared. The results are then presented in image outputs and graphs. © 2016 National Laboratory for Aeronautics and Astronautics


Rajakumar R.,Hindustan Aeronautics Ltd | Meenambal T.,Anna University | Banu J.R.,Anna University | Yeom I.T.,Sungkyunkwan University
International Journal of Environmental Science and Technology | Year: 2011

The wastewater discharged by poultry slaughterhouse industries are characterized mainly by high biochemical oxygen demand, high suspended solids and complex mixture of fats, proteins and fibers requiring systematic treatment prior to disposal. In this study, the performance of an upflow anaerobic filter reactor for treating Indian poultry slaughterhouse wastewater under low upflow velocity of 1.38 m/day at mesophilic temperature (29-35 °C) was investigated. The reactor was inoculated with anaerobic non-granular sludge from an anaerobic reactor treating the poultry slaughterhouse wastewater. The reactor took 147 days for complete start-up with removal efficiencies of total chemical oxygen demand and soluble chemical oxygen demand of 70 and 79 % respectively. The maximum total chemical oxygen demand removal efficiency of 78 % was achieved at an organic loading rate of 10.05 kg/m3/day and at an hydraulic retention time of 12 h. The average methane content varied between 46 and 56 % and methane yield at maximum removal efficiency was 0.24 m3 CH4 /kg CODremoved.day. Sludge granules of 1-2 mm were observed in between the packing media. Scanning electron microscope analysis revealed that sludge granules are composed of clumps of Methanosarcina clustered with less intertwined Methanosaeta fibre of granules. The lower velocity used in this study has achieved better performance of the reactor by creating active microbial formation with stable pH upto an organic loading rate of 14.3 kg/m3/day. This has proved that the poultry slaughterhouse wastewater can be treated using anaerobic filter reactor under low upflow velocity. © IRSEN, CEERS, IAU.


Notes:  Production, means the output of Civil Helicopter  Revenue, means the sales value of Civil Helicopter This report studies Civil Helicopter in Global market, especially in North America, Europe, China, Japan, Southeast Asia and India, with production, revenue, consumption, import and export in these regions, from 2011 to 2015, and forecast to 2021. This report focuses on top manufacturers in global market, with production, price, revenue and market share for each manufacturer, covering  Bell Helicopter Textron Inc  AVIC Helicopter Company  Airbus Helicopters  MD Helicopters Inc  Korea Aerospace Industries Ltd  Hindustan Aeronautics Ltd.  Enstrom Helicopter Corporation  Sikorsky Aircraft Corporation  Russian Helicopters JSC  Robinson Helicopter Company By types, the market can be split into  Small helicopter (maximum takeoff weight < 2 MT)  Light Helicopter (maximum takeoff weight between 2MT to 4 MT)  Medium Helicopter (maximum takeoff weight between 4MT to 10 MT)  Large helicopter (maximum takeoff weight between 10MT to 20 MT) By Application, the market can be split into  Exploration  Agriculture  Other By Regions, this report covers (we can add the regions/countries as you want)  North America  China  Europe  Southeast Asia  Japan  India Global Civil Helicopter Market Professional Survey Report 2016  1 Industry Overview of Civil Helicopter  1.1 Definition and Specifications of Civil Helicopter  1.1.1 Definition of Civil Helicopter  1.1.2 Specifications of Civil Helicopter  1.2 Classification of Civil Helicopter  1.2.1 Small helicopter (maximum takeoff weight < 2 MT)  1.2.2 Light Helicopter (maximum takeoff weight between 2MT to 4 MT)  1.2.3 Medium Helicopter (maximum takeoff weight between 4MT to 10 MT)  1.2.4 Large helicopter (maximum takeoff weight between 10MT to 20 MT)  1.3 Applications of Civil Helicopter  1.3.1 Exploration  1.3.2 Agriculture  1.3.3 Other  1.4 Market Segment by Regions  1.4.1 North America  1.4.2 China  1.4.3 Europe  1.4.4 Southeast Asia  1.4.5 Japan  1.4.6 India Wise Guy Reports is part of the Wise Guy Consultants Pvt. Ltd. and offers premium progressive statistical surveying, market research reports, analysis & forecast data for industries and governments around the globe. Wise Guy Reports understand how essential statistical surveying information is for your organization or association. Therefore, we have associated with the top publishers and research firms all specialized in specific domains, ensuring you will receive the most reliable and up to date research data available.


This report studies Civil Helicopter in Global market, especially in North America, Europe, China, Japan, Southeast Asia and India, with production, revenue, consumption, import and export in these regions, from 2011 to 2015, and forecast to 2021. This report focuses on top manufacturers in global market, with production, price, revenue and market share for each manufacturer, covering Bell Helicopter Textron Inc AVIC Helicopter Company Airbus Helicopters MD Helicopters Inc Korea Aerospace Industries Ltd Hindustan Aeronautics Ltd. Enstrom Helicopter Corporation Sikorsky Aircraft Corporation Russian Helicopters JSC Robinson Helicopter Company By types, the market can be split into Small helicopter (maximum takeoff weight < 2 MT) Light Helicopter (maximum takeoff weight between 2MT to 4 MT) Medium Helicopter (maximum takeoff weight between 4MT to 10 MT) Large helicopter (maximum takeoff weight between 10MT to 20 MT) By Application, the market can be split into Exploration Agriculture Other By Regions, this report covers (we can add the regions/countries as you want) North America China Europe Southeast Asia Japan India View Full Report With Complete TOC, List Of Figure and Table: http://globalqyresearch.com/global-civil-helicopter-market-professional-survey-report-2016 Global Civil Helicopter Market Professional Survey Report 2016 1 Industry Overview of Civil Helicopter 1.1 Definition and Specifications of Civil Helicopter 1.1.1 Definition of Civil Helicopter 1.1.2 Specifications of Civil Helicopter 1.2 Classification of Civil Helicopter 1.2.1 Small helicopter (maximum takeoff weight < 2 MT) 1.2.2 Light Helicopter (maximum takeoff weight between 2MT to 4 MT) 1.2.3 Medium Helicopter (maximum takeoff weight between 4MT to 10 MT) 1.2.4 Large helicopter (maximum takeoff weight between 10MT to 20 MT) 1.3 Applications of Civil Helicopter 1.3.1 Exploration 1.3.2 Agriculture 1.3.3 Other 1.4 Market Segment by Regions 1.4.1 North America 1.4.2 China 1.4.3 Europe 1.4.4 Southeast Asia 1.4.5 Japan 1.4.6 India 8 Major Manufacturers Analysis of Civil Helicopter 8.1 Bell Helicopter Textron Inc 8.1.1 Company Profile 8.1.2 Product Picture and Specifications 8.1.2.1 Type I 8.1.2.2 Type II 8.1.2.3 Type III 8.1.3 Bell Helicopter Textron Inc 2015 Civil Helicopter Sales, Ex-factory Price, Revenue, Gross Margin Analysis 8.1.4 Bell Helicopter Textron Inc 2015 Civil Helicopter Business Region Distribution Analysis 8.2 AVIC Helicopter Company 8.2.1 Company Profile 8.2.2 Product Picture and Specifications 8.2.2.1 Type I 8.2.2.2 Type II 8.2.2.3 Type III 8.2.3 AVIC Helicopter Company 2015 Civil Helicopter Sales, Ex-factory Price, Revenue, Gross Margin Analysis 8.2.4 AVIC Helicopter Company 2015 Civil Helicopter Business Region Distribution Analysis 8.3 Airbus Helicopters 8.3.1 Company Profile 8.3.2 Product Picture and Specifications 8.3.2.1 Type I 8.3.2.2 Type II 8.3.2.3 Type III 8.3.3 Airbus Helicopters 2015 Civil Helicopter Sales, Ex-factory Price, Revenue, Gross Margin Analysis 8.3.4 Airbus Helicopters 2015 Civil Helicopter Business Region Distribution Analysis 8.4 MD Helicopters Inc 8.4.1 Company Profile 8.4.2 Product Picture and Specifications 8.4.2.1 Type I 8.4.2.2 Type II 8.4.2.3 Type III 8.4.3 MD Helicopters Inc 2015 Civil Helicopter Sales, Ex-factory Price, Revenue, Gross Margin Analysis 8.4.4 MD Helicopters Inc 2015 Civil Helicopter Business Region Distribution Analysis 8.5 Korea Aerospace Industries Ltd 8.5.1 Company Profile 8.5.2 Product Picture and Specifications 8.5.2.1 Type I 8.5.2.2 Type II 8.5.2.3 Type III 8.5.3 Korea Aerospace Industries Ltd 2015 Civil Helicopter Sales, Ex-factory Price, Revenue, Gross Margin Analysis 8.5.4 Korea Aerospace Industries Ltd 2015 Civil Helicopter Business Region Distribution Analysis 8.6 Hindustan Aeronautics Ltd. 8.6.1 Company Profile 8.6.2 Product Picture and Specifications 8.6.2.1 Type I 8.6.2.2 Type II 8.6.2.3 Type III 8.6.3 Hindustan Aeronautics Ltd. 2015 Civil Helicopter Sales, Ex-factory Price, Revenue, Gross Margin Analysis 8.6.4 Hindustan Aeronautics Ltd. 2015 Civil Helicopter Business Region Distribution Analysis 8.7 Enstrom Helicopter Corporation 8.7.1 Company Profile 8.7.2 Product Picture and Specifications 8.7.2.1 Type I 8.7.2.2 Type II 8.7.2.3 Type III 8.7.3 Enstrom Helicopter Corporation 2015 Civil Helicopter Sales, Ex-factory Price, Revenue, Gross Margin Analysis 8.7.4 Enstrom Helicopter Corporation 2015 Civil Helicopter Business Region Distribution Analysis Global QYResearch is the one spot destination for all your research needs. 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Kumar R.V.,Hindustan Aeronautics Ltd
Journal of Failure Analysis and Prevention | Year: 2016

The paper discusses finite element (FE) modeling for predicting structural damage and correlation studies of dynamic responses in rotorcraft composite structures under high energy bird impact. Before these applications of numerical modeling techniques the simulations are to be accepted by the industry for design development and certification of composite aircraft structures, composites damage models have to be developed and implemented in commercial FE codes, and validation studies at specimen and substructure level have to be performed. Since the experimental tests are expensive and difficult to perform, numerical simulations can only provide significant help in designing high-efficiency bird-proof structures. The design concept is based on the absorption of the major portion of the bird kinetic energy by the composite skins, in order to protect the inner honeycomb core from damage, thus preserving the end plate functionality for safe landing. To this purpose, the end plate skin is fabricated from composite layers, which unfold under the impact load and increase the energy absorption capability. The numerical modeling of bird strike using the Lagrangian approach and smooth particle hydrodynamics formulation and the critical design parameters are considered in carrying out the analysis. A numerical model of this problem has been developed with an explicit finite element code Autodyn. Analysis is carried out for the developed model using the test parameters. Numerical results by means of bird modeling approaches and accurate simulations of composite structures phenomena during impact are substantiated with experimental test results. The results obtained from the analysis and test shows close conformity implying their appropriateness in the simulation of bird strike. © 2016 ASM International


Datta P.P.,Indian Institute of Management | Srivastava A.,Hindustan Aeronautics Ltd | Roy R.,Cranfield University
Computers in Industry | Year: 2013

A major shift in support and maintenance logistics for complex engineering systems over the past few years has been observed in defence and aerospace industry. Availability contracting, a novel approach in this area and a special type of performance based contract, is replacing traditional service procurement practices. The service provider is measured against an equipment availability target set by the customer and rewarded on savings achieved. The performance of such contracts depends on proper utilization of right mix of labour resources. Contemporary literature on resource modelling has not attempted at modelling the entire aircraft maintenance line along with the labour resources. This research work aims to improve resource utilization in availability type contracts by simulating human resources and processes in an aircraft maintenance line. © 2013 Elsevier B.V.


Tajar A.R.,Hindustan Aeronautics Ltd
41st European Rotorcraft Forum 2015, ERF 2015 | Year: 2015

Flying Qualities is one of the very important aspects of helicopter design and operational use. The flight envelopes associated with flying qualities are to be clearly understood and established. The regulations and operational requirements are in many cases, no more than guidelines and essentially to be converted into engineering parameters. The establishment of helicopter limitations majorly depends on the theoretical analysis and component testing. These limitations are generally demonstrated during development and certification flights. The establishment of limitations also ensures the smooth extension of the flight envelope for the growth potential. The conversion of these limitations to engineering parameters is very important from the operation and safety point of view. During some flight regimes, it becomes vital to display these engineering parameters as guidance to indicate helicopter limitations. These indications also ensure safety of the helicopter by respecting the operational boundaries associated with environment. This paper examines the various levels of limitations associated with rotor stall. These flight limitations come from Engine/Transmission limits, control margins and rotor aerofoil characteristics. These limitations appear during the flight depending on the helicopter configuration and the environment. The maximum speed at low altitude is generally limited by the Transmission limit however it is limited by Engine limits at high altitudes. The Flying Qualities boundary comes into picture when the maximum speed and steady bank turn (without loss of altitude) is limited by the control margin and not by the Engine power. The flying qualities limitations are above the Engine limits at low altitude however it moves below the engine limits during high altitude operations. To achieve maximum level flight speed, pilot gets driven by engine limits. When the engines are new, the engine limits may be far from the flying qualities because of availability of higher power available from new engines. The pilot may get misguided by the power available and can still push for higher speeds. Pushing for speeds beyond flying qualities deterioration boundary results in loss of control margin and pitch, roll or yaw oscillations. The several level of limitations associated with rotor stall boundary are function of Blade loading and advance ratio. In turn, blade loading and advance ratio reflect the properties such as maximum lift coefficient, Mach number, drag divergence number and blade geometry. The prediction of flying qualities deterioration was based on the blade loading and advance ratio. The prediction of Flying Qualities (FQ) deterioration limit was also validated by availability of control margins. It was observed that the FQ deterioration limit was also related to loss of control margin. Flight tests were carried out with different All up weights and altitudes condition from low speed to maximum level flight speed. Flight tests data was gathered and stall area of the rotor disk was derived with the help of constant inflow downwash model and aerofoil data. The rotor capability was also compared for two different helicopters with same rotors. It was proved that the reduction in fuselage drag and employment of auxiliary lift source of lift such as wing improves the overall performance of the helicopter. Furthermore, a warning logic was developed to predict the flying qualities deterioration boundary for a helicopter.

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