Реферат

This specification covers the manufacture of gyroplanes and includes design and performance requirements for light sport gyroplane aircraft. A gyroplane is a rotorcraft to be used for day visual flight rules (VFR) only, with rotor blades that are not engine-driven in flight and are supported in flight by the reaction of the air on a single rotor that rotates freely on a substantially vertical axis when the aircraft is in horizontal flight. Aircraft having the following basic features will be so regarded: rotors of either fixed collective pitch or collective pitch control that are not adjustable in flight, single engine with fixed or ground adjustable pitch propeller, no more than two occupant seats, and a maximum gross weight of some value. For compliance, the following flight requirements should be met: load distribution limit, weight limit, empty weight, removable ballast, and rotor speed limit. In order to comply in terms of performance, the requirements for the following shall be evaluated: takeoff, climb, glide, never exceed airspeed, minimum controllable airspeed for level flight, best rate of climb airspeed, landing distance, maximum operating altitude, and height/velocity envelope. The gyroplane must be safely controllable and maneuverable with sufficient margin of control movement and blade freedom to correct for atmospheric turbulence and permit control of the attitude of the gyroplane at all power settings at the critical weight and balance at sea level and at the maximum operating altitude. The evaluation of the gyroplane's longitudinal lateral and directional control and stability shall be discussed. In terms of structure requirements, the following should be taken into consideration: flight loads, engine torque, control system loads, stabilizing and control surfaces, ground loads, main component requirements, emergency landing conditions, and other loads.

Область применения

1.1 This specification covers the manufacture of gyroplanes. This specification includes design and performance requirements for light sport gyroplane aircraft.

1.2 This specification applies to light gyroplane aircraft seeking civil aviation authority approval in the form of flight certificates, flight permits, or other like documentation.

1.3 A gyroplane for the purposes of this specification is defined as a rotorcraft to be used for day VFR only, with rotor blades that are not engine-driven in flight and are supported in flight by the reaction of the air on a single rotor that rotates freely on a substantially vertical axis when the aircraft is in horizontal flight.

1.4 These requirements apply to light gyroplanes of orthodox design. Aircraft having the following basic features will be so regarded:

1.4.1 Rotors of either fixed collective pitch or collective pitch control that are not adjustable in flight,

1.4.2 Single engine with fixed or ground adjustable pitch propeller,

1.4.3 No more than two occupant seats, and

1.4.4 A maximum gross weight (MGW) of 725 kg (1600 lb) or less.

1.5 Where it can be shown that a particular feature is similar in all significant respects to a feature that has historically demonstrated compliance with this specification and can be considered a separate entity in terms of its operation, that feature shall be deemed to be applicable and in compliance with this specification.

1.6 Where these requirements are inappropriate to particular design and construction features, it will be necessary to submit an appropriate amendment of this specification to ASTM Committee F37 on Light Sport Aircraft for consideration and approval.

1.7 The values in SI units are to be regarded as the standard. The values in parentheses are for information only.

1.8 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 and health practices and determine the applicability of regulatory limitations prior to use.

1.9 Table of Contents:

Section Scope1 Table of Contents1.9 Referenced Documents2 Terminology3 Definitions3.1 Acronyms3.2 Flight4 General4.1 Performance4.2 Controllability and Maneuverability4.3 Longitudinal Lateral and Directional Control4.4 Stability4.5 Ground-Handling Characteristics4.6 Miscellaneous Flight Requirements4.7 Structure5 General5.1 Flight Loads5.2 Engine Torque5.3 Control System Loads5.4 Stabilizing and Control Surfaces5.5 Ground Loads5.6 Main Component Requirements5.7 Emergency Landing Conditions5.8 Other Loads5.9 Design and Construction6 General6.1 Materials6.2 Fabrication Methods6.3 Locking of Connections6.4 Protection of Structure6.5 Inspection6.6 Provisions for Rigging and Derigging6.7 Material Strength Properties and Design Values6.8 Fatigue Strength6.9 Special Factors of Safety6.10 Bearing Factors6.10.2 Fitting Factors6.10.3 Cable Factor6.10.4 Rotor Components Factor6.10.5 Flutter Prevention and Structural Stiffness6.11 Control Surfaces and Rotors6.12 Control Surface Installations (Other Than Rotor Blades)6.13 Control Surface Hinges (Other Than Rotor Blades)6.14 Rotor Mass Balance6.15 Rotor Blade Clearance6.16 Rotor Head Bearings6.17 Control Systems6.18 Cockpit Design6.19 Powerplant7 General7.1 Engine7.2 Engine and Propeller Compatibility7.3 Rotor Spin-Up and Brake Systems7.4 Powerplant and Rotor System Compatibility7.5 Propeller Clearance7.6 Fuel System7.7 Oil System7.8 Cooling7.9 Induction System7.10 Exhaust System7.11 Powerplant Controls and Accessories7.12 Cowling and Nacelle7.13 Equipment8 General8.1 Instruments—Installation8.2 Electrical Systems and Equipment8.3 Miscellaneous Equipment8.4 Operating Limitations and Information9 General9.1 Airspeed Limitations9.2 Weight and Balance9.3 Powerplant and Propeller Limitations9.4 Pilot Operating Handbook, POH9.5 Maintenance Manual9.6 Markings and Placards9.7 Propellers10 Design and Construction10.1 Keywords12