1、ADS - 1B- PRF AERONAUTICAL DESIGN STANDARD ROTORCRAFT PROPULSION SYSTEM , AIRWORTHINESS QUALIFICATION REQUIRENTS GROUND AND FLIGHT TEST SURVEYS AND DEMONSTRATIONS 24 APRIL 1996 UNITED STATES ARMY AVIATION AND TROOP COMMAND ST.LOUIS, MISSOURI AVIATION RESEARCH AND DEVELOPMENT CENTER DIRECTORATE FOR E
2、NGINEERING DISTRIBUTION STATEMENT A. Approved for public release, distribution is unlimited. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-1B-PRE AERONAUTICAL DESIGN STANDARD ROTORCRAFT PROPULSION SYSTEM AIRWORTHINESS QUALIFICATION REQUIREMENTS
3、 GROUND AND FLIGHT TEST SURVEYS AND DEMONSTRATIONS 24 APRIL. 1996 UNITED STATES ARMY AVIATION AND TROOP COMMAND ST.LOUIS, MISSOURI AVIATION RESEARCH AND DEVELOPMENT CENTER DIRECTORATE FOR ENGINEERING Chief Propulsion Integration Branch REVIEWED BY: VERNON R. EDWARDS Chief Propulsion Technology Divis
4、ion APPROVED BY: / BARRKJA BXSKETT of Engineering zation Executive Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-1B CONTENTS 1. 2. 3. 4. 5. 6. 7. REQUIREMENTS 1.2 PERFORMANCE 1.3 QUALIFICATION 1.2.4 ANALYSIS/COMPONENT QUALIFICATION 1.2.5 SURVEY
5、S AND DEMONSTRATIONS SCOPE 2.1 GENERAL 2.2 SURVEYS 2.3 DEMONSTRATIONS 2.4 TEST PLANS AND REPORTS 2.5 APPLICABLE DOCUMENTS ENGINE/AIRFRAME COMPATIBILITY 3.1 GENERAL 3.2 DYNAMIC RESPONSE GROUND TESTS 3.3 DYNAMIC RESPONSE FLIGHT TESTS 3.4 DYNAMIC SYSTEM ENGINE COMPATIBILITY 3.5 ENGINE STARTING 3.6 ENGI
6、NE FAILURE MODES AND EFFECTS 3.7 ENGINE MONITORING SYSTEM 3.8 COCKPIT INDICATIONS PROPUSION SYSTEM VIBRATION 4.1 GENERAL 4.2 PROPULSION SYSTEM VIBRATION PLAN 4.3 TEST CRITERIA 4.4 INSTRUMENTATION AND DATA ANALYSIS 4.5 VIBRATION REPORT PROPULSION SYSTEM TEMPERATURE 5.1 GENERAL 5.2 TEMPERATURE PLAN 5.
7、3 TEST CRITERIA 5.4 INSTRUMENTATION AND DATA ANALYSIS 5.5 TEMPERATURE REPORT ENGINE AIR INDUCTION SYSTEM 6.1 GENERAL 6.2 AIR INDUCTION PLAN 6.3 TEST CRITERIA 6.4 EFFECT ON ENGINE PERFORMANCE 6.5 INSTRUMENTATION AND DATA ANALYSIS 6.6 REPORT ENGINE EXHAUST 7.1 GENERAL 7.2 TEST CRITERIA 7.3 INSTRUMENTA
8、TION AND DATA ANALYSIS 7.4 REPORT PAGE 3 5 7 13 16 18 21 1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-8. DRIVE AND ACCESSORY SYSTEM 9. LUBRICATION SYSTEM 9.1 GENERAL 9.2 TEST PLAN 9.3 TEST CRITERIA 10. FUEL SYSTEM 10.1 GENERAL 10.2 FUEL SYSTEM P
9、LAN 10.3 TEST CRITERIA 11. FIRE DETECTION AND EXTINGUISHING SYSTEM 11.1 GENERAL 11.2 FIRE DETECTION AND EXTINGUISHING PLAN 11.3 GROUND TEST 11.4 POST TEST ANALYSIS 12 COMPARTMENT DRAINAGE 13. ENGINE WATER WASH SYSTEM 14. HYDRAULIC SYSTEM 14.1 GENERAL 14.2 GROUND TEST 14.3 FLIGHT TEST 15. PNEUMATIC S
10、YSTEM 15.1 GENERAL 15.2 GROUND TEST 15.3 FLIGHT TEST 22 22 25 36 37 37 38 42 16. ENVIRONMENTAL CONTROL SYSTEM 45 16.1 HEATING, VENTILATING, AND AIR CONDITIONING 16.2 DEFOGGING, DEFROSTING, ANTI-ICING/DEICING 16.3 CONTROL SYSTEM 17. AUXILIARY POWER UNITS 17.1 GENERAL 17.2 ELECTRICAL INTERFACE TESTING
11、 17.3 HYDRAULIC INTERFACE TESTING 17.4 PNEUMATIC INTERFACE TESTING 2 48 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1. REQUIREMENTS. 1.1 PERFORMANCE. The Propulsion systems shall meet their allocated performance and operate in such a manner that
12、the aircraft shall be able to be function safely throughout the operational envelope and meet the performance requirements as defined in the applicable weapon system specification. 1.2 UALIFICATION. The following qualification requirements for the propulsion systems are required to verify compliance
13、 with the performance requirements of paragraph 1.1 above as applicable to the aircraft design configuration. 1.2.1 Analysis and Component Qualification. Design and performance analysis shall be conducted on propulsion system components/assemblies using ADS-9C as a guide. Component qualification sha
14、ll be conducted in accordance with ADS-50-PW. 1.2.2 Propulsion Surveys and Demonstrations. Propulsion qualification survey and demonstration requirements for the aircraft shall be as listed below. a. Engine/Airframe Compatibility i. Dynamic Response Characteristics 2. Starting Performance 3. Failure
15、 Modes Effects 4. Heal th Monitoring 5. Cockpit Indications b. Propulsion System Vibration i. Rotor Induced Effects (Frequency, RPM) 2. Engine Induced Effects (Frequency, Power) 3. Other Subsystem Effects a. Propulsion System Temperature 3. Power Effects 4. Flight Condition Effects 4. Power, Speed,
16、Flow Field Effects s. inlet Pressure Recovery/Losses, Performance 6. Inlet Pressure/Temperature Distortion 7. Annament Gas Ingestion 5. Power, Speed, Flow Field Effects 6. Losses, Performance Effects 7. Exhaust Flow Impingement a. Engine Air Induction System Effects a. Engine Exhaust System 3 Provid
17、ed by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-8. IR Suppressor Performance a. Drive and Accessory System b. Lubrication System i. Usable Oil, Oil Tank Expansion/Pressure 2. Bypass, Vent, Debris Detection Systems 3. Cooling Capacity, Margins 8. Fuel Avail
18、ability/Capacity, Feed System 9. Boost/Transfer Pump, Suction Feed Performance io. Fuel Management 11. Hot Fuel Performance, Starting 12. Auxiliary Fuel System 13. Pressurization/Explosion Suppression System 14. Refuel/Defuel System Performance is. mel Vent System Performance i. Fire Detection and E
19、xtinguishing System a. Compartment Drainage b. Engine Water Wash System C. Hydraulic System a. Fuel System Performance io. Flight Control System Performance, 11. Utility System Performance, Temperatures, 12. Filtration, Contamination, Servicing 13. High Pressure Systems 14. LOW Pressure/Vacuum Syste
20、ms 14. Heating/Cooling System Performance 15. Pressurization Performance 16. Nuclear/Biological/Chemical System Performance 17. Defogging, Defrosting, Anti-icing/Deicing 18. Control System Performance Temperatures, Pressures Pressures a. Pneumatic System a. Environmental Control System Perf ormance
21、o. Auxiliary Power Unit 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2. SCOPE. 2.1 Genera. This document contains rotorcraft airworthiness qualification requirements for propulsion systems. The issuance of a Contractor Flight Release (CFR) to in
22、itiate aircraft ground and flight testing is contingent upon successful completion of the analysis and component qualification requirements as contained in ADS-50-PRF. The issuance of an Airworthiness Release (AWR), from a propulsion point of view, is contingent upon successful completion of the ana
23、lysis, surveys, and demonstrations listed in paragraph 1.2 above. The remaining paragraphs below, are to be used as guidance in defining the required surveys and demonstrations above. The surveys and demonstrations herein are normally divided into two segments; an initial series of propulsion interf
24、ace surveys and subsequent propulsion demonstrations. In effect, propulsion surveys are considered a subset of the more formal propulsion demonstrations leading to airworthiness qualification. The original ADS-1 addressed only propulsion interface surveys. This revision has been expanded to include
25、all propulsion demonstrations. to reflect current technology and lessons learned from recent flight test programs. 2.2 Surveys. Propulsion surveys are conducted early in a flight test This ADS has also been updated program to obtain preliminary engineering performance data pertaining to selected pro
26、pulsion systems/subsystems. Surveys are intended to determine the necessary design changes, if any, which must be incorporated in either the engine, airframe, or other propulsion systems, and to incorporate these changes prior to completion of engine qualification and/or subsequent engine/airframe o
27、r propulsion system airworthiness qualification. Surveys are performed through portions of an aircrafts operating envelope and over a worst case range of c.g., airspeed, altitude, maneuver load factor, and rotor rpm. Usually, propulsion surveys are conducted prior to completion of engine qualificati
28、on by the engine manufacturer. (PFR) engine(s) is installed on the test (prototype) aircraft and limited propulsion interface ground and flight testing is conducted. interface surveys normally include: engine/airframe compatibility tests to evaluate the torsional stability and control system dynamic
29、 response characteristics of the engine/rotor/drive system; engine vibration, to measure installed vibration characteristics to determine mode shapes and assess compliance with engine and engine component vibration limits and vibration characteristics of other propulsion components; propulsion syste
30、m temperatures, to measure airflow and temperature within the engine compartment to compare with engine component limits; air induction system, to measure inlet distortion characteristics and mass airflow, pressure and temperature distribution, and to map the inlet loss characteristics for use in ca
31、lculating (installed) engine power and performance; and exhaust system, to map temperature, pressure and flow characteristics (exhaust swirl angle) of the exhaust system for use in calculating (installed) engine performance. In those aircraft installations employing IR-Suppression devices, as part o
32、f the exhaust system, the increase in part power fuel flow becomes an important consideration. In installations employing (fixed geometry, ejector type) hover suppressors, the increase in aircraft power required (due to high momentum losses in the suppressor), becomes significant in high speed fligh
33、t. For a new development aircraft program, the above propulsion surveys are considered the minimum tests necessary to clear aircraft limitations in the initial Contractor Flight Release (CFR) and thereby permit subsequent envelope expansion. The propulsion survey test program leads to much more succ
34、essful and expeditious propulsion qualification testing (demonstrations) at the end of the development program. Propulsion survey results can be used to satisfy the requirements of a propulsion demonstration providing the configuration of the components and systems have not changed appreciably. A te
35、st Preliminary Flight Rating Propulsion 2.3 Demonstrations. Propulsion demonstrations are the full complement of ground and flight tests necessary to “qualify“ the aircraft propulsion systems throughout the entire aircraft operating envelope. Propulsion demonstrations are intended to verify that the
36、 operational and performance characteristics of the propulsion system and associated subsystems meet the performance requirements of the aircraft weapon system specification. propulsion demonstrations are normally conducted near the end of the 5 Provided by IHSNot for ResaleNo reproduction or networ
37、king permitted without license from IHS-,-,-development program to insure the tested configuration is representative of production hardware. In addition to validating the survey test results, as described above, propulsion demonstrations also include a functional demonstration of the following: comp
38、artment drainage, engine water wash, lubrication system, drivetrain accessories, anti-ice and de-ice system, condi ti on moni t orlng/dia gnos ti cs, cockpi t displays , fuel sys tem (in cl uding auxiliary fuel system provisions), auxiliary power unit and accessories, environmental control system, p
39、neumatic system, hydraulic system, and armament gas ingestion. Any of these demonstrations can be performed early in the program along with the propulsion surveys, particularly if program risk would be reduced by an early investigation, providing the configuration of the components or system does no
40、t change prior to production. 2.4 Analysis, Test Plans and Reports. The contractor should prepare and submit analysis, using ADS-9C as a guide, and component test reports, in accordance with ADS-50-PRFt prior to the request for a CFR to initiate aircraft ground and flight testing. The contractor sho
41、uld then prepare and submit subsequent ground and flight test plans prior to the start of the propulsion system surveys and/or demonstrations. The test plans should discuss all test criteria described herein to show how the ground and flight test requirements are to be verified. The contractor shoul
42、d define the testing to be conducted early in the program as part of the propulsion surveys and the tests that will be deferred to future propulsion demonstrations. The contractor should define all test details for the propulsion surveys and include the instrumentation required to obtain the necesii
43、ary data to efficiently evaluate the performance of the propulsion systems. commencement of the more formal propulsion demonstrations, the contractor should submit a demonstration test plan, which revises the original test plan, to include the details of the testing planned due to deferment of testi
44、ng in the original submittal. The contractor should prepare and submit corresponding test report(s) after the completion of the propulsion surveys and other test report(s) after the completion of the propulsion demonstrations. The test reports should contain the contractors (and subcontractors, wher
45、e applicable) engineering assessment of the test data (including failure investigations, as applicable) along with appropriate recommendations and conclusions. The submittal of the test plans and reports should be in accordance with the applicable Contract Statement of Work and Contract Data Require
46、ments List. Prior to the 2.5 APPLICABXB Documwrs. ADS-9c Propulsion System Technical Data ADS-50-PRF Rotorcraft Propulsion System Performance and Qualification Requirements and Guidelines 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3. ENGINE/AI
47、RFRAME COMPATIBILITY TESTS 3.1 General Guidance. Compatibility testing of the engine and airframe should be conducted during steady state and transient operation. Generally, compatibility includes considerations such as steady state and transient response characteristics of the engine and engine con
48、trol system in combination with the drive system and rotor(s). The aircraft manufacturer should define the requirements to verify compatibility using this ADS as a guide. Details of propulsion system stability test criteria are dependent on the specific operating characteristics of the aircraft. The
49、refore, detailed test requirements to evaluate torsional stability must be defined by the airframe manufacturer. For instance, the rotor/drive system will be subjected to torsional oscillations due to rotor dynamics and acceptable levels of these oscillations will depend upon the size and design of the particular helicopter. Particular attention must be focused on determining that engine fuel flow is not modulated by unwa
