航空事故調査報告 書 - mlit.go.jp

1 AA2013-5.. Japan Transport Safety Board .. Above Field Level Cockpit Voice Recorder Collective Pitch Control Cyclic Stick Digital Flight Data Recorder Enhanced Ground Proximity Warning System Global Positioning System Main Rotor Torque Visual Flight Rules Vortex Ring State . lb . kg ft .. kt . km/h . m/s . in . mm slug . kg .. ) . - 1 - .. kt .. kt . Above Field Level) AFL . , ft . ftAFL .. *1 .. ftAFL .. ftAFL . *1 .. - 2 - .. ftAFL .. (1) .. - 3 - .. kt .. (2) .. - 4 - .. (3) .. (1) .. (2) cm . (3) .. - 5 - .. , .. , .. , . ( 4 ) .. , lb . in . in . in . , lb , lb .. in . in .. in . in.

2 M/s kt .. - 6 - . 09:50 10:00 10:10 12:50 13:00 13:10. 7kt 7kt 5kt 9kt 11kt 10kt 5kt 5kt 4kt 7kt 9kt 9kt .. cm cm .. (1) .. - 7 - (2) .. (3) . ( .. (4) .. (5) . eTrex Legend .. (1) .. kt . - 8 - .. kt . (2) .. 09:59:58 685m . 12:53:57 698m . 09:58:05 1,393m 09:59:47 702m 12:52:41 1,239m 12:53:48 768m .. 09:59:38 766m 12:53:39 850m 09:59:29 824m 12:53:30 929m . 09:58:58 1,047m 12:53:16 1,011m . 0 500 1,000m .. - 9 - . ft .. , ft .. (ft) (%) (%) (%). , .. - 10 - kt .. 5.. 45 40.. 60 20.. 25.. 55 35 10.. 50.. 30 15.. (1) .. - 11 - .. 15.. 50 45.. 60 55 30 20 10 5.. 40 35 25.. (2) . , ftAFL.)

3 *2 , ft .. , ft/min . ftAFL . ftAFL . , ft/min . ftAFL . , ft ftAFL . ftAFL ftAFL .. *2 .. - 12 - . ft/min .. ft/min .. (1) .. ft . , ft . (2) . (Scientific Technical - 13 - Information) Report Series . (Wayne Johnson, Model for Vortex Ring State Influence on Rotorcraft Flight Dynamics NASA/TP-2005-213477 December 2005, ,11,13,25,49).. OVERVIEW. A rotor is operating in vortex ring state when it is descending at low forward speed with a vertical velocity that approaches the value of the wake-induced velocity at the rotor disk. In this condition the rotor tip vortices are not convected away from the disk rapidly enough, and the wake builds up and periodically breaks away (Fig.)

4 1). The tip vortices collect in a vortex ring, producing a circulating flow down through the rotor disk, then outward and upward outside the disk. The resulting flow is unsteady,hence a source of considerable low frequency vibration and possible control problems. For descent at forward speeds sufficiently high enough that the wake is convected away from the rotor, vortex ring state does not develop.. - 14 - .. VRS BOUNDARIES. A number of the boundaries that have been proposed for vortex ring state are presented in Figure 33. The boundary from the ONERA VRS. model is based on the Vz drop encountered in helicopter flight tests.

5 The boundary for the VRS model of the present investigation is based on the flight dynamics stability of helicopters and tiltrotors. The other boundaries are based primarily on the vibration and roughness that a helicopter encounters in VRS. Of particular note are the boundaries that Washizu constructed for T/T = and (Ref. 30),which are found in numerous documents on VRS (including the Field Manual FM 1-203, Fundamentals of Flight).. T/T .. T/T .. [ Vx Vz vh ]. - 15 - .. (3) .. ( ) . , lb .. km . , ft , ft . , ft .. slug/ft . ft . , . ft/min kt .. (1) .. - 16 - .. (2) .. (1-3) . 1) .. (2).

6 - 17 - .. (3) .. (1) (2) .. kt . - 18 - .. (1) .. (1) .. kt .. (1) . (1) .. (1) .. (2) . (2) . , ft/min .. - 19 - .. ft/min .. (1) . (1) .. ftAFL .. (2) . (2) .. - 20 - .. [ Vx Vz vh ].. (2) . kt . , ft/min (3) . , ft/min kt .. (1) . kt kt .. kt . kt kt . 1, ft/min kt .. (2) . , ft/min . kt .. - 21 - .. [ Vx Vz vh ].. , ft/min .. kt kt .. (2) .. - 22 - ft/min . ft/min .. (3) .. (2) .. ft .. (2) .. ftAFL .. (2) . , ft/min .. (2) . kt . kt . - 23 - .. (3) .. (3) .. - 24 - .. (1) .. (2) .. (2) .. (2) .. (1) kt .. *3. (2) . *3 . - 25 - .. (3) .. ftAFL .. (1) . (4) .. kt .. (2) . (5) .. , ft/min.

7 - 26 - .. (3) . (6) .. (7) .. - 27 - .. (1) .. kt ft/min . , ft/min .. kt ft/min . (2) . kt .. (3) .. - 28 - .. (1) .. (2) .. (3) .. (4) .. - 29 - . N.. 12:52:40. 2,200ftAFL. 81kt . kt .. 12:54:09. 320ftAFL.. 0 500 1,000m AFL .. - 30 - .. N.. kt .. 0 50 100m .. 0 50 100m - 31 - .. kt .. - 33 - .. - 34.