X-15 FLIGHT REQUEST

Flight No.: 3-46-70 Scheduled Date: July 30, 1965

Pilot: Capt. Joe Engle

Purpose: To obtain data for the following programs:
 

1. NSL Scanner (Exp. #25) - (Joe Lapierre)

2. BLN - (Tom Lewis)

3. Reentry Maneuver Techniques


Instrumentation Engineer: Febo Bartoli

Launch: Delamar Lake on a magnetic heading of 215°, MH-96 Adaptive, R.C. "AUTO," BCS "ON," heading vernier to "Standby," ventral off.

Launch point coordinates: 37° 22' N, 114° 35' W.
 
 
 No. Time  Alt  V   a q            Event
             
1. 0 45 790 2 145 Launch, light engine, increase to 100%T. Rotate to a » 11°, maintain a » 11° to q = 39°.
             
2. 30 54 1900 11 550 q = 39°, maintain q = 39°.
             
3. 81 147 5200 7 50 Shutdown at 5200 fps, pushover to a » 0°.
             
4. 104 200 4700 0 9 Check b = 0, heading vernier to "·Y."
             
5. 167 266 4400 0 .8 Peak altitude, extend speed brakes to 20°.
             
6. 195 210 4500 0 5 q = -9, maintain q = -9 to a = 22°.
             
7. 233 200 4900 10 9 Heading vernier to "STANDBY."
             
8. 250 165 5100 22 36 a = 22°, maintain a = 22° to g max = 5, max reentry q » 1200 psf.
             
9. 285 100 4200 20 1000 H dot = -600, pushover to maintain -400, extend speed brakes to -35°, R.C. "OFF."
             
10. 310 60 3600 4 1400 Cuddeback, vector to high key, speed brakes as required.
             
11.           High Key - check flap and "Squat" circuit breakers in. Data calibrate, experiment switch "OFF."
             
            Before APU shutdown, cycle flaps, set stabilizer trim to zero, data "Off."

Notes:

1. q vernier will be set at 39°, a cross-pointer null at 22°.

2. Emergency lakes: Hidden Hills and Cuddeback.

3. Flight duration: Approximately 12 minutes.

4. Flight plan based on 59,000lb thrust - Engine (#107).

Total burn time at 100% = 83 sec.

Launch Wt. = 33,700lb Burnout Wt. = 15,550lb
 

 Ground Rules For No Launch:
  1. FCS malfunction as indicated on Analyzer check list.

2. Malfunction of inertial platform.

3. Malfunction of ball nose.

4. Malfunction of either B.C.S.

5. Radio, radar or T.M. malfunction.
 

 Alternate Situations After Launch:
  Failure   Action
       
1. Radio or Radar   Proceed as planned.
       
2. Total damper any axis,

failure to fixed gain any axis

(For roll failure turn yaw off)

 (a) 0 - 32 sec.

Alternate Flight Plan.

Proceed normally until t = 32 sec. At 32 sec. pushover to » 2° a and extend speed brakes to 35°. Shutdown at 5200 fps and retract speed brakes to 20° after shutdown. Vector to high key (q » 550 psf). Peak altitude » 145,000 ft.
       
(b) Attitude (b) Hold 11° a till t = 32 sec, then proceed with alternate flight plan.
       
(c) Ball Nose (c) Same as alternate, except use » 0.1 g instead of 2° a. Heading vernier to "·Y."
       
3. Total damper any axis,

failure to fixed gain any axis

(For roll failure turn yaw off)

 (a) 32 sec - S.D.

Pushover to 2° a and extend speed brakes when failure occurs. Shutdown at 5200 fps. Reenter at 20° a and 20° speed brakes.
       
(b) Attitude (b) Same as 3 (a).
       
(c) Ball Nose (c) Same as 3 (a) except use » 0.1 g instead of 2° a. Use q = 0 for reentry.
       
4. Total damper any axis,

failure to fixed gain any axis

(For roll failure turn yaw off)

 (a) After Shutdown

Proceed as planned, reenter at 20° a. (Min.)
       
(b) Attitude (b) Proceed as planned.
       
(c) Ball Nose (c) Use q = -10° for reentry.
       
5. Delayed engine light   Proceed - shut down at 5000 fps.

 

6. Inadvertent engine shutdown:

0 - 43 sec Delamar

43 - 45 sec (2400 fps)

45 - 67 sec Hidden Hills (2500 fps)

67 - 69 sec Cuddeback (3900 fps)

69 - Up sec Edwards (4200 fps)