X-15 FLIGHT REQUEST

Flight No.: 3-35-56 Scheduled Date: September 23, 1964

Pilot: Capt. Joe Engle

Purpose: To obtain data for the following programs:
 

1. Martin MA - 45R Ablative Material - (Joe Watts)

2. Boundary layer noise - (Tom Lewis)


Instrumentation Engineer: Febo Bartoli

Launch: Delamar Lake #1 on a magnetic heading of 214°, MH-96 Adaptive, R.C. "OFF," BCS "OFF," heading vernier to "Standby," ventral off.

Launch point coordinates: 37° 18' N, 114° 36' W.
 
 
 No. Time  Alt  V   a q            Event
             
1. 0 45 790 2 145 Launch, light engine, increase to 100%T. Rotate at 11° a until q = 30°.
             
2. 21 48 1600 11 500 q = 30° - Maintain q = 30°.
             
3. 35 58 2200 4 600 Pushover to 0 "g."
             
4. 70 90 4600 0 550 Extend speed brakes to 35°.
             
5. 82 96 5650 0 550 Burnout, retract speed brakes. Maintain a = 0 until H dot = -200 fps.
             
6. 95 99 5400 0 500 Peak altitude.
             
7. 102 98 5350 0 500 H dot = -200 fps. Descend at 200 fps until q » 700 psf.
             
8. 135 90 5000 4 700 q » 700 psf. Maintain q » 700 psf to Cuddeback. (B.L.N. data point)
             
9. 175 84 4500 4 700 B.L.N. data point.
             
10. 211 80 4000 3 700 B.L.N. data point.
             
11. 278 68 3000 3 700 B.L.N. data point. - Cuddeback, vector to High Key, speed brakes as required. Engine Master OFF.
             
12.           High Key. Check flap and "Squat" circuit breakers in.
             
13.           Before APU shutdown, cycle flaps, set stabilizer trim to zero, data "Off."

Notes:

1. q vernier will be set at 30°, a cross-pointer null at 0°.

2. Emergency lakes: Hidden Hills and Cuddeback.

3. Flight duration: Approximately 11 minutes.

4. Flight plan based on 59,900lb thrust. Engine #103.

Total burn time at 100% = 82 sec.

Launch Wt. = 33,750lb Burnout Wt. = 15,500lb

Ground jettison check
 

 Ground Rules For No Launch:
  1. Radio, Radar, or TM malfunction.

2. FCS malfunctions as indicated on Analyzer check list.

3. Malfunction of Ball Nose.

4. Malfunction of inertial platform.
 

 Alternate Situations After Launch:
  Failure   Action
       
1. Radio or Radar   Proceed as planned.
       
2. Total Pitch/Roll Damper   Turn Yaw OFF, maintain a > 0, proceed as planned.
       
3. Total Yaw Damper

Fixed Gain in any axis

   Proceed as planned.
       
4. Attitude   Proceed as planned except use 5° a in place of 30° q.
       
5. Ball Nose   Heading vernier to ·y, proceed, use 2 g for rotation.
       
6. Delayed engine light   Pushover to 0 g at H = 55,000 ft.

7. Inadvertent engine shutdown:

0 - 44 sec Delamar

44 - 65 sec Hidden Hills (2700 fps)

65 - 70 sec Cuddeback (4200 fps)

70 - Up sec Edwards (4600 fps)