X-15 FLIGHT REQUEST

Flight No.: 3-27-44 Scheduled Date: March 4, 1964

Pilot: John B. McKay

Purpose: Heat Transfer and skin friction experiments with the sharp upper vertical fin, boundary layer noise experiment, and pilot checkout utilizing MH-96.

Launch: Hidden Hills on a magnetic heading of 212°, MH-96 Adaptive, R.C. "OFF," BCS "OFF," heading vernier to "Standby," ventral off.

Launch point coordinates: 36° 20' N, 115° 59' W.

No. Time Alt V a q Event

1. 0 45 790 2 145 Launch, light engine, increase to 100%T. Rotate at 10° a until q = 20°.

2. 17 46 1500 10 495 q = 20° - Maintain q = 20°.

3. 36 56 2400 4 825 Pushover to 0 "g." (H-dot = 700 fps)

4. 55 66 3600 0 1100 Reduce to minimum thrust (40%). Modulate speed brakes to maintain slow longitudinal acceleration.

5. 63 68 3800 0 1110 Increase a to maintain H-dot » 50 ft/sec.

6. 107 71 4200 3 1170 Burnout. Retract peed brakes, maintain H » 71,000 ft until V = 3400 ft/sec.

7. 115 71 3800 3 960 Engage f hold and a hold.

8. 133 71 3400 3 770 Roll to 30° left bank, then release stick force. Roll to 30° right bank, then release stick force.

9. 165 71 2900 3 560 Disengage hold modes. Set up a rate of descent of » 400 ft/sec.

10. 180 67 2700 3 590 Switch to fixed gain in Yaw, Roll and Pitch at pilot's discretion, perform control inputs in all three axes.

11. 210 54 2200 4 725 Switch to adaptive in Pitch, Roll and Yaw. Vector to High Key, speed brakes as required.

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 20°, a cross-pointer null at 0°.

2. Emergency lakes: Cuddeback.

3. Flight duration: Approximately 9 minutes.

4. Flight plan based on 59,800lb thrust engine.

Minimum thrust = 29,500lb.

Total burn time at 100% = 81.5 sec.

Launch Wt. = 33,000lb Burnout Wt. = 15,000lb

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 attitudes.

5. APU gear box malfunction.

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. Do not use hold modes.

3.	Total Yaw Damper Fixed Gain in any axis	Proceed as planned. Do not use hold modes.

4.	Attitude	Proceed as planned except use 4.5° a in place of 20° q at 17 seconds. Do not use f hold.

5.	Ball Nose	Heading vernier to "^·y," proceed, use 1.8g for rotation. Do not use a hold.

6.	Delayed engine light	Pushover to 0 g at H = 54,000 ft. (H-dot = 700 fps).

7. For inadvertent engine shutdown:

0 - 47 sec Hidden Hills

47 - 52 sec Cuddeback (3000 fps)

52 - Up sec Edwards (3400 fps)


1.	0	45	790	2	145	Launch, light engine, increase to 100%T. Rotate at 10° a until q = 20°.

2.	17	46	1500	10	495	q = 20° - Maintain q = 20°.

3.	36	56	2400	4	825	Pushover to 0 "g." (H-dot = 700 fps)

4.	55	66	3600	0	1100	Reduce to minimum thrust (40%). Modulate speed brakes to maintain slow longitudinal acceleration.

5.	63	68	3800	0	1110	Increase a to maintain H-dot » 50 ft/sec.

6.	107	71	4200	3	1170	Burnout. Retract peed brakes, maintain H » 71,000 ft until V = 3400 ft/sec.

7.	115	71	3800	3	960	Engage f hold and a hold.

8.	133	71	3400	3	770	Roll to 30° left bank, then release stick force. Roll to 30° right bank, then release stick force.

9.	165	71	2900	3	560	Disengage hold modes. Set up a rate of descent of » 400 ft/sec.

10.	180	67	2700	3	590	Switch to fixed gain in Yaw, Roll and Pitch at pilot's discretion, perform control inputs in all three axes.

11.	210	54	2200	4	725	Switch to adaptive in Pitch, Roll and Yaw. Vector to High Key, speed brakes as required.

12.						High Key. Check flap and "Squat" circuit breakers in.

13.						Before APU shutdown, cycle flaps, set stabilizer trim to zero, data "Off."