X-15 FLIGHT REQUEST

Flight No.: 3-13-23 (Revised) Scheduled Date: December 20, 1962

Pilot: Joseph A. Walker

Subject of test: Ventral Off Stability Investigation and MH-96 Limit Cycle Investigation.

Launch: Mud Lake on a magnetic heading of 177°, MH-96 FCS Adaptive, BCS "ON," MH-96 RC "OFF."

No. Time Alt V a q Event

1. 0 45 790 2 145 Launch - light engine, advance to 100%T - rotate to a = 6°. Maintain a = 6° until 2g is attained.

2. 30 43 2250 6 1150 Maintain 2g until q = 20°.

3. 35 45 2450 5 1400 Maximum q.

4. 55 60 3600 3 1220 Pushover to a = 2° (.2g).

5. 70 75 4600 2 1000 Extend speed brakes to 20°.

6. 80 87 5560 2 850 Shutdown, increase a to 25°, perform da pulses.

7. 110 125 4000 20 50 Decrease a to » 6°. MH-96 R.C. "AUTO."

8. 170 173 3400 6 10 Peak altitude.

9. 220 135 3700 6 35 Increase a to 15° - MH-96 R.C. "OFF."

10. 260 75 3500 15 625 Max reentry g = 4. Pushover to » 8° a.

11. 270 70 3200 8 600 Retract speed brakes. Increase a to 12°. Perform da pulse.

12. 280 70 2800 12 480 Vector to high key, speed brakes as required.

13. High Key - pressurize tanks at 17,000 ft. Check flap and "Squat" circuit breakers in.

14. Before APU shutdown, cycle controls, retract flaps, trim stabilizer zero, data off.

Notes:

1. q vernier will be set at 20°, a cross-pointer null at 6°.

2. Duration of flight approximately 11 minutes.

3. Emergency lakes: Grapevine and Cuddeback.

Alternate Situations After Launch:
1. For radio or radar failure, proceed as planned.

2. If engine light cannot be accomplished within 30 sec., jettison propellants and land at Mud Lake.

3. For delayed engine light, use a = 9° for rotation, otherwise proceed as planned.

4. For total pitch damper failure, proceed, do not exceed 15° a.

5. For FCS failure to fixed gain in yaw, proceed as planned.

For FCS failure to fixed gain in roll, set yaw fixed, proceed.

For FCS failure to fixed gain in pitch, proceed but do not exceed 15° a.

6. For total roll damper failure, turn yaw damper off, extend speed brakes 20°, proceed to Edwards, do not exceed 15° a.

7. For total yaw damper failure, proceed as planned.

8. For attitude failure, proceed, do not exceed 15° a.

9. For inadvertent engine shutdown:

0 - 46 sec Mud.

46 - 67 sec Grapevine.

67 - 70 sec Cuddeback.

70 - Up sec Edwards.


1.	0	45	790	2	145	Launch - light engine, advance to 100%T - rotate to a = 6°. Maintain a = 6° until 2g is attained.

2.	30	43	2250	6	1150	Maintain 2g until q = 20°.

3.	35	45	2450	5	1400	Maximum q.

4.	55	60	3600	3	1220	Pushover to a = 2° (.2g).

5.	70	75	4600	2	1000	Extend speed brakes to 20°.

6.	80	87	5560	2	850	Shutdown, increase a to 25°, perform da pulses.

7.	110	125	4000	20	50	Decrease a to » 6°. MH-96 R.C. "AUTO."

8.	170	173	3400	6	10	Peak altitude.

9.	220	135	3700	6	35	Increase a to 15° - MH-96 R.C. "OFF."

10.	260	75	3500	15	625	Max reentry g = 4. Pushover to » 8° a.

11.	270	70	3200	8	600	Retract speed brakes. Increase a to 12°. Perform da pulse.

12.	280	70	2800	12	480	Vector to high key, speed brakes as required.

13.						High Key - pressurize tanks at 17,000 ft. Check flap and "Squat" circuit breakers in.

14.						Before APU shutdown, cycle controls, retract flaps, trim stabilizer zero, data off.