X-15 FLIGHT REQUEST

Flight No.: 3-14-24 Scheduled Date: January 17, 1963

Pilot: Joseph A. Walker

Subject of test: Ventral Off Altitude Buildup and I. R. Experiment

Launch: Delamar Lake on a magnetic heading of 205°, MH-96 "Adaptive," FCS reaction controls "Auto," Both BCS "ON," ^·y switch "Standby."

No. Time Alt V a q Event

1. 0 45 790 2 145 Launch - light engine, increase to 100%T, rotate until 2g is attained.

2. 31 50 1950 10 625 Maintain 2g until q = 38°, maintain a = 38°.

3. 77 132 5220 6 110 Shutdown. (Shutdown will be accomplished at 77 sec. or 5300 ft/sec, whichever occurs first). Maintain a » 6°.

4. 125 220 4600 6 4 ^·y switch to "^·y."

5. 173 250 4320 - 1 Peak altitude. Extend speed brakes to 20°. Maintain a » 0° until a = 23°, maintain a = 23°.

6. 215 220 4600 »15 4 ^·y switch to "Standby."

7. 278 92 4500 23 550 5g - Maintain 5g ("g" limiting) until H-dot = -1000 ft/sec.

8. 284 82 4000 20 625 H-dot = -1000 ft/sec., pushover to a » 3°, extend speed brakes to 35°, vector to high key. Reaction control switch "Off." Engine master "Off."

9. High Key - Speed brakes as required - pressurize tanks at 17,000 ft. Check flap and "Squat" circuit breakers in.

10. Before APU shutdown, cycle flaps, set stabilizer trim to zero, turn all data "Off."

Notes:

1. q vernier will be set at 38°, a cross-pointer null at 23°.

2. Flight plan based on Engine No. 109 with a predicted thrust of 60,000 pounds.

3. Emergency lakes: Grapevine and Cuddeback.

4. Flight duration: Approximately 11 minutes.

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 Delamar.

3. For delayed engine light, proceed as planned.

4. For total FCS failure or failure to fixed gain in any axis prior to 50 sec., pushover at 50 sec., extend speed brakes to 20°, proceed to Edwards, shut down at 75 seconds.

5. For total failure or failure to fixed gain in pitch or yaw after shutdown, reaction controls to "On," proceed as planned.

6. For total failure or failure to fixed gain in roll, switch yaw damper to correspond to the roll damper, reaction controls to "On," proceed as planned.

7. For attitude failure, pushover at 50 sec., extend speed brakes to 20°, proceed to Edwards, shutdown at 75 seconds.

8. For ball nose failure, pushover to .2g at 50 sec., extend speed brakes to 20°, proceed to Edwards. For reentry, maintain dh = 25° until g = 5.

9. For inadvertent engine shutdown:

0 - 43 sec Delamar.

43 - 62 sec Hidden Hills.

62 - 68 sec Cuddeback.

68 - Up sec Edwards.


1.	0	45	790	2	145	Launch - light engine, increase to 100%T, rotate until 2g is attained.

2.	31	50	1950	10	625	Maintain 2g until q = 38°, maintain a = 38°.

3.	77	132	5220	6	110	Shutdown. (Shutdown will be accomplished at 77 sec. or 5300 ft/sec, whichever occurs first). Maintain a » 6°.

4.	125	220	4600	6	4	^·y switch to "^·y."

5.	173	250	4320	-	1	Peak altitude. Extend speed brakes to 20°. Maintain a » 0° until a = 23°, maintain a = 23°.

6.	215	220	4600	»15	4	^·y switch to "Standby."

7.	278	92	4500	23	550	5g - Maintain 5g ("g" limiting) until H-dot = -1000 ft/sec.

8.	284	82	4000	20	625	H-dot = -1000 ft/sec., pushover to a » 3°, extend speed brakes to 35°, vector to high key. Reaction control switch "Off." Engine master "Off."

9.						High Key - Speed brakes as required - pressurize tanks at 17,000 ft. Check flap and "Squat" circuit breakers in.

10.						Before APU shutdown, cycle flaps, set stabilizer trim to zero, turn all data "Off."