X-15 FLIGHT REQUEST

Flight No.: 3-9-17 Scheduled Date: August 10, 1962

Pilot: Joseph A. Walker

Subject of test: Constant q entry and stability at minimum yaw gain.

Launch: Delamar Lake on a magnetic heading of 205° with MH-96 FCS on Adaptive Damper, FCS Reaction Controls "AUTO" and both BCS "ON."
 
 
 No. Time  Alt  V   a q            Event
             
1. 0 45 790 1.5 145 Launch - light engine, advance to 100%T - use pitch rate trim for rotation to a » 10° (dh » -8) - Do not exceed 3 g. Trim f if necessary.
             
2. 29 47 1850 10 700 Maintain pitch rate until q = 32°, maintain q = 32°.
             
3. 70 110 4300 4 300 Pushover to 0 "g" (use dh trim to +3°).
             
4. 83 140 5800 0 160 Burnout.
             
5. 120 200 5400 0 16 Roll to 30° right bank, maintain for approximately 30 seconds.
             
6. 161 220 5200 0 9 Peak altitude - engage q Hold (at q = 0°), zero side stick trim knob and use pitch vernier trim wheel to maintain q = 0° - extend speed brakes. amax during entry approximately 20°.
             
7. 239 125 5500 20 180 At 1 "g" reduce to fixed gain in yaw, RC "OFF," perform dv pulse (no da inputs).
             
8.           After entry completed, vector to high key, depress CSS button - jettison (H2O2 "OFF").
             
9.           High Key. Check ventral armed and pressurize tanks. Push to test ball nose.
             
10.           After touchdown, disengage MH-96 FCS.
             
11.           Before APU shutdown, cycle controls, retract flaps, trim stabilizer zero, data off.

Notes:

1. q vernier will be set at 32°, a cross-pointer null at 20°.

2. Duration of flight approximately 10 minutes.

3. Emergency lakes: Hidden Hills and Cuddeback.

 Ground Rules for No Launch: 1. FCS malfunction as indicated in attached sheets.

2. Stable platform malfunction in attitudes.

3. Ball nose malfunction.

4. Radio or radar failure.

 Alternate Situations Before Launch: 1. MH-96 FCS malfunctions in auto-pilot, proceed but do not operate affected FCS modes. Alternate Situations After Launch: 1. If engine does not light within 30 sec., jettison and land at Delamar.

2. For delayed engine light, proceed as planned, maintain less than 3g during rotation.

3. For radio, radar or microwave failure, proceed as planned.

4. For FCS failure to fixed gain damper in yaw, proceed as planned, attempt to reengage damper and turn FCS reaction controls to "ON."

5. For total yaw damper failure, proceed but do not increase a above 15°. Attempt to reengage damper. Make entry with speed brakes open. Use b-dot if necessary.

6. For FCS failure to fixed gain in pitch or roll, push over to zero "g" at 50 sec. Use speed brakes open for entry at a between 13° and 20°.

7. For total FCS failure in pitch or roll, push over to zero g at 40 sec., extend speed brakes, proceed to Edwards.

8. For ball nose or attitude failure, do not use Hold modes, push over at 50 sec., reduce throttle and continue to Edwards. Enter with dh » 20°. Extend speed brakes.

8. For inadvertent engine shutdown prior to:

 0 - 48 sec Delamar.

48 - 65 sec Hidden Hills.

65 - 70 sec Cuddeback.

70 - Up sec Edwards.

Only one engine start may be attempted - for any emergency situation requiring a turn, jettison will be started as soon as positive "g" is attained.