Flight Procedures Handbook Publications
The following is a list of the Integrated Flight Procedures Handbooks of which this document is a part. These handbooks document integrated and or flight procedural sequences covering major shuttle crew activity plan phases. OMS RCS On-Orbit Operations 10588 Inertial Measurement Unit Alignment 12842 Ascent Orbit Entry Pocket Checklists, Ascent Entry Systems 16873 Procedures and Cue Cards with Rationale Update document through OI-28, including Updated nose wheel steering section New single APU...
Appendix B Flare And Shallow Glide Slope
In the early design of the FSGS geometry, it was decided to use a two-flare approach instead of one flare. The one flare design was more sensitive to trajectory and vehicle disturbances near the ground, and it provided no stable flight time just prior to T D. Using an initial pullup circle for a reference profile minimizes the maximum load factor and eases the monitoring task because the pullup g's are nearly constant. Also, using an IGS before an FF provided a stable flight time, which was...
Trail Mark
This discussion is also limited due to the fact that once the yaw jets are disabled Mach 1 , the YAW L and R and the ROLL L and R lights no longer have a function. At this point, the PITCH U and D lights are the only lights that are still functioning. The PITCH U and D lights take on a new meaning after Q-bar gt 50 psf. Both lights U and D are lit whenever the elevon surface drive rate exceeds 20 deg sec 10 deg sec for only one hydraulic system remaining . Thus, for A L or for entry and Q-bar...
Info Qmb
Left right probe data, no flags unless commfaults Left right probe data, no flags unless commfaults Center air data unless RM dilemma, then NAV data 2.11.4. Altitude Vertical Velocity Indicator AVVI The AVVI Figure 2.11.4-1 displays the navigation or barometric altitude H, ft , and the altitude rate Hdot, ft s . Below 5000 feet, the radar altimeter altitude is displayed on the altitude tape R, ft . The altitude scale, H, is a moving tape read against a fixed digital display which displays the...
Touchdown And Rollout Discretes
T D and rollout are two distinct phases of the orbiter landing. At MGTD, the No-WOW discrete on each gear is set to false zero . When both WOW discretes on one main gear are set false for more than l second, the WOWLON discrete is set true. If the other main gear discretes are not set false within 7.2 sec, a WOW dilemma is annunciated. To clear a WOW dilemma set WOWLON , the crew must manually mode to ROLLOUT by depressing either the Solid Rocket Booster SRB or External Tank ET separation SEP...
Flight Data File
5.2.1. Landing and Rollout Briefing The deorbit prep timeline allows a period of time for an entry briefing. This period, labeled Entry Review, typically occurs about 1 hour 40 minutes before the deorbit burn. Landing and rollout briefing items should include, but are not limited to, the items in the bottom third of the DEL PAD. These are b. Type of HAC overhead or straight-in, left or right turn f. Aimpoint nominal or close-in g. Winds at 50k, 38k, 28k, 20k, 12k, 7k, 3k, 1k and at the surface...
Navigation
The entry navigation software processes inputs from the IMU's, ADTA, Tactical Air Navigation TACAN system, and MSBLS, using a Kalman filter to maintain an estimate of the orbiter state vector. Operating cyclically, the navigation software selects the available sensor measurements each cycle, computes the proper state vector gain based on the measurement via a covariance matrix, applies that gain to the state vector, and then adjusts the covariance matrix to reflect the update. The navigation...
Drag Chute
The addition of the drag chute on the Shuttle has been the biggest single improvement made to the rollout phase. The actual flight stopping distance and brake energy have both been significantly reduced with the aid of the drag chute, thus improving the landing safety margins. Nominal drag chute deploy is planned for every flight. Exceptions might include very slow touchdowns and or very high crosswinds. The pilot initiates nominal chute deploy 2 seconds prior to the start of derotation. For a...
Appendix B Final Flare
Very important factors in arresting the altitude rate are the powerful aerodynamic ground effects of the orbiter. These ground effects grow exponentially as the altitude decreases, and the resulting increase in L D is approximately 25 percent, which eases the landing task for the pilot and guidance at this very critical stage of flight. Figure B.4-1 compares the altitude-altitude rate history of two trajectories, one with ground effects and one without ground effects the resulting altitude rate...
Appendix B Heading Alignment Cone And Prefinal
Before STS-5 the orbiter flew around a heading alignment circle. After STS-4 the reference profile was changed from a circle to an inverted cone Figure B.1-l , where the orbiter would fly a 42 bank angle. This allowed the orbiter to fly more constant bank angles during large turns and also to better manage high-energy situations. Profile options were also included to improve low-energy situations. These options included straight-in approach, radius adjust, and MEP HAC. Of the three, only the...
Info Xxr
2.11.2. Horizontal Situation Indicator HSI The HSI serves several functions including an independent source to compare entry auto guidance, a means of assessing the health of individual Navigation Aids NAVAID's during entry and crew display for flying manually when required. Figure 2.11.2-1 is an HSI display. The HSI displays magnetic heading angle between magnetic North and vehicle direction , course direction primary runway heading with respect to magnetic North , course deviation angular...
Papi Light Outer Glide Slope
To assist the crew in identifying the OGS, PAPI lights are installed 6500 ft and 7500 ft from the threshold of the runway, Figure 3.4-1. The PAPI lights are highly directional and OGS cueing is a function of the apparent change in PAPI light color. There are four PAPI light units, spaced 40 ft apart, at both the 6500 ft close-in aimpoint and 7500 ft nominal aimpoint locations, perpendicular to-the runway centerline due to local conditions and constraints, some PAPI sites may be offset slightly...
Heading Alignment Cone And Prefinal
After the orbiter speed decreases below Mach 2.5, the vehicle enters the TAEM phase of descent guidance. TAEM guidance delivers the vehicle from an altitude of 85,000 ft, at a range to the runway of 60 NM and a speed of Mach 2.5, down to an altitude of 10,000 ft, a range of 6 NM, and a speed of 300 KEAS. The orbiter should be ready to enter the final A L phase of descent guidance. This document addresses only the last two segments of TAEM guidance the heading alignment segment for descending...