Space shuttle contingency functional


DEPARTMENT OF DEFENSE MANNED SPACE FLIGHT SUPPORT OFFICE



Download 2.5 Mb.
Page6/31
Date31.03.2018
Size2.5 Mb.
#45357
1   2   3   4   5   6   7   8   9   ...   31

DEPARTMENT OF DEFENSE

MANNED SPACE FLIGHT SUPPORT OFFICE

Patrick AFB FL 32925-3239

15 February 2003



TAB A TO APPENDIX 1 TO ANNEX C TO DDMS CONTINGENCY FUNCPLAN 3610-03

AIRSPACE CLEARANCE PLANNING GUIDANCE


1. General. This tab provides airspace clearance planning guidance for DOD landing sites. The data presented is based upon the use of the orbiter's own guidance and control systems in the automatic mode and should also be representative of the approach envelope for manually controlled approaches. The SOC will provide the orbiter inbound approach track after notification of an intended landing.
2. Planning Factors.
a. The volume of airspace to be cleared for a particular approach is depicted by Figure 1. This airspace, based upon the geographic center of the airport, provides maneuvering clearance for the orbiter regardless of the runway utilized. The airspace clearance consists of four parts. The first part is a corridor 15 nautical miles (NM) either side of the orbiter's approach course beginning at 35 NM from the geographical center of the airport, upper limit being the orbiter's entry into controlled airspace at flight level (FL) 600 and down to and including FL 300. The second part consists of the airspace within a horizontal radius of 12 to 15 NM from the geographical center of the airport, extending from 15,000 feet above ground level (AGL) up to the upper limits of controlled airspace. The third part is the airspace within a horizontal radius of 6 to 12 NM from the geographical center of the airport, extending from 5,000 AGL up to the upper limits of controlled airspace. The fourth part is the airspace within a horizontal radius of 6 NM from the geographical center of the airport, extending from the surface to the upper limits of controlled airspace.
b. The orbiter will normally maneuver within the heading alignment cone approximately 6 NM in diameter at 30,000 - 40,000 feet, and intercept the final approach course at approximately 12,000 feet, 7 NM from touchdown. Figure 2 shows a typical landing profile.

FIGURE 1


TYPICAL ORBITER APPROACH USING

HEADING ALIGNMENT CONE (HAC)




FIGURE 2


(INTENTIONALLY BLANK)
DEPARTMENT OF DEFENSE


Download 2.5 Mb.

Share with your friends:
1   2   3   4   5   6   7   8   9   ...   31




The database is protected by copyright ©ininet.org 2022
send message

    Main page