(a) Lightning protection. A licensee shall ensure that the public is not exposed to hazards due to the initiation of explosives by lightning.
(1) Elements of a lighting protection system. Unless an explosive hazard facility meets the conditions of paragraph (a)(3) of this section, all explosive hazard facilities shall have a lightning protection system to ensure explosives are not initiated by lightning. A lightning protection system shall meet the requirements of this paragraph and include the following:
(i) Air terminal. An air terminal to intentionally attract a lightning strike.
(ii) Down conductor. A low impedance path connecting an air terminal to an earth electrode system.
(iii) Earth electrode system. An earth electrode system to dissipate the current from a lightning strike to ground.
(2) Bonding and surge protection. A lightning protection system must meet the requirements of this paragraph and include the following:
(i) Bonding. All metallic bodies shall be bonded to ensure that voltage potentials due to lightning are equal everywhere in the explosive hazard facility. Any fence within six feet of a lightning protection system shall have a bond across each gate and other discontinuations and shall be bonded to the lightning protection system. Railroad tracks that run within six feet of the lightning protection system shall be bonded to the lightning protection system.
(ii) Surge protection. A lightning protection system shall include surge protection to reduce transient voltages due to lightning to a harmless level for all metallic power, communication, and instrumentation lines entering an explosive hazard facility.
(3) Circumstances where no lightning protection system is required. No lightning protection system is required for an explosive hazard facility when a lightning warning system is available to permit termination of operations and withdrawal of the public to public area distance prior to an electrical storm, or for an explosive hazard facility containing explosives that cannot be initiated by lightning. If no lightning protection system is required, a licensee must ensure the withdrawal of the public to a public area distance prior to an electrical storm.
(4) Testing and inspection. Lightning protection systems shall be visually inspected semiannually and shall be tested once each year for electrical continuity and adequacy of grounding. A licensee shall maintain at the explosive hazard facility a record of results obtained from the tests, including any action taken to correct deficiencies noted.
(b) Electrical power lines. A licensee shall ensure that electric power lines at its launch site meet the following requirements:
(1) Electric power lines shall be no closer to an explosive hazard facility than the length of the lines between the poles or towers that support the lines unless an effective means is provided to ensure that energized lines cannot, on breaking, come in contact with the explosive hazard facility.
(2) Towers or poles supporting electrical distribution lines that carry between 15 and 69 KV, and unmanned electrical substations shall be no closer to an explosive hazard facility than the public area distance for that explosive hazard facility.
(3) Towers or poles supporting electrical transmission lines that carry 69 KV or more, shall be no closer to an explosive hazard facility than the public area distance for that explosive hazard facility.
Sec. Appendix A to Part 420--Method for Defining a Flight Corridor
(a) Introduction
(1) This appendix provides a method for constructing a flight corridor from a launch point for a guided suborbital launch vehicle or any one of the four classes of guided orbital launch vehicles from table 1, Sec. 420.19, without the use of local meteorological data or a launch vehicle trajectory.
(2) A flight corridor includes an overflight exclusion zone in a launch area and, for a guided suborbital launch vehicle, an impact dispersion area in a downrange area. A flight corridor for a guided suborbital launch vehicle ends with the impact dispersion area, and, for the four classes of guided orbital launch vehicles, 5000 nautical miles (nm) from the launch point.
(b) Data requirements
(1) Maps. An applicant shall use any map for the launch site region with a scale not less than 1:250,000 inches per inch in the launch area and 1:20,000,000 inches per inch in the downrange area. As described in paragraph (b)(2), an applicant shall use a mechanical method, a semi-automated method, or a fully-automated method to plot a flight corridor on maps. A source for paper maps acceptable to the FAA is the U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, National Ocean Service.
(i) Projections for mechanical plotting method. An applicant shall use a conic projection. The FAA will accept a ``Lambert-Conformal'' conic projection. A polar aspect of a plane-azimuthal projection may also be used for far northern launch sites.
(ii) Projections for semi-automated plotting method. An applicant shall use cylindrical, conic, or plane projections for semi-automated plotting. The FAA will accept ``Mercator'' and ``Oblique Mercator'' cylindrical projections. The FAA will accept ``Lambert-Conformal'' and ``Albers Equal-Area'' conic projections. The FAA will accept ``Lambert Azimuthal Equal-Area'' and ``Azimuthal Equidistant'' plane projections.
(iii) Projections for fully-automated plotting method. The FAA will accept map projections used by geographical information system software scaleable pursuant to the requirements of paragraph (b)(1).
(2) Plotting Methods.
(i) Mechanical method. An applicant may use mechanical drafting equipment such as pencil, straight edge, ruler, protractor, and compass to plot the location of a flight corridor on a map. The FAA will accept straight lines for distances less than or equal to 7.5 times the map scale on map scales greater than or equal to 1:1,000,000 inches per inch (in/in); or straight lines representing 100 nm or less on map scales less than 1:1,000,000 in/in.
(ii) Semi-automated method. An applicant may employ the range and bearing techniques in paragraph (b)(3) to create latitude and longitude points on a map. The FAA will accept straight lines for distances less than or equal to 7.5 times the map scale on map scales greater than or equal to 1:1,000,000 inches per inch (in/in); or straight lines representing 100 nm or less on map scales less than 1:1,000,000 in/in.
(iii) Fully-automated method. An applicant may use geographical information system software with global mapping data scaleable in accordance with paragraph (b)(1).
(3) Range and bearing computations on an ellipsoidal Earth model.
(i) To create latitude and longitude pairs on an ellipsoidal Earth model, an applicant shall use the following equations to calculate geodetic latitude (+N) and longitude (+E) given the launch point geodetic latitude (+N), longitude (+E), range (nm), and bearing (degrees, positive clockwise from North).
(A) Input. An applicant shall use the following input in making range and bearing computations. Angle units must be in radians.[GRAPHIC] [TIFF OMITTED] TR19OC00.007
(B) Computations. An applicant shall use the following equations to determine the latitude ([phis]2) and longitude ([lambda]2) of a target point situated ``S'' nm from the launch point on an azimuth bearing ([alpha]12) degrees.[GRAPHIC] [TIFF OMITTED] TR19OC00.008 where: a = WGS-84 semi-major axis (3443.91846652 nmi)b = WGS-84 semi-minor axis (3432.37165994 nmi)[GRAPHIC] [TIFF OMITTED] TR19OC00.009 [GRAPHIC] [TIFF OMITTED] TR19OC00.010 [GRAPHIC] [TIFF OMITTED] TR19OC00.011 [GRAPHIC] [TIFF OMITTED] TR19OC00.012 [GRAPHIC] [TIFF OMITTED] TR19OC00.013 [GRAPHIC] [TIFF OMITTED] TR19OC00.014 [GRAPHIC] [TIFF OMITTED] TR19OC00.015 [GRAPHIC] [TIFF OMITTED] TR19OC00.016 [GRAPHIC] [TIFF OMITTED] TR19OC00.017 [GRAPHIC] [TIFF OMITTED] TR19OC00.018 [GRAPHIC] [TIFF OMITTED] TR19OC00.019 [GRAPHIC] [TIFF OMITTED] TR19OC00.020 [GRAPHIC] [TIFF OMITTED] TR19OC00.021 [GRAPHIC] [TIFF OMITTED] TR19OC00.022 [GRAPHIC] [TIFF OMITTED] TR19OC00.023 [GRAPHIC] [TIFF OMITTED] TR19OC00.024 [GRAPHIC] [TIFF OMITTED] TR19OC00.025 [GRAPHIC] [TIFF OMITTED] TR19OC00.026 [GRAPHIC] [TIFF OMITTED] TR19OC00.027 [GRAPHIC] [TIFF OMITTED] TR19OC00.028 [GRAPHIC] [TIFF OMITTED] TR19OC00.029
(ii) To create latitude and longitude pairs on an ellipsoidal Earth model, an applicant shall use the following equations to calculate the distance (S) of the geodesic between two points (P1 and P2), the forward azimuth ([alpha]12) of the geodesic at P1, and the back azimuth ([alpha]21) of the geodesic at P2, given the geodetic latitude (+N), longitude (+E) of P1 and P2. Azimuth is measured positively clockwise from North.
(A) Input. An applicant shall use the following input. Units must be in radians.[GRAPHIC] [TIFF OMITTED] TR19OC00.030
(B) Computations. An applicant shall use the following equations to determine the distance (S), the forward azimuth ([alpha]12) of the geodesic at P1, and the back azimuth ([alpha]12) of the geodesic at P2. [GRAPHIC] [TIFF OMITTED] TR19OC00.031 where: a = WGS-84 semi-major axis (3443.91846652 nmi)b = WGS-84 semi-minor axis (3432.37165994 nmi)[GRAPHIC] [TIFF OMITTED] TR19OC00.032 [GRAPHIC] [TIFF OMITTED] TR19OC00.033 [GRAPHIC] [TIFF OMITTED] TR19OC00.034 [GRAPHIC] [TIFF OMITTED] TR19OC00.035 [GRAPHIC] [TIFF OMITTED] TR19OC00.036 [GRAPHIC] [TIFF OMITTED] TR19OC00.037 [GRAPHIC] [TIFF OMITTED] TR19OC00.038 [GRAPHIC] [TIFF OMITTED] TR19OC00.039 [GRAPHIC] [TIFF OMITTED] TR19OC00.040 [GRAPHIC] [TIFF OMITTED] TR19OC00.041 [GRAPHIC] [TIFF OMITTED] TR19OC00.042 [GRAPHIC] [TIFF OMITTED] TR19OC00.043 [GRAPHIC] [TIFF OMITTED] TR19OC00.044 [GRAPHIC] [TIFF OMITTED] TR19OC00.045 [GRAPHIC] [TIFF OMITTED] TR19OC00.046 [GRAPHIC] [TIFF OMITTED] TR19OC00.047
(c) Creation of a Flight Corridor
(1) To define a flight corridor, an applicant shall:
(i) Select a guided suborbital or orbital launch vehicle, and, for an orbital launch vehicle, select from table 1 of Sec. 420.19 a launch vehicle weight class that best represents the launch vehicle the applicant plans to support at its launch point;
(ii) Select a debris dispersion radius (Dmax) from table A-1 corresponding to the guided suborbital launch vehicle or orbital launch vehicle class selected in paragraph (c)(1)(i);
(iii) Select a launch point geodetic latitude and longitude; and
(iv) Select a flight azimuth.
(2) An applicant shall define and map an overflight exclusion zone using the following method:
(i) Select a debris dispersion radius (Dmax) from table A-1 and a downrange distance (DOEZ) from table A-2 to define an overflight exclusion zone for the guided suborbital launch vehicle or orbital launch vehicle class selected in paragraph (c)(1)(i).
(ii) An overflight exclusion zone is described by the intersection of the following boundaries, which are depicted in figure A-1:
(A) An applicant shall define an uprange boundary with a half-circle arc of radius Dmax and a chord of length twice Dmax connecting the half-circle arc endpoints. The uprange boundary placement on a map has the chord midpoint positioned on the launch point with the chord oriented along an azimuth 90[deg]from the launch azimuth and the half-circle arc located uprange from the launch point.
(B) An applicant shall define the downrange boundary with a half-circle arc of radius Dmax and a chord of length twice Dmax connecting the half-circle arc endpoints. The downrange boundary placement on a map has the chord midpoint intersecting the nominal flight azimuth line at a distance DOEZ inches downrange with the chord oriented along an azimuth 90[deg]from the launch azimuth and the half-circle arc located downrange from the intersection of the chord and the flight azimuth line.
(C) Crossrange boundaries of an overflight exclusion zone are defined by two lines segments. Each is parallel to the flight azimuth with one to the left side and one to the right side of the flight azimuth line. Each line connects an uprange half-circle arc endpoint to a downrange half-circle arc endpoint as shown in figure A-1.
(iii) An applicant shall identify the overflight exclusion zone on a map that meets the requirements of paragraph (b).
(3) An applicant shall define and map a flight corridor using the following method:
(i) In accordance with paragraph (b), an applicant shall draw a flight corridor on one or more maps with the Dmax origin centered on the intended launch point and the flight corridor centerline (in the downrange direction) aligned with the initial flight azimuth. The flight corridor is depicted in figure A-2 and its line segment lengths are tabulated in table A-3.
(ii) An applicant shall define the flight corridor using the following boundary definitions:
(A) An applicant shall draw an uprange boundary, which is defined by an arc-line GB (figure A-2), directly uprange from and centered on the intended launch point with radius Dmax.
(B) An applicant shall draw line CF perpendicular to and centered on the flight azimuth line, and positioned 10 nm downrange from the launch point. The applicant shall use the length of line CF provided in table A-3 corresponding to the guided suborbital launch vehicle or orbital launch vehicle class selected in paragraph (c)(1)(i).
(C) An applicant shall draw line DE perpendicular to and centered on the flight azimuth line, and positioned 100 nm downrange from the launch point. The applicant shall use the length of line DE provided in table A-3 corresponding to the guided suborbital launch vehicle or orbital launch vehicle class selected in paragraph (c)(1)(i).
(D) Except for a guided suborbital launch vehicle, an applicant shall draw a downrange boundary, which is defined by line HI and is drawn perpendicular to and centered on the flight azimuth line, and positioned 5,000 nm downrange from the launch point. The applicant shall use the length of line HI provided in table A-3 corresponding to the orbital launch vehicle class selected in paragraph (c)(1)(i).
(E) An applicant shall draw crossrange boundaries, which are defined by three lines on the left side and three lines on the right side of the flight azimuth. An applicant shall construct the left flight corridor boundary according to the following, and as depicted in figure A-3 :
(1) The first line (line BC in figure A-3) is tangent to the uprange boundary arc, and ends at endpoint C of line CF, as depicted in figure A-3;
(2) The second line (line CD in figure A-3) begins at endpoint C of line BC and ends at endpoint D of line DH, as depicted in figure A-3;
(3) For all orbital launch vehicles, the third line (line DH in figure A-3) begins at endpoint D of line CD and ends at endpoint H of line HI, as depicted in figure A-3; and
(4) For a guided suborbital launch vehicle, the line DH begins at endpoint D of line CD and ends at a point tangent to the impact dispersion area drawn in accordance with paragraph (c)(4) and as depicted in figure A-4.
(F) An applicant shall repeat the procedure in paragraph (c)(3)(ii)(E) for the right side boundary.
(iii) An applicant shall identify the flight corridor on a map that meets the requirements of paragraph (b).
(4) For a guided suborbital launch vehicle, an applicant shall define a final stage impact dispersion area as part of the flight corridor and show the impact dispersion area on a map, as depicted in figure A-4, in accordance with the following:
(i) An applicant shall select an apogee altitude (Hap) for the launch vehicle final stage. The apogee altitude should equal the highest altitude intended to be reached by a guided suborbital launch vehicle launched from the launch point.
(ii) An applicant shall define the impact dispersion area by using an impact range factor [IP(Hap)] and a dispersion factor [DISP(Hap)] as shown below:
(A) An applicant shall calculate the impact range (D) for the final launch vehicle stage. An applicant shall set D equal to the maximum apogee altitude (Hap) multiplied by the impact range factor as shown below:[GRAPHIC] [TIFF OMITTED] TR19OC00.048 where: IP(Hap) = 0.4 for an apogee less than 100 km; and
IP(Hap) = 0.7 for an apogee 100 km or greater.
(B) An applicant shall calculate the impact dispersion radius (R) for the final launch vehicle stage. An applicant shall set R equal to the maximum apogee altitude (Hap) multiplied by the dispersion factor as shown below:[GRAPHIC] [TIFF OMITTED] TR19OC00.049 where: DISP(Hap) = 0.05
(iii) An applicant shall draw the impact dispersion area on a map with its center on the predicted impact point. An applicant shall then draw line DH in accordance with paragraph (c)(3)(ii)(E)(4).
(d) Evaluate the Flight Corridor
(1) An applicant shall evaluate the flight corridor for the presence of any populated areas. If an applicant determines that no populated area is located within the flight corridor, then no additional steps are necessary.
(2) If a populated area is located in an overflight exclusion zone, an applicant may modify its proposal or demonstrate that there are times when no people are present or that the applicant has an agreement in place to evacuate the public from the overflight exclusion zone during a launch.
(3) If a populated area is located within the flight corridor, an applicant may modify its proposal and create another flight corridor pursuant to appendix A, use appendix B to narrow the flight corridor, or complete a risk analysis in accordance with appendix C.
Table A-1--Debris Dispersion Radius (Dmax) (in)------------------------------------------------------------------------
Orbital launch vehicles Suborbital----------------------------------------------------------- launch
vehicles
Small Medium Medium large Large -------------
Guided------------------------------------------------------------------------
87,600 111,600 127,200 156,000 96,000
(1.20 nm) (1.53 nm) (1.74 nm) (2.14 nm) (1.32 nm)------------------------------------------------------------------------
Table A-2--Overflight Exclusion Zone Downrange Distance (Doez) (in)------------------------------------------------------------------------
Orbital launch vehicles Suborbital----------------------------------------------------------- launch
vehicles
Small Medium Medium large Large -------------
Guided------------------------------------------------------------------------
240,500 253,000 310,300 937,700 232,100
(3.30 nm) (3.47 nm) (4.26 nm) (12.86 nm) (3.18 nm)------------------------------------------------------------------------
[GRAPHIC] [TIFF OMITTED] TR19OC00.050
[GRAPHIC] [TIFF OMITTED] TR19OC00.051 [GRAPHIC] [TIFF OMITTED] TR19OC00.052 [GRAPHIC] [TIFF OMITTED] TR19OC00.053 [GRAPHIC] [TIFF OMITTED] TR19OC00.054
Sec. Appendix B to Part 420--Method for Defining a Flight Corridor
(a) Introduction
(1) This appendix provides a method to construct a flight corridor from a launch point for a guided suborbital launch vehicle or any one of the four weight classes of guided orbital launch vehicles from table 1, Sec. 420.19, using local meteorological data and a launch vehicle trajectory.
(2) A flight corridor is constructed in two sections--one section comprising a launch area and one section comprising a downrange area. The launch area of a flight corridor reflects the extent of launch vehicle debris impacts in the event of a launch vehicle failure and applying local meteorological conditions. The downrange area reflects the extent of launch vehicle debris impacts in the event of a launch vehicle failure and applying vehicle imparted velocity, malfunctions turns, and vehicle guidance and performance dispersions.
(3) A flight corridor includes an overflight exclusion zone in the launch area and, for a guided suborbital launch vehicle, an impact dispersion area in the downrange area. A flight corridor for a guided suborbital launch vehicle ends with an impact dispersion area and, for the four classes of guided orbital launch vehicles, 5,000 nautical miles (nm) from the launch point, or where the IIP leaves the surface of the Earth, whichever is shorter.
(b) Data Requirements
(1) Launch area data requirements. An applicant shall satisfy the following data requirements to perform the launch area analysis of this appendix. The data requirements are identified in table B-1 along with sources where data acceptable to the FAA may be obtained.
(i) An applicant must select meteorological data that meet the specifications in table B-1 for the proposed launch site.
Table B-1--Launch Area Data Requirements------------------------------------------------------------------------
Data category Data item Data source------------------------------------------------------------------------Meteorological Data......... Local statistical These data may be
wind data as a obtained from:
function of Global Gridded Upper
altitude up to Air Statistics,
50,000 feet. Climate
Required data Applications Branch
include: altitude National Climatic
(ft), atmospheric Data Center.
density (slugs/ft
\3\), mean East/
West meridianal (u)
and North/South
zonal (v) wind (ft/
sec), standard
deviation of u and
v wind (ft/sec),
correlation
coefficient, number
of observations and
wind percentile (%).Nominal Trajectory Data..... State vector data as Actual launch
function of time vehicle trajectory
after liftoff in data; or trajectory
topocentric launch generation software
point centered that meets the
X,Y,Z,X,Y,Z requirements of
coordinates with paragraph
the X-axis aligned (b)(1)(ii).
with the flight
azimuth. Trajectory
time intervals
shall not be
greater than one
second. XYZ units
are in feet and
X,Y,Z units are in
ft/sec.Debris Data................. A fixed ballistic N/A.
coefficient equal
to 3 lbs/ft \2\ is
used for the launch
area.Geographical Data........... Launch point Geographical surveys
geodetic latitude or Global
on a WGS-84 Positioning System.
ellipsoidal Earth
model.
Launch point
longitude on an
ellipsoidal Earth
model.
Maps using scales of Map types with scale
not less than and projection
1:250,000 inches information are
per inch within 100 listed in the
nm of a launch Defense Mapping
point and Agency, Public
1:20,000,000 inches Sale, Aeronautical
per inch for Charts and
distances greater Publications
than 100 nm from a Catalog. The
launch point. catalog and maps
may be ordered
through the U.S.
Dept. of Commerce,
National Oceanic
and Atmospheric
Administration,
National Ocean
Service.------------------------------------------------------------------------
(ii) For a guided orbital launch vehicle, an applicant shall obtain or create a launch vehicle nominal trajectory. An applicant may use trajectory data from a launch vehicle manufacturer or generate a trajectory using trajectory simulation software. Trajectory time intervals shall be no greater than one second. If an applicant uses a trajectory computed with commercially available software, the software must calculate the trajectory using the following parameters, or clearly and convincingly demonstrated equivalents:
(A) Launch location:
(1) Launch point, using geodetic latitude and longitude to four decimal places; and
(2) Launch point height above sea level.
(B) Ellipsoidal Earth:
(1) Mass of Earth;
(2) Radius of Earth;
(3) Earth flattening factor; and
(4) Gravitational harmonic constants (J2, J3, J4).
(C) Vehicle characteristics:
(1) Mass as a function of time;
(2) Thrust as a function of time;
(3) Specific impulse (ISP) as a function of time; and
(4) Stage dimensions.
(D) Launch events:
(1) Stage burn times; and
(2) Stage drop-off times.
(E) Atmosphere:
(1) Density as a function of altitude;
(2) Pressure as a function of altitude;
(3) Speed of sound as a function of altitude; and
(4) Temperature as a function of altitude.
(F) Winds:
(1) Wind direction as a function of altitude; and
(2) Wind magnitude as a function of altitude.
(I) Aerodynamics: drag coefficient as a function of mach number for each stage of flight showing subsonic, transonic and supersonic mach regions for each stage.
(iii) An applicant shall use a ballistic coefficient ([beta]) of 3 lbs/ft\2\ for debris impact computations.
(iv) An applicant shall satisfy the map and plotting requirements for a launch area of appendix A, paragraph (b).
(2) Downrange area data requirements. An applicant shall satisfy the following data requirements to perform the downrange area analysis of this appendix.
(i) The launch vehicle weight class and method of generating a trajectory used in the launch area shall be used by an applicant in the downrange area as well. Trajectory time intervals must not be greater than one second.
(ii) An applicant shall satisfy the map and plotting data requirements for a downrange area of appendix A, paragraph (b).
(c) Construction of a Launch Area of a Flight Corridor
(1) An applicant shall construct a launch area of a flight corridor using the processes and equations of this paragraph for each trajectory position. An applicant shall repeat these processes at time points on the launch vehicle trajectory for time intervals of no greater than one second. When choosing wind data, an applicant shall use a time period of between one and 12 months.
(2) A launch area analysis must include all trajectory positions whose Z-values are less than or equal to 50,000 ft.
(3) Each trajectory time is denoted by the subscript ``i''. Height intervals for a given atmospheric pressure level are denoted by the subscript ``j'.
(4) Using data from the GGUAS CD-ROM, an applicant shall estimate the mean atmospheric density, maximum wind speed, height interval fall times and height interval debris dispersions for 15 mean geometric height intervals.
(i) The height intervals in the GGUAS source data vary as a function of the following 15 atmospheric pressure levels expressed in millibars: surface, 1000, 850, 700, 500, 400, 300, 250, 200, 150, 100, 70, 50, 30, 10. The actual geometric height associated with each pressure level varies depending on the time of year. An applicant shall estimate the mean geometric height over the period of months selected in subparagraph (1) of this paragraph for each of the 15 pressure levels as shown in equation B1.[GRAPHIC] [TIFF OMITTED] TR19OC00.055 where: Hj = mean geometric height hm = geometric height
for a given month nm = number of observations for a
given monthk = number of wind months of interest
(ii) The atmospheric densities in the source data also vary as a function of the 15 atmospheric pressure levels. The actual atmospheric density associated with each pressure level varies depending on the time of year. An applicant shall estimate the mean atmospheric density over the period of months selected in accordance with subparagraph (1) of this paragraph for each of the 15 pressure levels as shown in equation B2.[GRAPHIC] [TIFF OMITTED] TR19OC00.056 where: [rho]j = mean atmospheric density--[rho]m = atmospheric density for a given monthnm = number of observations for a given monthk = number of wind months of interest
(iii) An applicant shall estimate the algebraic maximum wind speed at a given pressure level as follows and shall repeat the process for each pressure level.
(A) For each month, an applicant shall calculate the monthly mean wind speed (Waz) for 360 azimuths using equation B3;
(B) An applicant shall select the maximum monthly mean wind speed from the 360 azimuths;
(C) An applicant shall repeat subparagraphs (c)(4)(iii)(A) and (B) for each month of interest; and
(D) An applicant shall select the maximum mean wind speed from the range of months. The absolute value of this wind is designated Wmax for the current pressure level.
(iv) An applicant shall calculate wind speed using the means for winds from the West (u) and winds from the North (v). An applicant shall use equation B3 to resolve the winds to a specific azimuth bearing.[GRAPHIC] [TIFF OMITTED] TR19OC00.057 where: az = wind azimuthu = West zonal wind componentv = North zonal wind componentWaz = mean wind speed at azimuth for each month
(v) An applicant shall estimate the interval fall time over a height interval assuming the initial descent velocity is equal to the terminal velocity (VT). An applicant shall use equations B4 through B6 to estimate the fall time over a given height interval.[GRAPHIC] [TIFF OMITTED] TR19OC00.058 [GRAPHIC] [TIFF OMITTED] TR19OC00.059 [GRAPHIC] [TIFF OMITTED] TR19OC00.060 where: [Delta]HTj= height difference between two mean geometric
heights[beta]= ballistic coefficient--[rho]x= mean atmospheric density for the corresponding mean geometric
heightsVTj = terminal velocity
(vi) An applicant shall estimate the interval debris dispersion (Dj) by multiplying the interval fall time by the algebraic maximum mean wind speed (Wmax) as shown in equation B7.[GRAPHIC] [TIFF OMITTED] TR19OC00.061
(5) Once the Dj are estimated for each height interval, an applicant shall determine the total debris dispersion (Di) for each Zi using a linear interpolation and summation exercise, as shown below in equation B8. An applicant shall use a launch point height of zero equal to the surface level of the nearest GGUAS grid location.[GRAPHIC] [TIFF OMITTED] TR19OC00.124 where: n = number of height intervals below jth height interval
(6) Once all the Di radii have been calculated, an applicant shall produce a launch area flight corridor in accordance with the requirements of subparagraphs (c)(6)(i)-(iv).
(i) On a map meeting the requirements of appendix A, paragraph (b), an applicant shall plot the Xi position location on the flight azimuth for the corresponding Zi position;
(ii) An applicant shall draw a circle of radius Di centered on the corresponding Xi position; and
(iii) An applicant shall repeat the instructions in subparagraphs (c)(6)(i)-(ii) for each Di radius.
(iv) The launch area of a flight corridor is the enveloping line that encloses the outer boundary of the Di circles as shown in Fig. B-1. The uprange portion of a flight corridor is described by a semi-circle arc that is a portion of either the most uprange Di dispersion circle, or the overflight exclusion zone (defined by subparagraph (c)(7)), whichever is further uprange.
(7) An applicant shall define an overflight exclusion zone in the launch area in accordance with the requirements of appendix A, subparagraph (c)(2).
(8) An applicant shall draw the launch area flight corridor and overflight exclusion zone on a map or maps that meet the requirements of table B-1.[GRAPHIC] [TIFF OMITTED] TR19OC00.062
(d) Construction of a Downrange Area of a Flight Corridor
(1) The downrange area analysis estimates the debris dispersion for the downrange time points on a launch vehicle trajectory. An applicant shall perform the downrange area analysis using the processes and equations of this paragraph.
(2) The downrange area analysis shall include trajectory positions at a height (the Zi-values) greater than 50,000 feet and nominal trajectory IIP values less than or equal to 5,000 nm. For a guided suborbital launch vehicle, the final IIP value for which an applicant must account is the launch vehicle final stage impact point. Each trajectory time shall be one second or less and is denoted by the subscript ``i'.
(3) An applicant shall compute the downrange area of a flight corridor boundary in four steps, from each trajectory time increment: determine a reduction ratio factor; calculate the launch vehicle position after simulating a malfunction turn; rotate the state vector after the malfunction turn in the range of three degrees to one degree as a function of Xi distance downrange; and compute the IIP of the resulting trajectory. The locus of IIPs describes the boundary of the downrange area of a flight corridor. An applicant shall use the following subparagraphs, (d)(3)(i)-(v), to compute the downrange area of the flight corridor boundary:
(i) Compute the downrange Distance to the final IIP position for a nominal trajectory as follows:
(A) Using equations B30 through B69, determine the IIP coordinates ([phis]max, [lambda]max) for the nominal state vector before the launch vehicle enters orbit where [alpha] in equation B30 is the nominal flight azimuth angle measured from True North.
(B) Using the range and bearing equations of appendix A, paragraph (b)(3), determine the distance (Smax) from the launch point coordinates ([phis]lp, [lambda]lp) to the IIP coordinates ([phis]max, [lambda]max) computed in accordance with (3)(i)(A) of this paragraph.
(C) The distance for Smax may not exceed 5000 nm. In cases when the actual value exceeds 5000 nm the applicant shall use 5000 nm for Smax.
(ii) Compute the reduction ratio factor (Fn) for each trajectory time increment as follows:
(A) Using equations B30 through B69, determine the IIP coordinates ([phis]i, [lambda]i) for the nominal state vector where [alpha] in equation B30 is the nominal flight azimuth angle measured from True North.
(B) Using the range and bearing equations of appendix A, paragraph (b)(3), determine the distance (Si) from the launch point coordinates ([phis]lp, [lambda]lp) to the IIP coordinates ([phis]i, [lambda]i) computed in (3)(ii)(A) of this paragraph.
(C) The reduction ratio factor is:
[GRAPHIC] [TIFF OMITTED] TR19OC00.122
(iii) An applicant shall compute the launch vehicle position and velocity components after a simulated malfunction turn for each Xi using the following method.
(A) Turn duration ([Delta]t) = 4 sec.
(B) Turn angle ([thetas])
[GRAPHIC] [TIFF OMITTED] TR19OC00.123
The turn angle equations perform a turn in the launch vehicle's yaw plane, as depicted in figure B-2.[GRAPHIC] [TIFF OMITTED] TR19OC00.063
(C) Launch vehicle velocity magnitude at the beginning of the turn (Vb) and velocity magnitude at the end of the turn (Ve)[GRAPHIC] [TIFF OMITTED] TR19OC00.064 [GRAPHIC] [TIFF OMITTED] TR19OC00.065
(D) Average velocity magnitude over the turn duration (V)
[GRAPHIC] [TIFF OMITTED] TR19OC00.066
(E) Velocity vector path angle ([gamma]i) at turn epoch
[GRAPHIC] [TIFF OMITTED] TR19OC00.121
(F) Launch vehicle position components at the end of turn duration
[GRAPHIC] [TIFF OMITTED] TR19OC00.067
where: g1 = 32.17405 ft/sec\2\
(G) Launch vehicle velocity components at the end of turn duration [GRAPHIC] [TIFF OMITTED] TR19OC00.068
(iv) An applicant shall rotate the trajectory state vector at the end of the turn duration to the right and left to define the right-lateral flight corridor boundary and the left-lateral flight corridor boundary, respectively. An applicant shall perform the trajectory rotation in conjunction with a trajectory transformation from the X90, Y90, Z90, X90, Y90, Z90, components to E, N, U, E, N, U. The trajectory subscripts ``R'' and ``L'' from equations B15 through B26 have been discarded to reduce the number of equations. An applicant shall transform from to E,N,U,E,N,U to E,F,G,E,F,G. An applicant shall use the equations of paragraph (d)(3)(iv)(A)-(F) to produce the EFG components necessary to estimate each instantaneous impact point.
(A) An applicant must calculate the flight angle ([alpha])
[GRAPHIC] [TIFF OMITTED] TR19OC00.069
[GRAPHIC] [TIFF OMITTED] TR19OC00.101
(B) An applicant shall transform X90,Y90,Z90 to E,N,U[GRAPHIC] [TIFF OMITTED] TR19OC00.102
(C) An applicant shall transform to X90, Y90, Z90 to E, N, U.[GRAPHIC] [TIFF OMITTED] TR19OC00.103
(D) An applicant shall transform the launch point coordinates ([phis]0[lambda]0,h0) to E0,F0,G0[GRAPHIC] [TIFF OMITTED] TR19OC00.104
(E) An applicant shall transform E,N,U to E90,F90,G90[GRAPHIC] [TIFF OMITTED] TR19OC00.070
(F) An applicant shall transform to E,N,U TO E,F,G
[GRAPHIC] [TIFF OMITTED] TR19OC00.071
(v) The IIP computation implements an iterative solution to the impact point problem. An applicant shall solve equations B46 through B69, with the appropriate substitutions, up to a maximum of five times. Each repetition of the equations provides a more accurate prediction of the IIP. An applicant shall use the required IIP computations of paragraphs (d)(3)(v)(A)-(W) below. An applicant shall use this IIP computation for both the left-and right-lateral offsets. The IIP computations will result in latitude and longitude pairs for the left-lateral flight corridor boundary and the right-lateral flight corridor boundary. An applicant shall use the lines connecting the latitude and longitude pairs to describe the entire downrange area boundary of the flight corridor up to 5000 nm or a final stage impact dispersion area.
(A) An applicant shall approximate the radial distance (rk,l) from the geocenter to the IIP. The distance from the center of the Earth ellipsoid to the launch point shall be used for the initial approximation of rk,l as shown in equation B46.[GRAPHIC] [TIFF OMITTED] TR19OC00.072
(B) An applicant shall compute the radial distance (r) from the geocenter to the launch vehicle position.[GRAPHIC] [TIFF OMITTED] TR19OC00.073
If r k,l then the launch vehicle position is below the Earth's surface and an impact point cannot be computed. An applicant must restart the calculations with the next trajectory state vector.
(C) An applicant shall compute the inertial velocity components.
[GRAPHIC] [TIFF OMITTED] TR19OC00.074
where: [omega] = 4.178074x10-3 deg/sec
(D) An applicant shall compute the magnitude of the inertial velocity vector.[GRAPHIC] [TIFF OMITTED] TR19OC00.075
(E) An applicant shall compute the eccentricity of the trajectory ellipse multiplied by the cosine of the eccentric anomaly at epoch [epsi]c).[GRAPHIC] [TIFF OMITTED] TR19OC00.076 where: K = 1.407644x10\16\ ft\3\/sec\2\
(F) An applicant shall compute the semi-major axis of the trajectory ellipse (a\t\).[GRAPHIC] [TIFF OMITTED] TR19OC00.077
If at 0 or at then the trajectory orbit is not elliptical, but is hyperbolic or parabolic, and an impact point cannot be computed. The launch vehicle has achieved escape velocity and the applicant may terminate computations.
(G) An applicant shall compute the eccentricity of the trajectory ellipse multiplied by the sine of the eccentric anomaly at epoch [epsi]s).[GRAPHIC] [TIFF OMITTED] TR19OC00.078
(H) An applicant shall compute the eccentricity of the trajectory ellipse squared [epsi]\2\).[GRAPHIC] [TIFF OMITTED] TR19OC00.079
If at(1-[epsi])-aE] 0 and [epsi] =0 then the trajectory perigee height is positive and an impact point cannot be computed. The launch vehicle has achieved Earth orbit and the applicant may terminate computations.
(I) An applicant shall compute the eccentricity of the trajectory ellipse multiplied by the cosine of the eccentric anomaly at impact ([epsi]ck).[GRAPHIC] [TIFF OMITTED] TR19OC00.080
(J) An applicant shall compute the eccentricity of the trajectory ellipse multiplied by the sine of the eccentric anomaly at impact ([epsi]sk).[GRAPHIC] [TIFF OMITTED] TR19OC00.081
If [epsi]sk <0 then the trajectory orbit does not intersect the Earth's surface and an impact point cannot be computed. The launch vehicle has achieved Earth orbit and the applicant may terminate computations.
(K) An applicant shall compute the cosine of the difference between the eccentric anomaly at impact and the eccentric anomaly at epoch ([Delta][epsi]ck).[GRAPHIC] [TIFF OMITTED] TR19OC00.082
(L) An applicant shall compute the sine of the difference between the eccentric anomaly at impact and the eccentric anomaly at epoch ([Delta][epsi]sk).[GRAPHIC] [TIFF OMITTED] TR19OC00.083
(M) An applicant shall compute the f-series expansion of Kepler's equations.[GRAPHIC] [TIFF OMITTED] TR19OC00.084
(N) An applicant shall compute the g-series expansion of Kepler's equations.[GRAPHIC] [TIFF OMITTED] TR19OC00.085
(O) An applicant shall compute the E,F,G coordinates at impact (Ei,Fi,Gi). [GRAPHIC] [TIFF OMITTED] TR19OC00.086
(P) An applicant shall approximate the distance from the geocenter to the launch vehicle position at impact (rk,2).[GRAPHIC] [TIFF OMITTED] TR19OC00.087 where: aE = 20925646.3255 fte\2\ = 0.00669437999013
(Q) An applicant shall let rk+1,1 = rk,2, substitute rk+1,1 for rk,1 in equation B55 and repeat equations B55--B64 up to four more times increasing ``k'' by an increment of one on each loop (e.g. k[epsi]{1, 2, 3, 4, 5{time} ). If [verbar]r5,1-r5,2[verbar] 1 then the iterative solution does not converge and an impact point does not meet the accuracy tolerance of plus or minus one foot. An applicant must try more iterations, or restart the calculations with the next trajectory state vector.
(R) An applicant shall compute the difference between the eccentric anomaly at impact and the eccentric anomaly at epoch ([Delta][epsi]).[GRAPHIC] [TIFF OMITTED] TR19OC00.088
(S) An applicant shall compute the time of flight from epoch to impact (t).[GRAPHIC] [TIFF OMITTED] TR19OC00.089
(T) An applicant shall compute the geocentric latitude at impact ([phis]').[GRAPHIC] [TIFF OMITTED] TR19OC00.090 Where: +90[deg] [phis]'i -90[deg]
(U) An applicant shall compute the geodetic latitude at impact ([phis]).[GRAPHIC] [TIFF OMITTED] TR19OC00.091 Where: +90[deg][phis]i-90[deg]
(V) An applicant shall compute the East longitude at impact ([lambda]).[GRAPHIC] [TIFF OMITTED] TR19OC00.092
(W) If the range from the launch point to the impact point is equal to or greater than 5000 nm, an applicant shall terminate IIP computations.
(4) For a guided suborbital launch vehicle, an applicant shall define a final stage impact dispersion area as part of the flight corridor and show the area on a map using the following procedure:
(i) For equation B70 below, an applicant shall use an apogee altitude (Hap) corresponding to the highest altitude reached by the launch vehicle final stage in the applicant's launch vehicle trajectory analysis done in accordance with paragraph (b)(1)(ii).
(ii) An applicant shall define the final stage impact dispersion area by using a dispersion factor [DISP(Hap)] as shown below. An applicant shall calculate the impact dispersion radius (R) for the final launch vehicle stage. An applicant shall set R equal to the maximum apogee altitude (Hap) multiplied by the dispersion factor as shown below:[GRAPHIC] [TIFF OMITTED] TR19OC00.093 where: DISP(Hap) = 0.05
(5) An applicant shall combine the launch area and downrange area flight corridor and any final stage impact dispersion area for a guided suborbital launch vehicle.
(i) On the same map with the launch area flight corridor, an applicant shall plot the latitude and longitude positions of the left and right sides of the downrange area of the flight corridor calculated in accordance with subparagraph (d)(3).
(ii) An applicant shall connect the latitude and longitude positions of the left side of the downrange area of the flight corridor sequentially starting with the last IIP calculated on the left side and ending with the first IIP calculated on the left side. An applicant shall repeat this procedure for the right side.
(iii) An applicant shall connect the left sides of the launch area and downrange portions of the flight corridor. An applicant shall repeat this procedure for the right side.
(iv) An applicant shall plot the overflight exclusion zone defined in subparagraph (c)(7).
(v) An applicant shall draw any impact dispersion area on the downrange map with the center of the impact dispersion area on the launch vehicle final stage impact point obtained from the applicant's launch vehicle trajectory analysis done in accordance with subparagraph (b)(1)(ii).
(e) Evaluate the Launch Site
(1) An applicant shall evaluate the flight corridor for the presence of populated areas. If no populated area is located within the flight corridor, then no additional steps are necessary.
(2) If a populated area is located in an overflight exclusion zone, an applicant may modify its proposal or demonstrate that there are times when no people are present or that the applicant has an agreement in place to evacuate the public from the overflight exclusion zone during a launch.
(3) If a populated area is located within the flight corridor, an applicant may modify its proposal or complete an overflight risk analysis in accordance with appendix C.
Sec. Appendix C to Part 420--Risk Analysis
(a) Introduction
(1) This appendix provides a method for an applicant to estimate the expected casualty (Ec) for a launch of a guided expendable launch vehicle using a flight corridor generated either by appendix A or appendix B. This appendix also provides an applicant options to simplify the method where population at risk is minimal.
(2) An applicant shall perform a risk analysis when a populated area is located within a flight corridor defined by either appendix A or appendix B. If the estimated expected casualty exceeds 30x10 -6, an applicant may either modify its proposal, or if the flight corridor used was generated by the appendix A method, use the appendix B method to narrow the flight corridor and then redo the overflight risk analysis pursuant to this appendix. If the estimated expected casualty still exceeds 30x10 -6 the FAA will not approve the location of the proposed launch point.
(b) Data Requirements
(1) An applicant shall obtain the data specified by subparagraphs (b)(2) and (3) and summarized in table C-1. Table C-1 provides sources where an applicant may obtain data acceptable to the FAA. An applicant must also employ the flight corridor information from appendix A or B, including flight azimuth and, for an appendix B flight corridor, trajectory information.
(2) Population data. Total population (N) and the total landmass area within a populated area (A) are required. Population data up to and including 100 nm from the launch point are required at the U.S. census block group level. Population data downrange from 100 nm are required at no greater than 1[deg] x 1[deg] latitude/longitude grid coordinates.
(3) Launch vehicle data. Launch vehicle data consist of the launch vehicle failure probability (Pf), the launch vehicle effective casualty area (Ac), trajectory position data, and the overflight dwell time (td). The failure probability is a constant (Pf = 0.10) for a guided orbital or suborbital expendable launch vehicle. Table C-3 provides effective casualty area data based on IIP range. Trajectory position information is provided from distance computations provided by this appendix for an appendix A flight corridor, or trajectory data used in appendix B for an appendix B flight corridor. The dwell time (td) may be determined from trajectory data produced when creating an appendix B flight corridor.
Table C-1--Overflight Analysis Data Requirements----------------------------------------------------------------------------------------------------------------
Data category Data item Data source----------------------------------------------------------------------------------------------------------------Population Data....................... Total population within a populated Within 100 nm of the launch point:
area (N). U.S. census data at the census
block-group level. Downrange from
100 nm beyond the launch point,
world population data are
available from:
Total landmass area within the Carbon Dioxide Information Analysis
populated area (A). Center (CDIAC) Oak Ridge National
Laboratory
Database--Global Population
Distribution (1990), Terrestrial
Area and Country Name Information
on a One by One Degree Grid Cell
Basis (DB1016 (8-1996)Launch Vehicle Data................... Failure probability--Pf = 0.10..... N/A.
Effective casualty area (Ac)....... See table C-3.
Overflight dwell time.............. Determined by range from the launch
point or trajectory used by
applicant.
Nominal trajectory data (for an See appendix B, table B-1.
appendix B flight corridor only).----------------------------------------------------------------------------------------------------------------
(c) Estimating Corridor Casualty Expectation
(1) A corridor casualty expectation [EC(Corridor)] estimate is the sum of the expected casualty measurement of each populated area inside a flight corridor.
(2) An applicant shall identify and locate each populated area in the proposed flight corridor.
(3) An applicant shall determine the probability of impact in each populated area using the procedures in subparagraphs (5) or (6) of this paragraph. Figures C-1 and C-2 illustrate an area considered for probability of impact (Pi) computations by the dashed-lined box around the populated area within a flight corridor, and figure C-3 illustrates a populated area in a final stage impact dispersion area. An applicant shall then estimate the EC for each populated area in accordance with subparagraphs (7) and (8) of this paragraph.
(4) The Pi computations do not directly account for populated areas whose areas are bisected by an appendix A flight corridor centerline or an appendix B nominal trajectory ground trace. Accordingly, an applicant must evaluate Pi for each of the bi-sections as two separate populated areas, as shown in figure C-4, which shows one bi-section to the left of an appendix A flight corridor's centerline and one to its right.
(5) Probability of impact (Pi) computations for a populated area in an appendix A flight corridor. An applicant shall compute Pi for each populated area using the following method:
(i) For the launch and downrange areas, but not for a final stage impact dispersion area for a guided suborbital launch vehicle, an applicant shall compute Pi for each populated area using the following equation:[GRAPHIC] [TIFF OMITTED] TR19OC00.094 where: x1, x2 = closest and farthest downrange distance
(nm) along the flight corridor centerline to the populated
area (see figure C-1)y1, y2 = closest and farthest cross range distance
(nm) to the populated area measured from the flight corridor
centerline (see figure C-1)[sigma]y = one-third of the cross range distance from the
centerline to the flight corridor boundary (see figure C-1)exp = exponential function (e \x\)Pf = probability of failure = 0.10R = IIP range rate (nm/sec) (see table C-2)C = 643 seconds (constant)
Table C-2--IIP Range Rate vs. IIP Range------------------------------------------------------------------------
IIP range
IIP range (nm) rate (nm/s)------------------------------------------------------------------------0-75....................................................... 0.7576-300..................................................... 1.73301-900.................................................... 4.25
901-1700................................................... 8.851701-2600.................................................. 19.752601-3500.................................................. 42.453501-4500.................................................. 84.854501-5250.................................................. 154.95------------------------------------------------------------------------
(ii) For each populated area within a final stage impact dispersion area, an applicant shall compute Pi using the following method:
(A) An applicant shall estimate the probability of final stage impact in the x and y sectors of each populated area within the final stage impact dispersion area using equations C2 and C3:[GRAPHIC] [TIFF OMITTED] TR19OC00.095 where: X1, X2 = closest and farthest downrange distance,
measured along the flight corridor centerline, measured from
the nominal impact point to the populated area (see figure C-
3)[sigma]x = one-third of the impact dispersion radius (see
figure C-3)exp = exponential function (e \x\)[GRAPHIC] [TIFF OMITTED] TR19OC00.096 where: y1, y2 = closest and farthest cross range distance
to the populated area measured from the flight corridor
centerline (see figure C-3)[sigma]y = one-third of the impact dispersion radius (see
figure C-3)exp = exponential function (e \x\)
(B) If a populated area intersects the impact dispersion area boundary so that the x2 or y2 distance would otherwise extend outside the impact dispersion area, the x2 or y2 distance should be set equal to the impact dispersion area radius. The x2 distance for populated area A in figure C-3 is an example. If a populated area intersects the flight azimuth, an applicant shall solve equation C3 by obtaining the solution in two parts. An applicant shall determine, first, the probability between y1 = 0 and y2 = a and, second, the probability between y1 = 0 and y2 = b, as depicted in figure C-4. The probability Py is then equal to the sum of the probabilities of the two parts. If a populated area intersects the line that is normal to the flight azimuth on the impact point, an applicant shall solve equation C2 by obtaining the solution in two parts in the same manner as with the values of x.
(C) An applicant shall calculate the probability of impact for each populated area using equation C4 below:[GRAPHIC] [TIFF OMITTED] TR19OC00.097 where: Ps = 1-Pf = 0.90 [GRAPHIC] [TIFF OMITTED] TR19OC00.098
(6) Probability of impact computations for a populated area in an appendix B flight corridor. An applicant shall compute Pi using the following method:
(i) For the launch and downrange areas, but not for a final stage impact dispersion area for a guided suborbital launch vehicle, an applicant shall compute Pi for each populated area using the following equation:[GRAPHIC] [TIFF OMITTED] TR19OC00.099 where: y1,y2 = closest and farthest cross range distance
(nm) to a populated area measured from the nominal trajectory
IIP ground trace (see figure C-2)[sigma]y = one-third of the cross range distance (nm) from
nominal trajectory to the flight corridor boundary (see figure
C-2)exp = exponential function (e\x\)Pf = probability of failure = 0.10t = flight time from lift-off to orbital insertion (seconds)td = overflight dwell time (seconds)
(ii) For each populated area within a final stage impact dispersion area, an applicant shall compute Pi using the following method:
(A) An applicant shall estimate the probability of final stage impact in the x and y sectors of each populated area within the final stage impact dispersion area using equations C6 and C7: [GRAPHIC] [TIFF OMITTED] TR19OC00.100 where: x1, x2 = closest and farthest downrange distance,
measured along nominal trajectory IIP ground trace, measured
from the nominal impact point to the populated area (see
figure C-3)[sigma]x = one-third of the impact dispersion radius (see
figure C-3)exp = exponential function (e\x\)[GRAPHIC] [TIFF OMITTED] TR19OC00.105 where: y1, y2 = closest and farthest cross range distance
to the populated area measured from the nominal trajectory IIP
ground trace (see figure C-3)[sigma]y = one-third of the impact dispersion radius (see
figure C-3)exp = exponential function (e\x\)
(B) If a populated area intersects the impact dispersion area boundary so that the x2 or y2 distance would otherwise extend outside the impact dispersion area, the x2 or y2 distance should be set equal to the impact dispersion area radius. The x2 distance for populated area A in figure C-3 is an example. If a populated area intersects the flight azimuth, an applicant shall solve equation C7 by obtaining the solution in two parts. An applicant shall determine, first, the probability between y1 = 0 and y2 = a and, second, the probability between y1 = 0 and y2 = b, as depicted in figure C-4. The probability Py is then equal to the sum of the probabilities of the two parts. If a populated area intersects the line that is normal to the flight azimuth on the impact point, an applicant shall solve equation C6 by obtaining the solution in two parts in a similar manner with the values of x.
(C) An applicant shall calculate the probability of impact for each populated area using equation C8 below:[GRAPHIC] [TIFF OMITTED] TR19OC00.106 where: Ps = 1-Pf = 0.90 [GRAPHIC] [TIFF OMITTED] TR19OC00.107 [GRAPHIC] [TIFF OMITTED] TR19OC00.108
(7) Using the Pi calculated in either subparagraph (c)(5) or (6) of this paragraph, an applicant shall calculate the casualty expectancy for each populated area within the flight corridor in accordance with equation C9. Eck is the casualty expectancy for a given populated area as shown in equation C9, where individual populated areas are designated with the subscript ``k''.[GRAPHIC] [TIFF OMITTED] TR19OC00.109 where: Ac = casualty area (from table C-3)Ak = populated areaNk = population in Ak
Table C-3--Effective Casualty Area (Miles \2\) as a Function of IIP Range (NM)----------------------------------------------------------------------------------------------------------------
Orbital launch vehicles Suborbital------------------------------------------------------------------------------------------------- launch
vehiclesInstantaneous impact point range Small Medium Medium large Large ---------------
(nautical miles) Guided----------------------------------------------------------------------------------------------------------------0-49............................ 3.14x10-2 1.28x10-1 4.71x10-2 8.59x10-2 4.3x10-150-1749......................... 2.47x10-2 2.98x10-2 9.82x10-3 2.45x10-2 1.3x10-11750-5000....................... 3.01x10-4 5.52x10-3 7.82x10-3 1.14x10-2 3.59x10-6----------------------------------------------------------------------------------------------------------------
(8) An applicant shall estimate the total corridor risk using the following summation of risk:[GRAPHIC] [TIFF OMITTED] TR19OC00.110
(9) Alternative casualty expectancy (EC) analyses. An applicant may employ specified variations to the analysis defined by subparagraphs (c)(1)-(8). Those variations are identified in subparagraphs (9)(i) through (vi) of this paragraph. Subparagraphs (i) through (iv) permit an applicant to make conservative assumptions that would lead to an overestimation of the corridor EC compared with the analysis defined by subparagraphs (c)(1)-(8). In subparagraphs (v) and (vi), an applicant that would otherwise fail the analysis prescribed by subparagraphs (c)(1)-(8) may avoid (c)(1)-(8)'s overestimation of the probability of impact in each populated area. An applicant employing a variation shall identify the variation used, show and discuss the specific assumptions made to modify the analysis defined by subparagraphs (c)(1)-(8), and demonstrate how each assumption leads to overestimation of the corridor EC compared with the analysis defined by subparagraphs (c)(1)-(c)(8).
(i) Assume that Px and Py have a value of 1.0 for all populated areas.
(ii) Combine populated areas into one or more larger populated areas, and use a population density for the combined area or areas equal to the most densely populated area.
(iii) For any given populated area, assume Py has a value of one.
(iv) For any given Px sector (an area spanning the width of a flight corridor and bounded by two time points on the trajectory IIP ground trace) assume Py has a value of one and use a population density for the sector equal to the most densely populated area.
(v) For a given populated area, divide the populated area into smaller rectangles, determine Pi for each individual rectangle, and sum the individual impact probabilities to determine Pi for the entire populated area.
(vi) For a given populated area, use the ratio of the populated area to the area of the Pi rectangle from the subparagraph (c)(1)-(8) analysis.
(d) Evaluation of Results
(1) If the estimated expected casualty does not exceed 30x10-6, the FAA will approve the launch site location.
(2) If the estimated expected casualty exceeds 30x10-6, then an applicant may either modify its proposal, or, if the flight corridor used was generated by the appendix A method, use the appendix B method to narrow the flight corridor and then perform another appendix C risk analysis. [Doc. No. FAA-1999-5833, 65 FR 62861, Oct. 19, 2000, as amended by Amdt. 420-2, 71 FR 51972, Aug. 31, 2006]
Sec. Appendix D to Part 420--Impact Dispersion Areas and Casualty
Expectancy Estimate for an Unguided Suborbital Launch Vehicle
(a) Introduction
(1) This appendix provides a method for determining the acceptability of the location of a launch point from which an unguided suborbital launch vehicle would be launched. The appendix describes how to define an overflight exclusion zone and impact dispersion areas, and how to evaluate whether the public risk presented by the launch of an unguided suborbital launch vehicle remains at acceptable levels.
(2) An applicant shall base its analysis on an unguided suborbital launch vehicle whose final launch vehicle stage apogee represents the intended use of the launch point.
(3) An applicant shall use the apogee of each stage of an existing unguided suborbital launch vehicle with a final launch vehicle stage apogee equal to the one proposed, and calculate each impact range and dispersion area using the equations provided.
(4) This appendix also provides a method for performing an impact risk analysis that estimates the expected casualty (Ec) within each impact dispersion area. This appendix provides an applicant options to simplify the method where population at risk is minimal.
(5) If the estimated Ec is less than or equal to 30x10-6, the FAA will approve the launch point for unguided suborbital launch vehicles. If the estimated Ec exceeds 30x10-6, the proposed launch point will fail the launch site location review.
(b) Data Requirements
(1) An applicant shall employ the apogee of each stage of an existing unguided suborbital launch vehicle whose final stage apogee represents the maximum altitude to be reached by unguided suborbital launch vehicles launched from the launch point. The apogee shall be obtained from one or more actual flights of an unguided suborbital launch vehicle launched at an 84 degree elevation.
(2) An applicant shall satisfy the map and plotting data requirements of appendix A, paragraph (b).
(3) Population data. An applicant shall use total population (N) and the total landmass area within a populated area (A) for all populated areas within an impact dispersion area. Population data up to and including 100 nm from the launch point are required at the U.S. census block group level. Population data downrange from 100 nm are required at no greater than 1[deg] x 1[deg] latitude/longitude grid coordinates.
(c) Overflight Exclusion Zone and Impact Dispersion Areas
(1) An applicant shall choose a flight azimuth from a launch point.
(2) An applicant shall define an overflight exclusion zone as a circle with a radius of 1600 feet centered on the launch point.
(3) An applicant shall define an impact dispersion area for each stage of the suborbital launch vehicle chosen in accordance with subparagraph (b)(1) in accordance with the following:
(i) An applicant shall calculate the impact range for the final launch vehicle stage (Dn). An applicant shall set Dn equal to the last stage apogee altitude (Hn) multiplied by an impact range factor [IP(Hn)] in accordance with the following:[GRAPHIC] [TIFF OMITTED] TR19OC00.111 where: IP(Hn) = 0.4 for an apogee less than 100 km, andIP(Hn) = 0.7 for an apogee of 100 km or greater.
(ii) An applicant shall calculate the impact range for each intermediate stage (Di), where i [epsi] {1, 2, 3, . . . (n- 1){time} , and where n is the total number of launch vehicle stages. Using the apogee altitude (Hi) of each intermediate stage, an applicant shall use equation D1 to compute the impact range of each stage by substituting Hi for Hn. An applicant shall use the impact range factors provided by equation D1.
(iii) An applicant shall calculate the impact dispersion radius for the final launch vehicle stage (Rn). An applicant shall set Rn equal to the last stage apogee altitude (Hn) multiplied by an impact dispersion factor [DISP(Hn)] in accordance with the following:[GRAPHIC] [TIFF OMITTED] TR19OC00.112 where: DISP(Hn) = 0.4 for an apogee less than 100 km, andDISP(Hn) = 0.7 for an apogee of 100 km or greater.
(iv) An applicant shall calculate the impact dispersion radius for each intermediate stage (Ri), where i [epsi] {1, 2, 3, . . . (n- 1){time} and where n is the total number of launch vehicle stages. Using the apogee altitude (Hi) of each intermediate stage, an applicant shall use equation D2 to compute an impact dispersion radius of each stage by substituting Hi for Hn. An applicant shall use the dispersion factors provided by equation D2.
(4) An applicant shall display an overflight exclusion zone, each intermediate and final stage impact point (Di through Dn), and each impact dispersion area for the intermediate and final launch vehicle stages on maps in accordance with paragraph (b)(2). [GRAPHIC] [TIFF OMITTED] TR19OC00.113
(d) Evaluate the Overflight Exclusion Zone and Impact Dispersion Areas
(1) An applicant shall evaluate the overflight exclusion zone and each impact dispersion area for the presence of any populated areas. If an applicant determines that no populated area is located within the overflight exclusion zone or any impact dispersion area, then no additional steps are necessary.
(2) If a populated area is located in an overflight exclusion zone, an applicant may modify its proposal or demonstrate that there are times when no people are present or that the applicant has an agreement in place to evacuate the public from the overflight exclusion zone during a launch.
(3) If a populated area is located within any impact dispersion area, an applicant may modify its proposal and define a new overflight exclusion zone and new impact dispersion areas, or perform an impact risk analysis in accordance with paragraph (e).
(e) Impact Risk Analysis
(1) An applicant shall estimate the expected average number of casualties, EC, within the impact dispersion areas according to the following method:
(i) An applicant shall calculate the Ec by summing the impact risk for the impact dispersion areas of the final launch vehicle stage and all intermediate stages. An applicant shall estimate Ec for the impact dispersion area of each stage by using equations D3 through D7 for each of the populated areas located within the impact dispersion areas.
(ii) An applicant shall estimate the probability of impacting inside the X and Y sectors of each populated area within each impact dispersion area using equations D3 and D4:[GRAPHIC] [TIFF OMITTED] TR19OC00.114 where: x1, x2 = closest and farthest downrange distance
to populated area (see figure D-2)[sigma]x = one-third of the impact dispersion radius (see
figure D-2)exp = exponential function (e\x\) [GRAPHIC] [TIFF OMITTED] TR19OC00.115 where: y1, y2 = closest and farthest cross range distance
to the populated area (see figure D-2)[sigma]y = one-third of the impact dispersion radius (see
figure D-2)exp = exponential function (e\x\)[GRAPHIC] [TIFF OMITTED] TR19OC00.116
(iii) If a populated area intersects the impact dispersion area boundary so that the x2 or y2 distance would otherwise extend outside the impact dispersion area, the x2 or y2 distance should be set equal to the impact dispersion area radius. The x2 distance for populated area A in figure D-2 is an example.
(iv) If a populated area intersects the flight azimuth, an applicant shall solve equation D4 by obtaining the solution in two parts. An applicant shall determine, first, the probability between y1 = 0 and y2 = a and, second, the probability between y1 = 0 and y2 = b, as depicted in figure D-3. The probability Py is then equal to the sum of the probabilities of the two parts. If a populated area intersects the line that is normal to the flight azimuth on the impact point, an applicant shall solve equation D3 by obtaining the solution in two parts in the same manner as with the values of x. [GRAPHIC] [TIFF OMITTED] TR19OC00.117
(v) An applicant shall calculate the probability of impact (Pi) for each populated area using the following equation:[GRAPHIC] [TIFF OMITTED] TR19OC00.118 where: Ps = probability of success = 0.98
(vi) An applicant shall calculate the casualty expectancy for each populated area. Eck is the casualty expectancy for a given populated area as shown in equation D6, where individual populated areas are designated with the subscript ``k''.[GRAPHIC] [TIFF OMITTED] TR19OC00.119 where: k { {1, 2, 3, . . . , n{time} Ac = casualty area (from table D-1)Ak = populated areaNk = population in Ak
Table D-1--Effective Casualty Area (Ac) vs. Impact Range------------------------------------------------------------------------
Effective
Impact range (nm) casualty area
(miles\2\)------------------------------------------------------------------------0-4..................................................... 9x10-35-49.................................................... 9x10-350-1,749................................................ 1.1x10-51,750-4,999............................................. 3.6x10-65,000-more.............................................. 3.6x10-6------------------------------------------------------------------------
(vii) An applicant shall estimate the total risk using the following summation of risk: [GRAPHIC] [TIFF OMITTED] TR19OC00.120
(viii) Alternative casualty expectancy (Ec) analysis. An applicant may employ specified variations to the analysis defined by subparagraphs (d)(1)(i)-(vii). Those variations are identified in subparagraphs (viii)(A) through (F) of this paragraph. Subparagraphs (A) through (D) permit an applicant to make conservative assumptions that would lead to an overestimation of Ec compared with the analysis defined by subparagraphs (d)(1)(i)-(vii). In subparagraphs (E) and (F), an applicant that would otherwise fail the analysis prescribed by subparagraphs (d)(1)(i)-(vii) may avoid (d)(1)(i)-(vii)'s overestimation of the probability of impact in each populated area. An applicant employing a variation shall identify the variation used, show and discuss the specific assumptions made to modify the analysis defined by subparagraphs (d)(1)(i)-(vii), and demonstrate how each assumption leads to overestimation of the corridor Ec compared with the analysis defined by subparagraphs (d)(1)(i)-(vii).
(A) Assume that Px and Py have a value of 1.0 for all populated areas.
(B) Combine populated areas into one or more larger populated areas, and use a population density for the combined area or areas equal to the most densely populated area.
(C) For any given populated area, assume Px has a value of one.
(D) For any given populated area, assume Py has a value of one.
(E) For a given populated area, divide the populated area into smaller rectangles, determine Pi for each individual rectangle, and sum the individual impact probabilities to determine Pi for the entire populated area.
(F) For a given populated area, use the ratio of the populated area to the area of the Pi rectangle used in the subparagraph (d)(1)(i)-(vii) analysis.
(2) If the estimated expected casualty does not exceed 30 x 10-6, the FAA will approve the launch point.
(3) If the estimated expected casualty exceeds 30 x 10-6, then an applicant may modify its proposal and then repeat the impact risk analysis in accordance with this appendix D. If no set of impact dispersion areas exist which satisfy the FAA's risk threshold, the applicant's proposed launch site will fail the launch site location review.
Sec. Appendix E to Part 420--Tables for Explosive Site Plan
Table E-1--Division 1.1 Distances to a Public Area or Public Traffic
Route for NEW <=450 lbs------------------------------------------------------------------------
Distance to
public
Distance to traffic
NEW (lbs.) public area route
(ft) \1 2\ distance
(ft) \2\------------------------------------------------------------------------<=0.5......................................... 236 1420.7........................................... 263 1581............................................. 291 1752............................................. 346 2083............................................. 378 2275............................................. 419 2517............................................. 445 26710............................................ 474 28415............................................ 506 30420............................................ 529 31730............................................ 561 33731............................................ 563 33850............................................ 601 36170............................................ 628 377100........................................... 658 395150........................................... 815 489200........................................... 927 556300........................................... 1085 651450........................................... 1243 746------------------------------------------------------------------------\1\ To calculate distance d to a public area from NEW:NEW <=0.5 lbs: d = 2360.5 lbs 450 lbs------------------------------------------------------------------------
Distance to
NEW (lbs) public area (ft) Distance to public
\1\ traffic route (ft)------------------------------------------------------------------------450 lbs1,000,000 lbs
d = 8*NEW \1/3\NEW is in pounds; d is in feet; exp[x] is e\x\; ln is natural logarithm.To calculate NEW from distance d to a public area or traffic route
(noting that d cannot be less than 75 ft):0 <=d <75 ft:
Not allowed (d cannot be less than 75 ft) for NEW <=1000 lbs75 ft <=d<=296 ft
NEW = exp[-30.833 + (307.465 + 260.417*(ln(d)))\1/2\]296 ft10,000 lbs Distance = 24 * W\1/3\Where Distance is in ft and W is in lbs.To calculate weight of hydrogen peroxide from a distance d:d 75 ftW = exp[-134.286 + 71.998*(ln(d)) -12.363*(ln(d))\2\ +
0.7229*(ln(d))\3\]
Table E-8--Separation Distance Criteria for Storage of Liquid Hydrogen and Bulk Quantities of Hydrazine--------------------------------------------------------------------------------------------------------------------------------------------------------
Public area Public area
and intraline Intraline and intraline Intraline
Pounds of distance to distance to Pounds of Pounds of distance to distance to
Pounds of energetic liquid energetic incompatible compatible energetic energetic incompatible compatible
liquid energetic energetic liquid liquid energetic energetic
liquids liquids liquids liquids--------------------------------------------------------------------------------------------------------------------------------------------------------
Over Not Over Distance in Distance in Over Not Over Distance in Distance in
feet feet feet feet--------------------------------------------------------------------------------------------------------------------------------------------------------
............ .............. .............. 60,000 70,000 1,200 130100........................................... 200 600 35 70,000 80,000 1,200 130200........................................... 300 600 40 80,000 90,000 1,200 135300........................................... 400 600 45 90,000 100,000 1,200 135400........................................... 500 600 50 100,000 125,000 1,800 140500........................................... 600 600 50 125,000 150,000 1,800 145600........................................... 700 600 55 150,000 175,000 1,800 150700........................................... 800 600 55 175,000 200,000 1,800 155800........................................... 900 600 60 200,000 250,000 1,800 160900........................................... 1,000 600 60 250,000 300,000 1,800 1651,000......................................... 2,000 600 65 300,000 350,000 1,800 1702,000......................................... 3,000 600 70 350,000 400,000 1,800 1753,000......................................... 4,000 600 75 400,000 450,000 1,800 1804,000......................................... 5,000 600 80 450,000 500,000 1,800 1805,000......................................... 6,000 600 80 500,000 600,000 1,800 1856,000......................................... 7,000 600 85 600,000 700,000 1,800 1907,000......................................... 8,000 600 85 700,000 800,000 1,800 1958,000......................................... 9,000 600 90 800,000 900,000 1,800 2009,000......................................... 10,000 600 90 900,000 1,000,000 1,800 20510,000........................................ 15,000 1,200 95 1,000,000 2,000,000 1,800 23515,000........................................ 20,000 1,200 100 2,000,000 3,000,000 1,800 25520,000........................................ 25,000 1,200 105 3,000,000 4,000,000 1,800 26525,000........................................ 30,000 1,200 110 4,000,000 5,000,000 1,800 27530,000........................................ 35,000 1,200 110 5,000,000 6,000,000 1,800 28535,000........................................ 40,000 1,200 115 6,000,000 7,000,000 1,800 29540,000........................................ 45,000 1,200 120 7,000,000 8,000,000 1,800 30045,000........................................ 50,000 1,200 120 8,000,000 9,000,000 1,800 30550,000........................................ 60,000 1,200 125 9,000,000 10,000,000 1,800 310-------------------------------------------------------------------------------------------------------------------------------------------------------- [Doc. No. FAA-2011-0105, 77 FR 55116, Sept. 7, 2012]
PARTS 421 430 [RESERVED]