Administration

Federal Aviation

FY-2009

Research and Development

Accomplishments

October 2009

Commercial Space Transportation

Federal Aviation Administration

Associate Administrator for Commercial Space Transportation

800 Independence Avenue, S.W., Rm. 331

Washington, D.C. 20591

www.ast.faa.gov 

HQ-10986.INDD

Commercial Space Transportation
Available from

Federal Aviation Administration

Associate Administrator for Commercial Space Transportation

800 Independence Avenue, S.W., Rm. 331

Washington, D.C. 20591

NOTICE

Use of trade names, services, or images associated with corporate entities 

in this document does not constitute official endorsement of such products, 

services, or corporate entities, either expressed or implied, by the Federal 

Aviation Administration.

Photo credits for front cover: 

Upper right corner image, UP Aerospace 

Center right image, Stock Image

Lower right image, Stock Image

Center image, courtesy of Space Exploration Technologies (SpaceX)

Upper left image, courtesy of Futron

Center left image, courtesy of NASA 

Lower left image: Aerospace Corporation
AST FY 2009 R&D Accomplishments

Commercial Space Transportation

1

Mission

AST’s mission is to ensure protection of the 

public, property, and the national security and 

foreign policy interests of the United States 

during commercial launch or reentry activities 

and to encourage, facilitate, and promote 

U.S. commercial space transportation.
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2 AST FY 2009 R&D Accomplishments

Introduction

This booklet describes several Research and Development (R&D) projects undertaken 

by the Associate Administrator for Commercial Space Transportation (AST) in the Federal 

Aviation Administration (FAA). Two of the research projects presented here were initiated 

and funded in Fiscal Year (FY) 2008 and completed in FY 2009. These are presented in the 

“Completed” section of the booklet. There were five research projects initiated and funded 

in FY 2009 and expect to be completed in FY 2010. Of the five, three are presented in 

the “In Progress” section of the booklet. These five new research projects were selected 

and assigned to an AST division to lead the research effort on them, but were able to 

commence only in March 2009, In addition to a description of each project, a summary 

of accomplishments to date is provided. 

The AST safety research supports the development of the policy, standards, and 

guidance material needed to meet FAA goals and objectives. Such research is also essential 

in developing the knowledge necessary to maintain and improve FAA/AST materials 

used to verify that the products and procedures of launch and reentry vehicle and site 

operator licensees, permitees, and applicants adequately comply with applicable safety 

standards. 

To that end, AST formulated and instituted an R&D activity to support its mission and the 

FAA’s strategic goal of safety. The AST Research and Development Plan provides a process for 

effectively applying resources for research based on clearly identified safety priorities each 

fiscal year. This Plan was used to solicit candidate research projects from internal sources, 

such as AST aerospace engineers and projects. External sources, such as the Commercial 

Space Transportation Advisory Committee’s (COMSTAC), were also solicited. 

First, the AST R&D Advisory Board evaluated candidate research projects for relevance 

to AST’s mission, relative importance, and cost. Second, the AST R&D Advisory Board ranked 

the candidate research projects to arrive at a prioritized list to present to the AST R&D Senior 

Steering Committee for review. Third, the AST R&D Senior Steering Committee selected the 

R&D projects to undertake in FY 2009 that had the greatest potential to fulfill AST’s mission 

and to meet its budgeted requirements. Lastly, the R&D Advisory Board and Senior Steering 

Committee held periodic R&D project status reviews throughout the year.
AST FY 2009 R&D Accomplishments

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3

Completed Studies
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4 AST FY 2009 R&D Accomplishments

HIGH ALTITUDE WIND PREDICTION AND MEASURMENT

TECHNOLOGY ASSESSMENT

This document presents an overview of the technologies for gathering wind data 

and atmospheric models for predicting winds. It also presents an assessment of possible 

upgrades to extend the vertical coverage for Doppler Radar Wind Profilers (DRWPs).

Within the Commercial Space Launch Amendments Act of 2004, Congress authorized 

the Federal Aviation Administration (FAA) to promulgate regulations in the areas of 

experimental permits and human spaceflight (crew and passenger) requirements. 

Legislation was written to allow humans to travel into space for the first time on commercial 

launch vehicles and to ensure that the passengers and crew involved in commercial space 

are informed of all risks inherent to space travel, including those associated with the launch 

vehicle. Commercial launch sites have limited equipment and real-time data to support 

real-time launch decision making. In particular, there is a relative paucity of wind data from 

50,000 ft (the altitude reliably attained by high resolution balloon measurements) and 

100,000 ft (the altitude attained by low resolution systems and high performance radars). 

Significantly higher altitudes would require some development. The altitude limitations are 

mitigated by the fact that by 100,000 ft (~ 30 km) air density is reduced from sea values by 

a factor of ~ 100. The aerodynamic drag on vehicles and debris is similarly reduced.

This study evaluates technology to detect winds at these altitudes. Accurate wind data 

at these altitudes is very important for suborbital reusable launch vehicles (RLVs) because 

of the lack of time to adjust the trajectory once the main engine cut-off has occurred. In 

addition, it is important to characterize the tendency of winds to move debris laterally as 

it falls. The dispersion of debris by the winds increases the risk on the ground and in the 

air, when risk to aircraft is considered. This study presents the results of a literature survey 

of possible remote sensing technologies and the sensitivity of proposed systems to high 

altitude wind conditions.

Study approach

1. Conduct literature study of available technologies [i.e., balloon-borne instruments, 

 atmospheric models, radar wind profilers, sounding rockets, Light Detection and 

 Ranging (lidar) instruments] capable of discerning winds in the 50 - 150 kft altitude 

 range. 

2. Conduct survey of sensitivities of proposed systems (models) to high-altitude wind 

 conditions.

3. Conduct survey of accuracies of proposed systems (models) for winds in 50 - 150 kft 

 altitude range.

4. Compare the identified technologies and list pros and cons of each.

5. Assess feasibility of significantly extending the altitude range covered by radar wind 

 profilers.
AST FY 2009 R&D Accomplishments

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Vertical Vertical Bias Precision

 Type Range (km) Resolution (m) (m/s) (m/s) Advantages Disadvantages

 AMPS 17 160 ≤ 0.7 0.6 

High Res

 AMPS 33 350 0.7 1.0

Low Res 

 Jimsphere 17 100-300 ≤ 0.7 0.5 + 1%

 of layer

 wind speed 

50 MHz 20 500 0.1 1.5 

UHF 5 (915 MHz) -

 14 (404 MHz) --- <1.7 1.7

GLOW 25 200 --- 3 up to ~

 12 km

 altitude

MM5 20 (50 hPa) Congurable 1 5 

 (AFWA) 

WRF 32 (10 hPa) Congurable 1 5

 (AFWA)

Summary of System Capabilities

Balloon (1,2,3) Doppler Radar (1,4,5, 6,7) Lidar (8) Mesoscale

Highest accuracy

and vertical 

resolution. 

All weather.

Good accuracy and 

resolution. All 

weather. Good 

temporal resolution. 

Retrievals for wind 

overhead.

Good accuracy and 

resolution. Good 

temporal resolution. 

Retrievals for wind 

overhead. Easier to

locate near launch 

site.

Inexpensive. Can be 

run from one 

location for arbitrary 

site. 

May take ~ hour or 

more to retrieve entire 

prole. Balloon may 

drift 10s of kilometers 

during ascent. For 

radar-tracked balloons 

drop out and sideband 

acquisition may occur.

Not mobile. Subject to

ground clutter, 

sideband ambiguities 

and spurious 

reections. Dropout due 

to low signal (weak 

turbulence) may occur.

Not all weather. 

Technology not as 

mature and performance is not as well 

characterized. Requires 

periodic calibration.

Subject to model biases 

for dierent locations 

(forecast mode). Less 

accurate than collocated 

observations.

5

6. Recommend best mix of wind technologies and modeling or best practices for 

 obtaining wind data (model data) for small RLVs operating out of remote launch 

 sites.

7. Compare the identified technologies and models and list pros and cons of each. 

 Consider:

 1. Cost

 2. Accuracy

 3. Altitude coverage

 4. Timeliness

8. Assess feasibility of significantly extending the altitude range covered by radar wind 

 profilers.

9. Discussions with experts

10. Recommendations for real-time winds for small RLVs operating out of remote launch 

 sites, based on Subtasks 2 - 6. 
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AST FY 2009 R&D Accomplishments

Table 2. Summary of Approximate Vertical Coverage for Various Systems

*Congurable: The basic limitation is the altitude coverage of the data 

used to initialize the models, up to ~ 32 km (105,000 ft) in practice.

Method Peak Altitude Capability (km) Peak Altitude Capability (ft)

Doppler radar 20 65,000

Doppler lidar 25 82,000

Jimsphere 17 56,000

AMPS (High res) 17 56,000

AMPS (Low res) 33 108,000

WRF model 32* 105,0000*

6

Table 2 summarizes the vertical range of the systems considered in this report in both 

metric and English units.

Recommendations

Three measurement systems (balloon, radar, and lidar) have been examined and 

characterized. In addition, numerical weather prediction models have been reviewed. 

Each system has its advantages and disadvantages. In terms of performance alone there 

is little to choose between balloons, radar, and lidar. In terms of accuracy and vertical 

resolution, balloons offer the best performance. However, it takes approximately an hour 

or more for balloons to reach their limiting altitude and in that time balloons can drift to 

distances approaching 100 km. This occurs when winds are strongest and are most likely 

to be an operational factor. There is a limitation on how many balloons can be tracked and 

processed simultaneously and this limits the time resolution. For single balloon tracking, 

the time resolution is limited to an hour or so and during this time large changes in the 

wind can occur. Doppler radar profi lers are less accurate and have poorer resolution but 

are nonetheless likely to be suffi ciently accurate for operational purposes. They offer the 

important advantage that the measured winds are overhead. As a result the Doppler radar 

profi ler is comparatively timely. Lidar has similar advantages to radar profi lers, but lacks 

an all weather capability. However, several commercial launch sites are in locations with 

rather dry climates and days with severe attenuation may occur comparatively seldom. 

In addition, reusable launch vehicle launches may be subject to lightning fl ight rules that 

could already constrain launches when there is signifi cant cloudiness . Numerical weather 

prediction models are less accurate than on site measurements but can be produced for 

a particular site and can be used to anticipate changes. 
AST FY 2009 R&D Accomplishments

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7

The precise system performance (accuracy, precision, reliability) required to support RLV 

flights is not known. Clearly, since balloon systems support launches of large expendable 

launch vehicles and the Space Shuttle, they would be accurate and dependable enough 

to support RLV launches. Since the performance of the large powerful radars such as the 

ER and WR 50 MHz, these most likely would also be adequate. Less certain is the adequacy 

of less capable radars, lidars and numerical weather prediction. 

Balloon systems and the most capable of radar systems should be adequate stand 

alone systems. Both are accurate, reliable, and essentially all-weather. The best balloon 

solution would be one based on GPS. This alleviates the need for expensive high precision 

tracking by radar. At present, there are no operational Doppler lidars. However, lidars offer 

the advantage of mobility. Future lidars should provide a good solution for locations that 

are not limited by layered cloud when lightning constraints allow flight. 

The safest system would be a remote measurement system (radar or lidar) in 

combination with a balloon system. This system would be robust and would offer the 

accuracy, precision, and reliability of the balloon system with the timeliness and localized 

sampling of a radar or lidar. 

Numerical weather prediction (NWP) is less accurate than measurements, but in the 

absence of accuracy criteria for RLVs its utility as a means for assessing wind effects cannot 

be ruled out. Whether NWP as a standalone system is adequate depends on the sensitivities 

of the vehicle and the control requirements. At a minimum, the accuracy of the model 

predictions is a great improvement over climatology. Models can be employed to provide 

situational awareness. They would provide a good indication that present conditions will not 

persist. They will also provide an understanding of the causes of changes in the weather 

that are being experienced and how long unsettled conditions might persist.

Summary

The principles and the operational characteristics of balloon and radar-based techniques 

for measuring upper air winds in support of launches and recoveries have been presented. 

Each technique has advantages and disadvantages. The most effective approach to 

meeting upper air wind requirements may involve a mixed set of instruments, each with 

different strengths.

Balloon-based systems tend to have finer spatial (vertical) resolution than radar-based 

ones, whereas the radar-based systems have finer temporal resolution. The two kinds of 

systems appear to have approximately equal accuracy and reliability. As implemented at 

the Eastern Range, the Quality Control latencies for balloon- and radar-based systems are 

each about 5 minutes. The radar profilers scan a fixed vertical volume whereas balloons 
Commercial Space Transportation

8 AST FY 2009 R&D Accomplishments

drift with the wind. The volume of the latter sample is neither constant from profile to 

profile, nor is the volume overhead. 

The best mix for generating high-quality wind profiles may consist of a DRWP in 

combination with balloons. The former gives more timely observations in a fixed volume, 

while the latter provide higher resolution.

Temporal Winds Database Considerations for Safety

Evaluation of Unguided Suborbital Launch Vehicles

The rise of new inland launch sites in the continental United States has raised awareness 

of the need to ensure suitable environment databases exist to assess the impact of winds 

on planned launch operations of unguided suborbital rockets from these launch sites. 

Quite often launch operators will measure the wind environment at the launch site of their 

planned launches and determine a planned impact point for their single or multistage 

vehicle given this measured wind and the implementation of a wind weighting system. 

In most instances the launch operator needs to account for the temporal effect of winds 

on their planned impact points. These temporal effects in combinations with dispersions 

influence the clear out zone for the launch of these rockets. 

In cooperation with the FAA, the Aerospace Corporation performed a study to 

evaluate the impact of temporal winds on unguided suborbital rockets. This study had 

two objectives:

First, to determine if suitable temporal wind database exists at three inland launch 

sites of interest and 

Second, to determine how much temporal winds can change the planned impact 

point of an unguided suborbital rocket, whether it is a suborbital to 30,000 feet or 360,000 

feet. 

The change in planned trajectories was related to the monthly wind variation.

Aerospace Corporation was tasked to develop this research and development effort and 

began a survey to determine if the Global Gridded Upper Air Station (GGUAS) database, a 

database the FAA regulation calls out, provides suitable environments at the launch sites 

of interest by comparing the GGUAS monthly winds with stations winds collected at these 

three launch sites (or stations). Aerospace Corporation collected existing temporal wind 

data from these stations and stations located at the ETR range and assessed a low altitude 

and high altitude unguided suborbital launch vehicle to determine the relationship between 

the temporal winds and the monthly winds. The figures below represent the launch of 

the Up Aerospace unguided suborbital launch vehicle and preliminary data showing that 
AST FY 2009 R&D Accomplishments

Commercial Space Transportation

0 2 4 6 8 10 12

1

0.8

0.6

0.4

0.2

0

0 2 4 6 8 10 12

1

0.8

0.6

0.4

0.2

0

0 2 4 6 8 10 12

1

0.8

0.6

0.4

0.2

0

0 2 4 6 8 10 12

1

0.8

0.6

0.4

0.2

0

Phoenix, Winter

Phoenix, Summer

Time, hours

Spinning Rocket Winter

Spinning Rocket Winter

Time, hours

Data Courtesy Aerospace Corporation

V Component, Norman OK/January 10

100

1000

-80 -60 -40 -20 0 20 40 60 80

Wind Speed (m/s )

GGUAC Mean

Station Mean

Station Lower Conf

Bound

Station Upper Conf

Bound

Pressure (hPa)

Data Courtesy Aerospace Corp.

9

station monthly winds are in good agreement with the GGUAS monthly winds. In addition, 

the fi gures below summarize the results of the analysis. They show – 

• the ratio of the temporal winds impact ranges relative to the monthly variation and 

• that low performing rockets are much more sensitive to the temporal winds pointing out 

 the need to have wind measurements closer to the actual launch time of these rockets.
Commercial Space Transportation

10 AST FY 2009 R&D Accomplishments

A CASE STUDY ON ROUTINE SPACE VEHICLE OPERATIONS IN

THE NAS FOR NEXTGEN

Futron Corporation was directed by the FAA to develop a short study to identify National 

Airspace System (NAS) integration requirements associated with proposed twice weekly 

commercial space transportation operations. The operations studied and included in this 

report are limited to those based on the Scaled Composites WhiteKnightOne /SpaceShipOne 

operations out of Mojave, California. This combination is the only one that has actually 

flown at this time and was used as a model for the newer, Virgin Galactic, commercial, 

WhiteKnightTwo (WK II) / SpaceShipTwo (SS II) vehicles. There are several other mission 

concepts under development including vertical launch/parachute recovery, horizontal 

air breathing launch with rocket powered Kármán Line penetration (328,000 feet) and 

air breathing powered return and landing. In addition, for the purpose of this study all 

operations are assumed to be from the former Cecil Field Naval Air Station south west of 

Jacksonville, Florida.

The case study was developed to depict typical operations in the 2025 timeframe and 

an assumed flight rate of 2 flights a week. The goal of the study is to uncover any unique 

requirements that must be considered in the development of the Next Generation Air 

Transportation System (NextGen) to allow for this type of commercial space tourism with 

minimal impact on the NAS as it develops.

Several issues that were believed to be critical prior to this study were found to present 

minimal impact to the NAS. The first of these was the impact of high altitude flight through 

commercial airways. After careful study of the flight paths of this type of operation it was 

found the actual footprint of the flight was fairly small and very little airspace was needed. 

Once the space craft is released, it climbs from above 40,000 feet to over 350,000 feet 

returning to the same small area over the ground. On return to between 40,000 and 

70,000 feet altitude, the spacecraft converts to a glider that proceeds on an almost straight 

line to approximately 8,500 feet directly over Cecil Field for landing. Because of the inability 

of the space craft to hold or perform a missed approach, the most important critical issue 

for airspace controllers is the requirement to have a window for the spacecraft to land 

after release from the carrier aircraft. The window for this clearance appears to open 

about 20 minutes after release from the carrier aircraft. Actual release of the spacecraft 

can also be significantly delayed to provide spacing for other aircraft approaching Cecil 

Field giving JAX TRACON controllers’ significant operational flexibility. The window for 

landing would normally be a period less than 5 minutes in duration. After landing, the 

spacecraft is normally clear of the runway within 30 minutes and the parallel runway is 

able to support normal operations throughout the removal of the spacecraft.
AST FY 2009 R&D Accomplishments

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11

Carrier aircraft (WK II) operation will have almost no impact on controllers as it is able 

to fly under a normal Flight Plan and its operation is relatively predictable and does not 

normally present any issues to NAS controllers. The carrier aircraft with SS II departs from 

and returns to Cecil Field like any other aircraft.

All other support aircraft operations are conducted in VFR conditions under normal 

local flight plans and operations are virtually transparent when compared to other normal 

aircraft operations in the area.

It was the top level conclusion of this study that the flights described in this report will not 

have a significant impact on NAS operations. Furthermore, export of this type of operation 

to other geographic areas could be easily integrated into the NAS in other areas, especially 

those with lower traffic density than the northern Florida area west of Jacksonville used in 

the study. Because of the unique nature of these kinds of flights, individual evaluation of 

other proposed sites would be necessary, but there were no systematic issues that would 

prevent export of this type of operation to other locations.
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12 AST FY 2009 R&D Accomplishments

In-Progress

Studies
AST FY 2009 R&D Accomplishments

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13

Non-traditional Mono-Propellants and Oxidizers Guideline Data

Background information

Efforts to develop and use alternative monopropellants and oxidizers for rocket 

propulsion date back to the 1940s, though NASA and DOD have largely abandoned 

them. However in emerging commercial space programs, there have been increased 

efforts in recent years to use nitrous oxide (N2O) and hydrogen peroxide (H2O2) both as 

monopropellants and as oxidizers, predominantly for hybrid systems. Both propellants 

have stability issues. In 2007, two serious incidents occurred with N2O and H2O2, one 

of which resulted in loss of life. Other industries handle these chemicals in extremely large 

quantities without explosions or loss of life.

Project focus

The objective of this research effort is to develop guidelines for safe transport, loading, 

usage, and disposal of N2O and H2O2 in the commercial space industry based upon 

lessons learned in handling and using non-traditional mono-propellants and oxidizers. 

Project plan and deliverables

The research effort is to:

- Determine the current state of knowledge. Examine existing FAA documents 

and other agency standards. Survey the Aerospace industry and other industries 

using these chemicals and review literature for any recent updates.

- Conduct small-scale laboratory tests if necessary. Measurements may be made of 

decomposition and conditions that lead to thermal runaway. 

- Identify regimes where these monopropellants and oxidizers may be safely 

handled.

- Document results and present at Annual FAA Commercial Space Transportation 

Conference or other FAA or industry forum.
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14 AST FY 2009 R&D Accomplishments

Application of GPS to Space Transportation Technologies

Background information

Global Positioning System (GPS) equipment is employed in all the navigation and flight 

safety systems of vehicles regulated by the FAA Office of Commercial Space Transportation 

(AST). Much of this GPS equipment is not space-qualified and consists of modified GPS 

equipment developed for other purposes. The technology associated with GPS (equipment, 

satellites, forecasting of outages, and performance) is evolving rapidly. 

Project focus

The baseline of the study will be an update of the 2006 study performed for AST by 

Aerospace Corporation in specific areas. It will also focus on additional areas of concern 

related to GPS that have emerged since that time.

Project plan and deliverables

The goal of this study is to address GPS technology as employed in the navigation 

and flight safety systems of current and future expendable launch vehicles (ELVs), reusable 

launch vehicles (RLVs), and re-entry vehicles (RVs). The data obtained will be used in the 

safety analyses of existing vehicles and those under development to protect the public 

during flight operations.

The research effort is to:

- Analyze specific use of GPS equipment on vehicles of FAA commercial space 

applicants.

- Survey GPS technology relevant to use on ELVs, RLVs, and RVs and update areas 

of the February 2006 report to AST on GPS technology re: technology realized or 

forecast advancements. 

- Provide AST with recommendations for existing or planned space-qualified GPS 

equipment use on commercial Reentry Vehicles under on-orbit, de-orbit, and reentry conditions. 

- Recommend future areas of study (potentially including ground and flight testing) 

of GPS technology relevant to safe commercial space activities in prioritized order.
AST FY 2009 R&D Accomplishments

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15

Issues and Approaches for Integrating PTP Systems into the

NAS and Beyond

Introduction

The advent of suborbital transport brings the promise of point-to-point (PTP) transportation 

as a revolutionary mode of air transportation. Studies have shown that transatlantic flight 

times for suborbital vehicles from Paris to New York would take approximately one hour, 

less than one-third the travel time required by the supersonic aircraft Concorde, and a 

fraction of the travel time required by conventional air transportation. The potential for 

rapid global passenger transport and fast distribution of goods make PTP transportation 

an attractive space technology concept worth exploiting.

In 2008, the International Space University (ISU) of Strasbourg, France, published a 

report documenting their appraisal of point-to-point transportation technology. This report 

describes the conditions that should be put in place to foster and sustain the growth of 

this industry from technical, market, financial, infrastructure, safety, and legal perspectives. 

Based on the ISU findings, the FAA Office of Commercial Space Transportation has identified 

the need to explore issues and approaches for integrating PTP systems into the U. S. National 

Airspace System (NAS) and beyond (International Airspace and high altitude regimes). The 

analyses would serve to help the FAA formulate effective policies and regulations related 

to air traffic management of suborbital missions.

Description of work

The Volpe National Transportation System Center was selected to perform this study, 

The specific tasks under this study are the following:

Task 1: Identify operational and technical issues that must be addressed for launching 

and operating either supersonic or hypersonic point-to-point (PTP) systems in or through 

the NAS and between transcontinental city pairs (e.g., New York to London, Los Angeles 

to Tokyo, Dubai to Sydney, etc.). The contractor shall identify areas that may require legal, 

regulatory, or policy changes. 

Task 2: Prioritize operational and technical issues, ranking them from “most challenging” 

to “least challenging” and explain the rationale for each ranking.

Task 3: Prioritize recommendations for a path forward to resolve each identified issue.