four wheeled vehicle was made with modification of the steering system from
electric control to proportional hydraulic control in order to reduce the pavement
loading and improve the steering capability of the vehicle. A cryogenic hydrogen
inflation system was developed in Palestine and considered suitable for field use.
In May 1970 the Balloon Panel endorsed three main fields of development that
drove the program for the next five years. First, increase long duration balloon
capability for zero-pressure flights of up to 72 hours, super-pressure flights for
several weeks, and launching balloons up to a volume of 100 million cubic feet.
Second, improve flight data bandwidths for science support. Third, pursue the
development of a high quality balloon facility in the southern hemisphere.
In April 1971, Mr. Alfred Shipley became the Director and all the staff were
consolidated into one group in Palestine, Texas. Planning for a new payload staging
building and launch pad was started; these facilities to be located on the 295 acre
site west of the present facilities. Improvements were started in the Consolidated
Instrument Package (CIP) as well as using Omega for flight navigation. Over the
next several years new electronic data and navigation systems were implemented,
improving system reliability and data bandwidth. From 1971 to 1975 the flight success rate oscillated from 81% to a high of 89.5% in fiscal 1975. In this period, balloon reliability oscillated with electronic system reliability improving.
Balloon flights during this period were launched from Toowoomba, Australia
and Sioux City, Iowa, Parana, Argentina, Rio Cuarto, Argentina, Midland, Texas
and Hope, Arkansas, with the majority being from Palestine, Texas. In March
1973 a super-pressure balloon launched near Brisbane, Australia completed two
orbits of the Earth at 23° to 30° south latitude. The flight was terminated by command and the payload recovered 9 miles from the launch site; the first planned
recovery of a global flight. By the end of fiscal year 1975, the NSBF had completed over 1,000 balloon flights including 894 from Palestine, Texas.
In the period between 1975 and 1978, NSBF continued refining operational
capability with better computers, upgraded flight electronic packages, more capable tracking aircraft (replacing the Cessna 310J with a Cessna 410A), and development of a simple ranging system that used the flight telemetry system.
Operational techniques were improved with flight readiness reviews, standard
procedures for taking low-level wind sounding, and acquisition of an MPS-19
auto-track radar system. In July 1978 the new staging building was completed and
put into use after a number of budget delays.
The development of a better long duration flight capability started with a
detailed study in 1977 of a dual balloon system using a zero-pressure balloon for
weight carrying and a super-pressure sphere for ballast. Development of the Sky
Anchor system included a large number of test flights through 1982, with mixed
results.
By 1977 NSBF was experiencing an increased failure rate on heavy load flights
(defined as having a total suspended weight in excess of 1,500 kg) from around 25%
to 43% in the previous two years. Investigation was focused into two areas: launch
Appendix 1: A Brief History of the NSBF/CSBF 259
electric control to proportional hydraulic control in order to reduce the pavement
loading and improve the steering capability of the vehicle. A cryogenic hydrogen
inflation system was developed in Palestine and considered suitable for field use.
In May 1970 the Balloon Panel endorsed three main fields of development that
drove the program for the next five years. First, increase long duration balloon
capability for zero-pressure flights of up to 72 hours, super-pressure flights for
several weeks, and launching balloons up to a volume of 100 million cubic feet.
Second, improve flight data bandwidths for science support. Third, pursue the
development of a high quality balloon facility in the southern hemisphere.
In April 1971, Mr. Alfred Shipley became the Director and all the staff were
consolidated into one group in Palestine, Texas. Planning for a new payload staging
building and launch pad was started; these facilities to be located on the 295 acre
site west of the present facilities. Improvements were started in the Consolidated
Instrument Package (CIP) as well as using Omega for flight navigation. Over the
next several years new electronic data and navigation systems were implemented,
improving system reliability and data bandwidth. From 1971 to 1975 the flight success rate oscillated from 81% to a high of 89.5% in fiscal 1975. In this period, balloon reliability oscillated with electronic system reliability improving.
Balloon flights during this period were launched from Toowoomba, Australia
and Sioux City, Iowa, Parana, Argentina, Rio Cuarto, Argentina, Midland, Texas
and Hope, Arkansas, with the majority being from Palestine, Texas. In March
1973 a super-pressure balloon launched near Brisbane, Australia completed two
orbits of the Earth at 23° to 30° south latitude. The flight was terminated by command and the payload recovered 9 miles from the launch site; the first planned
recovery of a global flight. By the end of fiscal year 1975, the NSBF had completed over 1,000 balloon flights including 894 from Palestine, Texas.
In the period between 1975 and 1978, NSBF continued refining operational
capability with better computers, upgraded flight electronic packages, more capable tracking aircraft (replacing the Cessna 310J with a Cessna 410A), and development of a simple ranging system that used the flight telemetry system.
Operational techniques were improved with flight readiness reviews, standard
procedures for taking low-level wind sounding, and acquisition of an MPS-19
auto-track radar system. In July 1978 the new staging building was completed and
put into use after a number of budget delays.
The development of a better long duration flight capability started with a
detailed study in 1977 of a dual balloon system using a zero-pressure balloon for
weight carrying and a super-pressure sphere for ballast. Development of the Sky
Anchor system included a large number of test flights through 1982, with mixed
results.
By 1977 NSBF was experiencing an increased failure rate on heavy load flights
(defined as having a total suspended weight in excess of 1,500 kg) from around 25%
to 43% in the previous two years. Investigation was focused into two areas: launch
Appendix 1: A Brief History of the NSBF/CSBF 259