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{{Short description|1959 US attempted lunar probe}}
{{Use dmy dates|date=May 2020}}
{{No footnotes|date=May 2020}}
{{Infobox spaceflight
{{Infobox spaceflight
| name = Pioneer P-3
| name = Pioneer P-3
| image = Able IV World's First Space Engine.jpg
| image = Pioneer P-1 P-3 P-30 P-31.jpg
| image_caption = Able IV, The World's first space engine{{what}}
| image_caption = Pioneer P-3 lunar probe

| mission_type = Lunar orbiter
| mission_type = Lunar orbiter
| operator = [[NASA]]
| operator = [[NASA]]
Line 9: Line 11:


| spacecraft_type =
| spacecraft_type =
| manufacturer =
| manufacturer = [[TRW Inc.|TRW Space Technology Laboratories]]
| dry_mass =
| dry_mass =
| launch_mass = {{convert|168.70|kg|lb}}
| launch_mass = {{convert|168.70|kg|lb}}
| power =
| power =


| launch_date = {{start-date|26 November 1959, 07:26:00|timezone=yes}} UTC
| launch_date = {{start-date|26 November 1959, 07:26:00|timezone=yes}} UTC
| launch_rocket = [[Atlas-Able|Atlas D Able]]
| launch_rocket = [[Atlas-Able|Atlas D-Able]]
| launch_site = [[Cape Canaveral Air Force Station|Cape Canaveral]] [[Cape Canaveral Air Force Station Launch Complex 14|LC-14]]
| launch_site = [[Cape Canaveral Air Force Station|Cape Canaveral]], [[Cape Canaveral Air Force Station Launch Complex 14|LC-14]]
| launch_contractor =
| launch_contractor =

| programme = ''[[Pioneer program|Pioneer]]''
| previous_mission = [[Pioneer P-1]]
| next_mission = [[Pioneer P-30]]
}}
}}


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== Mission ==
== Mission ==
The probe was originally intended for launch on Atlas 9C in October, but the launch vehicle was destroyed in a static firing accident on 24 September, so it was decided to use the Atlas D (an operational version of the Atlas ICBM) rather than the Atlas C, which was still a test model. The launch took place on Thanksgiving, 26 November 1959 from LC-14 at Cape Canaveral Air Station using Atlas vehicle 20D, which had originally been the backup booster for the Mercury [[Big Joe (Project Mercury)|Big Joe]] test in September. Since that flight was successful, Atlas 20D was reused for the Able program, coupled to Thor-Able upper stages including an Able x 248 rocket third stage. Because 20D had been custom-built for the Mercury program, it had thicker-gauge skin than the standard Atlas ICBM and could support the additional weight of upper stages. All proceeded normally until T+45 seconds when a shock was recorded by the Atlas's rate gyros followed by the fiberglass payload fairing breaking off of the launch vehicle. The third stage and payload were stripped away after being subjected to severe aerodynamic loads while passing [[Max Q]] and the second stage sustained damage followed by loss of its telemetry at T+104 seconds. The Atlas itself was unaffected by the incident and completed its burn on schedule, impacting in the [[Gulf of Guinea]]. The failure was traced to an improperly vented payload shroud that broke apart when the air pressure inside started exceeding the external pressure as the atmosphere thinned with altitude. In addition to changing prelaunch procedures, the shroud was redesigned to be more aerodynamic on future flights.
The spacecraft was launched on an Air Force-Convair Atlas intercontinental ballistic missile coupled to Thor-Able upper stages including an Able x 248 rocket third stage, on November 26, 1959. The fiberglass payload shroud broke away 45 seconds after launch, subjecting the payload and third stage rocket to critical aerodynamic loads. At 104 seconds after launch, communications with the upper stages was lost and the payload was stripped off followed by the third stage. [[Telemetry]] indicated the first and second stages continued as programmed.


== Spacecraft design ==
== Spacecraft design ==
[[File:Able IV World's First Space Engine.jpg|thumb|Propulsion system of Pioneer P-3]]
Pioneer P-3 was a 1 meter diameter sphere with a propulsion system mounted on the bottom giving a total length of 1.4 meters. The mass of the structure and aluminum alloy shell was 25.3 kg and the propulsion units 88.4 kg. Four solar panels, each 60 x 60 cm and containing 2200 solar cells in 22 100-cell nodules, extended from the sides of the spherical shell in a "paddle-wheel" configuration with a total span of about 2.7 meters. The solar panels charged chemical batteries. Inside the shell, a large spherical hydrazine tank made up most of the volume, topped by two smaller spherical nitrogen tanks and a 90 N injection rocket to slow the spacecraft down to go into lunar orbit, which was designed to be capable of firing twice during the mission. Attached to the bottom of the sphere was a 90 N vernier rocket for mid-course propulsion and lunar orbit maneuvers which could be fired four times. This space engine was designed and built under contract with NASA by the Space Technology Laboratories (STL) of TRW.
Pioneer P-3 was a 1-meter diameter sphere with a [[monopropellant]] propulsion system mounted on the bottom giving a total length of 1.4 meters. The mass of the structure and aluminum alloy shell was 25.3 kg and the propulsion units 88.4 kg. Four solar panels, each 60 x 60 cm and containing 2200 solar cells in 22 100-cell nodules, extended from the sides of the spherical shell in a "paddle-wheel" configuration with a total span of about 2.7 meters. The solar panels charged chemical batteries. Inside the shell, a large spherical [[hydrazine]] tank made up most of the volume, topped by two smaller spherical nitrogen tanks and a 90 N injection rocket to slow the spacecraft down to go into lunar orbit, which was designed to be capable of firing twice during the mission. Attached to the bottom of the sphere was a 90 N vernier rocket for mid-course propulsion and lunar orbit maneuvers which could be fired four times. This space engine was designed and built under contract with NASA by the Space Technology Laboratories (STL) of [[TRW Inc.|TRW]].


Around the upper hemisphere of the hydrazine tank was a ring-shaped instrument platform which held the batteries in two packs, two 5 W UHF transmitters and diplexers, logic modules for scientific instruments, two command receivers, decoders, a buffer/amplifier, three converters, a telebit, a command box, and most of the scientific instruments. Two dipole UHF antennas protruded from the top of the sphere on either side of the injection rocket nozzle. Two dipole UHF antennas and a long VLF antenna protruded from the bottom of the sphere.
Around the upper hemisphere of the hydrazine tank was a ring-shaped instrument platform which held the batteries in two packs, two 5 W [[UHF]] transmitters and [[diplexer]]s, logic modules for scientific instruments, two command receivers, decoders, a buffer/amplifier, three converters, a telebit, a command box, and most of the scientific instruments. Two dipole UHF antennas protruded from the top of the sphere on either side of the injection rocket nozzle. Two dipole UHF antennas and a long [[VLF]] antenna protruded from the bottom of the sphere.


Thermal control was planned to be achieved by a large number of small "propeller blade" devices on the surface of the sphere. The blades themselves were made of reflective material and consist of four vanes which were flush against the surface, covering a black heat-absorbing pattern painted on the sphere. A thermally sensitive coil was attached to the blades in such a way that low temperatures within the satellite would cause the coil to contract and rotate the blades and expose the heat absorbing surface, and high temperatures would cause the blades to cover the black patterns. Square heat-sink units were also mounted on the surface of the sphere to help dissipate heat from the interior.
Thermal control was planned to be achieved by a large number of small "propeller blade" devices on the surface of the sphere. The blades themselves were made of reflective material and consist of four vanes that were flush against the surface, covering a black heat-absorbing pattern painted on the sphere. A thermally sensitive coil was attached to the blades in such a way that low temperatures within the satellite would cause the coil to contract and rotate the blades and expose the heat-absorbing surface, and high temperatures would cause the blades to cover the black patterns. Square heat-sink units were also mounted on the surface of the sphere to help dissipate heat from the interior.


== On-board equipment ==
== On-board equipment ==
The scientific instruments consisted of an [[ion chamber]] and [[Geiger-Müller tube]] to measure total radiation flux, a proportional radiation counter telescope to measure high energy radiation, a [[scintillation counter]] to monitor low-energy radiation, a VLF receiver for natural radio waves, a transponder to study electron density, and part of the television facsimile system and flux-gate and search coil magnetometers mounted on the instrument platform. The television camera pointed through a small hole in the sphere between two of the solar panel mounts. The micrometeorite detector was mounted on the sphere as well. The total mass of the science package including electronics and power supply was 55 kg.
The scientific instruments consisted of an [[ion chamber]] and [[Geiger-Müller tube]] to measure total radiation flux, a proportional radiation counter telescope to measure high energy radiation, a [[scintillation counter]] to monitor low-energy radiation, a VLF receiver for natural radio waves, a transponder to study electron density, and part of the television facsimile system and flux-gate and search coil magnetometers mounted on the instrument platform. The television camera pointed through a small hole in the sphere between two of the solar panel mounts. The micrometeorite detector was mounted on the sphere as well. The total mass of the science package including electronics and power supply was 55 kg.

==See also==
{{Portal|Spaceflight}}
*[[Able (rocket stage)]]


== External links ==
== External links ==
* [http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=PIONX NSSDC Master Catalog: Spacecraft Pioneer P-3]
* [https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=PIONX NSSDC Master Catalog: Spacecraft Pioneer P-3]
* [http://www.sdfo.org/stl/ Space Technology Laboratories Documents Archive]
* [http://www.sdfo.org/stl/ Space Technology Laboratories Documents Archive]
* [http://www.firstspaceengine.com/ The fascinating story of the World's First Space Engine]
* [http://www.firstspaceengine.com/ The fascinating story of the World's First Space Engine] {{Webarchive|url=https://web.archive.org/web/20190611083729/http://www.firstspaceengine.com/ |date=11 June 2019 }}
* [http://sungoldsolar.us/ Portable Solar Panel]


{{Pioneer program | before=[[Pioneer P-1|Pioneer W]] | after=[[Pioneer P-30|Pioneer Y]] }}
{{Pioneer program | before=[[Pioneer P-1|Pioneer W]] | after=[[Pioneer P-30|Pioneer Y]] }}
{{Orbital launches in 1959}}
{{Orbital launches in 1959}}


[[Category:1959 in spaceflight]]
[[Category:Spacecraft launched in 1959]]
[[Category:Pioneer program]]
[[Category:Pioneer program]]

Latest revision as of 17:56, 27 December 2024

Pioneer P-3
Pioneer P-3 lunar probe
Mission typeLunar orbiter
OperatorNASA
Mission durationFailed to orbit
Spacecraft properties
ManufacturerTRW Space Technology Laboratories
Launch mass168.70 kilograms (371.9 lb)
Start of mission
Launch date26 November 1959, 07:26:00 (1959-11-26UTC07:26Z) UTC
RocketAtlas D-Able
Launch siteCape Canaveral, LC-14
The Atlas-Able rocket

Pioneer P-3 (also known as Atlas-Able 4 or Pioneer X) was intended to be a lunar orbiter probe, but the mission failed shortly after launch. The objectives were to place a highly instrumented probe in lunar orbit, to investigate the environment between the Earth and Moon, and to develop technology for controlling and maneuvering spacecraft from Earth. It was equipped to take images of the lunar surface with a television-like system, estimate the Moon's mass and topography of the poles, record the distribution and velocity of micrometeorites, and study radiation, magnetic fields, and low frequency electromagnetic waves in space. A mid-course propulsion system and injection rocket would have been the first United States self-contained propulsion system capable of operation many months after launch at great distances from Earth and the first U.S. tests of maneuvering a satellite in space.

Mission

[edit]

The probe was originally intended for launch on Atlas 9C in October, but the launch vehicle was destroyed in a static firing accident on 24 September, so it was decided to use the Atlas D (an operational version of the Atlas ICBM) rather than the Atlas C, which was still a test model. The launch took place on Thanksgiving, 26 November 1959 from LC-14 at Cape Canaveral Air Station using Atlas vehicle 20D, which had originally been the backup booster for the Mercury Big Joe test in September. Since that flight was successful, Atlas 20D was reused for the Able program, coupled to Thor-Able upper stages including an Able x 248 rocket third stage. Because 20D had been custom-built for the Mercury program, it had thicker-gauge skin than the standard Atlas ICBM and could support the additional weight of upper stages. All proceeded normally until T+45 seconds when a shock was recorded by the Atlas's rate gyros followed by the fiberglass payload fairing breaking off of the launch vehicle. The third stage and payload were stripped away after being subjected to severe aerodynamic loads while passing Max Q and the second stage sustained damage followed by loss of its telemetry at T+104 seconds. The Atlas itself was unaffected by the incident and completed its burn on schedule, impacting in the Gulf of Guinea. The failure was traced to an improperly vented payload shroud that broke apart when the air pressure inside started exceeding the external pressure as the atmosphere thinned with altitude. In addition to changing prelaunch procedures, the shroud was redesigned to be more aerodynamic on future flights.

Spacecraft design

[edit]
Propulsion system of Pioneer P-3

Pioneer P-3 was a 1-meter diameter sphere with a monopropellant propulsion system mounted on the bottom giving a total length of 1.4 meters. The mass of the structure and aluminum alloy shell was 25.3 kg and the propulsion units 88.4 kg. Four solar panels, each 60 x 60 cm and containing 2200 solar cells in 22 100-cell nodules, extended from the sides of the spherical shell in a "paddle-wheel" configuration with a total span of about 2.7 meters. The solar panels charged chemical batteries. Inside the shell, a large spherical hydrazine tank made up most of the volume, topped by two smaller spherical nitrogen tanks and a 90 N injection rocket to slow the spacecraft down to go into lunar orbit, which was designed to be capable of firing twice during the mission. Attached to the bottom of the sphere was a 90 N vernier rocket for mid-course propulsion and lunar orbit maneuvers which could be fired four times. This space engine was designed and built under contract with NASA by the Space Technology Laboratories (STL) of TRW.

Around the upper hemisphere of the hydrazine tank was a ring-shaped instrument platform which held the batteries in two packs, two 5 W UHF transmitters and diplexers, logic modules for scientific instruments, two command receivers, decoders, a buffer/amplifier, three converters, a telebit, a command box, and most of the scientific instruments. Two dipole UHF antennas protruded from the top of the sphere on either side of the injection rocket nozzle. Two dipole UHF antennas and a long VLF antenna protruded from the bottom of the sphere.

Thermal control was planned to be achieved by a large number of small "propeller blade" devices on the surface of the sphere. The blades themselves were made of reflective material and consist of four vanes that were flush against the surface, covering a black heat-absorbing pattern painted on the sphere. A thermally sensitive coil was attached to the blades in such a way that low temperatures within the satellite would cause the coil to contract and rotate the blades and expose the heat-absorbing surface, and high temperatures would cause the blades to cover the black patterns. Square heat-sink units were also mounted on the surface of the sphere to help dissipate heat from the interior.

On-board equipment

[edit]

The scientific instruments consisted of an ion chamber and Geiger-Müller tube to measure total radiation flux, a proportional radiation counter telescope to measure high energy radiation, a scintillation counter to monitor low-energy radiation, a VLF receiver for natural radio waves, a transponder to study electron density, and part of the television facsimile system and flux-gate and search coil magnetometers mounted on the instrument platform. The television camera pointed through a small hole in the sphere between two of the solar panel mounts. The micrometeorite detector was mounted on the sphere as well. The total mass of the science package including electronics and power supply was 55 kg.

See also

[edit]
[edit]
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