Orbiting Vehicle orOV, originally designatedSATAR (SATellite - Atmospheric Research), comprised five different series of standardized Americansatellites operated by theUS Air Force, launched between 1965 and 1971. Forty seven satellites were built, of which forty three were launched and thirty seven reachedorbit. With the exception of the OV3 series andOV4-3, they were launched as secondary payloads, using excess space on other missions. This resulted in extremely low launch costs and short proposal-to-orbit times. Typically, OV satellites carried scientific and/or technological experiments, 184 being successfully orbited through the lifespan of the program. A common research focus was assessing the hazards of the near Earth environment to astronauts and equipment.

The first OV series, designated OV1, was built byGeneral Dynamics and carried onsuborbitalAtlas missile tests; the satellites subsequently placed themselves into orbit by means of anAltair-2kick motor. The three (of five planned)Northrop-built OV2 satellites were built using parts left over following the cancellation of theAdvanced Research Environmental Test Satellite and flew onTitan IIIC test flights.Space General built the OV3 satellites, the only series to be launched on dedicated rockets; six were launched onScout-B rockets between 1966 and 1967. OV4 satellites were launched as part of a test flight for theManned Orbiting Laboratory (MOL), with two satellites conducting a communications experiment whilst a third, OV4-3, was the primary payload, aboilerplate mockup of the MOL space station. Two further OV4 satellites, duplicates of the first two, were built but not launched. OV5 satellites were launched as secondary payloads on Titan IIIC rockets as part of theEnvironmental Research Satellite program.

The OV program was phased out in the late 1960s, succeeded by theSpace Test Program, which focused on tailored satellites with specific payloads rather than standardized ones. The last of the series (an OV1) flew in 1971 (under the auspices of the new program).

The Orbiting Vehicle satellite program arose from a US Air Force initiative, begun in the early 1960s, to reduce the expense of space research. Through this initiative, satellites would be standardized to improve reliability and cost-efficiency, and where possible, they would fly on test vehicles and/or piggybacked on other satellite launches. In 1961, the Air Force Office of Aerospace Research (OAR) created the Aerospace Research Support Program (ARSP) to request satellite research proposals and choose mission experiments. The USAF Space and Missiles Organization created their own analog of the ARSP called the Space Experiments Support Program (SESP), which sponsored a greater proportion of technological experiments than the ARSP.^[1]: 417

In 1966, the OAR annual budget was only aboutUS$10,000,000 (equivalent to $96,912,821 in 2024), which was notably low. This was partly possible due to the satellites being launched as secondary payloads on rocket test flights. Since these were necessarily of lower reliability than launches on seasons rockets, this meant the failure rate was higher: of the five OV missions launched in 1965, only one was successful. As each rocket launched to a unique orbit, failure to loft a satellite on a given launch meant the loss of data to be gained on that particular course. Experiments built for a certain flight, designed for their rocket's orbit, often had no back-up.^[2]

Experiments to be flown on the OV satellites (as well as the 100+sounding rockets also flown under the auspices of OAR) were proposed by various laboratories in pursuit of their current research projects. These ranged in size from small black boxes to complete satellites. Each lab supported the building and testing of experiments as well as analysis of data returned from them. OAR prioritized the experiments on their scientific or engineering merit and also their feasibility; after picking the experiments, OAR then modified their choices based on funding available and managerial oversight. These final choices were passed by Air Force Headquarters and the Department of Defense—NASA was also consulted to ensure they were not launching flights to acquire the same data. OAR selected 22 experiments for satellite flights in 1966 and 30 for 1967.^[2]

Implementation of the OV program, as well as procurement of the launching rockets, was generally carried out by the Los Angeles OAR office, commanded by Lt. Col. John C. Hill, and sited at Air Force Space Systems Division (SSD) Headquarters in Los Angeles. Integration of the rocket and satellite was managed by SSD and the Air Force Ballistic Systems Division.^[2]

Five distinct OV series of standardized satellites were developed under the auspices of these agencies.^[1]: 425

The OV1 series was an evolution of the 2.7 m "Scientific Passenger Pods" (SPP), which, starting on 2 October 1961, were affixed to suborbital Atlas missile tests and conducted scientific experiments during their short time in space. General Dynamics received a $2 million contract on 13 September 1963 to build a new version of the SPP (called the Atlas Retained Structure (ARS)) that would carry a self-orbiting satellite. Once the Atlas missile and ARS reached apogee, the satellite inside would be deployed and thrust itself into orbit. In addition to the orbital SPP, General Dynamics would create six of these satellites, each to be 3.66 m (12.0 ft) long with a diameter of .762 m (2 ft 6.0 in), able to carry a 136 kg (300 lb) payload into a circular 805 km (500 mi) orbit.

Dubbed "Satellite for Aerospace Research" (SATAR), the series of satellites was originally to be launched from theEastern Test Range on Atlas missions testing experimental Advanced Ballistic Re-Entry System (ABRES) nosecones. However, in 1964, the Air Force transferred ABRES launches to theWestern Test Range causing a year's delay for the program. Moreover, because WTR launches would be into polar orbit as opposed to the low-inclination orbits typical of ETR launches, less mass could be lofted into orbit using the same thrust, and the mass of the SATAR satellites had to be reduced.^[1]: 417

AfterOV1-1, the last ABRES test launch, OV1-2 through 12 were launched on decommissionedAtlas DICBMs, with the exception ofOV1-6, launched via theTitan IIIC tasked for theManned Orbiting Laboratory test flight. The OV1 series fromOV1-13 onward were launched on decommissionedAtlas Fs.^{[1]: 418, 420–421}

The standard OV1 satellite, 1.387 m (4 ft 6.6 in) long and .69 m (2 ft 3 in) in diameter, consisted of a cylindrical experiment housing capped with flattened cones on both ends^[3] containing 5000 solar cells producing 22watts of power. Two .46 m (1 ft 6 in) antennae for transmitting telemetry and receiving commands extended from the sides of the spacecraft. 12 helium-pressurized hydrogen peroxide thrusters provided attitude control. Starting withOV1-7, the solar cells were flat rather than rounded, and the satellites carried the Vertistat attitude system that used a Sun sensor to determine the spacecraft's orientation to the Sun.^{[1]: 418–429}OV1-13 andOV1-14 were the first in the OV1 series to usepulse-code modulation digitaltelemetry, which afforded the return of more and more precise data from the satellites.^[4]

Ultimately, only the first of the SATARs, (OV1-1, called Atmospheric Research Vehicle (ARV) at the time)^[5]: 24 ever flew piggyback on an ABRES mission. The rest were flown on ex-ICBM Atlas D and F boosters specifically purchased by the OAR for the OV1 series (exceptOV1-6, which flew on theManned Orbiting Laboratory test flight on 2 November 1966).^{[1]: 418–422} The early Atlas D's were launched from "coffin" silos, and their aiming point was typically the island ofGuam.^[2] The satellites were mounted in the nose cone of the launching rocket; OV1-1, OV1-3 and OV1-86 were side mounted. A jettisonable propulsion module with anAltair-2 solid-propellant motor provided the thrust for final orbital insertion.^[1]: 418

The OV1/Atlas combination was economical for the time, costing justUS$1,250,000 (equivalent to $12,114,103 in 2024) per launch.^[1]: 418 By flying as many as three satellite pods on a single rockets, payload costs were brought down significantly.^[2] The standardized format also afforded a quick experiment proposal-to-launch period of just fifteen months.^[1]: 418 The OV-1 program was managed by Lt. Col. Clyde Northcott, Jr.^[6]

Data fromOV1-4's Tissue EquivalentIonization Chamber, calibrated against a similar instrument orbited onGemini 4, determined the radiation dose Gemini astronauts traveling at OV1-4's altitude (~950 km (590 mi)) would receive: 4rads per day at a 30° inclination orbit or 1.5 rads per day at a 90° (polar) inclination orbit.^[7]

In late May 1967, during a period of high solar and magnetic activity,OV1-9 returned the first evidence of Earth's long theorized but never measured electric field. The satellite detected a stream of protons flowing out of the atmosphere into space moving at more than 60,000 km (37,000 mi) per second. OV1-9 also studied the variation ofprotonfluxes in the outerVan Allen Belt during that same period, determining that fluxes were ten times greater four days after May's maximum solar activity than they had been before the flare; it took ten days for the fluxes to return to normal levels.^[8] The X-ray spectrometer on the co-launched OV1-10 returned the most comprehensive set of solar X-ray observations to date. These data enabled scientists to determine the relative density of neon to magnesium in the solar corona through direct observation rather than using complicated mathematical models. The ratio of neon to magnesium was found to be 1.47 to 1 (+/- .38).^[9]

OV1-13, launched 6 April 1968, measured increases in energy and intensity of electrons during a geomagnetic storm that took place 10 June 1968.^[10] OV1-13 data also clarified how the particle flow caused by solar storms created these high altitude increases.^[11]

Data returned byOV1s 15 and16 returned the first substantial set of data on the density of Earth's atmosphere between the altitudes of 100 km (62 mi) and 200 km (120 mi) and proved that increased solar activity increased the air density at high altitudes, contradicting the prevailing model of the time.^[12] Moreover, the satellites determined that the density of the upper atmosphere was 10% lower than predicted by theoretical models.^[13] OV1-15/16 data led to improved atmospheric models that allowed the Air Force to better predict where and when satellites would decay and reenter.^[12]

From 1966-69, gravity-gradient stabilization was tested in low Earth orbit on several satellites of theUnited States Air Force's OV-1 series with a system called Vertistat. Consisting of three 15.5 m (51 ft)-long horizontal booms forming a 'y' and two 19 m (62 ft)-long vertical booms,^[14] Vertistat was used unsuccessfully onOV1-7,OV1-86, andOV1-17, but successfully onOV1-10.^[1]

^[20][21]

The OV2 series of satellites was originally designed as part of the ARENTS (Advanced Research Environmental Test Satellite) program, intended to obtain supporting data for theVela satellites, which monitored the Earth for violations of the 1963Partial Test Ban Treaty. Upon the cancellation of ARENTS due to delays in theCentaur rocket stage, the program's hardware (developed byGeneral Dynamics) was repurposed to fly on theTitan III^{[1]: 417 : 422} (initially the A,^[22] ultimately the C) booster test launches.^[1] The USAF contractedNorthrop to produce these satellites, with William C. Armstrong of Northrop Space Laboratories serving as the program manager.^[22]

The OV2 satellites were all designed on the same plan, roughly cubical structures of aluminum honeycomb, .61 m (2.0 ft) in height, and .58 m (1.9 ft) wide, with four 2.3 m (7.5 ft) paddle-like solar panels mounted at the four upper corners, each with 20,160 solar cells. The power system, which includedNiCd batteries for night-time operations, provided 63 W of power. Experiments were generally mounted outside the cube while satellite systems, including tape recorder, command receiver, and PAM/FM/FM telemetry system, were installed inside. Four small solid rocket motors spun, one on each paddle, were designed to spin the OV2 satellites upon reaching orbit, providing gyroscopic stability. Cold-gas jets maintained this stability, receiving information on the satellite's alignment with respect to the Sun via an onboard solar aspect sensor, and with respect to the local magnetic field via two onboard fluxgate magnetometers. A damper kept the satellites from precessing (wobbling around its spin axis). Passive thermal control kept the satellites from overheating.^[1]: 422

Three OV2 satellites with different mission objectives were originally planned when the OV2 program began.^[22] The OV2 series was ultimately expanded to five satellites, all with different goals. OnlyOV2-5, a radiation and astronomical satellite, achieved a degree of success.^[23] However, duplicates of experiments intended forOV2-1 did ultimately fly onOV3-3.^[1]: 423

OV2-5 proton energy data collected 2–13 October 1968 in the energy range of 0.060 to 3.3Mev, showed an eight-fold reduction in particleflux between solar storms and quiet periods. Measuring the angle at which protons encountered the satellite also helped refine theoretical models of how themagnetosphere interacts with the flux of charged particles.^[24]

^[20][21]

Unlike the OV1 and OV2 series satellites, which were designed to use empty payload space on rocket test launches, the six OV3 satellites all had dedicatedScout boosters. In this regard, the OV3 series was more akin to its civilian science program counterparts (e.g.Explorer). OV3 differed from NASA programs in its heavy use of off-the-shelf equipment, which resulted in lower unit cost.

The first four satellites in the series were made theAerojet subsidiary Space General Corporation under a $1.35m contract awarded 2 December 1964, the first satellite due October 1965. The last two satellites were built byAir Force Cambridge Research Laboratory (AFCRL), which also managed the entire series and provided four of the OV3 payloads.^{[1]: 422–423}

Charles H. Reynolds, who worked at AFCRL from 1955, was the technical manager for the OV3 program.^[26]

The OV3 satellites were octagonal prisms, .74 m (2 ft 5 in) in length and width (for OV3-5 and OV3-6, length was reduced to .53 m (1 ft 9 in)), with experiments mounted on booms. 2560 solar cells provided 30Watts of power. The satellite was spin-stabilized, but because it was asymmetrical once its booms were extended,^[27] OV3-2 maintained its attitude in orbit with aprecession damper.^{[1]: 422–423} The spacecraft was spin stabilized at 8 revolutions per minute (rpm)^[25] A sun sensor, as well as an onboard tri-axialmagnetnometer, gave information on the satellite's aspect (facing), its spin rate, and rate ofprecession.^{[28][1]: 423} Design life-span was one year.^[1]: 423

The OV3 program ultimately comprised 6 missions, five of them successful. The last (OV3-6) flew on 4 December 1967.^[16] The OV3 program was terminated following OV3-6 in favor of the cheaper OV1 program.^[1]: 423

• OV3-1 had a near polar orbit and returned useful data on the energy and distribution of electrons in theauroral regions.^[27]
• Data returned by OV3-4 helped prove and refine theoretical models of radiation dosage an astronaut would receive at orbital altitudes.^[7]
• OV3-3 VLF receiver data determined the location of theplasmapause (the outer boundary of the Earth's inner magnetosphere).^[29]
• OV3-2 observed ambient charged particle variations before, during, and after the12 November 1966 South American solar eclipse.^[30] OV3-2 also conducted ionospheric and aurora research in orbit in conjunction with AFCRLKC-135 aircraft flying underneath, conducting simultaneous measurements.^[31] TheNational Research Council of Canada also conducted coordinated, simultaneous ionospheric observations.^[32]
• OV3-6 measured much larger latitude variations than current atmospheric models had expected. A bulge in the neutral density in the summer hemisphere was also discovered. The data obtained was used to construct more accurate atmospheric models, and to correlate physical chemistry reactions to disturbances originating from the sun.^[33]

^[20]

The OV4 series was designed to utilize space aboard theManned Orbiting Laboratory (MOL) test flights. In September 1964,Raytheon was awarded a $220,000 contract to build a one-off pair of satellites, designed by theU.S.A.F. Avionics Laboratory. These two satellites would investigate long range radio propagation in the charged atmosphere of theionosphere analogous to thewhispering gallery transmission of sounds under a physical dome.^[1]: 423 In this way, the OV4-1 pair would evaluate the ionosphere's F layer as method of facilitating HF and VHF transmissions between satellites not in line of sight of each other.^[20]

The OV4-1 satellite pair consisted of a transmitting spacecraft and a receiving spacecraft. OV4-1T'stransmitter broadcast on three frequencies in the 20-50MHz range. OV4-1R included receiving equipment andtelemetry broadcast equipment. Launched into slightly different 300 km (190 mi) orbits, the satellites would test whispering gallery communications over a range of distances; OV4-1T included a small rocket motor to maximize orbital separation (180°) from OV4-1R.^[1]: 423

Both satellites were cylindrical, .43 m (1 ft 5 in) in diameter, with domed upper ends. Total length was .9 m (2 ft 11 in). Silver oxide/zinc batteries provided for a 50-day lifespan.^[1]: 423

Two sets of OV4 "whispering gallery" satellites were built. OV4-2T and OV4-2R were never flown.^[1]: 423

OV4-1T and OV4-1R were scheduled for launch on theMOL Heat Shield Qualification flight, with aTitan IIIC rocket. The dummy MOL (a Titan first-stage oxidizer tank) was equipped with a variety of experiments and dubbed OV4-3.^{[1]: 423–424} OV1-6 was also mounted on the Titan III. The rocket took off from Cape Canaveral Launch Complex 40 on 3 November 1966 at 13:50:42 UTC.^[16]

^[20]

The OV5 program was a continuation of theEnvironmental Research Satellite (ERS) series developed bySpace Technology Laboratories, a subdivision ofTRW Inc. These were very small satellites launched pick-a-back with primary payloads since 1962—a natural fit under the Orbiting Vehicle umbrella. The primary innovation over the earlier ERS series was a command receiver, allowing instructions to be sent from the ground, and aPulse-code modulation digital telemetry system,^[1]: 425 versus the analog transmitters used on prior ERS missions.^[34] Like prior ERS, the OV5s were spin-stabilized and heat was passively controlled. All of the OV5 series were built by TRW with the exception of OV5-6, built by AFCRL, and OV5-9, built byNorthrop Corporation.^[1]: 425

^{[20][1]: 425}

The OV program orbited 184 experiments at extremely low launch costs and with very short proposal-to-orbit times. OV was succeeded by theSpace Test Program, managed by theSpace Missile Organization's Space Experiments Support Program, which had absorbed the ARSP in 1968. The Space Test Program followed the new trend in satellites, which preferred custom-built one-offs with specific payloads to vehicles built on standardized plans. Several late OV satellites were launched under the auspices of the new program^{[1]: 421–422, 425–426}

• Satellites orbiting Earth
• Military space program of the United States
• Satellite series

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