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Peacekeeper

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Peacekeeper Credit: via Andreas Parsch

AKA: LGM-118;LGM-118A;MX;W87. Status: Retired 2005. First Launch: 1983-06-18. Last Launch: 2004-07-21. Number: 51 . Payload: 3,600 kg (7,900 lb). Thrust: 1,711.00 kN (384,648 lbf). Gross mass: 88,430 kg (194,950 lb). Height: 21.60 m (70.80 ft). Diameter: 2.34 m (7.67 ft). Span: 2.34 m (7.67 ft). Apogee: 1,000 km (600 mi).

The Peacekeeper was supposed to replace both the 54 Titan 2 and 1000 Minuteman ICBM's in US service. However concepts changed continually in an attempt to get around the vulnerability of fixed missile siloes to increasingly-accurate Soviet ICBM's. Many different approaches were considered over five presidential administrations. After a long design and development process that went vastly over budget, only 50 were deployed in 1986-1988 to replace the Titan 2. These were in service for 16 years before being decommissioned under post-cold-war arms reduction agreements.

Concept studies began in 1966 for a new ICBM deployable in both fixed and mobile schemes under the WS-120A Advanced ICBM project. This was succeeded in April 1972 by Missile-X (MX) studies. After considering various mobile launch schemes, including air-launch, the decision was finally taken in 1977 to develop a ‘silo stuffer' four-stage solid propellant ICBM that could was the largest that could be fitted in existing Minuteman siloes. Decisions on mobile versions could wait. The new ICBM adopted Soviet design concepts. It would be transported and placed in the silo in a launch canister, from which it would be ‘cold launched' - popped out of the silo using a cold gas generator before the first stage ignited. This allowed the missile silo to be reloaded with a new missile in a few days (versus 17 days to refurbish a Minuteman silo after a launch). In April - May 1978, contracts were issued to Martin Marietta for development of the missile and to Thiokol, Aerojet, Hercules, and Rocketdyne for the rocket engines for the four stages. The US Congress however refused to fund development until the USAF selected a mobile basing scheme.

In September 1979, the USAF selected a ‘shell game' basing scheme involving hiding 200 missiles somewhere in 4600 soft shelters. It was presumed that Soviet planners would have to target all 4600 shelters to wipe out the force. This decision allowed full-scale development to begin. By January 1982 prototypes of all of the rocket stages and simulated cold launches had been tested. But the mobile basing scheme had been dropped by the USAF in 1980 because of its high cost. In early 1983, after Congressional threats of cancellation, it was decided that Peacekeeper would be deployed in Minuteman silos, initially as a Titan replacement, and that a smaller mobile ICBM would be developed for the mobile basing requirement (the Midgetman). The first Peacekeeper canister cold launch took place in June 1983, and the missile was deployed in 1986-1988 to 50 modified Minuteman silos. These remained in service until destroyed in 2004 under the Start II Treaty. A 1986 plan to deploy 50 additional Peacekeeper missiles on 25 special USAF trains was cancelled in 1991 after the end of the Cold War. Midgetman was cancelled as well, and the Minuteman was to continue in service as America's only remaining ICBM until at least 2030.

Development Cost $: 10,926.800 million. Recurring Price $: 77.877 million in 1982 dollars. Flyaway Unit Cost 1985$: 77.398 million in 1982 dollars. Guidance contractor: Boeing. Maximum range: 13,000 km (8,000 mi). Number Standard Warheads: 10. Standard RV: Mk. 12A. Standard warhead: W87. Warhead yield: 300 KT. Boost Propulsion: Solid rocket. Initial Operational Capability: 1987. Total Number Built: 226.

• Advanced ICBM program cancelled. - . Headquarters USAF effectively cancelled BSD's Advanced ICBM program when it directed all studies to be separate line items in exploratory and advanced development areas..

• Missile X Program Office established - . The Missile X Program Office was established in SAMSO's Deputy for Minuteman located at Norton AFB, California..

• The Deputy for Minuteman completed the program plan for the Advanced Missile (M-X). - .

• SAMSO presented the Advanced Missile (M-X) briefing to Headquarters AFSC. - .

• Peackeeper Lower Stage Nozzle awarded to UTC. - . The Minuteman System Program Office awarded the Missile X Lower Stage Nozzle Development Program contract F04701-74-C-0215 to United Technology Center, Sunnyvale, California..

• The Missile X Upper Stage motor awarded to Aerojet. - . The Missile X Upper Stage motor development program contractor selections were made. Contract F04701-73-C-0423 went to the Aerojet Solid Propulsion Company, Sacramento, California..

• Air mobile concepts for Missile X were reduced. - . Considered would be three aircraft types- modified wide-bodied types, new endurance types and a new high acceleration aircraft- and three operating modes-continuous air alert, dash-on warning strip alert and combination of previous two..

• Peacekeeper program reviewed by DSARC, - . The Missile X program was reviewed by the Defense Systems Acquisition Review Council (DSARC)-I. This review approved the conceptual work that had been initiated in 1973..

• Deputy for Intercontinental Ballistic Missiles - . Deputy for Minuteman was renamed Deputy for Intercontinental Ballistic Missiles because of the growth of the Missile X program..

• A Missile X upper stage motor successfully test-fired - . A Missile X upper stage motor developed by Aerojet Solid Propulsion Company was successfully test-fired at the AFRPL..

• Potential sites for deployment of Missile X. - . Fugro International Corporation completed a coarse screening investigation of potential sites for deployment of Missile X..

• Missile X Buried Trench Construction and Test Project. - . SAMSO awarded the Ralph M. Parsons Company a contract for the Missile X Buried Trench Construction and Test Project..

• MX full scale development postponed. - . Program Management Directive 9 postponed full scale development of the Missile X system to FY 1979 following President Carter's proposed funding reduction of $160 million for FY 1978..

• Survivability testing of MX shelter and trench designs. - . First of the HAVE HOST tests at Luke AFB, involving survivability testing of Missile X shelter and trench designs with detonation of conventional high explosives in wind tunnel facilities..

• Peacekeeper extendible nozzle exit cone successfully tested. - .

  A sub-scale model of an extendible nozzle exit cone (ENEC), developed by Hercules Incorporated for Missile X second and third stages, was successfully tested at the AFRPL. This was the first successful deployment of an ENEC over a rocket motor plume which did not result in structural damage to the nozzle.

• Limited funds for Missile X basing concepts. - .

  An authorization bill passed by Congress reduced the amount of funds to be spent on validation of Missile X basing concepts to $69 million, forbade expenditure of funds on silo or air mobile basing. $1 million to be spent on MAP (ground mobile basing) validation.

• Verification of trench- or shelter-based ICBM systems with a SALT treaty. - . The ICBM program office submitted to HQ AFSC and HQ USAF the results of a study of possible ways to verify compliance of trench- or shelter-based ICBM systems with a SALT treaty..

• MX shelter-based system costs. - . The Ralph M. Parsons Company and the C.F. Braun Company submitted final reports on how much it would cost to build a Missile X shelter-based system and how rapidly the construction could be done..

• Missile X lower stage movable nozzle failure. - . A redesigned Missile X lower stage movable nozzle was ground tested on a rocket motor at the AFRPL. The nozzle failed when the exit cone broke away from the nozzle..

• Systems definition of Missile X booster stages I, II, III, and IV. - . The ICBM Program Office released requests for proposals on systems definition of Missile X booster stages I, II, III, and IV..

• Request for proposals for full scale development of the Missile X. - . SAMSO released requests for proposals for systems definition and full scale development of the Missile X system, following delegation of source selection authority by HQ AFSC..

• Nozzle for the Missile X lower stage ground tested - . A trapped-ball movement nozzle for the Missile X lower stage was successfully ground tested by the Wasatch Division of Thiokol Corporation..

• Request for proposals for Missile X guidance and control integration. - . SAMSO released a request for proposals for system definition of Missile X guidance and control integration. Proposals were received from contractors on 21 December..

• Reentry vehicles for use with Peacekeeper warhead. - . Spacecraft: ABRES. The Reentry Systems program office held a preliminary design review for the first two reentry vehicles designed by the Avco Corporation for use with the Almendro (Peacekeeper Mk 21 / W87) warhead..

• Potential sites for deployment of Missile X. - . Fugro International Corporation delivered its final report on the intermediate screening of potential sites for deployment of Missile X..

• Proposals from contractors for Missile X. - . Proposals from contractors were due at SAMSO for work on Missile X propulsion motor stages, assembly test and system support, and guidance and control integration..

• Peacekeeper extendible nozzle exit cone successfully tested over a rocket motor plume. - . An extendible nozzle exit cone developed by Chemical Systems Division of United Technologies was successfully tested over a rocket motor plume at the AFRPL..

• SAMSO's ICBM Program Office began a Multiple Aimpoint Basing Study for Missile X basing. - .

  The study had been requested by the Defense Science Board after briefings by SAMSO late in CY 1977 on the subject of alternate basing modes. The study was concluded in April, and the results were presented in a briefing to the Air Force Scientific Advisory Board and the Defense Science Board. The study recommended the vertical shelter basing mode, with the horizontal shelter basing mode as a second choice.

• Missile X Buried Trench Construction and Test Project - .

  Construction began on the Missile X Buried Trench Construction and Test Project under a contract previously awarded to the Ralph M. Parsons Company. The contractor was to demonstrate its recommended construction method with test trenches in the San Cristobal Valley of the Luke Bombing and Gunnery Range in Arizona.

• System definition of Missile X assembly, test, and system support. - .

  SAMSO awarded a contract to Martin Marietta Aerospace for system definition of Missile X assembly, test, and system support. The contract also contained an option for full-scale engineering development to be performed between 1 January 1979 and 30 September 1983. Under the contract, Martin Marietta began studies to prepare for system definition of Missile X reentry systems.

• Peacekeeper Stage IV awarded to Rocketdyne. - . SAMSO awarded a contract for the system definition phase of the development program for Missile X Stage IV to the Rocketdyne Division of Rockwell International Corporation..

• Common missile could be used in place of both Trident II and the MX. - .

  The Undersecretary of Defense for Research and Engineering asked the Navy and Air Force to conduct a joint study to define a common missile which could be used in place of both Trident II and the MX. These were under separate development by the respective services. The study was also to formulate a management plan for development of the common missile and to estimate the potential savings from such a joint development.

• Multiple Aimpoint Basing Study for Missile X. - . The results of a Multiple Aimpoint Basing Study for Missile X basing, conducted by SAMSO's ICBM Program Office, were briefed to the Air Force Scienctific Advisory Board..

• System definition for three Missile X stages. - .

  The period of performance began on contracts awarded by SAMSO for the system definition phase of the development program for three Missile X propulsion stages. The contracts were awarded to Thiokol Corporation for Stage I, Aerojet Solid Propulsion Company for Stage II, and Hercules Incorporated for Stage III.

• Multiple Aimpoint Basing Study for Missile X. - . The results of a Multiple Aimpoint Basing Study for Missile X basing, conducted by SAMSO's ICBM Program Office, were briefed to the Defense Science Board..

• Missile X Milestone II Draft Environmental Impact Statement. - . A Missile X Milestone II Draft Environmental Impact Statement, prepared by Henningson, Durham and Richardson, Ecosciences Division, was delivered to SAMSO..

• Study to define a common missile for the Trident II and Missile X programs. - .

  The results of the joint Navy-Air Force study to define a common missile which could be used in place of both the Trident II and Missile X were briefed to the Undersecretary of Defense. The study concluded that some cost savings could result from development of a "common" or "mostly common" missile, and that a common missile was technically feasible and would meet the requirements for the Trident II. However, no common or mostly common missile could approach the performance of the baseline Missile X.

• Missile X design review delayed - . SAMSO exercised contract options to extend the system definition phase of development programs for Missile X propulsion stages. At the same time, SAMSO postponed the missile design review three months.

• Missile X flight computer contract. - . SAMSO awarded a contract for the system definition phase of a Missile X flight computer to Autonetics Group of Rockwell International Corporation..

• Peacekeeper vertical shelter engineering prototype. - .

  Air Force Chief of Staff General Allen directed AFSC to develop and deploy a vertical shelter engineering prototype to obtain data on construction, operations, and cost. Both the vertical shelter and the hybrid in-line trench concepts were to be developed as options for full-scale engineering development, and information on these was to be presented at AFSARC II in preparation for DSARC II.

• Missile X buried trench breakout erection system demonstrated. - . The Boeing Company successfully demonstrated its Missile X buried trench breakout erection system at the Luke Bombing and Gunnery Range in Arizona..

• Public hearing on the MX draft Environmental Impact Statement. - . A public hearing was held at Lompoc, California, on the revised Missile X Milestone II Draft Environmental Impact Statement, which had been filed with the Environmental Protection Agency..

• Missile X buried trench breakout erection system demonstration. - . Martin Marietta successfully demonstrated its Missile X buried trench breakout erection system at the Luke Bombing and Gunnery Range in Arizona..

• Moveable nozzle for Missile X stage I. - . The Wasatch Division of Thiokol Corporation successfully tested a "trapped ball" moveable nozzle for Missile X stage I..

• Contract for definition of MX vertical shelter operational requirements. - .

  SAMSO awarded a contract for definition of vertical shelter operational requirements for Missile X basing to the Boeing Company. Besides performing studies, Boeing was to conduct a test program to validate key vertical shelter concepts beginning in mid-CY 1979.

• Missile X test Buried Trench constructed. - . The Ralph M. Parsons Company completed construction of the Missile X Buried Trench Construction and Test Project at the Luke Bombing and Gunnery Range in Arizona..

• Source selection board for System Definition of the Missile X reentry system. - . SAMSO formed a source selection board in preparation for the award of a contract for the System Definition Phase of the Missile X reentry system..

• MX moved among multiple vertical shelters recommended. - . Air Force Systems Acquisition Review Council II for Missile X was held. As a result, the Air Force recommended development of a 92-inch-diameter Missile X moved among multiple vertical shelters..

• Intensive study of an air-mobile basing system for Peacekeeper requested. - . The Defense Systems Acquisition Review Council II (DSARC II) for Missile X was held. The DSARC asked the Air Force to conduct an intensive study of an air-mobile basing system..

• Air-mobile basing for Missile X - . SAMSO began a study of air-mobile basing for Missile X as a result of direction from DSARC II on Missile X..

• Environmental impact statement on Missile X air-mobile basing - . The final version of the environmental impact statement on Missile X air-mobile basing was filed with the Environmental Protection Agency..

• Missile design review for Missile X - . A missile design review (MDR) for all four stages of Missile X was held at the Martin Marietta Corporation's facilities in Denver, Colorado..

• MX airmobile option - . Missile X DSARC IIB met to consider studies of alternative Missile X configurations and basing modes, particularly the airmobile option developed by SAMSO at the direction of DSARC II in December 1978.

• Site selection and land acquisition for Peacekeeper. - . SAMSO's Deputy for ICBMs created a Multiple Protective Structure Deployment Area Selection Working group to coordinate site selection and land acquisition for deployment of Missile X..

• Carter announced full-scale developmentof the Missile X. But no decision on the basing mode. - . President Jimmy Carter announced his decision to authorize full-scale engineering development (FSED) of the 92-inch Missile X. However, he deferred a decision on the basing mode..

• Peacekeeper to use horizontal shelters. - . At a Missile X horizontal shelter kickoff meeting, SAMSO's ICBM program office directed associate contractors to reorient their activities from vertical to horizontal shelters..

• Basing mode for Missile X with multiple horizontal protective structures. - . President Jimmy Carter authorized full-scale engineering development (FSED) of a basing mode for Missile X. The basing mode would involve multiple horizontal protective structures..

• Full-scale engineering development of all four stages of Peacekeeper. - . SAMSO exercised contract options to enter full-scale engineering development of all four stages of Missile X, and system development contracts were allowed to terminate on 30 September..

• 6 RVs to BOA-KMR - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• 6 RVs to BOA-KMR - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• 8 RVs to BOA-Guam - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• 10 RVs sent to KMR impact area. - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• 6 RVs to KMR(1 Mk21) - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• RVs to KMR - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• 6 RVs Test - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• Test mission - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• Test mission - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• 4 RVs Test - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• Test mission - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• 10 Mk 21 warheads sent to KMR impact area. - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• Test mission - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• 6 RVs to KMR - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• 10 RV (2 ft deploy) - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• Test mission - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• Test mission - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• 7 Mk 21 RVs to KMR - . Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF SAC. Apogee: 200 km (120 mi).

• Operational test - . Nation: USA. Agency: USAF SAC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF SAC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF SAC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF SAC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF SAC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF SAC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF SAC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF ACC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF ACC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF ACC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• Operational test - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• 9 RVs operational test launch - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,000 km (600 mi).

• 7 RVs operational test launch - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• 8 RVs operational test launch - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• 8 RVs operational test launch - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• 8 RVs operational test launch - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• 8 RVs operational test launch - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• 9 RVs Functional Dependency gate operational test launch - . Nation: USA. Agency: USAF AFSPC. Apogee: 100 km (60 mi). FDEP. The Peackeeper ICBM was destroyed during flight and did not reach its planned 1000 km apogee..

• GT-31PA - 9 RVs Functional Dependency gate operational test launch - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• GT-32PA - 8 RVs Functional Dependency gate operational test launch - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi). ICBM Demonstration Flight - Dummy Warheads..

• GT-33PA - 8 RVs Functional Dependency gate operational test launch - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi). ICBM Demonstration Flight. Delayed from March..

• HTV-2a - . Nation: USA. Agency: USAF. Apogee: 100 km (60 mi). Hypersonic test.

• USA 216 - . Payload: SBSS. Mass: 1,031 kg (2,272 lb). Nation: USA. Agency: USAF. Manufacturer: Ball. Class: Surveillance. Type: Orbital object tracking satellite. Spacecraft: BCP-2000. USAF Sat Cat: 37168 . COSPAR: 2010-048A. Apogee: 633 km (393 mi). Perigee: 632 km (392 mi). Inclination: 98.00 deg. Period: 97.40 min. First Space-Based Surveillance Satellite; designed to track satellites and orbital junk from a space-based vantage point..

• USA 217 - . Payload: STPSat-2 SIV. Mass: 135 kg (297 lb). Nation: USA. Manufacturer: AeroAstro. Class: Technology. Type: Technology satellite. Spacecraft: Astro-200. USAF Sat Cat: 37222 . COSPAR: 2010-062A. Technology experiments. Lead satellite of USAF Space Test Program mission S26..

• USA 218 - . Payload: RAX. Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Cubesat. USAF Sat Cat: 37223 . COSPAR: 2010-062B. Radio Aurora Explorer, a National Science Foundation 3U cubesat, built by the University of Michigan, to study the aurora by picking up ground-based radar signals..

• USA 219 - . Payload: O/OREOS. Mass: 5.00 kg (11.00 lb). Nation: USA. Class: Biology. Type: Biology satellite. Spacecraft: Cubesat. USAF Sat Cat: 37224 . COSPAR: 2010-062C. 3U cubesat by NASA-Ames with life science experiments to study microbes in free fall and the effects of ultraviolet light on organic materials..

• USA 220 - . Payload: Fastsat-HSV. Mass: 140 kg (300 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Fastsat. USAF Sat Cat: 37225 . COSPAR: 2010-062D. Developed by NASA-Marshall and subcontractors in Huntsville; carried ionospheric and atmospheric experiments, a USAF experiment, and the Nanosail-D2 solar sail..

• USA 221 - . Payload: Falconsat-5. Mass: 161 kg (354 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Falconsat. USAF Sat Cat: 37226 . COSPAR: 2010-062E. US Air Force Academy satellite with experiments to study plasma and the ionosphere..

• USA 222 - . Payload: Fastrac 1. Mass: 30 kg (66 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Fastrac. Spacecraft: Fastrac satellite. USAF Sat Cat: 37227 . COSPAR: 2010-062F. Developed by University of Texas at Austin with USAF funding for formation flying experiments..

• USA 228 - . Payload: Fastrac 2. Mass: 30 kg (66 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Fastrac. Spacecraft: Fastrac satellite. USAF Sat Cat: 37380 . COSPAR: 2010-062M. Developed by University of Texas at Austin with USAF funding for formation flying experiments..

• Ballast A - . Payload: S26 Ballast A. Nation: USA. Class: Technology. Type: Technology satellite. USAF Sat Cat: 37230 . COSPAR: 2010-062J.

• Ballast B - . Payload: S26 Ballast B. Nation: USA. Class: Technology. Type: Technology satellite. USAF Sat Cat: 37231 . COSPAR: 2010-062K.

• Nanosail-D - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 37361 . COSPAR: 2010-062L. 3U cubesat for NASA with 3-m span solar sail; ejected from USA 220 on 18 January 2011 unexpectedly after earlier ejection efforts failed..

• HTV-2b - . Nation: USA. Apogee: 100 km (60 mi). Test mission. Hypersonic glider was launched from Vandenberg across the Pacific. The mission ended prematurely with loss of signal three minutes into the glider's free flight..

• Tacsat 4 - . Mass: 460 kg (1,010 lb). Nation: USA. Program: Tacsat. Class: Communications. Type: Military communications satellite. Spacecraft Bus: Road Runner. Spacecraft: Tacsat ORS. USAF Sat Cat: 37818 . COSPAR: 2011-052A. Apogee: 12,010 km (7,460 mi). Perigee: 742 km (461 mi). Inclination: 63.60 deg. Period: 238.90 min.

  Naval Research Laboratory UHF communications satellite, equipped with a 3.7-meter-diameter communications antenna to support military handheld satellite telephones. Launch used an uprated Minotaur IV with an ATK Star 48V motor replacing the Orion 38 upper stage.

• LADEE - . Mass: 383 kg (844 lb). Nation: USA. Class: Moon. Type: Lunar probe. Spacecraft: MCSB. Decay Date: 2014-04-18 . USAF Sat Cat: 39246 . COSPAR: 2013-047A.

  NASA Lunar Atmosphere and Dust Enviroment Explorer mission. It carried an ultraviolet spectrometer, a lunar dust experiment, a neutral mass spectrometer, and a laser communications experiment. An Aerojet Rocketdyne/Redmond R-4D-15 HiPAT 455N thruster, with 135 kg of propellant, was used for lunar orbit insertion and orbit maneuvers. After three perigee boost maneuvers it entered lunar gravitational sphere of influence on 6 October at 18:02 GMT. The lunar orbit insertion burn at 10:57 GMT placed LADEE in a 24-hour-period 269 km x 15,772 km selenocentric orbit inclined 157 deg to the lunar equator. Two further burns, the last on 12 October at 10:40 GMT, placed the spacecraft in a 248 km x 251 km orbit. The spacecraft was lowered into an orbit with a 2 km perilune in early April 2014, and it impacted the lunar farside between 04:30 and 05:22 GMT April 18, possibly on the east rim of the crater Sundman V at 12N 93W, north of Mare Orientale.

• ORS-5 - . Nation: USA. USAF Sat Cat: 42921 . COSPAR: 2017-050A. See ORS 5 (SensorSat). ..

• DHFR - . Payload: DARPA High Freq. Receiver. Nation: USA. USAF Sat Cat: 42922 . COSPAR: 2017-050B. Apogee: 576 km (357 mi). Perigee: 384 km (238 mi). Inclination: 24.52 deg. Period: 94.20 min. See DHFR. ..

• Prometheus 2.2 - . Nation: USA. USAF Sat Cat: 42923 . COSPAR: 2017-050C. Apogee: 389 km (241 mi). Perigee: 314 km (195 mi). Inclination: 24.64 deg. Period: 91.57 min. See Prometheus 2.2 ?. ..

• Prometheus 2.4 - . Nation: USA. USAF Sat Cat: 42924 . COSPAR: 2017-050D. Apogee: 280 km (170 mi). Perigee: 245 km (152 mi). Inclination: 24.70 deg. Period: 89.75 min. See Prometheus 2.4 ?. ..