JCIC-DIP-09-011: PROVISION IN ADVANCE OF DATA ON

S E C R E T STATE 099779 SIPDIS, GENEVA FOR JCIC E.O. 12958: DECL: 09/23/2029 TAGS: PARM KACT START US RS UP BO KZ SUBJECT: JCIC-DIP-09-011: PROVISION IN ADVANCE OF DATA ON MINOTAUR IV SPACE LAUNCH VEHICLE Classified By: Jerry A. Taylor, Director, VCI/SI. Reason: 1.4(b) and (d). ¶1. This is an action request. See paragraph 4 below. ¶2. (U) BACKGROUND: In Joint Compliance and Inspection Commission (JCIC) Joint Statement Number 21, the Parties committed to provide, in advance, information on ICBMs and SLBMs used to deliver objects into the upper atmosphere or space, including space launch vehicles (SLVs) that incorporate the first stage of an ICBM or SLBM. Such information is to include technical data, development plans, and photographs or, until such ICBMs and SLBMs, including such space launch vehicles, are available to be photographed, schematic drawings. JCIC Joint Statement Number 31 specifies the minimum information that shall be provided pursuant to the aforementioned obligation contained in JCIC Joint Statement Number 21. ¶3. (U) The United States is about to conduct the first launch of an SLV, designated the Minotaur IV. Joint Statement 31 specifies that SLV data shall be provided to the other Parties no later than 10 days prior to the first time the SLV is assembled at a facility other than a production facility, including a space launch facility. The Minotaur IV SLV that incorporates the first stage of a Peacekeeper ICBM will be assembled at the Vandenberg Air Force Base, California, Test Range. ¶4. (U) ACTION REQUEST: Drawing on the above background as needed, embassies Moscow, Kyiv, and Astana are requested to provide the paper in paragraph 5 below to appropriate host government officials, under cover of a letter signed by an appropriate embassy official, not later than September 28. Washington will provide each embassy a courtesy Russian-language translation of the paper. An associated schematic drawing of the Minotaur IV SLV will be emailed to capitals separately, and should be provided to these officials at the same time. Washington requests that each embassy confirm delivery of this paper, the name and office of the official to whom it was delivered, the date of delivery, and any comment or reaction provided at that time. The text in paragraph 5 will be sent directly to the Belarusion Government via a service message transmitted by the U.S. Nuclear Risk Reduction Center. ¶5. (S) Begin text of paper: ¶I. Development plan for a space launch vehicle that incorporates a first stage of a Peacekeeper ICBM The Minotaur IV space launch vehicle incorporates the first stage of a Peacekeeper ICBM. Orbital Sciences Corporation, under a contract with the U.S. government, will provide launch and technical support for the operation of the Minotaur IV space launch vehicle. The Minotaur IV SLV has four stages and an assembled length of 23.88 meters. The Minotaur IV space launch vehicle will be assembled at the Vandenberg Air Force Base, California, Test Range. The Minotaur IV space launch vehicle will be launched from a soft site launcher located at a space launch facility declared under the START Treaty. An associated schematic drawing of the Minotaur IV space launch vehicle is attached to this paper. II. Technical data for the Minotaur IV space launch vehicle that incorporates a first stage of a Peacekeeper ICBM: ¶A. Name or designation of the space launch vehicle: Minotaur IV ¶B. Type of ICBM or SLBM whose first stage is incorporated into the space launch vehicle: Peacekeeper ICBM ¶C. Total number of stages: 4 ¶D. For an upper stage of the SLV that is an ICBM or SLBM stage, the type and stage of that ICBM or SLBM: Peacekeeper second stage, Peacekeeper third stage ¶E. For space launch vehicles not contained in launch canisters, total length of assembled space launch vehicle with or without payload fairing: 23.88 meters with payload fairing ¶F. For space launch vehicles contained in launch canisters, total length of space launch vehicle as a unit with launch canister, with or without payload fairing: Not applicable ¶G. For space launch vehicles that are transported in separate launch canister sections, length of launch canister sections: Not applicable ¶H. Length and diameter of launch canister, if applicable: Not applicable ¶I. Description of launcher type/launch method: Soft Site Launcher ¶J. Calculated value, for reference purposes, of the weight of the fully-fueled space launch vehicle without payload: 86322 kilograms. End text of paper. CLINTON