Two stage launch vehicle and launch trajectory method
Patent 5568901 Issued on October 29, 1996. Estimated Expiration Date: 
August 1, 2014. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.
August 1, 2014. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent References 2977080 3000593 3262655 3285175 3286629 3702688 Orbiter/launch system Launch and ascent system Space launch vehicle Detachable thrust vector mechanism for an aeronautical vehicle InventorAssigneeApplicationNo. 283739 filed on 08/01/1994US Classes:244/63, Launching244/2COMPOSITE AIRCRAFTExaminersPrimary: Kashnikow, AndresAssistant: Mojica, Virna Lissi Attorney, Agent or FirmInternational ClassesB64C 037/02B64D 005/00 B64F 001/04 B64G 001/40 AbstractA method of launching a two stage vehicle and a trajectory for use with a two stage vehicle which allows recovery of both stages at the launch site. This is accomplished by launching the first stage completely vertically so that on burnout the first stage is positioned directly above the recovery site. In order to get maximum benefit from launching the stage vertically gravitational losses are minimized by a first stage thrust to weight ratio of 1.6. The high thrust to weight ratio results in burnout at approximately 100,000 feet altitude within the atmosphere. Therefore the vehicle employs engines which produce at altitude approximately 15 percent of the sea level thrust of the first stage and consume the last 5 percent of propellant over a time period of 40 seconds. Staging is accomplished at 200,000 feet altitude. The second stage employs uprated RL-10 engines and has a thrust to weight ration of 1.45 and can achieve orbit with a velocity change of approximately 24,500 feet per second. The first stage employs air breathing vertical lift engines for recovery. The second stage utilizes a parawing.Other References
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