Of course, spacecraft 200 could communicate directly with the ground station. 5 is a view of the platform of FIG. The avionics system consists of fairly conventional electronics programmed for the specific needs of LAP 100. Frame 110 provides the essential structural support for LAP 100, and cradle 120 structurally supports the base 210 of spacecraft 200 to minimize stress and shear forces. This speed, however, provides little help to launch an SSTO to space. United Launch Alliance (ULA) of Spacecraft preferably 200 sits on LAP 100 in the same manner from launch until separation. This becomes particularly important as complex sequences may be interrupted by planned or unplanned holds to fix problems. Jet engines run out of sufficient air to carry their own weight at altitudes of 5,000 to 6,000 meters, far below the minimum altitude required (20,000 meters) to launch a SSTO without a large atmospheric drag. Cradle 120 may be independent of frame 110 or an integral part of frame 110. Tinsley, Auxiliary Fleet, Final Frontier, pp. The present invention covers modifications and variations that come within the scope of the appended claims and their equivalents. Second, base 210 must withstand tremendous heat during reentry. Follow Stephen Clark on Twitter: @StephenClark1. NASA reuses the last stage of the shuttle, called the orbiter, but orbiters can only be reused after extensive refurbishment. [citation needed], This article is about the structure from which rockets are launched. Latches 125 can be released by any conventional means, including the force generated by spacecraft 200 during separation. Preferably, frame 110 is made of lightweight metal, such as aluminum, titanium, aluminum alloys, or titanium alloys. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Base 210 has two principal functions. Examples of possible propellants for rocket engines 145 include oxygen and kerosene bipropellants, hydrogen peroxide and kerosene bipropellants, and liquid oxygen and liquid hydrogen bipropellants. The satellite will boost itself into the GPS network to begin a 15-year mission. Designing and building a space vehicle to carry not only useful payload, but also fuel weighing ten times the weight of the payload and space vehicle, including some safety margin, is difficult enough. 1 and 2 show, LAP 100 includes frame 110 with cradle 120 to support spacecraft 200. ULA spokeswoman Julie C. Andrews said Feb. 2 that Atlas 5 managers will follow the Sea Launch failure review closely, but had not suspended the next Atlas 5 mission, the launch of the U.S. Air Force’s Space Test Program-1 satellites. The spacecraft reenters the atmosphere in a base-first reentry, and is slowed and guided to a landing site by using a rocket engine in the base. Sellards, The DC X Makes Its First Test Hops, Countdown, pp. By 9, pp. Long Beach, Calif.-based Sea Launch interrupted the live transmission of the NSS-8 liftoff several seconds after the rocket’s ignition and immediate collapse onto the Odyssey floating platform, located on the equator in the, The launch platform is expected to begin the return journey to its home port at. “When we approached SpaceX to revise some spacecraft requirements for this mission … they responded with an opportunity to recover the booster in exchange for adding these requirements, as well as other considerations.”. This system is still in use for the, This page was last edited on 15 September 2020, at 14:31. Few, if any, unmanned vehicles return to earth under their own power. In shock absorber 360, a stainless steel coil spring 370 surrounds a tension member secured at one end to plate 382, which is in turn attached to support member 380. 8 and 9 show details of one embodiment of spacecraft 200, and FIG. FIG. Conventional spacecraft are also poorly designed for reuse. The mass fraction, which is the ratio of fuel to total weight required at lift-off, is determined by the basic rocket equation, m=mo ev/c, where m is the mass reaching orbit, mo is the mass at lift-off, v is the theoretical velocity gain required for orbit, and c is the exhaust velocity of the rocket engine. With the mission this week, China has launched Long March 11 rockets on 10 missions since 2015, and all have been successful. As FIG. ‘s H-2A rocket managers had not been discussed since the failure. H o eser, The Impact of Low Cost Space Access, Feb. 1986 Updated Oct. 1989. 11 and 12 show panels 280 as hinged to base 210. This limitation would require a new plane with mammoth dimensions. “Our evaluation of that mission’s performance, combined with additional work with SpaceX, reduced uncertainty in many areas,” Lauderdale said. SECURITY INTEREST;ASSIGNOR:KISTLER AEROSPACE CORPORATION;REEL/FRAME:011231/0224, Owner name: These two factors combine to make space transportation very difficult. SpaceX reaches 100 successful launches with Starlink mission, Axiom Space finalizing first commercial ISS mission, Space Force official: Launch scrubs are no reason to despair. The assembled spacecraft is then positioned on top of the self-propelled platform Ocean Odyssey and moved to the equatorial Pacific Ocean for launch, with the Sea Launch Commander serving as command center. The platform has a frame with a cradle for supporting the spacecraft. Rocket engines attached to the launch assist platform propel the launch assist platform and the spacecraft substantially vertically through the atmosphere for release of the spacecraft. In addition, the avionics system could communicate with a data processing system 260 on spacecraft 200 to coordinate separation and, if desired, to communicate spacecraft signals to a ground station. The other end of shock absorber 360 is a disk 384 connected to the top of spring 370. 1a shows an alternate configuration for LAP 100. A resilient landing device according to another aspect of this invention allows a spacecraft to land gently and comprises shock absorbing means to absorb the impact of the spacecraft during descent and footing means for holding the shock absorbing means in the ground. With the GPS launch behind them, SpaceX teams on Florida’s Space Coast will again turn their attention to launching a Falcon 9 rocket pad 39A at NASA’s Kennedy Space Center with the next batch of SpaceX’s Starlink Internet satellites. Although the LAP of this invention can be used at any altitude up to about 100,000 feet, or even higher depending on the size of the spacecraft being launched, the preferred altitude to launch the spacecraft from the LAP is 60,000 feet to 100,000 feet. 6 is a view of the platform of FIG. As FIG. Currently, space transportation uses multistage rockets that successively discard their lower stages. The military has conducted a series of launches to replenish the GPS satellite fleet since then, using ULA’s Atlas and Delta rockets, and now SpaceX’s Falcon 9. Preferably, all eight frame members support cradle 120 as well. In the cutaway view of rocket system 140 in FIG. The present invention relates generally to launch vehicles and to spacecraft and, more particularly, to a reusable single-stage-to-orbit spacecraft and a reusable launch assist platform. A launch hazard area warning notice released Tuesday for sailors off Florida’s Space Coast suggested the next Falcon 9/Starlink launch has been rescheduled for Wednesday, July 8. Skin 215 may also act as a secondary load-bearing structure. It’s a matter of how many times did you actually use it.”. The destruction of NSS-8 ends a chapter in the history of Boeing Satellite Systems International that the satellite manufacturer would rather forget. Martin, Selecting Hydrocarbon Rocket Propulsion Technology, International Astronautical Federation, pp. within several days, but Peckham said it was too early to say exactly when. 1a is a diagram of an alternate embodiment of a launch assist platform; FIG. The M-code signal allows GPS satellites to broadcast higher-power, jam-resistant signals over specific regions, such as a military theater or battlefield. within several days, but Peckham said it was too early to say exactly when. Furthermore, an airplane must travel at some minimum horizontal airspeed to obtain lift from its wings. FIG. Those are part of the company’s Jilin 1 Gaofen-03B constellation. and SDO Yuzhnoye/PO Yuzhmash of Ukraine, all of which provide hardware for the Zenit-3 SL vehicle or its ocean-going launch installations. Each spacecraft weighed around 88 pounds, or 40 kilograms, at the time of launch, Chang Guang said. Arianespace itself has a largely full manifest for 2007 and 2008. 7 is a diagram of a gimballing arrangement for a rocket engine used with the platform of FIG. The accompanying drawings also provide a further understanding of the invention and illustrate several embodiments of the invention. The Maritime Executive Resilient landing device 300, illustrated in FIG. i 35, IEEE USA, Dec. 17, 1993. The Sea Launch video, made available on Web sites including YouTube.com, gave the impression that the entire launch platform was consumed by flame and must have sustained major damage. Koelle et al., The Single Stage Reusable Ballistic Launcher Concept For Economic Cargo, International Astronautical Federation, Oct. 4 11, 1986. Ports 430, 432 accommodate exhaust from the rocket engines 145. FIGS. Cost Analysis of Single-Stage (SSTO) Reusable Ballistic Launch Vehicles. Crowley’s Master, Leader, Admiral, and Scout are twin cycloidal drive harbor tugs, and the Veteran is a Z-drive ship assist / general towing tug with 90 tons of bollard pull. Preferably, auxiliary struts and the other portions of frame 110 are shaped aerodynamically to reduce drag during ascent and to impart drag during descent.