The goal of the Reusable Launch Vehicle RLV technology program is to mature the technologies essential for a next-generation reusable launch system capable of reliably serving National space transportation needs at substantially reduced costs. The primary objectives of the RLV technology program are to 1 mature the technologies required for the next-generation system , 2 demonstrate the capability to achieve low development and operational cost, and rapid launch turnaround times and 3 reduce business and technical risks to encourage significant private investment in the commercial development and operation of the next-generation system.
Developing and demonstrating the technologies required for a Single Stage to Orbit SSTO rocket is a focus of the program becuase past studies indicate that it has the best potential for achieving the lowest space access cost while acting as an RLV technology driver since it also encompasses the technology requirements of reusable rocket vehicles in general.
Onboard guidance system design for reusable launch vehicles in the terminal area energy management phase. The mathematical model representing the RLV gliding motion is provided, followed by a transformation of extracting the required dynamics for reference profile generation. Reference longitudinal profiles are conceived based on the capability of maximum dive and maximum glide that a RLV can perform.
The trajectory is obtained by iterating the motion equations at each node of altitude, where the angle of attack and the flight-path angle are regarded as regulating variables.
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An onboard ground-track predictor is constructed to generate the current range-to-go and lateral commands online. Although the longitudinal profile generation requires pre-processing using the RLV aerodynamics, the ground-track prediction can be executed online. This makes the guidance scheme adaptable to abnormal conditions.
Finally, the guidance law is designed to track the reference commands. Numerical simulations demonstrate that the proposed guidance scheme is capable of guiding the RLV to the desired touchdown conditions. Many exciting new opportunities in space, both government missions and business ventures, could be realized by a reduction in launch prices.
Reusable launch vehicle RLV designs have the potential to lower launch costs dramatically from those of today's expendable and partially-expendable vehicles. Unfortunately, governments must budget to support existing launch capability, and so lack the resources necessary to completely fund development of new reusable systems.
In addition, the new commercial space markets are too immature and uncertain to motivate the launch industry to undertake a project of this magnitude and risk. Low-cost launch vehicles will not be developed without a mature market to service; however, launch prices must be reduced in order for a commercial launch market to mature.
This paper estimates and discusses the various benefits that may be reaped from government incentives for a commercial reusable launch vehicle program. Reusable launch vehicle facts and fantasies. Many people refuse to address many of the realities of reusable launch vehicle systems , technologies, operations and economics. Basic principles of physics, space flight operations, and business limitations are applied to the creation of a practical vision of future expectations.
While reusable launcher concepts have been proposed for several decades, serious review of potential designs began in the mids, when NASA decided that a Space Shuttle replacement had to be pursued. The potential for a vastly expanded space program motivated the entire space community. By the lates, and after over one billion dollars were spent on the technology development and privately-funded concepts, it had become clear that there would be no new, near-term operational reusable vehicle. Many factors contributed to a very expensive and disappointing effort to create a new generation of launch vehicles.
It began with overly optimistic projections of technology advancements and the belief that a greatly increased demand for satellite launches would be realized early in the 21st century. Cost, schedule and performance margins were all highly optimistic. Several entrepreneurs launched start up companies to take advantage of the excitement and the availability of investor capital. Millions were raised from private investors and venture capitalists, based on little more than flashy presentations and animations.
By , it was clear that market projections, made just two years earlier, were not going to be realized.
Efficient handling of payloads destined for a planetary surface, such as the moon or mars, requires robust systems to secure the payloads during transport on the ground, in space and on the planetary surface. In addition, mechanisms to release the payloads need to be reliable to ensure successful transfer from one vehicle to another. An efficient payload handling strategy must also consider the devices available to support payload handling. Cranes used for overhead lifting are common to all phases of payload handling on Earth.
Similarly, both recent and past studies have demonstrated that devices with comparable functionality will be needed to support lunar outpost operations. A first generation test-bed of a new high performance device that provides the capabilities of both a crane and a robotic manipulator, the Lunar Surface Manipulation System LSMS , has been designed, built and field tested and is available for use in evaluating a system to secure payloads to transportation vehicles.
A payload handling approach must address all phases of payload management including: ground transportation, launch , planetary transfer and installation in the final system. In addition, storage may be required during any phase of operations.
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Each of these phases requires the payload to be lifted and secured to a vehicle, transported, released and lifted in preparation for the next transportation or storage phase. A critical component of a successful payload handling approach is a latch and associated carrier system. The latch and carrier system should minimize requirements on the: payload, carrier support structure and payload handling devices as well as be able to accommodate a wide range of payload sizes.
In addition, the latch should; be small and lightweight, support a method to apply preload, be reusable , integrate into a minimal set of hard-points and have manual interfaces to actuate the latch should a problem occur. A latching system which meets these requirements has been. Advanced repair and refurbishment technologies are critically needed for the thermal protection system of current space transportation systems as well as for future launch and crew return vehicles.
There is a history of damage to these systems from impact during ground handling or ice during launch. In addition, there exists the potential for in-orbit damage from micrometeoroid and orbital debris impact as well as different factors weather, launch acoustics, shearing, etc. The adhesive paste cures at C and transforms into a high temperature ceramic during reentry conditions. In this presentation, performance of the repair materials as applied to RCC is discussed. Additionally, critical in-space repair needs and technical challenges are reviewed.
Reusable launch vehicle model uncertainties impact analysis. Reusable launch vehicle RLV has the typical characteristics of complex aerodynamic shape and propulsion system coupling, and the flight environment is highly complicated and intensely changeable. So its model has large uncertainty, which makes the nominal system quite different from the real system. Therefore, studying the influences caused by the uncertainties on the stability of the control system is of great significance for the controller design. In order to improve the performance of RLV, this paper proposes the approach of analyzing the influence of the model uncertainties.
According to the typical RLV, the coupling dynamic and kinematics models are built. Then different factors that cause uncertainties during building the model are analyzed and summed up. After that, the model uncertainties are expressed according to the additive uncertainty model. Choosing the uncertainties matrix's maximum singular values as the boundary model, and selecting the uncertainties matrix's norm to show t how much the uncertainty factors influence is on the stability of the control system. The simulation results illustrate that the inertial factors have the largest influence on the stability of the system , and it is necessary and important to take the model uncertainties into consideration before the designing the controller of this kind of aircraft like RLV, etc.
Further evolution of existing expendable launch vehicles will be an obvious element influencing the future of space transportation.
Besides this reusability might be the change with highest potential for essential improvement. The expected cost reduction and finally contributing to this, the improvement of reliability including safe mission abort capability are driving this idea. Although there are ideas of semi- reusable launch vehicles, typically two stages vehicles - reusable first stage or booster s and expendable second or upper stage - it should be kept in mind that the benefit of reusability will only overwhelm if there is a big enough share influencing the cost calculation.
Today there is the understanding that additional technology preparation and verification will be necessary to master reusability and get enough benefits compared with existing launch vehicles. This understanding is based on several technology and system concepts preparation and verification programmes mainly done in the US but partially also in Europe and Japan. The major areas of necessary further activities are: - System concepts including business plan considerations - Sub- system or component technologies refinement - System design and operation know-how and capabilities - Verification and demonstration oriented towards future mission mastering: One of the most important aspects for the creation of those coming programmes and activities will be the iterative process of requirements definition derived from concepts analyses including economical considerations and the results achieved and verified within technology and verification programmes.
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It is the intention of this paper to provide major trends for those requirements focused on future launch vehicles structures. This will include the aspects of requirements only valid for reusable launch vehicles and those common for expendable, semi- reusable and reusable launch vehicles. Structures and materials is and will be one of the. On the economics of staging for reusable launch vehicles. There has been much recent discussion concerning possible replacement systems for the current U. Attention has been focused upon the feasibility and potential benefits of reusable single-stage-to-orbit SSTO launch systems for future access to low Earth orbit LEO.
In this paper we assume the technical feasibility of such vehicles, as well as the benefits to be derived from system reusability. We then consider the benefits of launch vehicle staging from the perspective of economic advantage rather than performance necessity.
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The Bantam technology project is focused on providing a low cost launch capability for very small kilogram NASA and University science payloads. The cost goal has been set at one million dollars per launch. The Bantam project, however, represents much more than a small payload launch capability. Bantam represents a unique, systematic approach to reusable launch vehicle technology development. This technology maturation approach will enable future highly reusable launch concepts in any payload class.
These launch vehicle concepts of the future could deliver payloads for hundreds of dollars per pound, enabling dramatic growth in civil and commercial space enterprise. The Bantam project represents an approach to space transportation technology maturation that is very similar to the Mars Exploration Program. New reusable space transportation capability will be demonstrated at a small Bantam scale approximately every two years. Each flight demonstration will build on the knowledge derived from the previous flight tests.
The Bantam scale flight demonstrations will begin with the flights of the X The X will demonstrate reusable launch vehicle technologies including; flight regimes up to Mach 8 and , feet, autonomous flight operations, all weather operations, twenty-five flights in one year with a surge capability of two flights in less than twenty-four hours and safe abort. The Bantam project will build on this initial.
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Future launch vehicles must be lightweight, fully reusable and easily maintained if low-cost access to space is to be achieved. A series of trade studies were performed to meet three objectives. First, to provide structural weights and parametric weight equations as inputs to configuration-level trade studies. Second, to identify, assess and quantify major weight drivers for the RLV airframe.
The real-time checkout procedures and diagnostics are designed to detect components that need maintenance based on their condition, rather than using more conventional approaches such as scheduled or reliability centered maintenance.