Low Cost Launch Vehicles Research Articles

PREREQUISITES FOR CREATING ULTRA-LIGHT LAUNCH VEHICLES WITH POLYMER BODIES

The relevance of the problem of creating new light and ultra-light launch vehicles from the point of view of the development of the modern space industry is shown. First of all, this problem is related to the expansion of the market and the scope of use of small satellites, most of which are now launched into orbit as passing load by medium and heavy launch vehicles, which is not at all prompt and too expensive. The estimated forecast of the small satellite launch market, which is presented herein, indicates a growing demand for their launch services. A low-cost launch vehicle for the launch of small satellites would greatly expand their use, development, and production. This indicates the need for creation of special-purpose cheap transport vehicles for the operative decision of tasks of launching such satellites into orbit. It is shown that the main directions for increasing the efficiency and reducing the cost of launches are reducing the cost of making a transport space system, increasing of mass the payload, increasing the multiplicity of reusable uses, and reducing one-time costs per start. World trends in solving this problem are connected with the solution problem of creating ultra-light launch vehicles. The historical review of studies on prototype rockets that use the principle of reducing the mass of a launch vehicle during flight by burning spent structural elements indicates the possibility of creating launch vehicles on this principle by using complex hydrocarbon polymers as structural materials. It is shown that polymer materials, in particular polyethylene, can become the main material for the manufacture of fuel tanks for solid rockets, which use the new principle of burning the design during flight. The use of fuel tanks as fuel will give a possibility to reduce the cost of the propulsion system, which is one of the most expensive parts of the launch vehicle. The development of such launch vehicles and the commercialization of scientific research will allow domestic aerospace companies to occupy a niche in the market of small satellite launches.

저비용 발사체를 위한 다단연소 사이클 액체로켓 엔진 시스템 설계

저비용 발사체를 위한 다단연소 사이클 액체로켓 엔진 시스템 설계

Low cost small-satellite access to space using hybrid rocket propulsion

Increased demand for smallsat launch capabilities drives on the search for low-cost launch vehicles. Hybrid rocket technology has been pushed forward in the recent years and is now ready to meet the demand of this low-cost rocket development. With intrinsic safety and reliability the development and production cost of hybrid rocket engines can be a small fraction of bi-liquid propulsion systems. At the German Aerospace Center DLR a hybrid rocket engine is developed in cooperation with the German start-up company HyImpulse Technologies GmbH in order to advance launcher technology in Germany. A concept for a mini-launcher has been designed by HyImpulse and the development of a 75 kN (SL) hybrid rocket engine is on-going with a test campaign foreseen in 2019. This engine will be the largest hybrid rocket engine ever tested in Europe. It takes advantage of the long development and research history of paraffin-based hybrid rockets at the DLR Lampoldshausen. Since 2010 paraffin-based fuels have been analyzed and improved. Additives have been found to greatly improve the mechanical properties of the paraffin solid fuel. At the same time the regression rate has been modulated to adapt the fuel for use in launcher applications. The concept of the HyImpulse mini-launcher includes eleven engines of this type, which will result in large scale serial production for the foreseen launch rate of twelve launches per year. This further reduces production costs of the hybrid rocket engine. The advantage of paraffin-based fuel lies in the simple geometry of the grain caused by the high regression rate. A cylindrical fuel grain will have a much lower manufacturing cost compared to classical wagon wheel fuel grains with HTPB. Hybrid launchers are often used within pressure fed propulsion systems, but in order to increase the payload of the launcher, this is replaced with a gas generator and turbo pump driven propulsion system for this launcher concept.

Status and Trends of Smallsats and their Launch Vehicles — An Up-to-date Review

This paper presents an analysis of the scenario of small satellite and its correspondent launch vehicles. The miniaturization of electronics, together with reliability and performance increase as well as reduction of cost, have allowed the use of commercials-off-the-shelf in the space industry, fostering the Smallsat use. An analysis of the launched Smallsats during the last 20 years is accomplished and the main factors for the Smallsat (r)evolution, outlined. Based on historic data, future scenarios for different mass categories of Smallsats are presented. An analysis of current and future launch vehicles reveals that we are currently in a phase of transition, where old launch vehicles get retired and new ones enter the market. However, the satellite launch vehicle business has been established to carry payloads of thousands of kilos into low Earth orbit and has not adjusted itself to the market of Smallsats. As a result, there is only 1 launch vehicle for dedicated Smallsat launches commercially available, but it carries a high price tag. Several small lowcost launch vehicles under development are identified and the challenges to overcome, discussed. Since these small launch vehicles have similar complexity as huge launch vehicles, high development costs are intrinsic, leading to a high specific price (USD/kg payload).

低成本运载火箭发展与分析

为适应未来军事和商业航天低成本发射需求，世界各航天机构纷纷提出各自的低成本运载火箭设计方案，并采取各种技术措施大幅降低发射成本。对各主要方案和技术进行对比，从美国某型运载火箭各组成部分与其质量和成本估计、猎鹰9R可重复使用运载火箭运载能力损失和总低成本估计两个方面分析了运载火箭成本与性能的关系，并为我国低成本运载火箭研制提出相应发展建议。 By the low cost requirement in military and commerce spacecraft launch tasks, many space institutions in the world have proposed multifarious design schemes of low cost launch vehicles, and all kinds of new technologies and measures have been adapted to reduce the total launch cost. The paper researched the major design schemes and key technologies comparatively. Then the relationship between of cost and performance of the launch vehicles are independently analyzed from mass percents and cost percents of the major components for a certain American launch vehicle and carrying capability loss and total low cost for a reusable launch vehicle. At last, several proposals were presented for the development of low cost launch vehicles in China.

低成本运载火箭总体设计研究

数十年来，高昂的发射成本一直是制约航天业发展的主要因素。随着SpaceX公司成功回收猎鹰9R火箭的一子级，世界各航天机构纷纷提出各自的低成本火箭研制发展计划。通过收集和分析国外低成本火箭发展计划，针对低成本火箭研制难题，主要从结构设计、发动机设计等六个方面进行了总体设计研究，为我国低成本运载火箭研制发展提供借鉴。 Expensive launch cost is a key limitation factor of aerospace technology and application development for decades. With the success recovery of FALCON-9 first stage, many space institutions in the world have proposed their different development schemes of low cost launch vehicles. This paper collected and analyzed abroad development schemes of low cost launch vehicles. Aiming at the difficulty of the design and manufacturing, the overall design researches are presented in six fields, such as structure design, engine design, and so on. The research results can afford us lessons for development of low cost launch vehicles.

Small Solid Propellant Launch Vehicle Mixed Design Optimization Approach

For a small country with limited research budget and lack of advanced space technology, it is imperative to find new approaches for the development of low-cost launch vehicles (LV), which is, among all possibilities, an interesting option for rapid access to space, focused on integration of acquired components complemented with indigenously developed subsystems. This approach requires the cooperation of developed countries with huge experience and knowledge in LV development and operations. The main objective is to develop a small three stage solid propellant LV capable of delivering a payload of 100 kg to a circular low earth orbit of 600 km altitude, with the first and second stage solid rocket motors (SRM) hypothetically acquired from different countries and the third one designed and produced domestically in accordance with the production and technological capability. This approach provides main advantages such as: reduction in total time to access the space and to master the basic knowledge of launch operations. For this purpose, an integer continuous genetic algorithm global optimization method was selected and implemented, the SRM characteristics of the first and second stage were considered as integer variables, whereas the design variables of the third stage SRM and the trajectory variable were considered as continuous. A multi discipline feasible (MDF) framework was implemented along with the propulsion, aerodynamic, mass and trajectory models. Despite their particular characteristics and constraints, the results show highly acceptable values, and the approach proved to be reliable for conceptual design level.

Ecological aspect of launch vehicles development by criterion of minimal cost

One of the topical problems in modern aerospace engineering is accordance between ecological requirements and performance of the vehicle. On the other hand, problem of economical efficiency leads to change of the main criterion of designing to the minimization of costs (instead of maximal performance). According to modern trends of “low-cost” vehicles, different concepts of the future cost-effective launch vehicles are considered. It is necessary to validate these concepts according to requirements of ecological safety for the purpose of detection of the dominant launch vehicle configuration. Typical configurations of the future 'low-cost' launch vehicle are presented by 6 conceptual groups (Koelle, 2001). Conceptual group 1 (CG1) is presented by the Ballistic “Single stage to orbit” (SSTO) reusable vehicle. All vehicles which use classical rocketry scheme of the propulsion trajectory are called “Ballistic” i.e. the ballistic vehicle is lifted to orbit under the impact of rocket engines thrust. CG1-vehicle is able to reach the low earth orbit (LEO) without stage separation reducing the number of required rocket engines. Technological feasibility of SSTO concepts is proven by numerous studies (Koelle, 2001). CG2 representatives are ballistic “Two stages to orbit” (TSTO) reusable vehicles. The difference between CG1 and CG2 consists in application of vacuum rocket engines in the second stage and, consequently, stage separation. CG2 are the most mass-effective vehicles. CG3 is presented by the winged SSTO vehicles with rocket propulsion by “Lifting body” aerodynamic scheme. Ascensional force is provided by the aerodynamic shape of the vehicle’s structure at high speeds. Winged TSTO vehicles with rocket propulsion and parallel or tandem staging form the CG4. The winged configuration provides wide landing capability for both stages. CG5 is presented by winged TSTO vehicles with airbreathing propulsion in the first stage and rocket-propelled second stage. Airbreathing jet engines provide high reusability ratio comparing with other concepts as well as the widest landing capability. Aerospace Plane with scramjet-rocket propulsion forms CG6. The vehicle is able to reach near-cosmic speed in rarefied layers of the atmosphere and then accelerate with rocket engines. The most ecologically important resemblance of represented concepts is reusability. This reduces space debris formation (due to lack of waste hardware). Reusable launch vehicles can also be used to return the spent satellites. Structural differences between the concepts form 3 criterions of comparison by ecological impact: 1) propellant toxicity; 2) safety of surface facilities (vehicle damage inside the atmosphere); 3) probability of space debris formation (vehicle damage outside the atmosphere). Comparison of the concepts by these criterions allows substantiating the most ecologically acceptable direction of research. Results of the comparison demonstrate that the most ecologically acceptable low-cost launch vehicle configuration is: Ballistic SSTO or TSTO reusable launch vehicle with “LOX+LH2” propellant. The results can be explained by following way: combustion products of the propellant “liquid oxygen + liquid hydrogen” are absolutely safe for environment. It also provides maximal performance of rocket engine (due to the highest specific impulse). Ballistic ascent scheme allows using relatively simple technologies and provides high reliability level. In combination with minimal time of atmospheric flight this provides high level of safety for surface facilities. These results may be used for substantiation of dominant research direction.

To the sun and pluto with solar sails and micro-sciencecraft

Innovative scenarios are described where solar sails are utilized to carry a micro-sciencecraft out to a Pluto flyby as well as to deliver a separate probe for a solar corona approach at 0.02AU. Passive lowthrust propulsion using solar sail technology and advanced micro-sciencecraft design would be combined to completely change mission planning for these high-priority science missions. It is described how solar sails, not consuming any propellant for primary propulsion, as a potential low-cost delivery system could enhance these scenarios by reducing launch mass, employing low-cost launch vehicles, as well as enable additional science return.

New low cost avionics with INS/GPS for a variety of vehicles

Development of a new vehicle avionics suite is described, including integration of a low-cost, tightly-coupled integrated Inertial Navigation System/Global Positioning System (INS/GPS) to support vehicle guidance, navigation, and control (GN&C). A wide variety of next-generation low-cost launch vehicles could potentially benefit from integrated INS/GPS technology for GN&C and/or range safety applications. Coleman Aerospace Company (CAC) has developed a new low-cost avionics suite, the generic Integrated Mission Guidance & Tracking System (IMGTS), an open architecture, modular system that supports the requirements for various guidance applications and range safety tracking. As part of this development, Boeing North American, Inc. is supplying its Modular Miniature Integrated GPS/INS Tactical System (M-MIGITS/sup TM/) Military-Off-The-Shelf (MOTS) INS/GPS product to support CAC's IMGTS GN&C.

MEASURE-Jupiter: Low-cost missions to explore Jupiter in the post-Galileo era

MEASURE-Jupiter is a mission concept for the first wave of new missions to explore the giant planets in the post-Galileo era. This paper addresses the feasibility of low-cost, focused science missions to explore Jupiter based on the science information returned by the Galileo mission. Delivery mass performance for spacecraft in the range of 100 to 200 kg is analyzed for the Delta II low-cost launch vehicle. Judicious selection of advanced technology allows flyby and orbiter mission concepts powered by solar cells and trickle-charged secondary batteries. Two concepts, Io Skimmer and Jupiter Auroral Observer, are described as examples of MEASURE-Jupiter mission possibilities. Total life-cycle costs (i.e., including the cost of system development, launch vehicle, and mission operations and data acquisition) are estimated to lie in the range of $200 to $275 million.