Launch Equipment Research Articles

Numerical investigation on muzzle flow characteristics for small combustion chamber with embedded propelled body

Achieving a smaller size and lighter weight without affecting the launch performance is an important goal in the design of special launch equipment systems such as micro air vehicles and gun propulsion systems. An embedded structure is applied to small chamber systems to save launch space. This paper aims to illustrate the launch performance and muzzle flow characteristics of the embedded structure. The mathematical model of the launch process with a two-stage ignition is established. The muzzle flow model is used to simulate the launch process. The numerical method is verified by experiment. Numerical results indicate that a 21.1% space saving and a 4.2% muzzle velocity increase can be achieved by the embedded structure. The effect of the embedded structure on the muzzle flow is investigated. In the launch process, the Mach disk of the traditional structure travels farther, but that of the embedded structure catches up due to the greater velocity. The pressure oscillation of the embedded structure is larger, but the range of the oscillation is smaller. In the development process, compared with the traditional structure, the main parameters of the embedded structure, such as pressure and Mach number, are greater, which may lead to the launch risk. The findings will be applied to improve the design of small launchers.

Trajectory prediction of underwater launch equipment based on varying flow coefficient

In the underwater launch systems, a real-time prediction of the trajectory of the equipment out of the tube can provide accurate motion feedback for the closed-loop control. In this paper, using an analytical approach, a hydrodynamic mathematical model is developed for the open pipeline underwater launch system, along with an analysis of the coupling of pressure-flow variables influence mechanism on the trajectory. A time-varying coefficient-based prediction model for the equipment trajectory of the underwater launch process is developed for the compressible fluid and the strong transient characteristics of the fluid during the underwater launch process. Through the incorporation of the time-varying component of inertia into the flow coefficient, the interlinking relationship between the fluid, the pipe structure, and the equipment motion is clarified. This addresses the problem that the traditional steady-state hydrodynamic pipeline model cannot accurately describe the strong transient launch process. The experimental results show that, under typical firing conditions, the maximum error between the equipment motion velocity predicted by the mathematical model based on the time-varying flow coefficient and the measured velocity is 8.48%, with an error root mean square of 0.3035, proving the accuracy of the model based on the time-varying flow coefficient.

Перспективи використання азотовмісних однокомпонентних ракетних па-лив

The goal of this work is to analyze the possibility of using existing monopropellant compositions based on aqueous solutions of high-energy nitrogen-containing substances as the main propellant for low-thrust engines, for example, for meteorological rockets, for upper-stage engines, and in spacecraft control engine systems. This paper presents an approach that considers the selection and justification of ingredients based on renewable energy sources, the analysis being carried out primarily from standpoint of the availability of propellant components and their safety and energy efficiency. It is proposed that the energy of unitary reducing agent – oxidizer chemical propellants (energy-saturated compositions) be used as an alternative source. The development of nonhydrocarbon nitrogen-containing alternative energy sources with the possibility of their conversion and accumulation into the planetary nitrogen, oxygen, and water cycles is an urgent problem. The paper presents detailed information on propellant mixtures of nitrogen-containing substances as oxidizers and considers a number of reducing agents, such as alcohols, amides, etc. in composition with high-energy additives (aluminum, magnesium). The calculated results obtained meet the objectives and demonstrate that the compositions considered can be used as the main propellant for low-thrust engines. The advantages of the new propellant technology: availability, a low cost, produceability, environmental friendliness, a relatively low toxicity, and, primarily, a simpler design of the propulsion system and launch equipment. The proposed propellant composition, which is under test, is planned for use in the sustainer engines of ultralight suborbital rockets with the possibility of further development to an orbital rocket system.

Development of a low voltage railgun in the context of a swept lightning stroke on an aircraft.

When aircraft are struck by lightning, the aircraft's structural fuselage and components are stressed by electrical and thermo-mechanical constraints, which imposes a need for reliable experimental test benches to design accurate and enhanced lightning protection. In order to reproduce the in-flight conditions of an aircraft in a laboratory, the aim of this work is to design and implement launch equipment able to propel aeronautical test samples at speeds characteristic of an aircraft- from 10m/s for ultra-light gliders to 100m/s for airliners-before striking it with an electric arc within the laboratory dimensions of several meters. After a comparison of several propulsion techniques, the selected solution is an augmented electromagnetic railgun launcher. Since it requires the injection of a high current to be efficient and a low voltage operative point for safety considerations, specific and original electric generator and rail structures have been designed and experimentally implemented. Particular attention has been paid to the experimental problems encountered and mainly the sliding contact, since almost no literature references are available for railgun equipment at this level of performance. Then, based on different experimental implementations, a dynamic and ballistic model of the projectile has been developed to evaluate and characterize friction forces with the aim of predicting launcher performances with different inputs. This serves to control the speed of the material test sample during the lightning strike. Finally, the railgun equipment has been coupled to a lightning generator to reproduce the lightning strike of an aircraft respecting in-flight conditions.

Research on Demonstration and Validation of Space Rapid Response Launch System based on Data Link

Abstract The demonstration and verification of space rapid response launch system based on data link mainly combines with the process, style and characteristics of space rapid response launch, through construction the typical mission scenarios by simulation, carries out design and verification of wide-area maneuver anti-interference networking technology system between platforms such as space and ground data link nodes, container launcher and micro-nano satellite systems, research and design of formatting message standard system, etc., to promote the integrated application of data link and space rapid response launch equipment, so as to enhance command and control, situation sharing and tactical coordination capabilities.

The problem of block synthesis of missile preparation and start-up control system for missile complexes

According to the analysis of trends in the use and development of missile weapons, it is shown that in the coming decades such weapons (missile, anti-aircraft missile, anti-ship systems) will remain one of the main units of the armed forces of the advanced countries. At the same time, in the conditions of independent Ukraine there is a need to create its own production of appropriate samples in a “closed cycle”. The synthesis of such weapons includes conducting comprehensive research on the principles of construction and operation of their basic elements, namely: substantiation of algorithms for launch equipment, control systems and navigation of missiles. The article deals with an example of a general solution to the problem.

The problem of block synthesis of missile preparation and start-up control system for missile complexes

According to the analysis of trends in the use and development of missile weapons, it is shown that in the coming decades such weapons (missile, anti-aircraft missile, anti-ship systems) will remain one of the main units of the armed forces of the advanced countries. At the same time, in the conditions of independent Ukraine there is a need to create its own production of appropriate samples in a “closed cycle”. The synthesis of such weapons includes conducting comprehensive research on the principles of construction and operation of their basic elements, namely: substantiation of algorithms for launch equipment, control systems and navigation of missiles. The article deals with an example of a general solution to the problem.

Summarization of Vehicle Position and Azimuth Fast Determining Technology

To improve the rapidity, accuracy and autonomy of vehicle position and azimuth determining is an important theme in the development of land launch equipment. Based on this topic, a comprehensive summary is made of the theories and methods related to vehicle position and azimuth determining technology, including autonomous integrated navigation, initial alignment technology, error estimation and compensation technology, observability analysis method, and nonlinear filtering method. By summarizing and analyzing the related progress in recent years, this paper points out the existing problems in the research, and probes into the development direction of vehicle position and azimuth fast determining technology.

POSSIBILITIES OF UAS FOR MARITIME MONITORING

In the last few years, Unmanned Aircraft Systems (UAS) have become more important and its use for different application is appreciated. At the beginning UAS were used for military purposes. These successful applications initiated interest among researchers to find uses of UAS for civilian purposes, as they are alternative to both manned and satellite systems in acquiring high-resolution remote sensing data at lower cost while long flight duration. As UAS are built from many components such as unmanned aerial vehicle (UAV), sensing payloads, communication systems, ground control stations, recovery and launch equipment, and supporting equipment, knowledge about its functionality and characteristics is crucial for missions. Therefore, finding appropriate configuration of all elements to fulfill requirements of the mission is a very difficult, yet important task. UAS may be used in various maritime applications such as ship detection, red tide detection and monitoring, border patrol, tracking of pollution at sea and hurricane monitoring just to mention few. One of the greatest advantages of UAV is their ability to fly over dangerous and hazardous areas, where sending manned aircraft could be risky for a crew. In this article brief description of aerial unmanned system components is introduced. Firstly characteristics of unmanned aerial vehicles are presented, it continues with introducing inertial navigation system, communication systems, sensing payloads, ground control stations, and ground and recovery equipment. Next part introduces some examples of UAS for maritime applications. This is followed by suggestions of key indicators which should be taken into consideration while choosing UAS. Last part talks about configuration schemes of UAVs and sensor payloads suggested for some maritime applications.

POSSIBILITIES OF UAS FOR MARITIME MONITORING

Abstract. In the last few years, Unmanned Aircraft Systems (UAS) have become more important and its use for different application is appreciated. At the beginning UAS were used for military purposes. These successful applications initiated interest among researchers to find uses of UAS for civilian purposes, as they are alternative to both manned and satellite systems in acquiring high-resolution remote sensing data at lower cost while long flight duration. As UAS are built from many components such as unmanned aerial vehicle (UAV), sensing payloads, communication systems, ground control stations, recovery and launch equipment, and supporting equipment, knowledge about its functionality and characteristics is crucial for missions. Therefore, finding appropriate configuration of all elements to fulfill requirements of the mission is a very difficult, yet important task. UAS may be used in various maritime applications such as ship detection, red tide detection and monitoring, border patrol, tracking of pollution at sea and hurricane monitoring just to mention few. One of the greatest advantages of UAV is their ability to fly over dangerous and hazardous areas, where sending manned aircraft could be risky for a crew. In this article brief description of aerial unmanned system components is introduced. Firstly characteristics of unmanned aerial vehicles are presented, it continues with introducing inertial navigation system, communication systems, sensing payloads, ground control stations, and ground and recovery equipment. Next part introduces some examples of UAS for maritime applications. This is followed by suggestions of key indicators which should be taken into consideration while choosing UAS. Last part talks about configuration schemes of UAVs and sensor payloads suggested for some maritime applications.

2015 WSGC Elijah High-Altitude Balloon Payload Project Final Report

The purpose of this report is to discuss the research, development, and findings of several experiments performed on a high-altitude balloon payload platform. The team decided on the following five experiments to be performed during the flight: Oxygen Generation, Internal Heating, Speed of Sound Properties, Ozone Levels, and a new payload structure concept. The entire team was required to research and develop new skills to effectively design our experiments, including: Arduino programming, 3-D modeling/printing, soldering, launch equipment handling, and construction techniques. While the launch was successful, we did fall short of our overall goal in terms of data acquisition. The internship proved to be a rewarding introductory experience to real-world engineering. The project help us learn how to implement the entirety of the engineering process, using each person’s strengths to achieve an objective.

О классификации стартового оборудования ракетно-космических комплексов при обосновании норм прочности

О классификации стартового оборудования ракетно-космических комплексов при обосновании норм прочности

Aluminium Alloy Welding the Weld Stress Deformation and Control

Welding technology, as one of the process of manufacturing material in the permanent link, are already widely used in various kinds of aerospace ground launch equipment. Modern manufacturing industry is in rapid development phase, the welding automation is inevitable trend of production, which not only can greatly improve the efficiency of welding, but also what more important is to ensure the welding quality, thus to improve the operating environment. Modern welding is developing in the direction of mechanization, automation, intelligence, robot welding has become an important symbol of welding automation technology modernization. This paper focuses on regularity and influence of welding deformation, the welding deformation and deformation control, control and eliminate problems for research.

Parameterization of Micro Satellite Launch Vehicle

The new trends in micro satellites mission for wide range of applications has motivated worldwide research in design and development of micro satellite launch vehicles (MSLVs) as a vital options in the deployment of such satellites into their respective mission orbits. Presently, most micro satellites are launched through rideshares with rockets or rocket-like systems, which were developed essentially in the seventieth and eightieth of the last century. The MSLV as a proportional micro satellite launch vehicle, up till now has only the status of technology and system study work and is well known that the research and development of MSLV are diversified in different fields. However, the realization of MSLVs is rigorous since such vehicles compound the inherent difficulties of traditional launch experiment with intrinsic problems of uneven mass distribution, slenderness, high frequency and amplitude of vibration etc. MSLV are also more likely to be affected by wind gusts and other disturbances than their conventional counterpart, and the physical parameters such as mass distribution and moments of inertia can be easily altered by changing the payload location and unpredictable propellant burning. All these factors compromise the additional velocities to overcome the aerodynamic drag, to account for steering of the vehicle and other losses. Consequently, We prototype a three stage micro-satellite launch equipment as a similitude of the European Space Agency’s VEGA launcher using a scale down derivation model and parameterized using existing VEGA launch vehicle (LV) technical data. VEGA launch data, total orbital velocity requirement including the losses and stage payload ratio are inferred and applied to the model of parameterization of launch vehicles through coupledparameters simulations. This approach can be helpful in viability and performance insights in terms of payload mass, stage mass distribution and material properties precision and effectiveness. It can also serve as a background for the development of time optimal waypoint trajectory of micro satellite launchers.

Обоснование некоторых основных характеристик стартового оборудования космодромов ХХI века

Обоснование некоторых основных характеристик стартового оборудования космодромов ХХI века

Submarine Escape and Rescue Operations—The Holistic Approach to Safety

ABSTRACTEscape and/or rescue from a submarine is an emergency activity that is undertaken only rarely and, by its very nature, is hazardous. Such operations will naturally attract wide industry and media attention, focusing on both the outcome and the approach taken. A successful escape and rescue mission is the objective, and it is consistent with this to require that such a mission must not unduly endanger the lives of anyone involved. Consequently, the effective safety management of the entire escape and rescue system capability (covering both the equipment and the operations) is essential.An extensive range of equipment is required for the rescue system. For example, a Mother-ship is required to transport the rescue vehicle with its launch and recovery equipment and associated mission support equipment in order to provide a platform for rescue operations. The major elements of the capability (the rescue vehicle, launch and recovery system etc) will normally be expected to have a validated design, be manufactured and maintained in accordance with a classification society's rules (and obtain subsequent certification as such), thereby providing an element of assurance of the inherent safety of their design. However, the interfaces between the equipments that make up the rescue system (for example the rescue vehicle, the launch and recovery system etc), their operation and the operating environment are not covered by classification society rules. Consider the condition of the watertight integrity of the rescue vehicle when it mates with the distressed submarine. This condition is not covered by classification society rules for either the disabled submarine or the escape and rescue system, nor would the particular combination of rescue vehicle with every submarine have been considered in the design process of either component. However, in order for the owner of the rescue system to discharge their safety responsibilities they must be able to demonstrate that this condition has an acceptable level of risk attached to it.This paper reviews the elements that, together, provide a versatile overall capability, and discusses how the safety aspects of this specialist type of capability present some particular challenges. It describes the assurance applicable to equipments that are ‘in-class’, and suggests how, with correct management of the hazards and risks associated with this intrinsically dangerous capability, the interfaces between the escape or rescue equipments and the disabled submarine can also be proven and reported to be acceptably safe.

404 ハイブリッドロケット回収系用飛翔体の開発 : 有翼飛翔体打ち上げ装置の開発

404 ハイブリッドロケット回収系用飛翔体の開発 : 有翼飛翔体打ち上げ装置の開発

Back and Upper Extremity Disorders among Enlisted U.S. Marines: Burden and Individual Risk Factors

Although musculoskeletal disorders of the low back and upper extremities can affect military readiness, little is known about their extent and risk factors in the U.S. Marine Corps. Using the Defense Medical Epidemiology and Defense Medical Surveillance System databases, back and upper extremity diagnostic categories were among the top four sources of outpatient visits and duty limitation among enlisted Marines. Back disorders were also found to be the fifth most common cause for lost time. Subsequently, high-risk occupations were identified, age-related trends for clinic visit rates were determined, and rate ratios were computed for the top 15 low back and upper extremity diagnoses among enlisted Marines from 1997 through 1998. Occupational categories with the highest rates of musculoskeletal-related outpatient visits included image interpretation, auditing and accounting, disturbsing, surveillance/target acquisition, and aircraft launch equipment. Significantly increasing linear trends in rates across age groups were found for most diagnoses. For 1998, age-specific rate ratios indicated significantly higher rates for most low back and upper extremity disorders for females; lower rank (i.e., E1-E4) was also a risk, but for fewer diagnoses. The findings emphasize the need to identify modifiable (e.g., work-related, individual) risk factors and to develop focused primary and secondary prevention programs for musculoskeletal disorders in the Marine Corps. Subsequently, these efforts can assist in reducing associated effects, maximizing resource utilization, and enhancing operational readiness.

Alternate Mode of Operation Program

The increasing complexity of the launch support equipment and the narrow launch windows of the Saturn IB and Saturn V missions require that methods be developed to minimize any delay attributable to launch support equipment failures. Since even short delays cannot be tolerated for Saturn manned missions, it is necessary to develop a method to prevent the occurrence of these delays. The Alternate Mode of Operation (AMO) concept, an analytical methodology, can be used to achieve this goal. The AMO Program is an engineering analysis of launch support equipment consisting of three phases. a. The design analysis phase which consists of performing the analysis as soon as the preliminary design is completed and constructing failure isolation logic diagrams. b. The operations analysis phase which consists of validating the failure isolation procedures, making launch decisions prior to the countdown which may result in built-in holds, and establishing repair plans prior to the countdown for personnel familiarization. c. The implementation phase which consists of instantly displaying the failure isolation logic and launch decisions for use by personnel in case of equipment failure during the countdown. The Alternate Mode of Operation Program provides: a. Launch support equipment capable of meeting launch windows. b. Optimized failure isolation procedures. c. Predetermined launch decisions in case of launch support equipment failure during the countdown.

Umbilical Arms for the Saturn V Vehicle

Umbilical arm design for the Saturn V vehicle is presented with emphasis on the arm servicing the S-IVB stage aft position. Arm criteria are outlined, followed by a description and operation of the launch equipment, in this order:the hinged, truss structure; the arm retraction system; the withdrawal mechanism; and the extension platform. Systems equipment and reliability, an important result of this work, will be substantiated by a rigorous testing program.