Launch Safety Research Articles

The Use of Laser Sensing for Solving Meteorological Problems Related to Researching and Ensuring the Safety of Space Flights

This paper is devoted to the issue of using laser (lidar) sensing to determine wind speed and direction when solving practical problems during the analysis of meteorological conditions in the area around spaceports. This issue is relevant both for making decisions on the possibility of a safe launch of a launch vehicle and for conducting search and rescue operations using groups of manned and unmanned aerial vehicles. Based on numerical and experimental modeling, it is shown that lidars provide highly accurate measurements of wind speed profiles and allow for the determination of weak wind shear in vertical and horizontal directions. This paper proposes a method for determining the main parameters of lidar sensing (range, resolution, detectability, etc.), which allows for the capabilities of this technology in solving the practical problems of meteorological monitoring to be predicted. Of particular interest in this article are experimental modeling data verifying the proposed calculation methods and the experimental determination of the capabilities of lidar diagnostics. This paper summarizes the data from multi-month experiments measuring wind speed in clear weather conditions when other means of remote diagnostics are ineffective. As a result of the experiments, a statistical distribution of the maximum range of wind speed measurement in normal weather conditions with natural variation in the concentration of scattering particles in the atmosphere was obtained. This article also discusses the possibility of combining lidars and meteorological radars for the meteorological support of flights.

Simulation of interior ballistic two-phase flow of storage propellant charge

ABSTRACT The launch safety evaluation of artillery considering the properties changes of propellant charge during storage has attracted much attention, and the determination of the interior ballistic process of storage propellant charge has been a bottleneck problem. Large scale firing test is difficult to implement due to its high risk and uncontrollability, and simulation is limited by the difficulty in describing the interaction of propellant parameters. In order to describe the multiple physical fields in the chamber and reveal the influence mechanism of storage on interior ballistic process, the theoretical analysis and physical simulation are combined in this paper. The fracture and the subsequent combustion of the storage propellant charge in the chamber environment were physically simulated, and then, the interior ballistic two-phase flow simulation method considering the fracture of storage propellant charge is proposed by coupling these performance parameters. Though describing the interior ballistic process variation with storage time, this paper provides a practical evaluation method for the interior ballistic performance of energetic materials.

Numerical investigation of the multiphase flow and loading state of underwater semiclosed initial interrupted bubbles

The pulsation of bubbles and the impact load from reverse flow, generated by the evolution of semiclosed initial intermittent bubble multiphase flow during underwater launches, are crucial factors affecting launch safety. This paper employs the mixture multiphase flow model and the interphase heat and mass transfer model to simulate the interaction between the gas inside a partially enclosed cylinder and the water medium outside the cylinder, combined with simulation and piggybacking experiments, to analyze the flow process and load state. The numerical model is further utilized to study the evolution of the multiphase flow field of the semienclosed initial intermittent bubble, the pulsating load of the bubble, the impact load of the inverted water flow, and the influence of structural dimensions on the load. The results show that the initial intermittent bubble in the mouth of the cylinder experiences an expansion–contraction–expansion pulsation process, and as the migration of the interface between the phases results in significant pressure pulsation, the peak pulsation can exceed twice the pressure difference between the initial gas pressure inside the cylinder and the hydrostatic pressure at the mouth of the cylinder. At the late stage of bubble pulsation, a large amount of water with pulsating bubbles flows into the semiclosed cylinder, and the pulsation-induced velocity and gravity are used to form a high-speed inverted water flow. The interaction between the inverted water and the gas inside the cylinder generates an oscillating shock load where the maximum shock load is significantly greater than the ambient pressure load. Additionally, the effect of structural dimensions on the load state under the same intermittent conditions is examined.

Study of the payload extraction trajectory heavy class carrier rocket

Relevance. As the weight and complexity of the payload that needs to be launched into orbit increases, the relevance of rational trajectory selection to ensure maximum efficiency and minimum costs for delivering the payload to a given orbit increases. Rational choice of the trajectory of a heavy-class launch vehicle has a number of important practical applications. Firstly, it allows you to increase the payload capacity of the launch vehicle and reduce the cost of delivering payload to the target orbit. This is especially important in the context of the development of the space industry, when more and more companies and organizations are showing interest in launching their own satellites and other spacecraft in conditions of fierce economic competition. Choosing a rational trajectory for launching a payload into orbit will significantly reduce the cost of launches and make them available to a wider range of potential customers. Secondly, the choice of launch vehicle trajectory parameters is important for ensuring safety and minimizing risks during spacecraft launches. Thanks to the rational choice of trajectory, it is possible to reduce adverse impacts on the environment and eliminate the possibility of emergency situations associated with loss of control over the flight of the launch vehicle. Rational selection of launch vehicle trajectory parameters is a complex task that requires comprehensive research and consideration of various factors, such as aerodynamic parameters of the atmosphere, mass and characteristics of the payload (spacecraft), engine operating parameters, characteristics of the target orbit, features of the launch of the launch vehicle and many other factors. A more thorough and systematic study of the influence of these parameters will significantly improve the efficiency and reliability of launching spacecraft into orbit. Thus, the choice of rational parameters for the launch vehicle trajectory is a relevant and important topic for scientific research. Increasing the rocket's payload capacity, reducing the cost of delivering a spacecraft to a given orbit, and ensuring launch safety are tasks that depend on the chosen shape and parameters of the rocket's trajectory. Such research has important practical significance and can become the basis for the development of new technologies and methods in the space industry. The purpose of the study is to study and select rational parameters for the trajectory of a heavy-class launch vehicle when launching a payload. The main task is to determine the flight path parameters that will allow achieving maximum efficiency and accuracy in delivering the payload to a given orbit. To achieve the goal of the study, an analysis of various factors influencing the launch parameters of the spacecraft is required, such as the structural and aerodynamic characteristics of the rocket, the influence of aerodynamic factors and the Earth’s gravitational field on the flight path. Taking these factors into account, numerical calculations were carried out on the basis of a system of differential equations of motion using a computer program created in the MAPLE software package. Based on calculations, modeling of the shape and parameters of the launch vehicle flight path was carried out. Research results. During the study, the rational parameters of the trajectory of a heavy-class launch vehicle were selected. Calculations were carried out using numerical modeling of the parameters of payload launch trajectories, and an analysis of the resulting trajectories was carried out. Minimizing the rocket's flight time was identified as the main criterion for the rational choice of trajectory, which allows increasing launch efficiency and saving energy resources. An increase in payload mass and minimization of fuel consumption were adopted as additional criteria. Conclusion. The procedure for choosing rational parameters for the trajectory of a heavy-class launch vehicle proposed in this work will improve the delivery accuracy and reliability of spacecraft launches at the stage of ballistic analysis when designing rockets. The results of the study have practical significance for the development of future heavy-duty launch vehicle missions and improving the efficiency of space launches.

Projects for the Regulation of Space Traffic Management

The elements of the STM regime are the two dimensions of space traffic (in the scientific-technical and regulatory domains) and the three phases of space traffic: the launch, the on-orbit operations and the return. Examples of traffic regulations include launch safety rules, a specific air-space regime, manned spacecraft safety rules, regulations governing debris removal, traffic laws for orbital phases, return safety regulations (e.g. descent corridors), frequency use and avoidance of interference, environmental regulations, etc. Implementation and control mechanisms are primarily national regulations for licensing, arbitration and enforcement, operational assessments, coordination, and civil-military cooperation. This article is based on the concept of STM, which emphasises the need to respond quickly to unexpected events in space by creating a regime that encompasses all aspects of space activities.

Launch Dynamics Analysis of Amphibious Launch Vehicle on the Sea

Due to its agility, concealment and excellent amphibious combat capability, amphibious vehicles can perform tasks in complex terrain and environment, and have important application value in the field of national defense and people ’s livelihood. In this paper, the method of experimental data-driven numerical simulation analysis is used, combined with batch simulation technology, and the frequency histogram in probability statistics is used to study the launch safety of amphibious vehicles under random waves, and the influence of missile launch sequence and launch time interval on missile launch is explored. The results show that the driving and sea launch of the amphibious vehicle are safe under the experimental conditions. The partial attitude angle of the car body and the attitude angle of the missile roughly conform to the normal distribution; considering the relationship between the weight of the vehicle body and the ejection load impulse, the launch sequence and the launch time interval will not have a great impact on the missile launch. By evaluating the driving safety of the amphibious vehicle and the launch safety of the missile, this paper can provide some theoretical significance and engineering application value for the sea launch of the amphibious vehicle.

Study on the coupling calculation method for the launch dynamics of a self-propelled artillery multibody system considering engraving process

The launch dynamics theory for multibody systems emerges as an innovative and efficacious approach for the study of launch dynamics, capable of addressing the challenges of complex modeling, diminished computational efficiency, and imprecise analyses of system dynamic responses found in the dynamics research of intricate multi-rigid-flexible body systems, such as self-propelled artillery. This advancement aims to enhance the firing accuracy and launch safety of self-propelled artillery. Recognizing the shortfall of overlooking the band engraving process in existing theories, this study introduces a novel coupling calculation methodology for the launch dynamics of a self-propelled artillery multibody system. This method leverages the ABAQUS subroutine interface VUAMP to compute the dynamic response of the projectile and barrel during the launch process of large-caliber self-propelled artillery. Additionally, it examines the changes in projectile resistance and band deformation in relation to projectile motion throughout the band engraving process. Comparative analysis of the computational outcomes with experimental data evidences that the proposed method offers a more precise depiction of the launch process of self-propelled artillery, thereby enhancing the accuracy of launch dynamics calculations for self-propelled artillery.

Influence of embedded structure on two-phase reactive flow characteristics for a small combustion chamber with a moving boundary

In special launch scenarios such as armament and aerospace, the scale of the launch system is severely restricted, which causes unstable combustion of propellant. An embedded structure for the small propulsion system driven by solid propellant is proposed to overcome this problem. This study aims to demonstrate the two-phase flow behaviors and launch safety of the combustion chamber with an embedded structure. A two-dimensional two-phase flow model based on the modified two-fluid theory is developed to describe the detailed two-phase flow behaviors in the combustion chamber during launching. Different from most of the existing studies, the constitutive equations determined from actual physical conditions are used to close the system of continuity equations. The numerical results are compared with that of the experiment to verify the accuracy of the numerical model. On this basis, the launch performance of the embedded structure is investigated. The numerical results indicate that the embedded structure facilitates the ignition process and reduces the risk of excessive pressure, but decreases the muzzle velocity at the same time. In addition, the effect of design parameters on launch safety is further investigated. Design parameters directly affect the launch safety, and the selection of reasonable parameters is a useful method for enhancing the launch performance.

Validation results on future flight safety methods to be instituted at the Guiana Space Center -New Generation

In the very short term, the European Spaceport in French Guiana (CSG) will welcome new kinds of missions and launchers, such as Ariane 6, micro-launchers or reusable vehicles, and must prepare to operate them. At the same time, the launch safety process must be improved in order to maintain flight safety standards and to respect the requirements of the French Space Operation Act (FSOA [1]) regarding the new risks induced. The Flight Safety Department at CSG has been working on the development of new methods to fit these upcoming challenges while enabling the best possible protection to people, the environment and infrastructures. These concepts will be implemented with the arrival of the new Operations Centre (CDO).Although the flight termination decision remains on a human authority, the process to evaluate the dangerousness of a mission is optimized in order to gain reactivity and effectiveness. As presented at the 73rd IAC [2], this optimization of methods relies on both decreasing the number of operators within the flight safety team during launch operations and on implementing decision-aiding algorithms to better characterize the launcher condition status at any time. This implies a new distribution of the responsibilities between the safety operators and a redesign of the systems in the future organization at CSG.A large test campaign has already been conducted with the participation of all flight safety officers in order to collect data covering different fields [2]: personal and collective impressions, level of comfort, trust in the new concepts and comparison to the current process, amongst others. In follow-up of this study, to consolidate and validate the operability of the presented concepts and methods, the impacts of this new organization on the flight safety officers have been evaluated in order to apprehend the main changes compared to the current organization. In addition, a specific evaluation was performed in order to study the operator behaviour during various simulations of dangerous-case scenarios in which the launcher trajectory or on-board parameters deteriorated. The most critical cases were analysed in order to measure the reaction times before terminating the flight, with respect to different configurations of launcher abnormality. When comparing the behaviour and the reaction time of operators between the current and the future organization, we obtained conclusive results that are presented in this paper. These results will help to determine and demonstrate the efficiency of the new suggested method for the future flight safety organization at the CSG New Generation. The test campaign presented in this paper was possible following significant ergonomics choices regarding both the flight safety room configuration and the operator HMI layout. Indeed, the enhancement of flight safety operations has been enabled by a careful selection of decision-aiding algorithms and logical equations, however the study determining the most adequate position of HMI elements has also played a major role in the safety officers’ ability to operate the new concepts.This paper will present the results of the test campaign based on initial ergonomic studies enabling this major change in the organization of the flight safety team within the future CSG.

Lifecycle mission safety for space nuclear systems

The development of novel space nuclear systems by governments and companies can greatly enhance space exploration, commerce, and defense capabilities. However, the predominant safety framework for space nuclear in soft law and in practice focuses narrowly on launch safety. A Lifecycle Mission Safety Framework provides a new heuristic to guide system designers, mission planners, regulators, and international law for safety across the broad range of space nuclear applications. It expands safety goals beyond protection of the terrestrial population to workers and astronauts, as well as to activities in orbital space and planetary surfaces. By defining mission phases and identifying safety considerations in each, this framework provides for proactive identification and management of risk.

Establishing the requirements for safe rocket launches with respect to weather

Space Concordia is launching the biggest student built Canadian rocket with the aim of passing the Karman Line. Launching from Churchill, Manitoba, a former military airbase used in the 1950s for suborbital sounding rocket launches, Space Concordia’s ambition is to reinstate the zone as a launch site. Being the first launch out of Churchill in decades, safety is mandatory and must follow the established safety protocols and regulations for suborbital launch vehicles. Space Concordia must structure its own guidelines and requirements leveraging expertise from the Federal Aviation Administration and various agreements with local authorities. To ensure safety, the Flight Performance team runs wind weighting optimization algorithms using Astos, a 6 degree of freedom flight simulation software utilizing wind data from a weather balloon. Launch simulations in Astos are done using historical wind data through a combination of Python and A programming and numeric computing software (MATLAB) analysis scripts. Casualty expectation plays a significant role in the launch safety analysis since the launch site is situated next to a national park and multiple small communities. The probability of casualty is calculated to be 2.61E−8, which is smaller than the 30E-6 Federal Aviation Administration requirement. Establishing a strict set of guidelines while building a rocket creates many difficulties in terms of both design and regulations, however they permit a clearer structure for future launches made by Space Concordia as well as augment predefined understanding of the weather effect on Churchill suborbital rocket launches.

A graph embedded in graph framework with dual-sequence input for efficient anomaly detection of complex equipment under insufficient samples

Real-time anomaly detection is essential for the safe launch of some sophisticated equipment, such as liquid rocket engines (LRE), in order to head off disasters. However, the Industrial Internet of Things (IIoT) edge's real-time requirements cannot be addressed by the present methodologies, and the outcome is poor when dealing with a lack of training samples on the device side. We provide a solution for device-side real-time anomaly detection using the architecture known as Graph Embedded in Graph Networks to address these issues (GG-Nets). To fully extract features under insufficient training data, in our method, we learn the temporal relationship of timestamps in the multivariate signal through a time-series graph attention network (T-GAT) and extract features, and use the extracted features to replace the original signal as the information of the sensor attention network (S-GAT) nodes. For efficiency, the signals in the original sample are divided into odd and even sequences, which greatly reduces the number of nodes in the T-GAT. Experiments reveal that the proposed method outperforms other state-of-the-art models on the LRE ignition dataset. Furthermore, the ablation experiment proves that each module of the model improves the effect and extensive discussions explore interpretability. Our code can be found on: https://github.com/yhd-ai/GG-Nets.

Study on impact damage mechanism of gun propellant based on bonding contact model

As the main launch energy of barrel weapon, the dynamic mechanical properties of gun propellant is very important to evaluate the launch safety. Through the transverse drop hammer impact damage test at room temperature and the initial dynamic vivacity ratio test of the propellant, the crack growth law and the fracture degree of the damaged propellant were obtained separately. Based on the Hertz-Mindlin bonding contact model, the discrete element mechanical model of the rosette 19-hole gun propellant was established, and the transverse drop hammer impact damage simulation was carried out. The damage mechanism of the bonding contact model and the fracture degree of the damaged propellant were acquired, which were also verified by tests. The results show that the bonding contact model can accurately describe the impact damage law of propellant. The research results of this paper can be used to predict the abnormal chamber pressure caused by fracture of propellant, provides a research means for mechanical property evaluation of 3D printing gun propellant, and lays a theoretical foundation for quantitative evaluation of launch safety.

Interior ballistic two-phase flow model and its calculation for a mixed charge structure

The mixed charge for guns generally consists of two or more kinds of propellants. Medium and large caliber guns usually adopt the typical combination of tubular and granular propellants, not only meeting interior ballistic indexes but also improving launch safety. However, numerical investigations, charge design, and optimizations of such charge structures rely heavily on classical interior ballistic theory. To gain insight into some crucial phenomena in this complex interior ballistic process, a two-phase flow dynamic model of a 125 mm smoothbore gun with mixed charge (granular propellants, tubular propellants, and a combustible cartridge case) is developed. Unlike the previous form of solid governing equations, the conservation equations, surface temperature and combustion law functions are simultaneously established. The space-time conservation element and solution element (CE/SE) method is used to solve the mathematical model, simplifying the calculations of partial derivatives in source terms. Results show that the model can describe the combustion and flow, and the predicted projectile velocity agrees well with the measured one. In addition, the effects of the mass ratio of mixed propellants on interior ballistic performance are discussed in detail. As the tubular propellant mass decreases, ignition consistency deteriorates, particle accumulation intensifies, and the maximum pressure exceeds the permitted one, all of which may affect launch safety. The work in this paper provides a powerful tool for observing and predicting the interior ballistic process of the mixed charge.

Analysis of motion interference characteristics of underwater vehicles salvo based on the RBF Neural Network

Compared with the launch process of a single underwater vehicle, the salvo of multiple vehicles is more complex and needs to be more deeply studied. When the first vehicle is launched, it will disturb the flow field and affect the attitudes and trajectories of the subsequent vehicles. If the impact range is not clearly defined, the launch safety will be threatened. In this paper, we outline the underwater salvo process of two vehicles. A RBF (radial basis function) neural network model is established, which is driven by data generated through numerical simulation. The model is applied to predict the interference variation law of motion characteristic variables that the first vehicle to the second under different launch conditions. The results show that the RBF neural network model can predict the interference of the motion characteristic variables that the first vehicle to the second vehicle in the process of salvo, which is more effective and accurate than the numerical simulation and experimental methods. In addition, the results reveal the influence of the first vehicle on the deflection angle and displacement of the second vehicle under different launch parameters, in which the launch time interval is the most sensitive factor affecting the motion characteristics of the vehicle.

A self-adaptive local diversity-preserving NSGA-II for the multidisciplinary design optimization of a miniaturized supersonic rocket

The miniaturized supersonic rocket or missile is an innovative concept most notably characterized by its small caliber, short length, and high flight speed. Tightly coupled design parameters and constrained objectives bring high complexity to launch safety assessments. The commonly used heuristic algorithm NSGA-II cannot address this complexity with its original density estimation strategy. In this paper, a multidisciplinary design optimization (MDO) based on a multidisciplinary feasible (MDF) architecture is established and simplified according to specific design requirements. The design system includes one coupled numerical model, two drivers, and six disciplines. As an optimizer for an MDO problem, multi-objective evolutionary algorithms (MOEAs) with heuristic features are very conducive to exploring the performance of complex rocket systems. The coupling relationship between the design variables of a small dual-chamber rocket is complex, and its optimal design is challenging to obtain empirically by traditional methods. Optimizing its propulsion performance and launch safety is imperative. For engineering designs, the convergence process of algorithms is often passive with a high degree of randomness, and the diversity of the final results is difficult to guarantee. This paper improves the Pareto front's diversity in designing a miniaturized supersonic rocket by using a self-adaptive local diversity-preserving NSGA-II (SLDNSGA-II) in an MDO framework with an active control strategy.

Numerical Method of Propulsion Concept: Partially Cut Multiaperture Stick Propellant

The partially cut Multiaperture stick propellant is a new concept charging structure. In this paper, in order to accurately obtain the change and development process of the two-phase flow field in different stages of the whole interior ballistic process in this propulsion concept system, a coupled calculation model of computational interior ballistic is established, which converts the Euler-Lagrange method to the Euler-Euler method. Firstly, at the initial stage of ignition, the Euler-Lagrange method is used to describe the flow field. During this period, the gas phase is based on Euler coordinates, while the solid phase is based on Lagrangian coordinates. After the projectile starts, the partially cut Multiaperture stick propellant is fractured into granular propellant. The flow field is converted to describe by the Euler-Euler method by using the initial mapping method. Finally, by comparing the calculated results with the experimental results, the maximum pressure error is only 0.54%, which verifies the accuracy and effectiveness of the coupling calculation method. It effectively captures the distribution of the physical parameters in the combustion chamber, providing a new research method for the computational interior ballistic of the propulsion concept. Based on this method, the pressure distribution in the propulsion concept system is obtained, and no obvious shock waves and expansion waves are seen, indicating that the charge scheme of partially cut Multiaperture stick propellant can improve launch safety.

Design and optimization of a novel supersonic rocket with small caliber

<p style='text-indent:20px;'>It's difficult to meet the design requirements of a rocket with sensitive parameters using the traditional methods. This paper develops a design and optimization concept for a lightweight solid-propellant rocket with a small caliber and a high Mach number. The structural design and numerical modeling depend on the interior ballistic methodology. The model is validated by comparing pressure-time data from simulation and experiment. A modified evolutionary algorithm with constraints is applied because of the interactive design parameters and conflicting objects. The launch performance is improved by single- and multi-objective optimization. Under unchanged interior ballistic performance conditions, the peak pressure is reduced by 46.4%, and the erosive peak ratio is reduced by 46.4%. Despite the constraints, the Mach number is improved by 4.9%, the total impulse is improved by 6.3%, the peak pressure is reduced by 92.5%, and the erosive effects are reduced by 38.1% using different optimal solutions. A Pareto front is obtained by a constrained NSGA-Ⅱ, which reveals non-linear and non-uniform relations among design objects. A tidying method is proposed for a clear Pareto front. It indicates that, despite the sensitive parameters, launch safety and higher velocity are possible. The results help designers choose the best design schemes.</p>

Retracted: Study on Optimization of Interior Ballistic Performance of Cased Telescoped Ammunition Based on Improved Firefly Algorithm

AbstractConsidering that the evolution operators of common optimization algorithms such as genetic algorithm has a poor convergence speed and solution accuracy in the interior ballistic performance optimization of artillery, an improved firefly algorithm is selected for the interior ballistic performance optimization of cased telescoped ammunition (CTA). It is applied to the interior ballistic mathematical model of CTA to carry out single‐objective optimization and multi‐objective optimization respectively. The results show that in the single‐objective optimization, the muzzle velocity obtained by using the improved firefly algorithm is larger than other commonly used optimization algorithms. Under the constraints of maximum chamber pressure and relative burnout point, the muzzle velocity can be increased by about 30 m/s. In the multi‐objective optimization, three sub‐objectives of muzzle velocity, ballistic efficiency and muzzle pressure are considered respectively, and the multi‐objective firefly algorithm is applied to comprehensively optimize the interior ballistic performance of CTA. Then, the results are compared with the commonly used multi‐objective optimization algorithms, such as non‐dominated sorting genetic algorithm version II (NSGA‐II) and non‐dominated sorting genetic algorithm version III (NSGA‐III), the solution results are a series of Pareto optimal solutions. The obtained optimization results improved the interior ballistic performance and launch safety, providing reference for the reasonable matching of charge structure parameters and the selection of optimization algorithm upon the interior ballistic performance optimization of CTA to some extent.

AN OVERVIEW OF METHODS AND TECHNICAL MEANS OF SPACE DEBRIS REMOVAL FROM LOW EARTH ORBITS

Debris in Earth's orbit poses a significant threat to existing spacecraft and hinders the safe launch of new spacecraft. This paper discusses various methods of space debris removal from orbit. In particular, active, passive, and combined methods are considered. The possibility of using suborbital rockets to launch the removal system into orbit is also considered. The purpose of this paper is to review existing methods and technical means of space debris de-orbiting and analyze and identify promising areas for the development of such systems. A patent analysis was conducted for the period from 2002 to 2022. Modern scientific works on various methods of space debris removal were also analyzed. The papers on the combined method of space debris removal were analyzed separately. Non-standard approaches to space debris removal are considered. In particular, the possibility of using suborbital launch vehicles to launch removal systems into orbit is considered. As a result of the work, the current state of development of methods and technical means for space debris removal was determined. It has been found that the most commonly patented and studied in scientific papers are technical means based on the passive removal method. At the same time, the active method receives less attention in scientific papers. Because of this, it has been established that the study of passive and combined methods and the development of technical means based on these methods are promising areas. It was found that the combined method is promising, but little was studied, and the basic requirements for systems using suborbital launch vehicles were also identified. This work allowed us to summarize the current state of the problem of space debris management and identify the most promising areas for the development of space debris removal systems.