Browse Topic: Missiles

Items (463)
This Aerospace Information Report (AIR) addresses the subject of aircraft inlet-swirl distortion. A structured methodology for characterizing steady-state swirl distortion in terms of swirl descriptors and for correlating the swirl descriptors with loss in stability pressure ratio is presented. The methodology is to be considered in conjunction with other SAE inlet distortion methodologies. In particular, the combined effects of swirl and total-pressure distortion on stability margin are considered. However, dynamic swirl, i.e., time-variant swirl, is not considered. The implementation of the swirl assessment methodology is shown through both computational and experimental examples. Different types of swirl distortion encountered in various engine installations and operations are described, and case studies which highlight the impact of swirl on engine stability are provided. Supplemental material is included in the appendices. This AIR is issued to bring together information and ideas required to address the inlet-swirl problem for which common industry practice has yet to be established. This document should foster the tests and analyses necessary to mature the ideas proposed by the committee to a recommended practice. These tests and analyses must include information that justifies three main features of the proposed swirl methodology: (1) swirl descriptors for correlating inlet swirl and stability pressure ratio loss, (2) computational techniques for analyzing compression systems (inlets, fans, compressors), and (3) test protocols (instrumentation and test techniques). The committee anticipates serving the industry by using such information to establish the consensus necessary for issuance of an SAE recommended practice.
S-16 Turbine Engine Inlet Flow Distortion Committee
Accurate projectile dynamic modelling requires identifying aerodynamic parameters. The traditional methods for identifying aerodynamic parameters of missiles suffer from significant modeling errors. Therefore, this study proposes an improved butterfly-shaped optimization hybrid extreme learning machine algorithm. It combines the butterfly algorithm with a hybrid extreme learning machine, Cauchy mutation, and adaptive weight. The search ability of the Butterfly algorithm is enhanced by introducing the Cauchy distribution function and adaptive weighting factors. In addition, to balance the weights of searches and to optimize the regularization coefficients and kernel function parameters, the dynamic switching probability p is introduced. The identification accuracy of four different algorithms was compared under noise-free conditions. The feasibility of the improved butterfly-optimized hybrid extreme learning machine was verified. When there is noise, the strength of the algorithm is confirmed by comparing the effect of different noise levels on how well it can identify things. The simulation results show that the improved butterfly optimization hybrid extreme learning machine algorithm has higher accuracy and better robustness in identifying projectile aerodynamic parameters. The simulation results show that the improved butterfly optimization hybrid extreme learning machine algorithm has higher accuracy and better robustness in identifying projectile aerodynamic parameters.
Wang, QianqianWang, KangjianJiao, WenjieYi, WenjunChen, Jintong
The canard configuration has been widely adopted in short-range missiles. However, its main drawbacks include difficulties in roll control and a limited angle-of-attack (AoA) range. Compared to conventional canard missiles, the addition of a pair of control surfaces (referred to as “aileron”) behind the canard control surfaces achieves decoupling between the roll channel and pitch-yaw channel. To investigate the influence of ailerons on the aerodynamic characteristics of canard configuration missiles, numerical simulations were conducted for two typical flow conditions: subsonic (Mach 0.5) and supersonic (Mach2.0). The results show that the introduction of ailerons increases the normal force of missiles, causes the center of pressure to shift forward, and reduces the static stability of missiles, thus enhancing their maneuverability. When the ailerons control the roll channel, the effectiveness of the rolling moment remains consistent over the entire AoA range without adverse effects. However, when the canards control the pitch channel, the interference caused by the deflection of the canards on the ailerons leads to increased lift and generates additional nose-up pitching moments, which reduces the pitching moment effectiveness of the missile.
Zhang, ZilunXu, JiashengMei, Zhiwei
Rocket projectiles are a type of ammunition that get their power from rocket engines. Long-range guided rockets, in particular, hold great significance as they seem to mark the way forward in modern warfare. These guided projectiles take full advantage of the considerable range that long-range rockets offer and, at the same time, manage to achieve improved accuracy. This paper delves into a model that is used for predicting the impact point of rocket projectiles, with the application of the proportional navigation guidance law. It also undertakes an analysis of both the strengths and the weaknesses of this model. Through the formulation of equations related to the dynamics of the center of mass and some other supplementary equations, a rather comprehensive trajectory equation was worked out. When this trajectory was simulated, it brought about the creation of a firing table, which is of help in predicting the initial trajectory inclination angle.
Tao, WenwenWang, RuZhang, LiangPi, Runge
In order to meet the demand for missile miniaturization and simplify the system complexity, this paper designs a guidance control integration method according to sliding mode control based on the longitudinal plane motion model, which is combined with the theory of sliding mode control. The design realizes tracing of attack angle to line-of-sight angle through sliding mode control of the outer loop, and the tracking of the control volume rudder deflection angle to the virtual control volume angle of attack through the sliding mode control of the inner loop. The stability of the guidance law is also verified by the Lyapunov function. The simulation results show that the guidance law can hit the target successfully, which verifies the feasibility and effectiveness of the design method.
Bai, JiajunMing, ChaoAn, ZhichaoNiu, ZhaoqiWen, Guangbao
With the increasing demand for multi-unmanned aerial vehicle (UAV) cooperative operations, the design of guidance laws with time and angle synchronization constraints has become a critical technology to enhance strike precision. This paper focuses on a UAV-launched multi-missile cooperative attack scenario, proposing a composite guidance law that integrates the advantages of existing optimal time/angle control guidance laws. By introducing a time error feedback term and an angle constraint term, combined with an adaptive disturbance observer to compensate for aerodynamic errors and target maneuvers, the proposed guidance law ensures a terminal miss distance of less than 0.5 m while achieving a time error ≤0.6 s and an incidence angle deviation ≤2° among multiple missiles. Simulation and test results both demonstrate that the four-missile cooperative attack achieves time dispersion within 1s, satisfying engineering practicality and anti-interference requirements.
Xie, LijunWang, DeshuangYang, XiaodongZhang, TingtingLi, Yang
This paper presents a monocular vision-based system for high-precision missile pose measurement using ArUco markers and Perspective-n-Point (PnP) algorithms. By deploying 6 × 6 ArUco markers on a cylindrical missile mock-up, the system establishes 3D-2D correspondences between structured-light-scanned models and camera images to solve the PnP problem. The proposed approach integrates optimized ArUco marker recognition — leveraging adaptive thresholding, contour simplification, and grid-based validation — with the Efficient PnP (EPnP) algorithm to achieve real-time pose estimation. Experimental validation demonstrates angular accuracy of ± 0.3° in roll/pitch/yaw and positional accuracy of ± 2 mm within a 2 m range under controlled conditions. The system exhibits robustness against partial occlusions and motion blur, with degraded performance (± 1.2°, ± 5 mm) in extreme scenarios. Key innovations include a streamlined marker detection pipeline and adaptive pose refinement using Levenberg-Marquardt optimization. This work provides a cost-effective, non-contact solution for flight tests, with potential applications in weapon separation testing.
Wang, RuiyangZhang, Chaofan
In modern warfare, military control of the airspace determines aircraft survivability against the most widespread missile threats. The aero-engine exhaust system is an important source of infrared (IR) signatures from the rear aspect, particularly in the 2–3 μm and 3–5 μm IR bands. Two-dimensional (2D; non-axisymmetric) nozzle exits with high aspect ratio (AR > 5) are widely used in stealth aircraft engines due to their low IR signature, ease in thrust vectoring, and high maneuverability and agility. This analytical study compares the specific thrust (for choked and unchoked flow regimes) and the visible planar areas of a 2D nozzle exit with different ARs with those of a circular nozzle, as seen from the direct rear view. The nozzle’s isentropic efficiency (ηis,noz) is obtained in terms of the total pressure ratio, and the effect of AR on ηis,noz is examined for 1 ≤ AR ≤ 15. It is found that ηis,noz decreases with increasing AR, but this decrease is more rapid in unchoked flow than in choked flow. For the same value of nozzle exit cross-sectional area, the corresponding visible planar areas of aero-engine hot parts are compared for a 2D nozzle exit with different AR with that of the baseline case (circular nozzle), from bore-sight. This study shows that the optical blocking of aero-engine hot parts by a round-to-rectangular nozzle of AR ≤ 4 is almost the same as that of a circular nozzle, from bore-sight.
Baranwal, Nidhi
Submarine-launched missiles with domed nose cones are highly vulnerable to cavitation erosion as they travel at high speed through an underwater launch tube and then into the air from the sea surface. The collapse of vapour cavities crystallizes intense damage on the vehicle surfaces so that the vehicle structure and aerodynamic performance are threatened. In this work, we show the full 3D numerical and analytical analysis of surface protection concepts for the reduction of cavitation damage on such an axisymmetric dome-shaped body. A computational methodology was developed by importing a complex computer-aided design (CAD) model of a dome and the connecting tubular structure into a high-fidelity simulation environment. The geometry was simplified by omitting non-essential details to facilitate the generation of quality mesh for CFD analysis. Simulations have been carried out to analyze the flow field and pressure distribution under two critical stages, at two angles of attack of 0° and 12° and different launch depths. This investigation focuses on a passive mitigation technique that bonds an optimised rubber padding to the dome's exterior surface. The impact forces from collapsing cavitation bubbles are thought to be absorbed and dissipated by the rubber due to its viscoelastic nature, leading to a reduction of the impulsive stress on the substrate. The results show that the controlled introduction of such a compliant material dramatically changes the surface response to cavitation implosions. The suggested rubber padding is demonstrated to be an efficient and practicable means of protecting the surface; thus, the risk of cavitation erosion is diminished considerably, and the service life and reliability of the underwater projectile vehicle can be improved.
Velayudhan, GauthamP S, PremkumarS, Suhail AhmedP, KrishnakumarVasantharaj, C
Grid fins are non-conventional aerodynamic lifting and control surfaces which are made of a frame supporting lifting surfaces positioned in the form of a lattice structure. Grid fins are also called as lattice fins and are used as control surfaces in launch vehicles, crew escape systems, missiles etc. to achieve static stability. Each panel of the grid fin acts as fin and it produces force which increases stability of the vehicle. For a crew escape system module, grid fins are used as a passive aerodynamic control surfaces to achieve static stability. Grid fins are positioned at the end of crew escape system module to provide required static margin by increasing moment arm. In contrast to conventional fins, grid fins incorporate a distinctive waffle-like pattern or grid pattern configuration, offering superior aerodynamic performance in supersonic regimes and enabling compact storage in stowed position during launch followed by deployment at the time of exigency. In case of an emergency, crew escape system is activated and it will take crew escape module away from the launch vehicle during atmospheric regime. In this scenario, grid fins are deployed simultaneously along with firing of high-thrust, fast-acting solid rocket motors (SRMs) which provide the impulsive force needed for clean separation. Grid fins help to stabilize the crew escape system module by counteracting aerodynamic instabilities, especially when the module is moving through the atmosphere at high speeds. The primary structural loads acting on grid fins include deployment forces (hinge forces, locking), aerodynamic, and inertial forces. Additionally, the exhaust plumes from the firing of SRMs impinge directly upon the grid fins, generating intense thermal loads characterized by rapid temperature gradients and localized heating. The simultaneous presence of thermal and structural loads influences displacements, stresses, interface joints integrity and maximum buckling loads. Furthermore, elevated temperatures degrade mechanical properties such as yield strength, ultimate strength, and Young’s modulus, therefore a thermo-structural analysis is carried out to study the effects of these combined loads on grid fins. This paper presents typical grid fin configuration, thermo-structural formulation, finite element model details, and thermo-structural analysis results including stress margins, deformations, buckling load factors and preload variations for the maximum design load case.
Mali, Somanath NanduSundar Raj, RSundaresan, MKR, Suresh
Nasa Tech Briefs: May 202626AERP055/7/2026
How Machina Labs is Reshaping Defense Manufacturing with AI-Driven 7-Axis Robotics Engineering at the Speed of Conflict: The New Era of Defense Testing MyDefence Expands Production, Validation of Wearable and Mobile Counter-UAS Systems Keeping Pace with Changes in Defense Technology: Why Embedded Systems Must Deliver Agility, Resilience, and Endurance From Autonomous Vehicles to Ship-to-Shore to: Designing 60 GHz Networks for Tactical Applications Defense Research Program Developing Tactical Clocks for GPS-Free Navigation The Drone Equation: Proportional Response to the UAS Threat High-end interceptors. Low-end threats. The answer isn't bigger missiles but smarter integration. Virginia Tech Experts Accelerate Skydio Drone Flights Over People and Vehicles Researchers recently helped Skydio, the leading U.S. drone manufacturer, demonstrate compliance to the Federal Aviation Administration's rules for safe flights over people and vehicles. Teaching Robots to Fly Like Birds Rutgers researchers replace motors with smart materials in an innovative approach to flight. RPI Researchers Harness Agentic AI for Smarter, Faster Aerospace Design Funding from Google and the U.S. Department of Energy helped a team of researchers develop an assortment of agentic AI-enabled tools to help optimize traditional aerospace design processes. Can Multi-Fingered Robots Transform Shipboard Operations and Autonomous Maintenance? USC Viterbi researcher received Office of Naval Research's Young Investigator Program award with Study on dexterous robotics. Can Multi-Fingered Robots Transform Shipboard Operations and Autonomous Maintenance? USC Viterbi researcher received Office of Naval Research's Young Investigator Program award with Study on dexterous robotics.
On a clear afternoon over a contested airspace, a drone suddenly appears on radar. Within seconds, more follow, and they're small, fast, and unpredictable. For the U.S. Army's air and missile defense operators, every moment counts. The difference between mission success and mission failure is measured in milliseconds. During that brief window, sensors must connect instantly, embedded systems must process floods of data at the edge, and command links must hold steady even under electronic interference.
Leonardo DRS has opened a new naval power and propulsion manufacturing and testing facility in Charleston, South Carolina, expanding its role in delivering next generation electric propulsion, integrated power systems, and high energy payload support for U.S. Navy surface and undersea platforms. The 140,000 square foot site consolidates advanced manufacturing, final assembly, and high fidelity testing for electric power conversion and propulsion systems, while also supporting naval steam turbine design, production, and subsystem integration for programs including the Columbia class ballistic missile submarine. A representative for Leonardo's Naval Power Systems business unit provided emailed statements with details about the type of advanced manufacturing the company will deploy at the new facility.
Pyrovalves (also known as pyrotechnic valves) have long been a staple in defense systems, particularly in missile and munition launcher applications. The rapid growth of counter-UAS and missile defense systems makes this an ideal time to explore smarter alternatives to pyrovalves. One of the largest ongoing U.S. military efforts is the Missile Defense Agency's (MDA) Scalable Homeland Innovative Enterprise Layered Defense (SHIELD) Multiple Award Indefinite Delivery/Indefinite Quantity (IDIQ) contract. In December, MDA issued two tranches of SHIELD awards to more than 2,100 companies, including major defense contractors and startups such as Lockheed Martin, Raytheon, Boeing, Shield AI, Anduril, and Virtualitics.
The U.S. Army Space and Missile Defense Command Technical Center's Aerophysics Research Facility, (ARF), fired a successful hypersonic shot to test its new rainfield simulator. U.S. Army Space and Missile Defense Command Technical Center, Huntsville, AL Zack Perrin, ARF manager and technical lead engineer of the U.S. Army Space and Missile Defense Command (USASMDC's) Targets and Test Resources Branch of the Ronald Reagan Ballistic Missile Defense Test Site, said ARF is SMDC's premier hypersonic flight and hypervelocity impact laboratory. Perrin said their largest gun system, the 254 mm light gas guns, or LGGs, is the fastest gun in the Army and can launch projectiles 6 inches in diameter to speeds up to 3 kilometers per second or smaller projectiles on the order of 2.7 inches in diameter to velocities exceeding 6 km/s. “I like to tell people that the facility is a gun range the size of an aircraft carrier and within the facility are multiple engineering tools, called light gas guns,” Perrin said. “Aerophysics' core mission is to efficiently and affordably provide both the Army and the broader Department of Defense (DoD) engineering community with state-of-the-art hypersonic aerodynamic data, hypervelocity impact physics data, and weapons system performance data.”
RF and fiber have long co-existed within modern military and aerospace systems, with each medium dedicated to separate, mission-critical roles. Increasingly, however, system designers are turning to RF-over-fiber (RFoF) architectures to bridge the gap between over-the-air RF interfaces and the long, interference-resistant transport advantages of fiber. When it comes to over-the-air communications uses like tactical radio or satellite communications terminals, radio frequency (RF) is still the dominant signal format. RF is also commonly used at the front end of radar and electronic warfare, supporting search, tracking, fire control radar, missile seekers, jammers and electronic support measures.
Moog Inc. East Aurora, NY kgibas@moog.com
This AIR provides information about the specific requirements for missile hydraulic pumps and their associated power sources.
A-6C4 Power Sources Committee
When a Marine in the field launches an uncrewed aerial vehicle (UAV) to gather intelligence, it becomes more than just a drone. It's a flying data center that processes AI workloads, runs machine learning algorithms, and transmits critical information through a complex network designed to provide situational awareness across multiple commands. All of this computational power generates significant heat, and in the confined space of a UAV operating in harsh environmental conditions, thermal management becomes critical to mission success. But there's a fundamental question the U.S. defense isn't asking: how will we manage the heat? The Golden Dome, the Trump administration's vision for missile defense, builds upon the existing Joint All-Domain Command and Control (JADC2) framework for connecting sensors from all branches of the U.S. armed forces into a unified network powered by artificial intelligence. This plan faces an existential threat from thermal management challenges that have plagued edge computing systems for years.
U.S. Army Redstone Arsenal, AL 703-697-9603
A joint acoustic flight test was conducted by NASA Langley Research Center and the U.S. Army Combat Capabilities Development Command Aviation & Missile Center, with the goal of investigating new methods for acoustic data collection. The impetus for the effort is the anticipated growth of Urban Air Mobility and Future Vertical Lift vehicles. Many of these vehicles are expected to have distributed propulsion systems that may result in unsteady vehicle state conditions even during steady flight. This work examines the acoustic measurements collected during purposefully unsteady maneuvers performed by an MD530F helicopter. A snapshot microphone array design was deployed for this test to capture the acoustic signature on the ground from the helicopter under maneuver conditions. An analysis of the acoustic emissions indicated the presence of blade-vortex interactions, not only during the rolls towards the advancing side of the main rotor, but also rolls towards the retreating side and during pitch-up maneuvers. The strength of the interaction noise was found to be strongly dependent on the acceleration of the vehicle.
Stutz, ColinStephenson, JamesPascioni, KyleHouston, Mary
BlueHalo Arlington, VA paul.frommelt@bluehalo.com
BlueHalo Arlington, VA 703-718-4050
Defense Equipment & Support (DE&S) Bristol, UK 0117-913-0893
The aim of this paper is to present a numerical analysis of high-speed flows over a missile geometry. The N1G missile has been selected for our study, which is subjected to a high-speed flow at Mach 4 over a range of Angle of attack (AoA) from 0° to 6°. The analysis has been conducted for a 3-dimensional missile model using ANSYS environment. The study contemplates to provide new insights into the missile aerodynamic performance which includes the coefficient of lift (CL), coefficient of drag (CD) and coefficient of moment (CM) using computational fluid dynamics (CFD). As there is a lack of availability of data for missile geometries, such as free stream conditions and/or the experimental data for a given Mach number, this paper intends to provide a detailed analysis at Mach 4. As the technology is advancing, there is a need for high-speed weapons (missiles) with a good aerodynamic performance, which intern will benefit in reduction of fuel consumption. In order to meet the requirements, aerodynamic shape optimization can be performed. This paper will create a basic knowledge about the N1G missiles aerodynamic performance at Mach 4. This can be referred in future studies into the hypersonic regime and shape optimization to get the best suited geometry with high aerodynamic performance for a given free stream condition.
Padmanabha, M AnanthPrasad, BhoomikaSivasubramanian, Jayahar
Severe problem of aerodynamic heating and drag force are inherent with any hypersonic space vehicle like space shuttle, missiles etc. For proper design of vehicle, the drag force measurement become very crucial. Ground based test facilities are employed for these estimates along with any suitable force balance as well as sensors. There are many sensors (Accelerometer, Strain gauge and Piezofilm) reported in the literature that is used for evaluating the actual aerodynamic forces over test model in high speed flow. As per previous study, the piezofilm also become an alternative sensor over the strain gauges due to its simple instrumentation. For current investigation, the piezofilm and strain gauge sensors have mounted on same stress force balance to evaluate the response time as well as accuracy of predicted force at the same instant. However, these force balance need to be calibrated for inverse prediction of the force from recorded responses. A reliable multi point calibration methodology has been used to recover the calibration force. Initially, a blunt bicone shaped scaled “DASA CTV” model has been fabricated in house along with three component stress wave balance. Further, a multi-point calibration experiment has been performed over a test model at nine different locations. In literature, there is no any evidence has been found that effect of various sensors during calibration or actual shock tunnel experiments on a recovered forces. Hence, a calibration experimental studies focus on various sensors mounted on stress wave force balance to understand its behavior and also recovery of calibration forces during the experiment.
Kamal, AbhishekDeka, SushmitaSahoo, NiranjanKulkarni, Vinayak
Lockheed Martin Orlando, FL 407-284-9248
Aerospace & Defense Technology: May 202424AERP055/9/2024
Explaining MOSA from the Team that Led the Army Aviation Mission Computing Environment Task Order What's the Best DC Motor for Your Commercial Aerospace Application? Aerospace Production: Overcoming Challenges in Composite Machining Understanding the Limits of Artificial Intelligence for Predictive Maintenance Pushing the Limits: Engineering Advanced RF Interconnects to Meet the Challenges of Hypersonic Missile Development Expanding Possibilities for Superconducting Qubits With Niobium Researchers Help Robots Navigate Efficiently in Uncertain Environments A new algorithm reduces travel time by identifying shortcuts a robot could take on the way to its destination. New, Portable Antenna Could Help Restore Communication After Disasters Researchers from Stanford and the American University of Beirut have developed a lightweight, portable antenna that can communicate with satellites and devices on the ground, making it easier to coordinate rescue and relief efforts in disaster-prone areas. NRL Scientists Deliver Quantum Algorithm to Develop New Materials and Chemistry U.S. Naval Research Laboratory scientists unveil the Cascaded Variational Quantum Eigensolver (CVQE) algorithm expected to become a powerful tool to investigate the physical properties in electronic systems for disruptive defense technologies. Evaluation of Additively Manufactured Ultrahard Steels Recent advances in both alloy development and additive manufacturing have enabled the production of ultrahigh-strength steels in nearnet shape parts.
U.S. Army Combat Capability Development Command Aviation and Missile Center (DEVCOM AvMC) and Georgia Tech Research Institute (GTRI) developed the Mission Systems Flying Testbed (MSFTB) to enable rapid evaluation of innovative technologies and integration approaches against Modular Open System Approach (MOSA) objectives. The MSFTB is a flight test capability to evaluate and demonstrate integration of mission systems to inform Army stakeholders on satisfaction of Modular Open System goals for the Army Aviation enterprise, Future Vertical Lift family of systems, and enduring aviation platforms.
Farr, AshtonWigginton, ScottAl-Husseini, MohammadIbere, Ayende
Corrosion occurs in diverse environments mainly on metallic parts. Helicopters are made of a huge percentage of metallic parts and need to have several maintenance steps to guarantee its functioning and its durability. The military helicopters are flying in different kinds of environment, which cover large spectrum of severity of the atmospheric corrosion [1]. In maritime conditions, the most influencing factor is the Time of Wetness, which is a direct result Relative Humidity and Salt loading. The main material used for aircraft and that is suffering from corrosion is aluminium. There are plenty of data to follow the corrosion as a function of the environmental conditions, mainly on the sensitivity with sodium chloride, Relative Humidity, film thickness, etc... [2][3]. The maintenance efficiency on helicopters is dependent on the environmental severity. The U.S. armed forces estimate $10.2 billion in corrosion costs for their aviation and missile fleets during 2016 [4] [5] [6]. The aim of the present analysis consists of defining the Condition Based Maintenance related to corrosion risk to better apply a maintenance program when it is really needed.
Sinopoli, Davidmiranda dias, PATRICIADEVILLIERS, GEORGES
The development of hypersonic missiles represents the most significant advancement of defense weaponry since the 1960s. However, they also pose unique challenges for both design and technology. The term “hypersonic” refers to any speed faster than five times the speed of sound, or above Mach 5. Modern hypersonic missile systems require extensive communications interconnects within a highly confined space. This space requirement creates a demand for solutions combining small form factor with reduced weight and rugged construction to withstand high vibration and impact conditions from deployment to target. Currently there are two types of hypersonic weapons. Hypersonic glide vehicles (HGVs), also known as boost-glide vehicles, typically launch from ballistic missiles and are released at a specific altitude, speed, and with the flight path tailored to a target without being powered. Hypersonic cruise missiles (HCMs) are powered all the way to their targets, flying at lower altitudes than HGVs and launched from rockets or jet aircraft. Power for HCMs comes from air-breathing scramjet engines, which have been in development since the 1950s and most successful since the 2000s.
L3Harris Technologies Melbourne, FL 585-465-3592
In 2023, Parry Labs was awarded two tasks under the Aviation and Missile Technology Consortium's (AMTC) Other Transactions Agreement to lead a multi-vendor team to collaboratively define the Army's Modular Open Systems Approach (MOSA) requirements for computing and software operating environments for all future Army Aviation procurements. This relatively new approach for the Army and industry drove collaboration and allowed U.S. Government (USG) to make key modularity and openness decisions relative to Aviation Mission Computing Environment (AMCE). This unique opportunity provided a platform for industry to openly inform requirements at a much more granular level than previously possible, providing assurances that such detailed requirements wouldn't be an overreach or constrain innovation and disrupt industry business models. Solicited to the entire AMTC, which represents the vast majority of the aviation industrial base, the AMTC and USG team selected the most qualified vendors to work together with USG subject matter experts to develop a Component Specification Model (CSM) for the AMCE. The real-time collaboration that occurred as a result of this arrangement helped surface new technologies to the USG, and a clear mechanism for industry members from across the consortium to see the progressing requirements and raise any concerns, especially regarding the insertion of proprietary design patterns.
Raytheon Arlington, VA 202-384-2474
Unguided sounding rockets, also known as sub-orbital rockets, are vehicles that carry scientific experiments and/or sensors to collect data during their trajectory. These rockets lack active control but are capable of traversing the Earth’s atmosphere. It is crucial to thoroughly analyze the flight parameters during the preliminary design phase. The Open Rocket flight simulation software, developed by Sampo Niskanen, is a widely used open-source project. However, it has some simplifications in comparison to its documentation. It does not specify the calculations of critical parameters required for the rocket’s stability during its flight. Additionally, it does not calculate data related to dynamic stability, which encompasses the system’s ability to make disturbances corrections during the rocket’s trajectory. Consequently, this study presents a flight simulation of a rocket with 6 degrees of freedom using Matlab/Simulink. Two scenarios are simulated: one without wind and another with wind coming from different directions. The simulations demonstrated good agreement with Open Rocket in the windless scenario. However, trajectory discrepancies were observed as the angle of attack and wind intensity increased. These divergences can be attributed to aerodynamic data. Open Rocket relies on analytical equations for low angles of attack, whereas the algorithm used in this study utilizes Missile Datcom data, specialized software for missiles and rockets. This enables more accurate simulation data to be generated.
de Oliveira Junior, Wilson LuizFazzolari, Heloise AssisFreire, Cesar Monzude Paiva Carvalho, Carlos Alberto
This recommended practice covers the requirements and qualification tests for two types of flexible all-metal hose assemblies intended for hydraulic use on missile and rocket applications at rated pressures of 4000 psi. Type I -65° to +650 °F service temperature range Type II -65° to +1000 °F service temperature range
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
During her recent remarks at the National Defense Industrial Association's (NDIA) Emerging Technologies for Defense conference, U.S. Deputy Secretary of Defense Kathleen Hicks outlined the agency's new “Replicator” initiative. Under the new Replicator initiative, over the next 18 to 24 months, the Defense Department will deploy thousands of low cost autonomous systems across multiple domains. DoD officials are limiting the amount of information they will release around technology or platform specifics for Replicator. Hicks did confirm however that Replicator has been established to counter the rapid buildup of the People's Republic of China's (PRC) armed forces, weapons and new technologies.
Kongsberg Defence & Aerospace selected a radar test setup from Rohde & Schwarz based on the R&S SMW200A vector signal generator for multi-channel phase-coherent radar signal generation. Kongsberg is Norway's premier supplier of defense and aerospace-related technologies. The joint strike missile (JSM) is a fifth generation long range precision strike missile. Using advanced sensors, the JSM can locate targets based on their electronic signature. Qualification of the JSM is under way with the Royal Norwegian Air Force (RNoAF). Kongsberg's JSM must operate autonomously in highly contested environments. To increase mission success, the missile has a passive RF sensor that can locate and identify radio frequency emitters. To test and verify this RF direction finding capability in a laboratory, Kongsberg required a multi-channel phase coherent vector signal generator that could be linked to existing test environments.
Kongsberg Defence & Aerospace selected a radar test setup from Rohde & Schwarz based on the R&S SMW200A vector signal generator for multi-channel phase-coherent radar signal generation. Kongsberg is Norway’s premier supplier of defense and aerospace-related technologies. The joint strike missile (JSM) is a fifth generation long range precision strike missile. Using advanced sensors, the JSM can locate targets based on their electronic signature. Qualification of the JSM is under way with the Royal Norwegian Air Force (RNoAF).
RF cable assemblies might appear to be a minor component in system design, but they can make all the difference between success and failure, especially in mission-critical industries such as defense and space. The RF interconnect is the vital bridge between many critical systems, including payload, communications, signal transport, and processing. This article will primarily focus on hypersonic missile systems and satellites to illustrate these concepts, as they jointly highlight the importance of RF cable assembly design in extreme environments.
Aerospace & Defense Technology: June 202323AERP066/1/2023
Overcoming Machining Productivity Challenges with Aerospace Components Why the Turbomachinery Industry is Increasingly Bullish on Additive Manufacturing 3D-printed metal-alloys are answering critical needs for high fluid flow, high-pressure parts. Airborne Inspection Sensor Evolves with LiDAR, Mid-IR and Artificial Intelligence Air Force eVTOL Research and Development Programs Make Remote Pilot Progress Creating a Digital Gateway for RF Domain Will Advance Designs That Meet DoD Initiatives Understanding the Unique RF Interconnect Requirements for Ultra-Demanding Hypersonic Missile and Satellite Applications ADS-B Classification Using Multivariate Long Short-Term Memory This analysis extends previous research that used long short-term memory-fully convolutional networks to identify aircraft engine types from publicly available automatic dependent surveillance-broadcast (ADS-B) data. Physics-Guided Neural Network for Regularization and Learning Unbalanced Data Sets Directed energy deposition is of interest to the aerospace and defense industries for the production of novel and complex geometries, as well as repair applications. However, variability during the build process can result in deviations in final component geometry, structure, and mechanical properties, which adds to the complexity of process planning and slows down adoption of this technology. Context-Aware Visual Search Using a Pan-Tilt-Zoom Camera While in some scenarios an Internet-of-Things (IoT) approach allows multiple distributed cameras to cooperatively survey a large region of interest (ROI), other scenarios, such as surveillance by a mobile robot, require the ROI to be surveyed by a small number of collocated cameras. Automated Atmospheric Correction of Nanosatellites Using Coincident Ocean Color Radiometer Data Researchers present a machine-learning-based method for utilizing traditional ocean-viewing satellites to perform automated atmospheric correction of nanosatellite data. Characterizing Motion Prediction in Small Autonomous Swarms Despite the expanded use of robotic swarms, little is known about how swarms are perceived by human operators. To characterize human-swarm interactions, we evaluate how operators perceive swarm characteristics, including movement patterns, control schemes, and occlusion.
The U.S. Air Force has completed the functional configuration audit (FCA) of the latest variant of Raytheon Technologies' Advanced Medium Range Air-to-Air Missile (AMRAAM). The AMRAAM AIM-120D-3 is on-track toward fielding by both the Air Force and Navy this year.
The purpose of this recommended practice is to provide the missile hydraulic and pneumatic component designer with information learned, tested, and substantiated in the correction of problems and failures experienced with seals that are subject to the unique requirements of missile static storage and subsequent dynamic operational conditions.
A-6C2 Seals Committee
This document defines and illustrates the process for determination of uncertainty of turbofan and turbojet engine in-flight thrust and other measured in-flight performance parameters. The reasons for requiring this information, as specified in the E-33 Charter, are: determination of high confidence aircraft drag; problem rectification if performance is low; interpolation of measured thrust and aircraft drag over a range of flight conditions by validation and development of high confidence analytical methods; establishment of a baseline for future engine modifications. This document describes systematic and random measurement uncertainties and methods for propagating the uncertainties to the more complicated parameter, in-flight thrust. Methods for combining the uncertainties to obtain given confidence levels are also addressed. Although the primary focus of the document is in-flight thrust, the statistical methods described are applicable to any measurement process. The E-33 Committee has endeavoured to gather industry-wide expertise in in-flight measurement and uncertainty analysis to collect and promulgate recommended practices in the subject disciplines. The Committee is organized into subcommittees to address both the analytical and test methodology for determination of in-flight thrust and also the uncertainty of the determination. This document; Uncertainty of In-flight Thrust Determination, AIR1678, addresses the process for determining the uncertainty of in-flight thrust. A companion document, In-Flight Thrust Determination, AIR1703, addresses the basic methodology for determining in-flight thrust. The Committee, after reviewing recommended changes and clarification in definitions and application of statistical uncertainty items, made small revisions to the original document published in 1985. These changes were incorporated into AIR1678 Rev A. This Revision B has the same Scope as preceding versions. The nomenclature and methodology used herein are now consistent with evolving world and national standards promulgated primarily by ISO and ASME.
E-33 In Flight Propulsion Measurement Committee
Aerospace & Defense Technology: February 202323AERP022/9/2023
Using an Open Architecture Approach to Military Avionics Can Embedded Electronics Components Meet the Demands of Hypersonic Missiles? CMOSS/CMFF Trades Interoperability for Free-Thinking Innovation Exploring High-Performance Applications for Distributed Transport Property Thermoelectrics Heterogeneous Integration and SiPs Benefit SWaP-C Reduction The Future of Automated Guided Vehicles for Aerospace and Defense Next-generation AGVs are already starting to deliver labor and cost savings for the U.S. defense industry, and the commercial aerospace sector is watching closely Deep Reinforcement Learning Achieves Multifunctional Morphing Airfoil Control Smooth camber morphing aircraft offer increased control authority and improved aerodynamic efficiency. Smart material actuators have become a popular driving force for shape changes, capable of adhering to weight and size constraints and allowing for simplicity in mechanical design. DEVCOM ARL FY22 Industry Autonomy Technology Assessment Final Report on Security and Mobility Forces that will conduct missions for extended periods in expeditionary situations require technologies that are mobile, robust, and have sufficient autonomy to increase team effectiveness. The U.S. Army Combat Capabilities Development Command Army Research Laboratory solicited solutions from industry that demonstrate autonomous mobility and autonomous security in operationally relevant scenarios. Design and Analysis of a Small Unmanned Aerial System (UAS) Power Distribution System All electrically powered autonomous vehicles possess a system that distributes power to all the vital components of the vehicle. The U.S. Army Combat Capabilities Development Command (DEVCOM) Army Research Laboratory (ARL) uses group 1 unmanned aerial systems (UASs) (weighing 20 lb) as the vehicle platform in several projects.
Today, defense organizations in several countries are attempting to expand military capabilities by investing in hypersonic missile development. Since these missiles travel at Mach 5, or nearly 4,000 mph, there are naturally a variety of challenges for developing both the actual weapons systems and the corresponding detection systems. While challenges span nearly every aspect of developing these missiles, in this article we will focus specifically on the key challenges associated with the embedded electronics and communication systems. We will also look at how aerospace and defense engineers working on hypersonic missiles can ensure they are selecting supplier partners that are well positioned to meet these unique challenges by looking into their space heritage and history developing high-reliability radiofrequency (RF) components.
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