Performances of a small hypersonic airplane (HyPlane)

Access to Space is still in its early stages of commercialization. Private enterprises have been making big progresses hoping to create a Space tourism business. Most of the attention is currently focused on suborbital Space Tourism, while orbital flights still appear limited and expensive. In the present work a preliminary study in the frame of the Space Renaissance (SR) Italia Space Tourism Program, regarding a small hypersonic airplane for a long duration space tourism mission named HyPlane, is presented. It is also consistent with a point-to-point medium range (5000 km) hypersonic trip, in the frame of the "urgent business travel" market segment. Main idea is to transfer technological solutions developed for aeronautical and space atmospheric re-entry systems to the design of such a hypersonic airplane. A winged vehicle characterized by high aerodynamic efficiency and able to manoeuvre along the flight path, in all aerodynamic regimes encountered, is taken into consideration. Rocket-Based Combined Cycle and Turbine-Based Combined Cycle engines are investigated to ensure higher performances in terms of flight duration and range. Different flight-paths are also considered, including sub-orbital parabolic trajectories and steady state hypersonic cruise. The former, in particular, takes advance of the high aerodynamic efficiency during the unpowered phase, in combination with a periodic engine actuation, to guarantee a long duration oscillating flight path. These trajectories offer Space tourists the opportunity of extended missions, characterized by repeated periods of low-gravity at altitudes high enough to ensure a wide view of the Earth from Space.

Journal of Aeronautics & Aerospace Engineering, 2013

In the present work a preliminary study on a small hypersonic airplane for a long duration space tourism mission is presented. It is also consistent with a point-to-point medium range (5000 km) hypersonic trip, in the frame of the "urgent business travel" market segment. Main idea is to transfer technological solutions developed for aeronautical and space atmospheric re-entry systems to the design of such a hypersonic airplane. A winged vehicle characterized by high aerodynamic efficiency and able to maneuver along the flight path, in all aerodynamic regimes encountered, is taken into consideration.

The ultimate objective of making the world smaller place and being able to fly to any point in just couple of hours which can be possible with “hypersonic aircraft”. This is aircraft moves with 7 times more than the speed of the sound i.e. (7 Mach). This aircraft uses air breathing type supersonic ramjet (scramjet) engine. having speed near about 7700 km/hr. nasa’s x-43 (hyper-x) is one of the hypersonic aircraft, which is construct with title based thermal protection system, carbon-carbon composites and high temperature resistance metal with gaseous hydrogen fuel in engine. This aircraft is carried out by booster rocket up to its test altitude of 100000 ft. where it separates from the booster and files under pre-programmed control system.

Progress in Aerospace Sciences, 2016

This paper provides an overview of the current technical issues and challenges associated with the design of hypersonic vehicles. Two distinct classes of vehicles are reviewed; Hypersonic Transports and Space Launchers, their common features and differences are examined. After a brief historical overview, the paper takes a multidisciplinary approach to these vehicles, discusses various design aspects, and technical challenges. Operational issues are explored, including mission profiles, current and predicted markets, in addition to environmental effects and human factors. Technological issues are also reviewed, focusing on the three major challenge areas associated with these vehicles: aerothermodynamics, propulsion, and structures. In addition, matters of reliability and maintainability are also presented. The paper also reviews the certification and flight testing of these vehicles from a global perspective. Finally the current stakeholders in the field of hypersonic flight are presented, summarizing the active programs and promising concepts.

Aerospace, 2018

The conceptual aircraft design and its integration with a combined cycle engine for hypersonic cruise at Mach 8 is documented in this paper. The paper describes the process taken to develop a hypersonic aircraft from a conceptual approach. The discussion also includes the design and CFD analysis of the integrated combined cycle engine. A final conceptual hypersonic transport aircraft with an integrated combined cycle engine was achieved through this study. According to the analysis carried out, the aircraft is able to take-off and land at the airports it is intended to be used and will be able to generate enough thrust to sustain hypersonic cruise at an altitude of 30 km.

International Journal of Engineering Applied Sciences and Technology, 2019

Global networking is the demand of the whole world and time plays a very crucial role in it, and it also plays a very important role in fastest and the reliable means of transport that become necessary, the Bullet train and the Hyper loop Projects are the live examples in that context, various countries from across the globe accept these project and as we all know that aviation sector id the one of the fastest growing means of transport across the world. Challenges faces by the machineries on the ground operation can be handled easily as compared to the air that's why after various research in the era of subsonic has been carried out by many developed countries firstly in the field of military in the form of the weapons and the when that technology proven safe and reliable it has become granted for commercial uses in that context era of supersonic flight the first one has been started on date 26September 1976 by Concord but as per the safety concerns the era of supersonic has closed in 24October 2003. Till now hypersonic platforms comes under in the form of fighter aircraft and reconnaissance aircraft and missile based platforms the demand of all these is to ensure the fastest approach towards the mission with least tile and more precision for the various control systems has been developed and still upgrading Hypersonic jets like very remarkable SR71 of USAF is mile stone in that ere problems occurring in the field of structural material, aerodynamic model and the robust control systems to operate in such a critical speed. It contains a huge present and future aspect of learning and developing new technologies. The demand of the space exploration with hypersonic technology is nearly impossible to predict without Hypersonic speed.

Optimizing the propulsion system for a hypersonic aircraft is examined. A combined cycle engine is selected; where the thrust is to be delivered by a turbine based combined cycle engine (TBCC).The engine cycle is analyzed and optimized to give the required thrust over the entire Mach envelope with minimum fuel consumption. The variation of cycle parameters versus the Mach number is the output of that study. It is to be used further in selecting the design point of each cycle. 2 Figure-1. Configuration of the hypersonic research model Figure-2. The configuration of the HYCAT-1.

9th International Space Planes and Hypersonic Systems and Technologies Conference, 1999

This paper presents a new conceptual launch vehicle design in the Bantam-X payload class. The new design is called Stargazer. Stargazer is a two-stage-toorbit (TSTO) vehicle with a reusable flyback booster and an expendable LOX/RP upper stage. Its payload is 300 lbs. to low earth orbit. The Hankey wedge-shaped booster is powered by four LOX/LH2 ejector scramjet rocket-based combined-cycle engines. Advanced technologies are also used in the booster structures, thermal protection system, and other subsystems. Details of the concept design are given including external and internal configuration, mass properties, engine performance, trajectory analysis, aeroheating results, and a concept cost assessment. The final design was determined to have a gross mass of 115,450 lb. with a booster length of 99 ft. Recurring price per flight was estimated to be $3.49M. The overall conceptual design process and the individual tools and processes used for each discipline are outlined. A summary of trade study results is also given. NOMENCLATURE C t thrust coefficient I sp specific impulse (sec.) q dynamic pressure (psf) T/W e engine thrust-to-weight ratio This paper summarizes part of an 18 month Bantam-X concept study conducted by the Space Systems Design Laboratory at Georgia Tech with the support and collaboration of NASA Marshall Space Flight Center. The study goal was to investigate a promising concept based on rocket-based combinedcycle (RBCC) propulsion for longer range Bantam-class missions. NASA MSFC currently has an ongoing development program in RBCC engines.

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2011

Hypersonic Turbojet Experimental vehicle is a vehicle proposed for the flight test at Mach 5. The capacity of the installing equipment has increased at recent design review. Therefore, it is necessary to increase the body volume. In this study, aerodynamic performance of this vehicle was examined to evaluate effect of body volume on aerodynamic performance. And effect of body shape on aerodynamic performance was evaluated. As the results, the body height is found not to affect the longitudinal static stability, but the directional static stability. And the effect of flow around airframe on aerodynamic performance is small.

CEAS Space Journal

This paper has the aim to report the status of the HYPLANE project to date. HYPLANE is a horizontal takeoff and landing Mach 4.5 bizjet-size aerospaceplane conceived by Trans-Tech and University Federico II of Naples and under study within the industrial-academic ecosystem of the Campania Aerospace District (DAC). HYPLANE has the aim to offer very fast suborbital flight for space tourism, microgravity experimentation and training, and also shortening time to connect two distant airports within a door-to-door scenario. The concept is based on the access to stratospheric altitudes (30 km) for either point-to-point stratospheric or suborbital flights as safe as today's commercial air transportation, by integrating enhanced state-of-the-art aeronautical and space technologies. Essentially, HYPLANE is mostly based on already relatively high TRL technologies which guarantees a sufficiently short time to market. The low wing loading configuration and designed ability to manoeuvre along the flight trajectories at small angles of attack, allow HYPLANE to guarantee accelerations and load factors of the same order as those characterizing the present civil aviation aircraft (FAA/EASA specifications). Thanks to its technical features, it may operate from/to more than 5000 airports all over the world needing short runways to takeoff and land, which for point-to-point business aviation is paramount. Furthermore, characteristics such as small dimension, configuration and high cruising altitude determine reduced noise in the airports surrounding and low sonic boom impact on ground. These conditions will further facilitate not only the development of the commercial use of such kind of transportation mean, but also its social acceptability.