Hybrid Propelled Access to Space: Feasibility Study on a Hybrid Propulsion Concept for the Mk-III Spaceplane

In pursuit of cost-effective and sustainable space access, Dawn Aerospace is pioneering innovative launch systems. Their focus lies on a semi-reusable, two-stage-to-orbit launch vehicle, designed for horizontal take-off and landing. While current launch vehicles rely solely on rocket propulsion, the potential of airbreathing engines on the first...

Mission Design for Flyback Boosters: Towards Reusable Launch Vehicles

The development of reusable launch vehicles in space exploration is a significant paradigm shift in the aerospace industry. Among numerous approaches to fully reusable launchers, a flyback booster, complemented by the emerging importance of spaceplanes, stands out as a viable solution. To outweigh the drawbacks associated with the cost, a...

An Evaluation of Next Generation Rocket Engines for VT SSTO RLV

Observing that the majority of SSTO programs failed due to the propulsion system being far ahead of its time. Furthermore, acknowledging the that the private launch markets is increasingly dominated by partly reusable TSTOs. This thesis aims to evaluate whether next generation rocket engines make an SSTO viable within a foreseeable economical...

Reliability and Cost Modeling of Reusable Launch Vehicles: Predicting, Preventing and Mitigating the Cost of Failure

The renaissance of reusable space launch vehicles that is being witnessed in the current space industry demands a new cost estimating approach, which takes into account not only the time dependency in the lifecycle brought upon by reusability, but also the complementary considerations of minimizing cost and reliability. To achieve this end, a...

Prototype X: A Cost-Based Design Optimization of an Upper Stage Liquid Propulsion Module with Green-Storable Propellants

This paper investigates the cost­-benefit, payload performance and technical feasibility of green storable upper stage design concepts on their potential implementation with existing launchers. Since the demand for reliable, safe, and cost­-effective transport to space is growing, it is necessary to find sustain­able rocket propellant solutions....

Dawn Aerospace Mk-III Spaceplane Aerothermodynamic Analysis

Dawn Aerospace is developing a horizontal take-off and landing two stage to orbit partially-reusable launcher concept. The re-usable first stage spaceplane operates on a return to launch site trajectory and integrates into the existing airspace, flying as an UAV. For any re-entry vehicle the design needs to account for aerothermodynamic...

Aerodynamic Design and Analysis of a Two Stage to Orbit Winged semi-Reusable Launching Vehicle

The commercialization of the space industry has led to a reduction in size and weight of satellites and launching vehicles, which have effectively reduced the cost of space services. The costs of launching payloads to space can be significantly reduced when the launching vehicles are reusable. The two-stage-to-orbit system with a winged,...

Necessity of non-rigid body models for launch vehicles

In previous research, the necessity of non-rigid body simulators was stated to be a requirement for long, slender bodies. However, it remains unclear for which vehicle design parameters non-rigid body effects become destabilising. A set of 2+N linearly independent equations of motions can be combined in a single matrix to determine the motion of...

Topology Optimization of Launcher Structures under Multiple Critical Load Cases

The launch vehicle industry is undergoing a major shift as new commercial organizations are staking claim to large market shares with bold technologies. To stay competitive in this new era, launch vehicle companies must develop new technologies to reduce launch costs while serving the growing demand for space accessibility. A possible solution...

Dawn Aerospace Mk-III: An exploration of cost driven mission scenarios of a winged Two Stage to Orbit semi-Reusable Launch Vehicle integrated in the common airspace

The demand of small payload launch vehicles has been growing over the past years. Customers base their selection of launch vehicles on cost-effectiveness, flexibility, availability and reliability. A new launch vehicle, the Dawn Aerospace Mk-III, is proposed to be developed, while designed to take into account all these criteria.<br/><br/>For...

Responsive Space Launch with the Mark 41 Vertical Launching System

For decades the space domain has been used for military purposes. When enemy forces establish counter-space capabilities, this could become a weakness. Responsive Space is a concept that focuses on replenishing lost capabilities and/or granting additional capabilities from space assets quickly. The continuous miniaturization of technologies has...

Active Thermal Protection System for Reusable Launch Vehicle: A Conceptual Design

The next step in spaceflight, among others, is the development of a reusable launch vehicle (RLV) suitable for manned missions. All existing designs of re-entry vehicles are either ballistic or low L/D vehicles. In the future, the aim is to develop a high L/D vehicle, because such vehicles experience lower g-loads, making the flight comfortable...

Tracking Ballistic Vehicles during Boost: Development and Performance Analysis of Tracking Filter Algorithms

Accurately tracking the trajectory of launching vehicles during the boost phase is crucial for a variety of reasons. First, an accurate burnout point location and  velocity of the launch vehicle will facilitate the estimation of its trajectory during the following phases of ballistic flight and the impact location. This has important...

Design and Optimization of a Small Reusable Launch Vehicle Using Vertical Landing Techniques

Recent years have seen a drastic increase in the number of small satellites launched per year, as these systems weighing less than 1000 kg have become less expensive alternatives to obtaining scientific data compared to satellites weighing multiple tons. A current drawback with these systems is their price to orbit, often reaching over $100k ...

Launch vehicle structural mass prediction model

Accurate dry mass prediction is essential in early design phases of a launch system. To predict structural mass<br/>of a launch vehicle more accurate at a conceptual design phase, a structural mass model was developed. The model<br/>predicts a launch vehicle’s structural mass, thickness, center of mass and mass moment of inertia. Load carrying...

Control of the atmospheric flight phase of small rocket launchers

This dissertation addresses Thrust Vector Control (TVC) design techniques for small launch vehicles with bounded roll rate. The first contribution of this dissertation is the development of a 6 Degree of Freedom (DoF) nonlinear model that serves as a tool for flight control system design. The nonlinear model is then trimmed and linearized, for a...

Air Launch versus Ground Launch: A Multidisciplinary Design Optimization Study of Expendable Launch Vehicles on Cost and Performance

During the entire era of space flight air launch is seen as a very promising concept. Despite its claimed advantages, air launch is up till now only a marginal success with the Pegasus launch vehicle from Orbital Sciences. In this study is investigated for which conditions expendable air launched vehicles can achieve a performance gain compared...

An Asymptotic Analysis of Compressible Base Flow and the Implementation into Linear Plug Nozzles

The major technical challenge the development of next-generation launchers is facing today, is to achieve complete reusability in two stages to orbit or ultimately in one single stage. These Two-Stage-To-Orbit (TSTO) or Single-Stage-To-Orbit (SSTO) Reusable Launch Vehicles (RLV) may reduce payload cost by a factor of ten or more. The challenge,...