Description:Field of Invention
The present invention is certain to reduce the payload fairing separations failures by modifying clam shells into three separate divisions.
Background of the Invention
Payload fairings acts as a shield to protect the satellite, it prevents the satellite from being affected by various loads, Aerodynamics forces, Thermal phenomena, Vibrations etc., which acts on the launch vehicles from take-off up to final stage of the rocket. These fairings are made up of Aluminium (Al) and various composite materials and are covered with acoustic blankets which assure the safety by protecting the payload from extremely high frequency vibrations.
Due to the high noise while launching and high vibrations the payload fairing often fails to sustain loads and the light weight, small jettisoning mechanisms such as Pyrotechnic-fasteners or explosive bolts which are placed on both sides of the fairing may get damaged and leads to fairing separation. To ensure safety we need to either increase the stiffness of the fairings or increase the thickness of the acousticblankets, but this will however increase the weight. So, the invention mainly focuses on simplifying the separation technique.
Acoustic blankets are applied to the inner surfaces of payload fairings to reduce acoustic vibrations induced by engines and friction against the atmosphere. This insulator is made up of glass wool and resin foam, in the insulating material is placed in filter-equipped covers to keep dust out of the satellite compartment. The goal is to keep the covers from rupturing as the launch vehicle climbs in decompressed atmosphere.
Generally, the payload fairings are two equal banana shaped clamshells which are joined together with actuators and as the launch vehicle reaches the orbit the pyrotechnic-fasteners are exploded so the fairings get separated from the satellite or cargo and get to the orbital path. In our invention, we divide the fairings into two conical clamshells half way through the fairing and the other cylindrical clamshell.
First, we separate the conical clamshells using explosive boltsand as soon as the fairings get separated then the payload needs some propulsive force so it can get out of the cylindrical clamshell. So, we provide some little thrust to the payload and let the inertia take care of the rest.
For instance US20050230562A1 ,discloses two stages of a fairing separation system that are both operational and resettable were designed. When we think about how the resettable seam conductors work, they hold the fairing together as one piece, with releasable point connectors. When there is a fairing separation, the seam connectors detach and release first, followed by the point connecters detaching and releasing. Instead of employing pyrotechnic charges or kiw shock, the payload in the fairing during rocket launch will be separated at an exact position and time by this approach.
EP1162598A2 discloses to improve payload fairings for launch vehicles like the Saunch and to improve payload fairings with jattisonable bulk that provides superior acoustic suppression. Due to the noise generated during the launch, the payload in the fairings will face high temperatures, enormous forces, and vibrations, which can cause mechanical damage, or fracture of satellites and other items like circuits, and other equipment in the rocket. To avoid such repercussions, the payload fairing and payload are covered with layers of materials, often fiber-based inner and outer skins, and two-dimensional aluminium honeycomb compromising with carbon-epoxy load skin, which helps dampen the acoustic energy created during launch.
For instance EP0738865B1 ,The rocket fairing's shape is ogival, which puts a lot of strain and stress on the upper surface. When the rocket is in atmospheric conditions that could cause the payload and fairing structure to collapse due to extreme vibrations and loads; However, we can see in our project that because of the conical shape, the shocks diverge at the top, reducing the pressure, stresses, and vibrations acting on the fairing (clamshell).
Summary of the Invention
In light of the above-mentioned drawbacks in the prior art, the present invention aims to reduce the failure criteria that takes place in rockets during the final separation for the payload to enter space and we are also using various pyrotechnic
The specific objective of the invention is to design a rocket payload fairing which reduce the chance of failing and also to protect the rockets from various kinds of atmospheric loads.
A further specific objective of the invention is preventing the production of turbulence formed by corrugated portion by adding a layer and also to alter the limitations of conventional wing.
Brief Description of Drawings
The invention will be described in detail with reference to the exemplary embodiments shown in the figures wherein:
Figure 1: Pictorial representation of Rocket Payload Fairing
Figure 2: Orthographic view of rocket and its payload fairing
Figure 3: Separation of Payload after stage separation and Fairing separation

Detailed Description of the Invention
Payload fairings serve as a shield for the satellite, shielding it from various loads, aerodynamic forces, thermal phenomena, vibrations, and other factors that affect launch vehicles from take-off until the last stage of the rocket. These fairings are built of aluminium (Al) and various composite materials, and they're wrapped in acoustic blankets to keep the cargo safe from extremely high-frequency vibrations. Small jettisoning mechanisms such as Pyrotechnic-fasteners/explosive bolts that are mounted on both sides of the payload fairing may be destroyed as a result of the high noise and high vibrations experienced during launch. Increase the rigidity of the fairings or the thickness of the acoustic blankets to assure safety, although this will add weight. As a result, the innovation focuses primarily on streamlining the separation process. The payload fairings are usually two equal banana-shaped clamshells that are connected together by actuators, and when the launch vehicle approaches orbit, the pyrotechnic-fasteners are exploded, separating the fairings from the satellite or cargo and allowing them to reach the orbital route. We split the fairings into two conical clamshells halfway along the fairing and one cylindrical clamshell in our innovation. We use explosive bolts to split the conical clamshells, and separate the fairings, the payload requires propulsive power to exit the cylindrical clamshell. So, we give the cargo a little push and let inertia take care of the rest.
Satellites and other space-faring payloads can be launched into orbit or to other locations in space using launch vehicles, rocket vehicles, rocket stages, or missiles. A nose cone or fairing is usually positioned on the upper portion of a launch system. The current application describes the structure of a launch vehicle fairing in detail. For split fairings, many upgraded rocket fairings and accompanying mechanics are explored.
Fairing separation concerns caused many launch flights to fail, including the Atlas SLV-3, Astra R 3.3, PSLV-C39 and Long March 2E launch vehicles. The vehicle is subjected to a range of stresses and forces as it reaches supersonic speed, which could cause the fairings to disintegrate. Even at the rocket's early stages are successful, the launch vehicle's payload, the satellite, will be destroyed if the fairings do not open. With our design, we are attempting to eliminate these failure scenarios by introducing a new method of separating the payload fairings. As a result, we are separating the rocket fairing into three segments to lessen the chances of failure. Pyrotechnic- fasteners/explosive bolts are the method we're utilising to separate these fairings. This is the most basic and effective separation technique available. When compared to conventional systems, these fasteners not only minimise shocks but also noise and vibration, which is why they are employed.
The rocket fairing is separated into three sections: a cylindrical section, a conical segment, and a third will be the conical part that will again be cut into equal halves. All of these components are removed at the same time, boosting the payload's chances of reaching space without being damaged. The cylinder shape is 1/3 the height of a standard rocket fairing, whereas the conical shape is 2/3 the height of a standard rocket fairing. We are taking PSLV C47 to do the experimentation along with stimulation as well as structural, static and vibrational analysis.
The mechanism we are using for separating these sections is pyrotechnics faster which are also called as explosive bolts. These bolts are the most efficient and simplest form of mechanism that can be used in rocket fairing for separation. These fasteners are less in weight, they reduce the shocks and also force the fairings to separate when exploded which will provide the fairings form being as far as possible. Hence we are taking the explosive bolts mechanism when compared with other separation mechanism.
So as the rocket reaches the spave along with other separation, the rocket will be at a speed of 75000km/min so at that time we explode the rocket fairings which will separate all the sections into 3 individual parts. So after this separation the rocket payload will be boosted by solid propellants leading them to enter the required orbit without getting touched by the fairings
3 Claims & 3 Figures , Claims:The scope of the invention is defined by the following claims:

Claim:
1. Rocket Payload Fairing operation, comprising:
a) A cylindrical section followed by a conical segment, and a third will be the conical part that will again be cut into equal halves.
b) The cylinder shape is 1/3 the height of a standard rocket fairing, whereas the conical shape is 2/3 the height of a standard rocket fairing.
c) The components are removed at the same time, boosting the payload's chances of reaching space without being damaged.
2. As mentioned in claim 1, Pyrotechnic-fasteners/explosive bolts are preferred to reduce shocks and noise stimulated in the rocket.
3. As mentioned in claim 1, the payload will be boosted by solid propellants leading them to enter the required orbit without getting touched by the fairings