The present disclosure primarily relates to solid rocket motors, more particularly, to propellant grain configuration for use in solid rocket motors.
To meet increasingly demanding performance requirements from solid rocket motors, new propellant grain configurations are conceived. Many factors contribute towards building a high performance solid rocket motor. Two of the geometric factors are high ‘propellant volumetric loading density’ and flexibility to tailor ‘grain regression pattern’ to deliver different mission-specific thrust profiles. Conventionally grain designers have used a variety of grain configurations viz. star, finocyl and conocyl, to name a few, with varying degrees of relative merits, to meet different requirements. Among them, finocyl is a versatile grain configuration that allows for high loading density as well as thrust tailoring flexibility. A finocyl grain configuration comprises of an axial cavity surrounded by longitudinal fin cavities in cyclic symmetry. By altering the size, shape, location and number of fin, finocyl grains can be configured for a variety of thrust profiles.
Few of the prior inventions dealing with conventional finocyl grains follow.
A finocyl grain disclosed in US 00000108211 (Andrew) describes a configuration used in large monolithic boosters. The aft-end located fin is dissimilar but their leading edges are swept backwards as in any conventional finocyl grain.
Another finocyl grain disclosed in U.S. Pat. No. 4,936,092 (Andrew) depicts a compact, monolithic grain configuration with deep fin cavities at the aft-end of the motor. Again the leading edges of the fin are reverse-swept.
Yet another finocyl grain disclosed in U.S. Pat. No. 4,148,187 (Younkin) relates to a multi-piece grain configuration for modulated thrust profiles. Illustrating figures show typical finocyl grains with reverse-swept fin leading edges.
The present disclosure relates to a solid rocket motor. The rocket motor comprises an internally insulated cylindrical casing with end domes having centrally located apertures at fore-end and aft-end. The rocket motor further comprises a solid propellant grain filled within the casing. The grain comprises an axial through-bore running from fore-end to aft-end along the axis of the rocket motor. The grain further comprises a plurality of longitudinal fin cavities formed in a circular array around the said axial through-bore at the aft-end of the rocket motor. Each of the plurality of longitudinal hollow fin cavities extends radially outwards with forward-swept leading edge and trailing edge.
The foregoing summary is illustrative only and is not intended to be in any way limiting. In addition to the illustrative aspects, embodiments, and features described above, further aspects, embodiments, and features will become apparent by reference to the drawings and the following detailed description.
The features of the present disclosure will become more fully apparent from the following description and appended claims, taken in conjunction with the accompanying drawings. Understanding that these drawings depict only several embodiments in accordance with the disclosure and are therefore, not to be considered limiting of its scope. The disclosure will be described with additional specificity and detail through use of the accompanying drawings.
The figures depict embodiments of the disclosure for purposes of illustration only. One skilled in the art will readily recognize from the following description that alternative embodiments of the structures and methods illustrated herein may be employed without departing from the principles of the disclosure described herein.
While the invention is susceptible to various modifications and alternative forms, specific embodiment thereof has been shown by way of example in the drawings and will be described in detail below. It should be understood, however that it is not intended to limit the invention to the particular forms disclosed, but on the contrary, the invention is to cover all modifications, equivalents, and alternative falling within the scope of the invention.
The terms “comprises”, “comprising”, or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a setup, device or method that comprises a list of components or steps does not include only those components or steps but may include other components or steps not expressly listed or inherent to such setup or device or method. In other words, one or more elements in a system or apparatus proceeded by “comprises . . . a” does not, without more constraints, preclude the existence of other elements or additional elements in the system or apparatus.
In the following detailed description of the embodiments of the invention, reference is made to the accompanying drawings that form a part hereof, and in which are shown by way of illustration specific embodiments in which the invention may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the invention, and it is to be understood that other embodiments may be utilized and that changes may be made without departing from the scope of the present invention. The following description is, therefore, not to be taken in a limiting sense. It will be readily understood that the aspects of the present disclosure, as generally described herein, and illustrated in the figures, can be arranged, substituted, combined, and designed in a wide variety of different configurations, all of which are explicitly contemplated and make part of this disclosure.
The present disclosure relates to a propellant grain configuration in rocket motors. In one embodiment, the coaxial, case-bonded, monolithic solid rocket propellant grain comprises a plurality of forward-swept, deep, longitudinal fin cavities circular-patterned about an axial conical and/or cylindrical cavity. It provides significant flexibility in thrust profile tailoring as well as high volumetric loading density.
As illustrated in
In one embodiment, the rocket motor 100 comprises a hollow casing 101 with fore-end 102 and aft-end 103 apertures. In one example, the fore-end aperture 102 may be smaller than the aft-end aperture 103. The casing 101 may be a cylindrical structure with convex end domes and internally insulated with a suitable insulating material. The propellant grain 104 may be cast inside the casing 101 and cured to final shape or machined to final shape. The rocket motor 100 further comprises an igniter (not shown) at the fore-end aperture 102 and a nozzle (not shown) at the aft-end aperture 103.
In one embodiment, the propellant grain 104 comprises the cylindrical cavity or axial through-bore 105 along the longitudinal axis 101a running from the fore-end aperture 102 to the aft-end aperture 103 of the rocket motor 100. In another embodiment, the propellant grain comprises a blind axial cavity opening towards the aft-end aperture. The shape of the central cavity or the blind axial cavity may be at least one of conical, cylindrical or combination of conical and cylindrical shapes. The propellant grain 104 further comprises the plurality of longitudinal hollow fin cavities (hereinafter referred to as “fin”) 106e. The fin 106e is circular-patterned about the longitudinal axis 101a and located near the aft-end aperture 103. The propellant grain 104 further comprises the counter-bore 109 near the aft-end aperture 103 to accommodate the submerged nozzle (not shown) of the rocket motor 100.
As shown in
In one embodiment, the fin 106 is configured with their leading edges (107) making an acute angle at least one of completely 107e, 107i, partly 107f, 107g and tangentially 107h with the forward motor axis 101a. The fin 106e is configured such that the acute angular dimension 114 made by the leading edge 108b with forward motor axis 101a is greater than the angular dimension 115 made by the trailing edge 111 with the forward motor axis 101a. The angular dimensions 108b, 115 made the by leading edge 107e and trailing edge 111 respectively with the forward motor axis 101a is acute (less than 90 degrees) and hence the leading and trailing edges of the fin are termed forward-swept.
The fin 106e is configured with increasing thickness from the tip to root and the maximum size of the fin 106e related to the diameter of the counter-bore 109 and aft-end aperture 103. In one embodiment, the maximum size of the fin 106e is determined such that the diameter of the largest circle inscribed on radial side of the fin 106e is lesser than the diameter of the counter-bore 109 and the aft-end aperture 103 in the motor casing 101. In other embodiment, the forward-swept leading edge 107e of the plurality of fin 106e is configured to form one or more acute angular dimensions with the forward motor axis 101a. The tip-chord 110 is configured to run parallel to local casing insulation.
In another embodiment, as shown in
Also as illustrated in
In one embodiment, the forward-swept leading edge 107e is configured to form one or more angular dimensions with the motor axis 101a including single, double or triple delta fin.
In one embodiment, the present disclosure relates to propellant grain configuration having a plurality of deep longitudinal fin cavities with forward-swept leading edges circular patterned about an axial cavity. The grain configuration provides flexibility to tailor burn surface area regression profiles to meet different performance requirements.
Further, being a finocyl grain configuration it enables high propellant volumetric loading density enabling a compact rocket motor.
The foregoing detailed description has described only a few of the many possible implementations of the present invention. While considerable emphasis has been placed herein on the particular features of this invention, it will be appreciated that various modifications can be made, and that many changes can be made in the preferred embodiments without departing from the principles of the invention. These and other modifications in the nature of the invention or the preferred embodiments will be apparent to those skilled in the art from the disclosure herein, whereby it is to be distinctly understood that the foregoing descriptive matter is to be interpreted merely as illustrative of the invention and not as a limitation.
Number | Date | Country | Kind |
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407/DEL/2015 | Feb 2015 | IN | national |
Filing Document | Filing Date | Country | Kind |
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PCT/IB2015/055027 | 7/3/2015 | WO | 00 |