• The invention provides a method for maximizing the regression rate in a hybrid rocket engine. The method comprises of attaching a bluff body to the head end of a combustion chamber of the hybrid rocket engine.
• The regression rate increases by around 2 times at higher Oxidizer Mass Flux (Gox =15 g/cm2s) and around 4 times at lower Gox (3 g/cm2s) for the case when a bluff body is used. This increase in regression rate is due to (a) decrease in the recirculation zone size near the head end and (b) redistribution of mass flux close to the wall
• When the bluff body is used, the oxidizer to fuel ratio is nearly constant and the regression rate obtained with different oxidizer flow rates show almost similar regression rates as it eliminates the effect of the recirculation zone at the head end.
• The increase in regression rate observed with bluff body reduces as the L/D (Ratio of total length to initial port diament of fuel) is increased from 9 to 27. However, it is still higher than the case when no bluff body was used.
• The burn rate variation with length of the hybrid rocket engine is less pronounced when a bluff body is used indicating a lower sliver loss
• The bluff body increases the regression rate even at a port diameter (60 mm) which was four times the initial port diameter (15 mm).

• Present patent describes a discloses an inductive voltage divider type sensor configured for detecting displacement.
• The sensor circuit comprises:
• a sensing part which has an inductive element having a single wound coil over which a contactless wiper is placed to slide laterally for measuring displacement;
• a signal conditioning circuit which has a voltage controlled amplifier to excite the inductive element;
• The disclosed inductive voltage divider type sensor has capability for sensing either unipolar or bipolar displacement. (Refer Fig.1, and Fig.3)
• Further subject invention relates to a displacement sensor that has an inductive voltage divider type sensing unit and a signal conditioning circuit.
• The inductive voltage divider type sensing unit includes an inductive element that has a single wound coil having an axis that terminate at a first end & a second end.
• A contactless wiper is placed at a fixed distance from the axis of the coil and is configured to be displaced laterally in a plane parallel to the axis of the coil. (Refer Fig.2)

Present patent describes a device and method for reducing jet noise using co-axial flat/helix curve vane swirler for various swirl numbers.   

The method comprising the steps of:

• providing for a nozzle;
• providing for a downstream end to discharge engine flow;

• providing for a co-axial vane swirler of a suitable swirl number before the downstream end.

• Generating first and second signals for combustor’s turbulent velocity and acoustic pressure fluctuations.
• Determining phase locked values for signal synchronization.
• Measuring parameters for recurring turbulent velocity fluctuations at each combustor location.
• Determining Hurst exponent values based on first signal.
• Identifying critical region for phase locked values, recurring fluctuations, and Hurst exponent values.
• Injecting micro-jets to suppress thermo-acoustic instabilities.

• Present patent describes a high velocity ballistic device for producing bulk functionally graded materials (FGMs) by impacting projectiles onto a stationery target, the device comprises of
• three tubes
• a high-pressure tube (HPT), a   pump tube (PT) and a launch   tube (LT);’
• a piston;
• two diaphragms separating the junctions between the three tubes (HPT, PT, and LT);and
• a means to pressurize the high-pressure tube. (Refer Fig.2)
• The velocity of the projectile is controlled by the pressure of air in the high-pressure tube & the diaphragm material & their total thickness.

Operation

• During the pressure inside the high-pressure tube reaches a critical value, the first diaphragm between HPT & PT  gets ruptured, pushing the piston forward which develops a very high pressure inside the PT that causes the second diaphragm to rupture, the projectile kept in the LT, just after the second diaphragm, gets accelerated & exits the launch tube at a high velocity to impact the stationary placed at a distance.

Solar Array for Rotatable Objects:

• Composed of a flexible sheet with solar cells on its surface.
• Deployment assembly includes links with distal and proximal ends.
• Fixed link ends fixed to the rotatable object.
• The distal end of movable link coupled with adjacent link’s proximal end via pivot joint.
• Flexible sheet’s periphery coupled with movable link’s distal end.
• Deployment assembly allows pivotal rotation of movable link to deploy sheet due to centrifugal force.

• Tilted Rotor Axes for Minimal Air Interaction: The quadcopter’s frame design includes longitudinal members with motor mounts that tilt the rotor axes toward the central axis, reducing air column interaction and improving stability.
• Wedge-shaped or Inclined Motor Mounts: The motor mounts, which can be wedge-shaped or inclined plane devices, are set at a predetermined angle (5°-25°) to achieve minimal air column overlap and maintain low vibration amplitude (0.1 g or less).
• Configurable and Modular Design: The quadcopter can feature four, six, or eight longitudinal members, with overlapping rotors (0-35%) to optimize space and performance, and includes components like ESC units, communication units, and landing gear for comprehensive functionality.

Present patent describes a discloses an inductive voltage divider type sensor configured for detecting displacement.

The sensor circuit comprises:

• The disclosed inductive voltage divider type sensor has capability for sensing either unipolar or bipolar displacement. (Refer Fig.1, and Fig.3)
• Further subject invention relates to a displacement sensor that has an inductive voltage divider type sensing unit and a signal conditioning circuit.
• The inductive voltage divider type sensing unit includes an inductive element that has a single wound coil having an axis that terminate at a first end & a second end.
• A contactless wiper is placed at a fixed distance from the axis of the coil and is configured to be displaced laterally in a plane parallel to the axis of the coil. (Refer Fig.2)

• Present patent describes a device and method for reducing jet noise using co-axial flat/helix curve vane swirler for various swirl numbers.   
• The method comprising the steps of:

• A jet noise suppressor in a jet engine having a jet center longitudinal axis, comprising of :
• a nozzle, a downstream end to discharge engine flow and a co-axial vane swirler of a suitable swirl number before the downstream end, wherein the swirl number (S) may be determined by the equation.
• The number of vanes may be six and or less than or more than six.

• Utilizes jet impingement cooling system.
• Includes structurally supported impingement inserts and holes/impingement tubes for cooling the leading edge.
• Cooled air from a chamber passes through the tubes, while hot gases pass through the trailing edge.
• A chamfer is made at the exit of the tubes, ensuring uniformity and extension in cooling coverage.
• 3-D hemispherical protrusions are disposed at the inner wall of the leading edge for further heat transfer enhancement.

Optimized Tooth Design:

• The invention introduces a unique tooth design for the primary core, featuring protrusions arranged in a curved profile with a convex shape.

Gradual Flux Distribution:

• The protrusions on the tooth allow for a gradual distribution of the magnetic flux, reducing abrupt drops in flux density at the end portion of the primary core.

Cubic Spline Formulation:

• The outer protrusion of the tooth is formed using a cubic spline, enhancing the smoothness of the flux distribution and optimizing magnetic field strength.

Improved Thrust Characteristics:

• By mitigating end-effects and facilitating a more uniform flux distribution, the invention leads to a notable increase in linear thrust generated by the linear induction motor.

Simplicity and Reliability:

• Unlike complex solutions involving additional components, this technology provides a straightforward approach to enhancing LIM performance without introducing unnecessary complexity.

Application Versatility:

• The improved LIM design can find applications in various fields such as magnetic levitation, linear propulsion, and transportation systems, offering efficiency and reliability benefits.

• Present invention describes a multi-rotor aerial vehicle. (Refer Fig.1)
• Said Vehicle includes a frame having an axis & housing a control unit, a plurality of rotors affixed to the frame, each driven by a drive motor & a foldable landing gear.
• Said gear comprising a plurality of legs which are placed beneath the frame, each leg having a length & a control mass at the end thereof & pivotably attached to the frame via a control motor.
• Each control motor is configured to vary the angle of folding of the leg & move the control mass either inward toward the aerial vehicle axis or outward away from the axis under instruction from the control unit to adjust attitude of the aerial vehicle by varying the center of gravity (CoG) of the aerial vehicle.
• Each control motor is configured to vary the angle of folding of the leg & move the control mass either inward toward the aerial vehicle axis or outward away from the axis under instruction from the control unit to adjust attitude of the aerial vehicle by varying the CoG of the aerial vehicle.
• The drive motors are controlled using PID control logic.
• Further, a method for controlling the attitude & position of the aerial vehicle through variation of center of gravity (CoG) by moving the control masses is disclosed.

• A lift separation sabot for kinetic energy projectiles, comprising
• A sabot using additional lifting surface (lift separation) close to the center of gravity to reduce the rotation of the sabot ensuring less mechanical contact between the projectile and the sabot.
• Thereby improving the accuracy of the ammunition wherein the pressurization of the cavity under the center band using high speed free stream flow achieves lift separation in the kinetic energy projectiles.
• From the figure 3 the distance (24) between center of gravity (21) and center of pressure(22) inside the annular cavity is very less compared to a conventional sabot.
• Aerodynamic force acts on the outer circumference which leads to less moment arm wherein the pressure acts on the aerodynamic surfaces is equal to a stagnation pressure behind a normal shock due to the hypersonic speed of the assembly.

• qThe sabot projectile assembly consists of three 120-degree sector sabots and a projectile and fin.

Two-stage design:

• Utilizes a two-stage gas gun mechanism for firing projectiles at high velocities, enhancing efficiency and control.

Pneumatic reservoir:

• Charges with high-pressure air to propel projectiles, providing a safer alternative to explosives.

Diaphragm rupture:

• Controlled diaphragm rupture at predetermined pressure levels enables precise propulsion of projectiles.

Pneumatic actuator:

• Regulates airflow between primary and secondary chambers, ensuring controlled acceleration of projectiles.

Use of light gases:

• Utilizes light gases like hydrogen, helium, or atmospheric air as working fluids, optimizing efficiency and safety in ballistic testing.

• Present invention describes an additive wall mounted pressurized spray/jet system for cooling intricate parts in rotating systems & engines.
• Said additive wall mounted pressurized spray/jet system comprises:
• plummer blocks, main shaft, side lid of driven unit, bearing holder & housing for driven unit, ring plate, disc assembly, middle housing, driven unit side bearings, drive side bearings, drive housing, shower heads, locknut, drive side lid, motor assembly and lube supply assembly including other associated parts.
• The system significantly increases the ability of cooling a shower head which force cools the components of a rotating system or engine.
• The system combines the pressurized lubrication system with a splash system with incorporating additional flow features on the housing components, which will reduce the heat generation & increase the life of all critical components of rotating system. (Refer the figure)

Variable Aspect Ratio Design:

• The invention introduces a swirler with a varying aspect ratio from entry to exit, allowing control over axial, tangential, and crucially, radial velocity components, enhancing fuel-air mixing.

Sheet Cutter:

• The design incorporates sheet breakers at the swirler exit, disrupting liquid sheets into ligaments and droplets, facilitating finer atomization even at lower injection pressures.

Improved Flow Guidance:

• The swirler’s smooth nozzle shape with a variable flow area guides the flow effectively, resulting in higher exit velocity components, contributing to enhanced combustion efficiency.

Enhanced Spray Characteristics:

• Flexibility to adapt trust computation to specific security requirements.

Adaptability in Design:

• The invention allows for flexibility in implementing the variable aspect ratio design on either the hub or tip side of the swirler, providing versatility to suit specific combustor requirements.

Rotating Spindle Mechanism:

• Utilizes a rotating spindle, powered by an external source, to eliminate air core formation and create a thin swirling liquid film.

Tangential Velocity Impartation:

• The rotating spindle imparts a tangential velocity to the fluid, facilitating the generation of a swirling flow for thinner liquid sheets and finer droplets.

Vane-Induced Turbulence:

• Mounted vanes induce turbulence in the flow, aiding in the early breakup of droplets and enhancing atomization.

Serrated Divergence at Exit Pipe:

• Features serrated divergence at the exit pipe, introducing controlled disturbances for early liquid sheet breakup and smaller droplet formation.

Combined Swirl and Rotary Atomization:

• Integrates elements of both swirl and rotary atomizers, offering a compact design, fine atomization at lower pressures, and improved control over droplet size and dispersion.