PatSeer

CANSAT CONTAINING CONTAINER AND GLIDER FOR MEASURING ATMOSPHERIC CONDITIONS�
Pub. No. IN201611010075A
App. No. IN201611010075
App. No. Original IN201611010075
Appl. Date 22-Mar-2016
Pub. Date 26-Jan-2018
Inventor(s) DR PARAS CHAWLA, DR, MS SUKHDEEP KAUR, MR AKASH MITTAL, MR HARMANDEEP, MR LAKHANPAL SINGH, MS EKNOOR KAUR, MR KARAN GARG, MR HITESH VOHRA, MR UDISH KAPOOR, MR GAURAV SARIN, MR NAVPREET SINGH
Assignee Norm. CHANDIGARH GROUP OF COLLEGES CGC (LANDRAN KHARAR BANUR HIGHWAY SECTOR 112 LANDRAN SAHIBZADA AJIT SINGH NAGAR PUNJAB 140307 PUNJAB INDIA, IN)
Current Assignee CHANDIGARH GROUP OF COLLEGES CGC (LANDRAN KHARAR BANUR HIGHWAY SECTOR 112 LANDRAN SAHIBZADA AJIT SINGH NAGAR PUNJAB 140307 PUNJAB INDIA, IN)
Current Owner CHANDIGARH GROUP OF COLLEGES CGC
IPC G01W1/00
ABSTRACT
There is provided a CanSat system for measuring atmospheric conditions, system comprising: a glider, comprising at least one sensor for measuring at least one atmospheric condition, wherein said glider is operable to follow a helical descent path; and a container, comprising a spring loaded release mechanism operable for programmed release of said glider.

CLAIMS

1. A CanSat system for measuring atmospheric conditions, system comprising: a) a glider, comprising at least one sensor for measuring at least one atmospheric condition, wherein said glider is operable to follow a helical descent path; and b) a container, comprising a spring loaded release mechanism operable for programmed release of said glider.

2. A system as claimed in claim 1, wherein said container further comprises a parachute attached to an outer surface of said container.

3. A system as claimed in claim 1, wherein said container further comprises a control module operable to initiate programmed release of said glider and to initiate deployment of said parachute.

4. A system as claimed in claim 1, wherein said spring loaded mechanism for programmed release of said glider comprises a spring in compressed condition, held by a spring release rod.

5. A system as claimed in claim 1, wherein said spring loaded release mechanism is operated via a normal release mechanism or a forced release mechanism.

6. A spring loaded mechanism as claimed in claim 5, wherein said normal release mechanism is configured to trigger autonomous release of said glider.

7. A spring loaded mechanism as claimed in claim 5, wherein said forced release mechanism is configured to release the glider in event of failure of said autonomous release.

8. A system as claimed in claim 1, wherein said glider comprises a wing assembly arrangement attached to an outer surface of said glider, wherein wings are made of strong flexible material.

9. A system as claimed in claim 1, wherein said at least one sensor of said glider is selected from a group of altitude sensors, image sensors, magnetometers, pitot tubes, temperature sensors, pressure sensors, humidity sensors or a combination thereof.

10. A system as claimed in claim 1, wherein said glider comprises a communication module, wherein said communication module is operable to send signals to said control module for programmed release of said glider and to receive data from said at least one sensor.


DESCRIPTION
























FIELD OF THE INVENTION

The present invention in general relates to CanSat system for space that is used to make measurements of atmospheric conditions. More particularly, the present invention relates to CanSat system which is composed of two primary components, glider used for measuring atmospheric conditions and the container used in the system to protect the glider from atmospheric conditions at high altitudes.

BACKGROUND OF THE INVENTION

In today's environment, the flight crew has limited access to tactically relevant atmospheric information needed to improve efficiency and safety of flight operations. Most of the information that is available is strategic in nature (long range forecasts covering large areas). This approach tends to be overly restrictive and conservative due the dynamic behavior of the atmosphere. The flight crew also has access to turbulence reports from other aircraft that have been reported to the air traffic control system. At the other extreme are turbulence and windshear warning systems that literally provide last second warnings.

New communications channels are being introduced into service that provides higher bandwidth at potentially lower costs. This allows more weather data to be transmitted between the aircraft to the operations center. More complete or detailed data from airborne sensors can be collected and transmitted to the operations center. More complex weather information can be provided in return to the aircraft. These higher bandwidth channels support the delivery of graphical weather information to the aircraft in addition to, or instead of, the current text-based weather data.

In a published WIPO application WO1993002919 A1 there is described a recoverable airborne instrument module (100) is implemented using a delta wing airframe (301) with a controllable rudder (310). The recoverable instrument module (301) is carried aloft by balloon (102) to enable its instrument package payload to perform a series of meteorologial measurements. A navigation circuit (211, 212) contained within the housing (301) references the radio frequency transmissions of a plurality of beacons to determine the altitude and geographic position of the instrument package (100). This information, as well as data identifying the location of at least one predetermined landing site is used to dynamically calculate a flight path.

In a US patent US6977608 B1 there is disclosed an airborne network system (ANS) on a member aircraft receives incoming geo-referenced atmospheric data regarding atmospheric conditions from other member aircraft and can re-transmit the data to other members. An air data system senses local pressure and temperature conditions. A navigation system calculates geo-referenced aircraft position. An inertial data system senses member aircraft attitude, angular rates and accelerations. A data processing system (DPS) generates the member aircraft's perspective of the atmospheric conditions, based on input data from the above-mentioned systems.

In another US patent US6667710 there is disclosed a system, a method, and a computer program product for generating various weather radar images. A weather radar display system includes a database, a display, and a display processor coupled to the database and the display.

Therefore, in light of the foregoing discussion, there exists a need for an easy to operate and compact CanSet system for measuring atmospheric conditions.

OBJECT OF THE INVENTION

The principal object of the present invention is to provide a CanSat system with glider for measuring atmospheric conditions.

An object of the present invention is to provide a CanSat system with an autonomous release mechanism for the glider at a particular height.

Another object of the present invention is to provide a CanSat system operable of being used a miniature satellite by launching the system in atmosphere of a planet through a space vehicle, plane or a rocket.

The foregoing and other objects, features and advantages of the present invention will become readily apparent upon further review of the following detailed description of the preferred embodiment as illustrated in the accompanying drawings.

SUMMARY OF THE INVENTION

The present invention seeks to provide a CanSat system for measuring atmospheric conditions.

In one aspect, an embodiment of the present invention provides a CanSet system including a glider, having at least one sensor, wherein the glider is operable to follow a helical descent path; and a container, having a spring loaded release mechanism operable for programmed release of the glider.

In another aspect, an embodiment of the present invention provides a container having a spring loaded release mechanism for programmed release of a glider.

In yet another aspect, an embodiment of the present invention provides a glider having a wing assembly arrangement and at least one sensor for measuring at least one atmospheric condition.

Embodiments of the present disclosure substantially eliminate or at least partially address the aforementioned problems in the prior art, and provide a compact CanSet system which is easy to release and operable to cover a maximum testing volume.

Additional aspects, advantages, features and objects of the present disclosure would be made apparent from the drawings and the detailed description of the illustrative embodiments construed in conjunction with the appended claims that follow.

It will be appreciated that features of the present disclosure are susceptible to being combined in various combinations without departing from the scope of the present disclosure as defined by the appended claims.

BRIEF DESCRIPTION OF THE DRAWINGS

The summary above, as well as the following detailed description of illustrative embodiments, is better understood when read in conjunction with the appended drawings. For the purpose of illustrating the present disclosure, exemplary constructions of the disclosure are shown in the drawings. However, the present disclosure is not limited to specific instrumentalities disclosed herein. Moreover, those in the art will understand that the drawings are not to scale. Wherever possible, like elements have been indicated by identical numbers.

Embodiments of the present disclosure will now be described, by way of example only, with reference to the following diagrams wherein:

FIG. 1 illustrates a perspective view of a glider, in accordance with an embodiment of the present invention;

FIG. 2 illustrates a perspective view of a container for holding the glider, in accordance with an embodiment of the present invention;

FIG. 3 illustrates a perspective view of a spring loaded release mechanism in the container, in accordance with an embodiment of the present invention;

FIG. 4 illustrates a perspective view of the container containing the glider, in accordance with an embodiment of the present invention;

FIG. 5 illustrates an exploded view of the glider, in accordance with an embodiment of the present invention; and

FIG. 6 illustrates a perspective view of a parachute, in accordance with an embodiment of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

As required, detailed embodiments of the present invention are disclosed herein; however, it is to be understood that the disclosed embodiments are merely exemplary of the invention which may be embodied in various forms. Therefore, specific structural and functional details disclosed herein are not to be interpreted as limiting, but merely as a basis for the claims and as a representative basis for teaching one skilled in the art to variously employ the present invention in virtually any appropriately detailed structure.

Various other objects, advantages, and features of the invention will become more readily apparent to those skilled in the art from the following detailed description when read in conjunction with the accompanying drawings, in which like reference numerals designate like parts throughout the figures thereof.

Modifications to embodiments of the present disclosure described in the foregoing are possible without departing from the scope of the present disclosure as defined by the accompanying claims. Expressions such as “including”, “comprising”, “incorporating”, “have”, “is” used to describe and claim the present disclosure are intended to be construed in a non-exclusive manner, namely allowing for items, components or elements not explicitly described also to be present. Reference to the singular is also to be construed to relate to the plural.

In an aspect, an embodiment of the present disclosure provides a CanSat system for measuring atmospheric conditions, including a glider, having at least one sensor, wherein the glider is operable to follow a helical descent path; and a container, having a spring loaded release mechanism operable for programmed release of the glider.

With reference to the drawings specifically to FIG.1, there is illustrated a perspective view of a glider 01, in accordance with an embodiment of the present invention. The glider 01 includes a hollow space for folded wings, a clamp 04 for mounting a wing frame, a glider head 05, an extrusion 06 for protecting the glider 01 during landing, a image sensor assembly cavity 07, a wheel mounting unit 08 for a glider-container interfacing, a glider tail 09 and a science component 10 for configuring at least one sensor within the glider 01.

With reference to the drawings specifically to FIG.2, there is illustrated a perspective view of a container 02 for holding the glider 01, in accordance with an embodiment of the present invention. The container 02 for holding the glider 01 includes a spring loaded release mechanism 11, at least one transparent component 12 on a container surface 13, and a groove 14 for glider-container interfacing.

With reference to the drawings specifically to FIG.3, there is illustrated a perspective view of a spring loaded release mechanism 11 operable for programmed release of the glider 01, in accordance with an embodiment of the present invention. The spring loaded release mechanism 11 includes a spring 15, a hook 16 for fixing the spring to a base of the container 02, and a screw 17 for holding the spring release rod 18.

With reference to the drawings specifically to FIG.4, there is illustrated a perspective view of the container 02 containing the glider 01, in accordance with an embodiment of the present invention. The glider 01 including a wing frame 19 is configures within the container surface 13 in such a manner that the spring loaded release mechanism 11 is in compressed position for facilitating programmed release of the glider 01 through the groove 14 for glider-container interfacing.

With reference to the drawings specifically to FIG.5, there is illustrated an exploded view of the glider 01, in accordance with an embodiment of the present invention. The glider 01 includes wings 20 elongated on the wing frame 19. The wing frame 19 further includes unfolding mechanism 21 for the wings 01.

With reference to the drawings specifically to FIG.6, there is illustrated a parachute 22, in accordance with an embodiment of the present invention. The parachute 22 includes a plurality of group A cords 23, a central cord 24 and a plurality of group B cords 25.

In an embodiment, the present disclosure provides a CanSat system for measuring atmospheric conditions, including a glider 01, having at least one sensor 10, wherein the glider 10 is operable to follow a helical descent path; and a container 02, having a spring loaded release mechanism 11 operable for programmed release of the glider 01.

In an embodiment, the container 02 of the CanSat system includes the parachute 22 attached to the outer surface 13 of the container 02 for facilitating safe and controlled return of the container 02 after releasing the glider 01 at a specific height in the atmosphere. The parachute 22 further includes the eight group A cords 23 connected to the central cord 24 and the central cord 24 may further connected to the four group B cords 25. The parachute 22 may connected on the outer surface 13 of the container 02 through the four group B cords 25.

In another embodiment, the container 02 containing the glider 01 may include a control module for initiating programmed release of the glider 01 at a specific altitude measured by the altitude sensor 10 and further initiating the deployment of the parachute 22 at the specific altitude after releasing the glider 01 from the container 02.

In yet another embodiment, the spring loaded release mechanism 11 may be a normal release mechanism including the spring 15, the hook 16 for fixing the spring to a base of the container 02, and a screw 17 for holding the spring release rod 18. In this embodiment, the glider 01 including the wings 20 fixed on wing frame 19 placed in the hollow space 04 may be mounted on the spring loaded release mechanism 11 from the glider tail 09. The glider 01 may exert pressure on the spring 15 to keep the release mechanism in compressed position held by the holding rod 17. In this embodiment, the normal release mechanism may be configured to trigger autonomous release of the glider 01.

In yet another embodiment, the spring loaded release mechanism 11 may be a forced release mechanism including the spring 15, the hook 16 for fixing the spring to a base of the container 02, and a screw 17 for holding the spring release rod 18. In this embodiment, the glider 01 including the wings 20 fixed on wing frame 19 placed in the hollow space 04 may be mounted on the spring loaded release mechanism 11 from the glider tail 09. The glider 01 may exert pressure on the spring 15 to keep the release mechanism in compressed position held by the holding rod 18. In this embodiment, the forced release mechanism may be configured to the glider 01 in an event when the glider 01 is not released by the autonomous release of the normal released mechanism from the container.

In an embodiment, at a specific altitude the altitude sensor 10 of the glider 01 send signals to DC motor 17 of the release mechanism 11 to remove the holding rod 18 and release the glider 01 through the wheel assembly 08 placed in the groove 14 for glider-container interfacing.

In another embodiment, the glider 01 may be of aero dynamic shape to provide least drag in its forward motion and it glides only due to the drag provided by the wings 20 in its downward motion. To minimize manufacturing difficulty of wings 20 these may designed without aerofoil shape so provides only drag with minimum lift. In this embodiment, the glider wings may be made of strong and flexible plastic sheet.

In various embodiments, the science component 10 may include a sensor selected from a group of altitude sensors, magnetometers, pitot tubes, temperature sensors, pressure sensors, humidity sensors or a combination thereof.

In yet another embodiment, the science component 10 may further include a communication module to send signals to the control module of the glider 01 for programmed release of the glider 01 from the container. The communication module may also receive data from the at least one sensor 10.

In an exemplary embodiment, the CanSat system for measuring atmospheric conditions includes the glider 01 with altitude sensor 10 for measuring height of the system. The glider 01 is operable to follow a helical descent path. The system further includes the container 02 with the spring loaded release mechanism 11 operable for programmed release the glider 01. The container further includes the parachute 22 attached to an outer surface 13 of the container 02. The container further comprises a control module operable to initiate programmed release of the glider 01 and to initiate deployment of the parachute 22, the spring loaded mechanism for programmed release of the glider 01 comprises the spring 15 in compressed condition, held by the spring release rod 18. The spring loaded release mechanism 11 is operated via a normal release mechanism or a forced release mechanism and the normal release mechanism is configured to trigger autonomous release of the glider 01. Further, the glider includes the wing assembly arrangement 10 attached to glider 01 and the wings are made of strong flexible plastic sheet. The glider 01 may further include at least one sensor 10 selected from the group of magnetometers, pitot tubes, temperature sensors, pressure sensors, humidity sensors or the combination thereof. The glider 01 may further include the communication module, wherein the communication module may be operable to send signals to the control module for programmed release of the glider 01 and to receive data from the at least one sensor 10.



While the disclosure has been presented with respect to certain specific embodiments, it will be appreciated that many modifications and changes may be made by those skilled in the art without departing from the spirit and scope of the disclosure. It is intended, therefore, by the appended claims to cover all such modifications and changes as fall within the true spirit and scope of the disclosure.