Claims:We Claim:
1. A reconfigurable deployer system to eject CubeSats into orbits and perform scientific experiments, comprising:

a container unit configured to accommodate one or more CubeSats and one or more hosted payloads;

one or more deployment springs and a mechanism configured to eject the one or more CubeSats into one or more orbits, the one or more hosted payloads configured to perform one or more scientific experiments in the low earth orbit after ejecting the one or more CubeSats; and

one or more data processing chipsets configured to collect data from the one or more hosted payloads and transmit the collected data to one or more ground stations via a space launch vehicle, whereby the space launch vehicle configured to provide required power for functioning of the one or more hosted payloads.

2. The reconfigurable deployer system of claim 1, wherein the one or more deployment springs are positioned between the one or more CubeSats and the one or more hosted payloads to push the one or more CubeSats in a direction of an outlet of the container unit.

3. The reconfigurable deployer system of claim 1, wherein the one or more hosted payloads remain active until the one or more scientific experiments are complete.

4. The reconfigurable deployer system of claim 1, wherein the container unit is configured to provide a microgravity lab in a form factor and a CubeSat deployer in volume of standard ‘U’ CubeSat configurations.

5. The reconfigurable deployer system of claim 1, wherein the one or more hosted payloads are configured to provide a flight heritage and perform the one or more scientific experiments to achieve required technology readiness level.

6. The reconfigurable deployer system of claim 1, wherein the one or more hosted payloads comprising a volume of 12U deployer has larger and a higher number of configurations.

7. The reconfigurable deployer system of claim 1, wherein the space launch vehicle comprising onboard systems are configured to handle power and telemetry or telecommand requirements.

8. A method for eject CubeSats into orbits and perform scientific experiments, comprising:

providing an orbital spacecraft with a reconfigurable deployer injected into a specified orbit and comprising a cargo area;

integrating one or more hosted payloads with one or more CubeSats in the cargo area of the reconfigurable deployer;

housing the orbital spacecraft in a space launch vehicle to reach the one or more orbits;

ejecting the one or more CubeSats in sequence into the one or more orbits using one or more elements of the reconfigurable deployer, whereby the one or more elements comprising one or more deployment springs and a mechanism;

performing scientific experiments in a low earth orbit by the one or more hosted payloads after ejecting the one or more CubeSats from the reconfigurable deployer;

collecting data from the one or more hosted payloads by one or more data processing chipsets of the reconfigurable deployer; and

transmitting the collected data to one or more ground stations via a space launch vehicle from the one or more data processing chipsets, whereby the space launch vehicle comprising onboard systems configured to handle power and telemetry or telecommand requirements. , Description:TECHNICAL FIELD
[001] The disclosed subject matter relates generally to field of satellites. More particularly, the present disclosure relates to a reconfigurable deployer system and method to eject CubeSats and perform scientific experiments in low earth orbit.

BACKGROUND
[002] Generally, miniature satellites or U-class spacecrafts most popularly referred to as CubeSats perform tasks such as earth observation and space data collection. CubeSats are being developed for scientific experiments in Universities, Government agencies, Research centers, Corporations, Companies, and the like. To deploy a CubeSat or payload in space, a deployer/dispensing device is used to push the CubeSat away from a spacecraft and eject it into the required orbit. The deployer is also used to transport the CubeSats and to secure it to the delivery spacecraft. Current designs in the industry have enhanced the robustness of the P-POD (Poly-Picosatellite Orbital Deployer). The P-POD deployer accommodates a 3U CubeSat, or equivalently, three 1U CubeSats, or one 1U CubeSat and one 2U CubeSat. The current designs by the companies have separated the microgravity lab and deployers. This lack of modularity increases the wait time for the researchers because launch brokers have to fill up the vacant spots in either of the systems to fly.

[003] Deployers are essentially space debris obtained post completion of the deployment process and are deorbited soon after. Existing deployers cannot predict potential space hazards in the LEO (low earth orbit) nor can they model the dynamics and stability of fluids for future manned missions required to study long term effects in the space environment. The existing deployers cannot provide any benefit for technology demonstrations of potential space systems to gain flight heritage. They are also unable to perform operations in the relevant environment to achieve the required Technology Readiness Level (TRL). Thus, there is an unmet need to provide a solution to this technical problem by incorporating modularity, providing functionality to act as both a Lab-in-orbit as well as a CubeSat deployer, all of which need to be incorporated within the volume of standard ‘U’ CubeSat configurations.

[004] In the light of the aforementioned discussion, there exists a need for a certain reconfigurable deployer system that would overcome the above-mentioned challenges.

SUMMARY
[005] The following presents a simplified summary of the disclosure in order to provide a basic understanding of the reader. This summary is not an extensive overview of the disclosure and it does not identify key/critical elements of the invention or delineate the scope of the invention. Its sole purpose is to present some concepts disclosed herein in a simplified form as a prelude to the more detailed description that is presented later.

[006] Exemplary embodiments of the present disclosure are directed towards a reconfigurable deployer system and method to eject CubeSats and perform scientific experiments in a low earth orbit.

[007] An objective of the present disclosure is directed towards a reconfigurable deployer system that provides either the requirement of the deployer or that of a hosted payload platform or combined may be on-demand in a singular or multiple packages of CubeSat(s).

[008] Another objective of the present disclosure is directed towards the reconfigurable deployer system that is beneficial for technology demonstrations of potential space systems to gain flight heritage and perform operations in the relevant environment to achieve the required Technology Readiness Level (TRL).
[009] Another objective of the present disclosure is directed towards the reconfigurable deployer system that enables users to utilize the volume available to analyze specimens or thermophysical property measurements of new materials that could find potential applications in interplanetary missions.

[0010] Another objective of the present disclosure is directed towards the reconfigurable deployer system that represents the evolution of and innovation in the deployer design that would fulfill the demands of the ever-growing satellite industry.

[0011] Another objective of the present disclosure is directed towards the reconfigurable deployer system that provides a rapid solution to the needs of both researchers and CubeSat developers by being readily available to fly more frequently than other deployers available in the market.

[0012] Another objective of the present disclosure is directed towards the reconfigurable deployer system that gives an impact of frequent and optimized flight solutions would greatly enhance the output of as scientific community in the context of microgravity experiments.

[0013] Another objective of the present disclosure is directed towards the reconfigurable deployer system that performs microgravity experiments in low earth orbit significantly benefits the scientific community, especially in the areas of pharmaceutical research and drug development.

[0014] Another objective of the present disclosure is directed towards the reconfigurable deployer system that provides a secure enclosure for CubeSats that may be used to monitor and predict potential space hazards in the low earth orbit.

[0015] Another objective of the present disclosure is directed towards the reconfigurable deployer system that involves modelling the dynamics and stability of fluids for future manned missions to study long term effects in the space environment.
[0016] According to an exemplary aspect of the present disclosure, a reconfigurable deployer system comprising a container unit configured to accommodate one or more CubeSats and one or more hosted payloads.

[0017] According to another exemplary aspect of the present disclosure, the reconfigurable deployer system comprising one or more deployment springs and a mechanism configured to eject the one or more CubeSats into one or more orbits, the one or more hosted payloads configured to perform one or more scientific experiments in the low earth orbit after ejecting the one or more CubeSats.

[0018] According to another exemplary aspect of the present disclosure, the reconfigurable deployer system comprising one or more data processing chipsets configured to collect data from the one or more hosted payloads and transmit the collected data to one or more ground stations via a space launch vehicle, whereby the space launch vehicle configured to provide required power for functioning of the one or more hosted payloads.

BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Other objects and advantages of the present invention will become apparent to those skilled in the art upon reading the following detailed description of the preferred embodiments, in conjunction with the accompanying drawings, wherein like reference numerals have been used to designate like elements, and wherein:

[0020] FIG. 1 is a flowchart depicting a method for ejecting CubeSats into desired orbits and performing scientific experiments by a reconfigurable deployer system, in accordance with one or more exemplary embodiments.

[0021] FIG. 2 is a diagram depicting a schematic representation of a reconfigurable deployer system, in accordance with one or more exemplary embodiments.

[0022] FIG. 3 is a diagram depicting an embodiment of the reconfigurable CubeSat deployer, in accordance with one or more exemplary embodiments.

[0023] FIG. 4 is a diagram depicting another embodiment of the reconfigurable CubeSat deployer, in accordance with one or more exemplary embodiments.

DETAILED DESCRIPTION OF EXAMPLE EMBODIMENTS
[0024] It is to be understood that the present disclosure is not limited in its application to the details of construction and the arrangement of components set forth in the following description or illustrated in the drawings. The present disclosure is capable of other embodiments and of being practiced or of being carried out in various ways. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting.

[0025] The use of “including”, “comprising” or “having” and variations thereof herein is meant to encompass the items listed thereafter and equivalents thereof as well as additional items. The terms “a” and “an” herein do not denote a limitation of quantity, but rather denote the presence of at least one of the referenced item. Further, the use of terms “first”, “second”, and “third”, and so forth, herein do not denote any order, quantity, or importance, but rather are used to distinguish one element from another.

[0026] Referring to FIG. 1 is a flowchart 100 depicting a method for ejecting CubeSats into desired orbits and performing scientific experiments by a reconfigurable deployer system, in accordance with one or more exemplary embodiments. The method 100 may be carried out in any desired environment. Further, the aforementioned definitions may equally apply to the description below.

[0027] The method commences at step 102, providing an orbital spacecraft with a reconfigurable deployer injected into a specified orbit and comprising a cargo area. Thereafter, at step 104, integrating a hosted payload with one or more CubeSats in the cargo area of the reconfigurable deployer. The CubeSats may be a customer’s CubeSats. Thereafter, at step 1006, housing the orbital spacecraft in a space launch vehicle to reach the deployment orbit. Thereafter, at step 1008, ejecting the CubeSats in sequence into a desired orbit using a deployment spring from the reconfigurable deployer. Thereafter, at step 1010, performing scientific experiments in a low earth orbit by the hosted payload after ejecting the CubeSats from the reconfigurable deployer. The scientific experiments may include, but not limited to, experiments in the pharmaceutical research, material sciences or any experiment requiring a microgravity environment, microgravity experiments, and the like. Thereafter, at step 1012, collecting data from the hosted payload by data processing chipsets of the reconfigurable deployer. Thereafter, at step 1014, transmitting the collected data to a ground station via a space launch vehicle’s communication system from the data processing chipsets. Where, the power and telemetry/ telecommand requirements may be handled by the onboard systems (for example, data processing chipsets) on the launch Vehicle. The data processing chipsets may include, but not limited to, field programmable gate array-based system-on-chip microcontrollers, and the like.

[0028] Referring to FIG. 2 is a diagram 200 depicting a schematic representation of a reconfigurable deployer system, in accordance with one or more exemplary embodiments. The reconfigurable deployer system 200 with modularity, and provide the functionality to a CubeSat deployer to act as both a lab-in-orbit as well as the CubeSat deployer, all in that volume of standard ‘U’ CubeSat configurations. The reconfigurable deployer system 200 has the capability to provide a secure housing for any experiments involving pharmaceutical research, material sciences or any experiment requiring a microgravity environment. The Reconfigurable deployer system 200 includes electrical and mechanical interface elements for autonomous operation of the hosted payload. The reconfigurable deployer system 200 may be a 12U reconfigurable deployer. The reconfigurable deployer system 200 may include a container unit 202, a hosted payload 204, deployment springs 206, and an opening or closing unit 208. The container unit 202 may be accommodated therein with CubeSats 210. In an embodiment of the present disclosure, the reconfigurable deployer 300 (shown in FIG. 3) may include a 2U deployer, as well as an on-orbit, the hosted payload 204, or microgravity lab in a form-factor of a 3U deployer (0.5U or 1U or 1.5U or 2U or 3U). In another embodiment of the present disclosure, the reconfigurable deployer system 200 may include the hosted payload volume a 12U deployer (4U configuration-1 or 4U configuration-2 or 6U or 12U) has larger and a higher number of configurations because of the additional volume available within the enclosure.

[0029] The reconfigurable deployer system 200 may be configured to eject the CubeSats 210 into the desired orbit using the deployment springs 206. The deployment mechanism may include, but not limited to, hold down and release mechanism, torsion springs, ejection springs, and the like. The application of the hosted payload 204 volume as an on-orbit lab to perform the scientific experiments in the low earth orbit can significantly benefit the scientific community, especially in the areas of pharmaceutical research and drug development. The reconfigurable deployer system 100 may be configured to provide a secure enclosure for the hosted payload 204 and CubeSats that may be used to monitor and predict potential space hazards in the low earth orbit (for example, space debris, burning heat, radiation, freezing temperature, etc.). The reconfigurable deployer system 100 may also be configured to model the dynamics and stability of fluids for future manned missions to study long term effects in the space environment.

[0030] In accordance with one or more exemplary embodiments of the present disclosure, the hosted payload 204 may be configured to provide benefits for technology demonstrations of potential space stations to gain flight heritage and perform operations in the relevant environment to achieve the required technology readiness level. The reconfigurable deployer system 200 may be configured to enable the users to utilize the volume of the hosted payload 204 to conduct analysis of the specimens or thermophysical property measurements of new materials. The reconfigurable deployer system 100 may include multiple configurations possible for the hosted payload 204 depending on the requirement.

[0031] In accordance with one or more exemplary embodiments of the present disclosure, the deployment springs 206 may be configured to apply force to the CubeSats to push the CubeSats when the CubeSats are separated. The deployment springs 206 may be positioned between the CubeSats and the hosted payload 204 to push the CubeSats in a direction of an outlet of the container unit 202. Due to such an operation of the deployment springs 206, the CubeSats 210 may be separated and deployed from the CubeSat deployer system 100 installed in the orbital spacecraft vehicle in a space, so that the CubeSats may be ejected into a desired orbit.

[0032] In accordance with one or more exemplary embodiments of the present disclosure, a communication device may be provided at an outer side of the reconfigurable deployer system 100 to make communication with Ground Stations. The hosted payload 204 may not be deployed but may stay inside the reconfigurable deployer system 100 atop the space launch vehicle and remain active until the microgravity experiments are complete. The reconfigurable deployer system 100 may include data processing chipsets configured to collect the data from the microgravity lab and transmit the collected data to a ground station via a launch vehicle’s communication device. The power and telemetry/ telecommand requirements may be handled by the onboard systems or data processing chipsets on the space launch vehicle.

[0033] A standardized power interface unit may be mounted to the space launch vehicle. The hosted payload 204 may include a mass of not having more than 2 kg per ‘U’ and an interface may be used to secure the hosted payload 204 to the CubeSat 210.

The following table provides a broad overview of the reconfigurable deployer system 300 parameters and relevant design variables of the reconfigurable deployer.

HOSTED PAYLOAD SPECIFICATIONS

Dimensions Given in Section 2.4
Mass Upto 2 kg per ‘U’

Telemetry/ Telecommand Via Launch Vehicle

[0034] Referring to FIG. 3 is a diagram 300 depicting an embodiment of the reconfigurable CubeSat deployer, in accordance with one or more exemplary embodiments. The embodiment of the reconfigurable CubeSat deployer 300 may include a 2U deployer with the 1U hosted payload 204 and the deployment spring 206.

[0035] Referring to FIG. 4 is a diagram 400 depicting another embodiment of the reconfigurable CubeSat deployer, in accordance with one or more exemplary embodiments. Another embodiment of the reconfigurable CubeSat deployer 400 may include a full 3U deployer configuration. The reconfigurable CubeSat deployer 400 may include the deployment spring 206.

Deployer Size Hosted Payload Volume A(mm) B(mm) C(mm)
3U Deployer

0.5U
1U
1.5U
2U
3U 63.5
113.5
170.2
227
340.5
100
100
100
100
100 100
100
100
100
100
12U Deployer 4U Conf-1
4U
conf-2
6U
8U
12U
227

113.5

366
227
366 200

200

200
200
200 100

200

100
200
200

[0036] In accordance with one or more exemplary embodiments of the present disclosure, the hosted payload 204 may be configured to provide benefits in the scientific community, especially in the areas of pharmaceutical research and drug development. The primary function of the reconfigurable CubeSat deployer system 100 is to eject the CubeSats into the desired orbit using the deployment springs 206. Once the CubeSats have been deployed, the hosted payload 204 may begin initialization and perform the relevant experiments or microgravity experiments in the low earth orbit. The power and telemetry or telecommand requirements may be handled by the onboard systems on the space launch vehicle.

[0037] Reference throughout this specification to “one embodiment”, “an embodiment”, or similar language means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the present disclosure. Thus, appearances of the phrases “in one embodiment”, “in an embodiment” and similar language throughout this specification may, but do not necessarily, all refer to the same embodiment.

[0038] Although the present disclosure has been described in terms of certain preferred embodiments and illustrations thereof, other embodiments and modifications to preferred embodiments may be possible that are within the principles and spirit of the invention. The above descriptions and figures are therefore to be regarded as illustrative and not restrictive.

[0039] Thus the scope of the present disclosure is defined by the appended claims and includes both combinations and sub-combinations of the various features described here in above as well as variations and modifications thereof, which would occur to persons skilled in the art upon reading the foregoing description.