A COMBINED LAUNCH VEHICLE AND SATELLITE SYSTEM

Abstract

A combined launch vehicle and satellite system relates to the satellite combined with the launch vehicle's upper stage to provide a more efficient system that includes tank separation technology which allows the satellite system to shed tanks that have used up all the propellants stored therein. The method separation of the tank set is enabled by using a merman band or pneumatic type of separation system; wherein the three bottom tanks are emptied first during the process, followed by the separation of the emptied tanks herein the fuel is completely filled in the second set of tanks. The first pair of tanks is then separated after the fuel is emptied. Similarly, the plumbing lines are also separated. The separation of the used components is achieved herein and the satellite is ready for orbit insertion.

Claims

1. A combined launch vehicle and satellite system characterized by: satellite (101); a separation plane (102); a set of propellant tanks (103), another separation plane below (104); a second set of propellant tanks (105); plumbing lines (106) and an engine (107).

2. The combined launch vehicle and satellite system as claimed in claim 1 wherein the said propellant tank is divided into a number of tanks (103, 105) and the plumbing line (106) is implemented in such a way that it does not affect the separation process.

3. The combined launch vehicle and satellite system as claimed in claim 1 wherein the said set of tanks when are emptied it are separated from the main structure which includes the complete combined satellite with upper stage (201).

4. The combined launch vehicle and satellite system as claimed in claim 1 wherein the said bottom tanks (105) are utilized first (202).

5. The combined launch vehicle and satellite system as claimed in claim 1 wherein the said connections between plumbing lines (106) and tanks are designed with mechanisms to close the plumbing line once the connection is removed.

6. The method of combined launch vehicle and satellite system as claimed in claim 1 wherein plane of separation in the plumbing line is placed at the end of the line away from the emptied propellant tank in order to reduce the mass of plumbing lines being carried during the flight.

7. A method of tank separation technology for combined launch vehicle and satellite is comprising of: stage wise separation of the tanks after usage; bottom tanks (105) are emptied first (202), is separated (204) of the filled tanks (203) wherein the fuel is completely filled (204) and the tanks that are empty (103) are of no use at present; first set of tanks (105) is then separated after the fuel is emptied (204). fuel is completely filled (103) and the tanks that are empty is of no use at present; the plumbing lines (106) are also separated along-with when the tank is separated; the separation of the used components is achieved herein (205) and the satellite is ready for orbit insertion (206). reduction in mass of the upper stage during flight results in higher DeltaV and thereby helps an optimized trajectory to reach higher orbits and increase the mass of the satellite being carried itself.

8. The method of tank separation technology for combined launch vehicle and satellite as claimed in claim 7 where non-pyro separation mechanism is used to separate the plumbing line from the propellant tanks (103, 105).

9. The method of tank separation technology for combined launch vehicle and satellite as claimed in claim 7 wherein trajectory is developed to provide a short coasting period during the switching from used propellant tanks to the fresh ones.

10. The method of tank separation technology for combined launch vehicle and satellite as claimed in claim 7 wherein after the first separation of tanks the propellant supply to the engine is switched to the existing tanks during the coasting time.

11. The method of tank separation technology for combined launch vehicle and satellite as claimed in claim 7 wherein the said separation of the tank set is enabled by using a merman band or pneumatic type of separation system.

12. The method of tank separation technology for combined launch vehicle and satellite as claimed in claim 7 wherein the said payload has reached a certain altitude, all used propellant tanks are separated from the primary payload, and the payload is further injected into desired orbit.

13. The method of tank separation technology for combined launch vehicle and satellite as claimed in claim 7 wherein the said separating of the spent propellant tank from the ongoing stage achieves a significant payload carrying capacity gain which is achieved by splitting the propellant tank to multiple tanks and arranging them in such a way that it could be separated out once spent.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0026] So that the manner in which the above recited features of the present invention are understood in detail, a more particular description of the invention, briefly summarized above, may be had by reference to embodiments, some of which are illustrated in the appended drawings. It is to be noted, however, that the appended drawings illustrate only typical embodiments of this invention and are therefore not to be considered limiting of its scope, for the invention may admit to other equally effective embodiments.

[0027] FIG. 1 illustrates the combined launch vehicle satellite system of the present invention;

[0028] FIG. 2 is a flowchart illustrating the method/process of the tank separation technology of satellite launch of the present invention;

[0029] FIG. 3 Payload mass achieved for 700 km altitude and orbital altitude achieved for 100 kg payload for different numbers of tank separations in accordance to the present invention;

[0030] FIG. 4 upper stage (stage 2) mass depletion for 1 tank separation (1st set of propellant tank separation) with respect to flight time in accordance to the present invention;

[0031] FIG. 5 upper stage (stage 2) mass depletion for 2 tank separation (2 sets of propellant tanks separated one after the other) with respect to flight time in accordance to the present invention;

[0032] FIG. 6: upper stage (stage 2) mass depletion for 3 tank separation (3 sets of propellant tanks separated one after the other) with respect to flight time in accordance to the present invention;

[0033] FIG. 7: upper stage (stage 2) mass depletion for 4 tank separation (4 sets of propellant tanks separated one after the other) with respect to flight time in accordance to the present invention;

[0034] FIG. 8: upper stage (stage 2) mass depletion for 5 tank separation (5 sets of propellant tanks separated one after the other) with respect to flight time in accordance to the present invention;

REFERENCE NUMERALS

FIG. 1

[0035] Satellite (101) [0036] Separation plane (102, 104) [0037] Propellant tanks set 1 and set 2 (103, 105) [0038] Plumbing lines (106) [0039] Engine (107)

FIG. 2

[0040] Satellite fused with upper stage (201) [0041] set 1 tanks getting emptied (202) [0042] Separation of emptied tanks (203) [0043] set 2 tanks propellent being used (204) [0044] Tank Separation (205) [0045] Satellite orbit insertion (206)

DETAILED DESCRIPTION OF THE INVENTION

[0046] The following invention disclosure illustrates various embodiments of a work holding device operably configured to hold a workpiece that is to be processed and the method for determining change in clamping force thereof.

[0047] The principles of the present invention and their advantages are best understood by referring to FIG. 1 and FIG. 2. In the following detailed description of illustrative or exemplary embodiments of the disclosure, specific embodiments in which the disclosure may be practiced are described in sufficient detail to enable those skilled in the art to practice the disclosed embodiments.

[0048] The following detailed description is, therefore, not to be taken in a limiting sense, and the scope of the present disclosure is defined by the appended claims and equivalents thereof. References within the specification to one embodiment, an embodiment, embodiments, or one or more embodiments are intended to indicate that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the present disclosure.

[0049] FIG. 1 is the illustration of the combined launch vehicle and satellite system of the present invention. In accordance to the present invention, the system includes and is characterized of satellite (101); a separation plane (102); first set of propellant tanks (103), another separation plane below (104); a another set of propellant tanks (105); plumbing lines (106) and an engine (107).

[0050] FIG. 2 is a flowchart illustrating a process of the entire launch system wherein the process involves stage wise separation of the tanks after usage and is explained in each of the embodiment below:

[0051] In one embodiment of the present invention the propellant tank is divided into a number of tanks (103, 105) and the plumbing line (106) is implemented in such a way that it does not affect the separation process.

[0052] In another embodiment of the present invention wherein once the set of tanks is emptied it is separated from the main structure which includes the complete combined satellite with upper stage (201). The separation of the tank set is enabled by using a merman band or pneumatic type of separation system and FIG. 2 shows the bottom set of tanks (105) in getting emptied condition (202) during the process, followed by the separation of these emptied tanks (203) wherein the fuel is completely utilized and the tanks that are empty are of no use at present. The first set of tanks (103) are then separated after the fuel is emptied (204). Similarly, the plumbing lines (106) are also separated along-with when the tank is separated. The emptied set of tanks (103) and separation of the used components is achieved herein (205) and the satellite is ready for orbit insertion (206). Here, reduction in mass of the upper stage during flight results in higher DeltaV and thereby helps an optimised trajectory to reach higher orbits and increase the mass of the satellite being carried itself, also reducing the overall cost of the launch vehicle manufacturing as well.

[0053] In another embodiment of the present invention the connections between plumbing lines (106) and tanks are designed with mechanisms to close the plumbing line once the connection is removed.

[0054] In accordance with the present invention the non-pyro separation mechanism is used to separate the plumbing line from the propellant tanks (103, 105). The plane of separation in the plumbing line is placed at the end of the line away from the propellant tank in order to reduce the mass of plumbing lines being carried during the flight.

[0055] In another embodiment of the present invention, the trajectory is developed to provide a short coasting period during the switching from used propellant tanks to the fresh ones. After the first separation of tanks the propellant supply to the engine is switched to the existing tanks during the coasting time

[0056] In accordance to the present invention, once the payload has reached a certain altitude, all used propellant tanks are separated from the primary payload, and the payload is further injected into desired orbit. Electrical components including batteries utilized for the separation mechanism are also separated after the separation is achieved.

[0057] In accordance to the present invention it was found that by separating the spent propellant tank from the ongoing stage we can achieve a significant payload gain. This is achieved by splitting the propellant tank to multiple tanks and arrange them in such a way that it could be separated out once spent.

[0058] FIG. 3 illustrates the payload mass that can be taken to 700 km altitude and the orbital altitude that can be achieved for 100 kg payload for different numbers of tank separations.

[0059] From the FIG. 3 we can observe that till separating the two sets of tanks the payload capacity that may be taken is high.

[0060] FIGS. 4,5,6,7, and 8 shows the stage mass depletion with the flight time for the different tank separation case.

[0061] While the foregoing written description of the invention enables one of ordinary skill to make and use what is considered presently to be the best mode thereof those of ordinary skill will understand and appreciate the existence of variations, combinations, and equivalents of the specific embodiment, method, and examples herein. The invention should therefore not be limited by the above described embodiment, method, and examples, but by all embodiments and methods within the scope of the invention as claimed.