The present disclosure relates to the field of space vehicles. More
particularly the present disclosure relates to a locking mechanism for landing legs of the space vehicle.
BACKGROUND
[0002] Background description includes information that may be useful in
understanding the present invention. It is not an admission that any of the
information provided herein is prior art or relevant to the presently claimed
invention, or that any publication specifically or implicitly referenced is prior art.
[0003] Conventionally, hydraulic systems and gravity assisted systems are
used in actuation of landing legs in space vehicles (such as Falcon 9 rocket model). These systems sometimes offer dysfunctional mechanical issues during rocket re-entry in earth's atmosphere. The lack of locking mechanism in the landing legs sometime makes it a tedious task to retract them. Also, sometimes mall functioning of the locking mechanism may compromise the safe landing of the space vehicle.
[0004] There is, therefore, a need of an improved locking mechanism for
landing legs of the space vehicle which is free from above discussed problems.
OBJECTS OF THE PRESENT DISCLOSURE
[0005] Some of the objects of the present disclosure, which at least one
embodiment herein satisfies are as listed herein below.
[0006] It is an object of the present disclosure to provide an assembly
adapted to be configured as a locking mechanism for landing legs of a space
vehicle, which is efficient.
[0007] It is an object of the present disclosure to provide an assembly
adapted to be configured as a locking mechanism for landing legs of a space
vehicle, which is cost effective.

[0008] It is an object of the present disclosure to provide an assembly
adapted to be configured as a locking mechanism for landing legs of a space
vehicle, which is easy to use.
[0009] It is an object of the present disclosure to provide an assembly
adapted to be configured as a locking mechanism for landing legs of a space
vehicle, which requires less maintenance cost.
[0010] It is an object of the present disclosure to provide an assembly
adapted to be configured as a locking mechanism for landing legs of a space
vehicle, which avoids shock loading.
[0011] It is an object of the present disclosure to provide an assembly
adapted to be configured as a locking mechanism for landing legs of a space
vehicle, which is simple and easy to extend.
SUMMARY
[0012] The present disclosure relates to the field of space vehicles. More
particularly the present disclosure relates to a locking mechanism for landing legs of the space vehicle.
[0013] An aspect of the present disclosure pertains to an assembly adapted
to be configured as a locking mechanism for landing legs of a space vehicle. The
assembly includes a first magnet, a motor having a rotor configured with a centre
of the first magnet. The motor is configured to controllably rotate the first magnet
on its axis. A second magnet centrally aligned with the first magnet such that the
unlike poles of the first magnet and the second magnet faces each other. An
electromagnet disposed between the first and second samarium cobalt magnets.
One or more memory alloys having a first end configured below the second
magnet and a second end is coupled with a metal disc. The metal disc is
operatively configured with the legs, and is configured to rotate on its axis.
[0014] In an aspect, the first and second magnets may be samarium cobalt
magnets and are diametrically magnetized.

[0015] In an aspect, the rotation of the first magnet, through the motor,
may facilitate like poles of the first magnet and the second magnet to face each
other.
[0016] In an aspect, like poles facing of the first magnet and the second
magnet may facilitate rotational deformation of the one or more memory alloys
leading to rotation of the metal disc with a pre-defined angle.
[0017] In an aspect, the rotation of the metal disc may facilitate unlocking
of the legs of the space vehicle and allows the legs to expand under gravity.
[0018] In an aspect, the electromagnet may comprise copper.
[0019] In an aspect, the assembly may comprise a hall effect sensor,
operatively configured with the electromagnet, is configured with the first magnet
and the second magnet, and may be configured to measure the magnetic flux
between the first magnet and the second magnet.
[0020] In an aspect, the hall effect sensor may actuate the electromagnet
of the magnetic flux between the first magnet and the second magnet is less than a
pre-defined threshold value.
[0021] In an aspect, the actuated electromagnet may facilitate an
additional magnetic flux between the first magnet and the second magnet.
[0022] Various objects, features, aspects and advantages of the inventive
subject matter will become more apparent from the following detailed description
of preferred embodiments, along with the accompanying drawing figures in which
like numerals represent like components.
BRIEF DESCRIPTION OF DRAWINGS
[0023] The accompanying drawings are included to provide a further
understanding of the present disclosure, and are incorporated in and constitute a part of this specification. The drawings illustrate exemplary embodiments of the present disclosure and, together with the description, serve to explain the principles of the present disclosure. The diagrams are for illustration only, which thus is not a limitation of the present disclosure.

[0024] In the figures, similar components and/or features may have the
same reference label. Further, various components of the same type may be distinguished by following the reference label with a second label that distinguishes among the similar components. If only the first reference label is used in the specification, the description is applicable to any one of the similar components having the same first reference label irrespective of the second reference label.
[0025] FIG. 1A-B illustrates exemplary representation of memory alloy
assembly, in accordance with an embodiment of the present disclosure.
[0026] FIG. 2 illustrates exemplary representation of the memory alloy
assembly integrated with a space vehicle, in accordance with an embodiment of the present disclosure.
DETAILED DESCRIPTION
[0027] The following is a detailed description of embodiments of the
disclosure depicted in the accompanying drawings. The embodiments are in such detail as to clearly communicate the disclosure. However, the amount of detail offered is not intended to limit the anticipated variations of embodiments; on the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the scope of the present disclosure as defined by the appended claims.
[0028] In the following description, numerous specific details are set forth
in order to provide a thorough understanding of embodiments of the present
invention. It will be apparent to one skilled in the art that embodiments of the
present invention may be practiced without some of these specific details.
[0029] The present disclosure relates to the field of space vehicles. More
particularly the present disclosure relates to a locking mechanism for landing legs of the space vehicle.
[0030] The present disclosure elaborates upon an assembly adapted to be
configured as a locking mechanism for landing legs of a space vehicle. The

of the first magnet. The motor is configured to controllably rotate the first magnet
on its axis. A second magnet centrally aligned with the first magnet such that the
unlike poles of the first magnet and the second magnet faces each other. An
electromagnet positioned between the first and second samarium cobalt magnets.
One or more memory alloys having a first end configured below the second
magnet and a second end is coupled with a metal disc. The metal disc is
operatively configured with the legs, and is configured to rotate on its axis.
[0031] In an embodiment, the first and second magnets can be samarium
cobalt magnets and are diametrically magnetized.
[0032] In an embodiment, the rotation of the first magnet, through the
motor, can facilitate like poles of the first magnet and the second magnet to face
each other due to magnetic flux between the first magnet and the second magnet.
[0033] In an embodiment, like poles facing of the first magnet and the
second magnet can facilitate rotational deformation of the one or more memory
alloys leading to rotation of the metal disc with a pre-defined angle.
[0034] In an embodiment, the rotation of the metal disc can facilitate
unlocking of the legs of the space vehicle and allows the legs to expand under
gravity.
[0035] In an embodiment, the electromagnet can comprise copper.
[0036] In an embodiment, the assembly can comprise a hall effect sensor,
operatively configure with the electromagnet, is configured with the first magnet
and the second magnet, and can be configured to measure the magnetic flux
between the first magnet and the second magnet.
[0037] In an embodiment, the hall effect sensor can actuate the
electromagnet of the magnetic flux between the first magnet and the second
magnet is less than a pre-defined threshold value.
[0038] In an embodiment, the actuated electromagnet can facilitate an
additional magnetic flux between the first magnet and the second magnet.
[0039] FIG. 1A-B illustrates exemplary representation of memory alloy
assembly, in accordance with an embodiment of the present disclosure.

[0040] FIG. 2 illustrates exemplary representation of the memory alloy
assembly integrated with a space vehicle, in accordance with an embodiment of the present disclosure.
[0041] As illustrated, an assembly 100 adapted to be configured as a
locking mechanism for landing legs 202-1, 202-2..202-n (collectively referred as landing legs and individually referred as landing leg 202) of a space vehicle 200. The assembly 100 can include a first magnet 102 and a second magnet 104. The first and second magnets (102, 104) can be samarium cobalt magnets and can be diametrically magnetized. Each of the first magnet 102 and the second magnet 104 can have a magnetic field strength between 0.4-0.8 Tesla. The first magnet 102 and the second magnet 104 can be centrally aligned such that unlike poles of the first magnet 102 and the second magnet 104 faces each other thereby cancelling any amount of magnetic flux between the first magnet 102 and the second magnet 104. A motor 112 having a rotor configured with a centre of the first magnet 102. The motor 112 can be configured to controllably rotate the first magnet on its axis. An electromagnet 106 can be disposed between the first and second samarium cobalt magnets. The electromagnet 106 can be but not limited to a copper electromagnet.
[0042] In an embodiment, cylindrically shaped one or more memory
alloys 108 having a first end 108-1 configured below the second magnet 104 and a second end 108-2 can be mechanically coupled with a metal disc 110. The metal disc 110 can be operatively configured with the legs of the space vehicle, and can be configured to rotate on its axis. The metal disc can be connected to an inner lateral surface of the space vehicle and its rotation can cause the opening of the lock which is present on an outer lateral surface of the vehicle. The one or more memory alloys can include but not limited to nickel manganese gallium (NiMnGa). Once the space vehicle wants to open the landing legs (such as re¬entering the earth), the motor can be triggered to rotate its rotor with a pre-defined amount. The rotation of the rotor can facilitate rotation of the first magnet 102. This can facilitate like poles of the first magnet 102 and the second magnet 104 to face each other due to magnetic flux caused between the first magnet 102 and the

second magnet 104. The like pole facing 104 of the first magnet 102 and the
second magnet can facilitate rotational deformation (FIG. IB) of the one or more
memory alloys 108, which can induce a rotational force on the metal disc 110 and
thereby the metal disc 110 can be rotated by a pre-defined angle. The pre-defined
angle of rotation of the metal disc 110 can be between 70-100 degrees.
[0043] In an embodiment, the rotation of the metal disc 110 can facilitate
unlocking of the legs of the space vehicle which can allow the legs to expand under the effect of gravity. The assembly 100 can comprise a hall effect sensor (not shown). The hall effect sensor can be operatively configured with the electromagnet 106, the first magnet 102, and the second magnet 104. The hall effect sensor can be configured to measure a magnetic flux between the first magnet 102 and the second magnet 104. The hall effect sensor can actuate the electromagnet 106 if the magnetic flux between the first magnet 102 and the second magnet 104 is less than a pre-defined threshold value. The pre-defined threshold value of the magnetic flux between the first magnet 102 and the second magnet can be between 0.8-1.6 Tesla. The actuated electromagnet 110 can facilitate an additional magnetic flux, to meet the pre-defined threshold value, between the first magnet 102 and the second magnet 104 to facilitate a required rotation of the metal disc 110 which could not be possible if the magnetic flux between the first magnet and the second magnet was less than the pre-defined threshold value.
[0044] Moreover, in interpreting the specification, all terms should be
interpreted in the broadest possible manner consistent with the context. In particular, the terms "comprises" and "comprising" should be interpreted as referring to elements, components, or steps in a non-exclusive manner, indicating that the referenced elements, components, or steps may be present, or utilized, or combined with other elements, components, or steps that are not expressly referenced. Where the specification claims refer to at least one of something selected from the group consisting of A, B, C ....and N, the text should be interpreted as requiring only one element from the group, not A plus N, or B plus N, etc.

[0045] While the foregoing describes various embodiments of the
invention, other and further embodiments of the invention may be devised without departing from the basic scope thereof. The scope of the invention is determined by the claims that follow. The invention is not limited to the described embodiments, versions or examples, which are included to enable a person having ordinary skill in the art to make and use the invention when combined with information and knowledge available to the person having ordinary skill in the art.
ADVANTAGES OF THE INVENTION
[0046] The proposed invention provides an assembly adapted to be
configured as a locking mechanism for landing legs of a space vehicle, which is
efficient.
[0047] The proposed invention provides an assembly adapted to be
configured as a locking mechanism for landing legs of a space vehicle, which is
cost effective.
[0048] The proposed invention provides an assembly adapted to be
configured as a locking mechanism for landing legs of a space vehicle, which is
easy to use.
[0049] The proposed invention provides an assembly adapted to be
configured as a locking mechanism for landing legs of a space vehicle, which
requires less maintenance cost.
[0050] The proposed invention provides an assembly adapted to be
configured as a locking mechanism for landing legs of a space vehicle, which
avoids shock loading.
[0051] The proposed invention provides an assembly adapted to be
configured as a locking mechanism for landing legs of a space vehicle, which is
simple and easy to extend.

We Claim:

1. An assembly adapted to be configured as a locking mechanism for landing
legs of a space vehicle, the assembly comprising:
a first magnet;
a motor having a rotor configured with a centre of the first magnet, wherein the motor is configured to controllably rotate the first magnet on its axis;
a second magnet centrally aligned with the first magnet such that unlike poles of the first magnet and the second magnet faces each other;
an electromagnet disposed between the first and second samarium cobalt magnets;
one or more memory alloys having a first end configured below the second magnet and a second end is coupled with a metal disc, wherein the metal disc is operatively configured with the legs, and is configured to rotate on its axis.
2. The assembly as claimed in claim 1, wherein the first and second magnets are samarium cobalt magnets and are diametrically magnetized.
3. The assembly as claimed in claim 1, wherein the rotation of the first magnet, through the motor, facilitates like poles of the first magnet and the second magnet to face each.
4. The assembly as claimed in claim 3, wherein the facing of the like poles of the first magnet and the second magnet facilitates rotational deformation of the one or more memory alloys leading to rotation of the metal disc with a pre-defined angle.
5. The assembly as claimed in claim 4, wherein the rotation of the metal disc facilitates unlocking of the legs of the space vehicle and allows the legs to expand under gravity.
6. The assembly as claimed in claim 1, wherein the electromagnet comprises copper.

7. The assembly as claimed in claim 1, wherein the assembly comprise a hall effect sensor, operatively configure with the electromagnet, is configured with the first magnet and the second magnet, and is configured to measure the magnetic flux between the first magnet and the second magnet.
8. The assembly as claimed in claim 7, wherein the hall effect sensor actuates the electromagnet of the magnetic flux between the first magnet and the second magnet is less than a pre-defined threshold value.
9. The assembly as claimed in claim 8, wherein the actuated electromagnet facilitates an additional magnetic flux between the first magnet and the second magnet.