BACKGROUND OF THE INVENTION
Birds have always been aerodynamically efficient. Through examining the shape of bird wings and tails, we have been able to learn how they maintain flight. In ways, we have created our own versions of these wings or tails so we can achieve flight with our aircrafts. The main forces that act on an aircraft are lift and drag. Lift sustains an aircraft in the air while drag pushes against the aircraft as a consequence of the aircraft moving forward. There have been different methodologies in reducing drag and increasing lift on aircraft by changing the shape of the wings and tails. However, in the case of tails, forces on an aircraft can be affected by also changing the location of them.
This invention is to be applied in the field of fluid mechanics. This invention targets making a vehicle or object more streamlined and therefore reducing drag and increasing stability. An aircraft produces less drag if the tail is moved further back. This entails the tail's root trailing edge being at the back or behind the fuselage. The less drag an aircraft produces, the more stable it becomes. As the tail's root leading edge moves further away after the nose of the aircraft, the aircraft can produce less drag and becomes more stable.
BRIEF SUMMARY OF THE INVENTION
Most vehicles and objects that consist of tails, have them being positioned towards the back. However, this invention promotes moving the tail further back and as far as it can go to become more streamlined. By moving the tail's root leading edge back, it reduces drag.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1A—FIG. 1A displays the front view of the aircraft. FIG. 1A displays the number 1 pointing to one out of two horizontal tails on the aircraft whose root trailing edge is even to the fuselage trailing edge. The number 2 is pointing to the area where the vertical tail's root trailing edge originate from, which is at the trailing edge of the fuselage.
FIG. 1B—FIG. 1B displays the top view of the aircraft. FIG. 1B displays the number 3 pointing to the area where the horizontal and vertical tails' root trailing edge, referenced in FIG. 1A, attach to the trailing edge of the fuselage. The number 3 in FIG. 1B denotes the top view of the tails that are denoted as number 1 and number 2 in FIG. 1A. The curve line with two slanted lines intersecting its middle on the left wing or left side of the figure denotes the end point of interest of the aircraft.
FIG. 1C—FIG. 1C displays the side view of the aircraft. FIG. 1C displays the number 4 pointing to the vertical tail root trailing edge being even with the trailing edge of the fuselage. This vertical tail is the side view of the vertical that is denoted in FIG. 1A as number 2. The number 5 is pointing to the area where the root trailing edge of the horizontal tail is located, which is at the trailing edge of the fuselage. The number 5 in FIG. 1C denotes the side view of number 1 in FIG. 1A. The general area that number 4 and 5 point to is the same area denoted as number 3 in FIG. 1B.
FIG. 2A—FIG. 2A displays the front view of the aircraft. FIG. 2A displays the number 6 pointing to one out of two horizontal tails on the aircraft whose root trailing edge is behind the fuselage trailing edge. The number 2 is pointing to the area where the vertical tail's root trailing edge originate from, which is behind the trailing edge of the fuselage.
FIG. 2B—FIG. 2B displays the top view of the aircraft. FIG. 2B displays the number 8 pointing to where the fuselage trailing edge ends. The number 9 in FIG. 2B points to where the horizontal tail trailing edge root ends, which is behind the fuselage trailing edge. This horizonal tail is the same as the horizontal tail denoted as number 6 in FIG. 2A. The number 10 in FIG. 2B points to the root trailing edge of the vertical tail, which is behind the trailing edge of the fuselage. The number 7 in FIG. 2A corresponds to the number 10 in FIG. 2B. The curve line with two slanted lines intersecting its middle on the left wing or left side of the figure denotes the end point of interest of the aircraft.
FIG. 2C—FIG. 2C displays the side view of the aircraft. FIG. 2C displays the number 11 pointing to where the fuselage trailing edge ends. The number 12 in FIG. 2C points to where the horizontal tail trailing edge root ends, which is behind the fuselage trailing edge. This horizonal tail is the same as the horizontal tail denoted as number 6 in FIG. 2A and number 9 in FIG. 2B. The number 13 in FIG. 2C points to the root trailing edge of the vertical tail, which is behind the trailing edge of the fuselage. The number 13 in FIG. 2C corresponds to the number 7 in FIG. 2A and the number 10 in FIG. 2B.
DETAILED DESCRIPTION OF THE INVENTION
The terminology within this section is used for describing the characteristics, functionality, and uses thereof. The term “and/or” used within a sentence denotes any and all combinations of one or more of the associated listed elements. The singular forms of “a,” “an,” and “the” are also intended to include the plural forms unless otherwise stated. It is presumed that scientific, technical, engineering, and mathematical terms are universally defined. It is further understood that these definitions are not limited to their common definitions and may be found through the use of dictionaries or other sources.
There are multiple types of vehicles and objects that can utilize this invention such as: an aircraft, spacecraft, propelled object, and projectile object. The following definitions of an aircraft, spacecraft, propelled object, and projectile object are simply defined, and are not limited to these definitions. An aircraft is any vehicle made to fly within the Earth's atmosphere. A spacecraft is any vehicle made to exit the Earth's atmosphere. A propelled object is any object that has a propulsion system to propel the object in a designated direction. A projectile object is any object that has the capability of being launched from a person's hand or a platform.
The tails on a vehicle or object sustain it in flight and provide directional stability. Depending on how the tails are shaped can affect how streamlined a vehicle or object is while also affecting lift and drag. Streamlined is defined as but not limited to, a shape of a vehicle or object that is resistant to drag. Lift is defined as but not limited to, the force that sustains the vehicle or object in air. Drag is the opposing force operating on the surface of a vehicle or object while it is in travel. This invention entails changing the location of where the tails' root leading edge is and/or where the tail root come out of the body of the vehicle or object to make it more streamlined. “Come out of the body” or “coming out of the body” describes the location where the root or base of the tail is connected to the main body of the vehicle or object. The root is defined as but not limited to, the part that connects to the body of a vehicle or object.
For example, in using the older tail configurations of an aircraft, the tails come out of the body in the back region. “Older” describes the root of the tail configurations coming out of the back region, but not having its root trailing edge at the fuselage trailing edge and/or the root trailing edge behind the fuselage. The tail's root leading edge is the backmost part of the tail that is closest to the axis of symmetry and/or the axis corresponding to the center of rotation of the vehicle's or object's main body and/or fuselage. “Behind” describes the tail's root trailing edge being even to the back of the fuselage of a vehicle or object, and/or describes the tail's root trailing edge being the backmost part of the aircraft. In applying the invention, if the tail's root come out of the body at the back of the fuselage, it can reduce drag. Also, if the tail's root leading edge is behind the fuselage, it can reduce drag.
It is important to note that there are some airplanes that have their tails' root at the back. However, this may be because of other reasons instead of specifically to become more streamlined and reduce drag. If a vehicle or object reduces drag and/or becomes more stable as a result of becoming streamlined, then this describes the invention. This invention describes all tail, including vertical and horizontal, configuration designs that have their root trailing edge located at the fuselage trailing edge and/or root trailing edge behind the fuselage to become more streamlined and reduce drag. This invention also describes putting the tails as far back as possible on a vehicle or object. “As far back as possible” describes the vehicle's and/or object's ability to be at the backmost part, as this may vary.
FIGS. 1A, 1B, and 1C display examples of the trailing edge of tail roots being located at the back of an aircraft. FIGS. 2A, 2B, and 2C display examples of the trailing edge of tail roots located behind the fuselage of an aircraft. It is presumed that these figures do not limit the scope or usefulness of the invention. For example, there can be different vehicles or objects with different tail shapes and different number of tails.
FIG. 1A displays the front view of the aircraft. FIG. 1A displays the number 1 pointing to one out of two horizontal tails on the aircraft whose root trailing edge is even to the fuselage trailing edge. The number 2 is pointing to the area where the vertical tail's root trailing edge originate from, which is at the trailing edge of the fuselage. FIG. 1B displays the top view of the aircraft. FIG. 1B displays the number 3 pointing to the area where the horizontal and vertical tails' root trailing edge, referenced in FIG. 1A, attach to the trailing edge of the fuselage. The number 3 in FIG. 1B denotes the top view of the tails that are denoted as number 1 and number 2 in FIG. 1A. The curve line with two slanted lines intersecting its middle on the left wing or left side of the figure denotes the end point of interest of the aircraft. FIG. 1C displays the side view of the aircraft. FIG. 1C displays the number 4 pointing to the vertical tail root trailing edge being even with the trailing edge of the fuselage. This vertical tail is the side view of the vertical that is denoted in FIG. 1A as number 2. The number 5 is pointing to the area where the root trailing edge of the horizontal tail is located, which is at the trailing edge of the fuselage. The number 5 in FIG. 1C denotes the side view of number 1 in FIG. 1A. The general area that number 4 and 5 point to is the same area denoted as number 3 in FIG. 1B.
FIG. 2A displays the front view of the aircraft. FIG. 2A displays the number 6 pointing to one out of two horizontal tails on the aircraft whose root trailing edge is behind the fuselage trailing edge. The number 2 is pointing to the area where the vertical tail's root trailing edge originate from, which is behind the trailing edge of the fuselage. FIG. 2B displays the top view of the aircraft. FIG. 2B displays the number 8 pointing to where the fuselage trailing edge ends. The number 9 in FIG. 2B points to where the horizontal tail trailing edge root ends, which is behind the fuselage trailing edge. This horizonal tail is the same as the horizontal tail denoted as number 6 in FIG. 2A. The number 10 in FIG. 2B points to the root trailing edge of the vertical tail, which is behind the trailing edge of the fuselage. The number 7 in FIG. 2A corresponds to the number 10 in FIG. 2B. The curve line with two slanted lines intersecting its middle on the left wing or left side of the figure denotes the end point of interest of the aircraft. FIG. 2C displays the side view of the aircraft. FIG. 2C displays the number 11 pointing to where the fuselage trailing edge ends. The number 12 in FIG. 2C points to where the horizontal tail trailing edge root ends, which is behind the fuselage trailing edge. This horizonal tail is the same as the horizontal tail denoted as number 6 in FIG. 2A and number 9 in FIG. 2B. The number 13 in FIG. 2C points to the root trailing edge of the vertical tail, which is behind the trailing edge of the fuselage. The number 13 in FIG. 2C corresponds to the number 7 in FIG. 2A and the number 10 in FIG. 2B. It is presumed that the processes, manufacturability, and assembly of these tail configurations on the body of the aircraft, spacecraft, propelled object, or projectile object should follow the same or similar guidelines in how the older designs of tail configurations for vehicles and objects are made.
Patent Application
20210362822
