CN214241213U - Aircraft - Google Patents
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- CN214241213U CN214241213U CN202023022318.XU CN202023022318U CN214241213U CN 214241213 U CN214241213 U CN 214241213U CN 202023022318 U CN202023022318 U CN 202023022318U CN 214241213 U CN214241213 U CN 214241213U
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Abstract
The utility model relates to an aircraft technical field especially relates to the aerodynamic layout technical field of aircraft, concretely relates to aircraft. Retractable and retractable vertical tails are arranged on the aircraft; the vertical fin is used for enhancing the navigation stability of the aircraft in the outburst state. The utility model provides a for the retractable vertical fin can be visited out to the aircraft setting, can increase the course stability of aircraft, can partially solve the relatively poor, the higher problem of control risk of all-wing aircraft take-off and landing section course stability, maintain the high-efficient pneumatic configuration of all-wing aircraft overall arrangement simultaneously.
Description
Technical Field
The utility model relates to an aircraft technical field especially relates to the aerodynamic layout technical field of aircraft, concretely relates to aircraft.
Background
Aircraft of conventional layout often have a vertical tail at the tail of the fuselage, which primarily serves to increase the stability of the aircraft heading. The flying wing layout without vertical tails is an advanced aircraft appearance layout design, has the characteristics of high aerodynamic efficiency, good stealth performance, strong loading capacity and the like, is applied to military aircraft, and is an important research direction of civil aircraft. However, the vertical tail of the flying wing layout aircraft is eliminated, so that the aircraft has an unstable course, and the difficulty of flight control is increased, particularly in the takeoff and landing stage of the aircraft. In the taking-off and landing stage of the aircraft, due to the fact that the flying speed is low and the air flow is low and complex, the control surface manipulation efficiency is low, and the aircraft without vertical tail flying wing layout has high course stability control risk. Bombers with the U.S. B-2 flying wing layout have been out of control during the takeoff phase, resulting in aircraft crash. Therefore, the flying wing layout aircraft needs to adopt corresponding technology to solve the problem of course stability in the taking-off and landing stage.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides a for the retractable vertical fin can be visited to the aircraft setting, can increase the course stability of aircraft, can partially solve flying wing overall arrangement aircraft take off and land the relatively poor, the higher problem of control risk of section course stability, maintain the high-efficient pneumatic configuration of flying wing overall arrangement simultaneously.
In order to achieve the above technical effects, the utility model discloses the concrete technical scheme who adopts is:
an aircraft provided with retractable and extendable vertical tails; the vertical fin is used for enhancing the navigation stability of the aircraft in the outburst state.
Furthermore, a skin of the aircraft is provided with a retraction groove; the retraction groove is used for accommodating the vertical fin in a retraction state.
Further, the vertical fin is attached to the skin of the aircraft in a retracted state.
Further, the portion of the tag that is on the outer surface of the aircraft when the tag is in the retracted state is adapted to the aerodynamic profile of the skin of the aircraft.
Further, the aircraft also comprises a mounting seat fixed on the aircraft, and the vertical fin is rotatably connected with the mounting seat; retraction and protraction of the tag is achieved by rotation of the tag about its mounting point on the mount.
Further, the rotation of the vertical fin around a point on the mounting seat is realized through an action device;
the mounting seat is a mounting lug, and the vertical fin is mounted on the mounting lug through a rotating shaft;
the action device comprises an action base, an actuator and an action lug; the actuating base is fixed on the aircraft; the actuator is a telescopic action device, the main body is connected with the actuating base through a rotating shaft, and the telescopic part is connected with the actuating lug piece through the rotating shaft; the actuating lug and the vertical tail are fixedly arranged.
Furthermore, the installation lug is two or more groups, and is connected with the vertical tail through a rotating shaft.
Further, in any state, the mounting seat and the action device are arranged inside the skin of the aircraft.
Further, the vertical fin comprises a left vertical fin and a right vertical fin, and the retracting directions of the left vertical fin and the right vertical fin face to the central axis of the aircraft or are far away from the central axis of the aircraft.
Further, the extending limit of the vertical fin is that when the airplane sails parallel to the horizontal plane, the vertical fin is perpendicular to the horizontal plane.
Adopt above-mentioned technical scheme, the utility model discloses following beneficial effect can be brought:
the utility model discloses a vertical fin function is similar with conventional aircraft, can play the effect that increases aircraft course stability. The vertical fin is suitable for the stages with higher course control risks such as take-off and landing of the aircraft, the safety of the flying wing layout aircraft is improved, and the flying wing layout aircraft cannot lose the original advantages after the vertical fin is folded.
The utility model discloses a vertical fin is packing up the back, and the surface and the aircraft covering slick and sly of vertical fin are excessive, have guaranteed the aerodynamic appearance of streamline of aircraft covering. Because the aircraft resistance is related to the forward sectional area of the aircraft, the sectional area can be reduced after the vertical fin is folded compared with the aircraft with the conventional layout, and the flight resistance caused by the vertical fin is avoided.
Aircraft radar wave stealth ability is relevant with forward, the side direction reflection area of aircraft, the utility model discloses an aircraft can reduce conventional overall arrangement aircraft's front, side radar wave reflection area after packing up the vertical fin, improves the radar wave stealth performance of aircraft.
The retractable vertical fin of the utility model can be pre-erected to a set angle before the ground takeoff of the aircraft, and can be retracted in the flying process; and can also be erected or folded during flight.
The utility model discloses can be according to the needs of aircraft, can set up retractable vertical fin into single vertical fin or two vertical fins.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic view of a vertical tail protruding state according to an embodiment of the present invention;
FIG. 2 is a schematic view of the retraction state of the vertical tail according to the embodiment of the present invention;
FIG. 3 is a schematic view of the structure of a vertical fin according to an embodiment of the present invention;
FIG. 4 is a schematic view of the hanging part extending out from the action device and the hanging part in a state of being engaged with each other according to the embodiment of the present invention;
FIG. 5 is a schematic view of the operation device of the present invention being engaged with the vertical fin to retract the vertical fin;
wherein: 1. a body; 2. hanging a tail; 3. a withdrawal tank; 4. a mounting seat; 5. an actuating base; 6. an actuator; 7. the tab is actuated.
Detailed Description
The embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will be readily apparent to those skilled in the art from the disclosure herein. It is to be understood that the embodiments described are only some embodiments of the invention, and not all embodiments. The present invention can also be implemented or applied through other different specific embodiments, and various details in the present specification can be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention, and the drawings only show the components related to the present invention rather than being drawn according to the number, shape and size of the components in actual implementation, and the form, amount and ratio of the components in actual implementation can be changed at will, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The embodiment of the utility model provides an aircraft, which is provided with a retractable and protrusive vertical fin 2; the vertical fin 2 is used to enhance the navigation stability of the aircraft in the probe-out state. In this embodiment, the vertical fin 2 is a retractable structure, and taking an aircraft with a flying wing layout as an example, the vertical fin 2 is retracted (as shown in fig. 1) when the aircraft is in a landing state, a troposphere rising state, and in severe weather or before a high-mobility sailing action is performed in advance, so that the influence of unstable airflow on the normal sailing of the aircraft in a low altitude or the insufficient stability of the fuselage to support the aircraft to perform the high-mobility action which is realized in advance can be avoided. When the aircraft is in a stratosphere, does not need to make high-maneuvering sailing actions and is in a gentle airflow, the vertical fin 2 is retracted (as shown in figure 2) so as to reduce the resistance and the radar scanning area brought by the vertical fin 2 and improve the aerodynamic efficiency of the aircraft. Aircraft resistance is related to the forward sectional area of the aircraft, and the folding of the vertical fin 2 can reduce the sectional area and avoid flight resistance caused by the vertical fin 2. The stealth capability of the radar wave of the aircraft is related to the forward and lateral reflection areas of the aircraft, and the vertical tails 2 are retracted to reduce the reflection areas of the radar wave on the front and the lateral surfaces of the aircraft and improve the stealth performance of the radar wave of the aircraft.
In this embodiment the tag 2 may be provided with a rudder to enable it to be used in more sailing situations.
In this embodiment, the vertical fin 2 can be retracted into the aircraft body 1 or folded and retracted to be attached to the outer surface of the aircraft body 1 in the retracted state of the vertical fin 2, the material of the vertical fin 2 is the same as that of the common vertical fin 2, and the surface coating is the same as that of the aircraft skin, so as to avoid influencing various indexes such as stealth of the aircraft. In this embodiment, the specific structure of the vertical fin 2 can be foldable to reduce the surface area in the retracted state.
In one embodiment, as shown in fig. 1, the skin of the aircraft is provided with a retraction slot 3; the retraction slot 3 is used to accommodate the depending tab 2 in the retracted state. In the embodiment, if the vertical fin 2 is selected to be attached to the skin to finish retraction, the retraction groove 3 is a concave surface formed on the skin; if the vertical fin 2 selects to retract the fuselage to finish the retraction, the retraction slot 3 is a strip-shaped slot for the vertical fin 2 to retract.
In one embodiment, in order to save the loss of the internal space of the fuselage, as shown in fig. 2, the vertical fin 2 is attached to the skin of the aircraft in a retracted state, and smooth transition is performed between the vertical fin 2 and the skin, so as to avoid influencing the aerodynamic configuration of the aircraft, and meanwhile, the outer surface of the vertical fin 2 is configured to be suitable for the aerodynamic shape of the skin of the aircraft, so that the overall aerodynamic configuration of the aircraft is not influenced.
In one embodiment, when the tag 2 is in the retracted fuselage embodiment, the top of the tag 2 is provided with an arc that can adapt to the aerodynamic profile of the aircraft skin so as not to affect the overall aerodynamic configuration of the aircraft.
In one embodiment, taking the example that the vertical fin 2 is retracted to be attached to the outer surface of the airframe 1, as shown in fig. 4 or fig. 5, the aircraft further comprises a mounting seat 4 fixed on the aircraft, and the vertical fin 2 is rotatably connected with the mounting seat 4; retraction and protraction of the tag 2 is achieved by rotation of the tag 2 about its mounting point on the mounting 4.
In this embodiment, the rotation of the tag 2 around the point on the mounting 4 is achieved by the action means;
the mounting seat 4 is a mounting lug, and the vertical fin 2 is mounted on the mounting lug through a rotating shaft;
the action device comprises an action base 5, an actuator 6 and an action lug 7; the actuating base 5 is fixed to the aircraft; the actuator 6 is a telescopic action device, the main body is connected with the actuating base 5 through a rotating shaft, and the telescopic part is connected with the actuating lug 7 through a rotating shaft; the actuating lug 7 is fixedly arranged with the vertical tail 2.
In this embodiment, two or more sets of mounting tabs are connected to the vertical tails 2 through the rotating shaft.
In one embodiment, the mounting 4 and the actuation means are arranged inside the skin of the aircraft in any state.
In the embodiment, the vertical fin 2 can be erected and is higher than the machine body 1, so that the heading stability is increased. And taking the front edge vertex and the rear edge vertex of the top end surface of the vertical fin 2 and the front edge vertex of the bottom end surface of the vertical fin 2 to form a plane for representing the position of the vertical fin 2. The angle alpha is the included angle between the plane of the vertical tail 2 and the horizontal plane, and the angle alpha is in the range of alpha' to 90 degrees. When α is α ', the vertical fin 2 is in the retracted state, and the specific value of α' is determined according to the retraction slot 3 reserved on the machine body 1.
The bottom of the vertical fin 2 is provided with an actuating lug 7, and a hinged lug is fixedly arranged at a position close to the bottom of the vertical fin 2. The hinged lug is connected with the mounting seat 4 through a rotating shaft, so that the vertical fin 2 can rotate around the rotating shaft on the mounting seat 4. The actuating lug 7 enables the vertical fin 2 and an actuating rod, namely a telescopic rod, of the actuator 6 to be connected through a rotating shaft, and the actuator 6 can push the vertical fin 2 to move.
When the vertical tail 2 needs to be extended out, the actuating rod of the actuator 6 is connected with the actuating lug 7 through the rotating shaft. The actuator 6 pushes the vertical fin 2 to erect, retract or to a set position. When the actuator 6 is held in a fixed operating condition, the tag 2 can be maintained in a fixed position, the energy source for operating the actuator 6 being provided by the aircraft itself.
The inside base 5 that actuates that sets up of organism 1, the articulated auricle of actuator 6 with actuate base 5 and be connected through the pivot. The function of the actuating base 5 is to provide support for the actuation of the actuator 6.
In this embodiment, as shown in fig. 5, the actuating rod of the actuator 6 is in the initial position, and the vertical fin 2 is retracted into the retraction groove 3 of the machine body 1.
In this embodiment, as shown in fig. 4, the actuator 6 extends out of the actuating rod, and the vertical fin 2 is erected by the actuating lug 7 pushing the vertical fin 2 to rotate around the rotating shaft of the mounting seat 4. In the erected state, the position angle of the tag 2 can be up to 90 °.
In one embodiment, as shown in fig. 2, to further avoid affecting the overall aerodynamic configuration of the aircraft, the vertical fin 2 comprises a left vertical fin 2 and a right vertical fin 2, and the retraction directions of the left vertical fin 2 and the right vertical fin 2 are both towards the central axis of the aircraft or both away from the central axis of the aircraft.
In one embodiment, the extended limit of the droop 2 is that the droop 2 is perpendicular to the horizontal plane when the aircraft is sailing parallel to the horizontal plane.
The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. An aircraft, characterized in that: retractable and retractable vertical tails are arranged on the aircraft; the vertical fin is used for enhancing the navigation stability of the aircraft in the outburst state.
2. The aircraft of claim 1, wherein: a skin of the aircraft is provided with a retraction groove; the retraction groove is used for accommodating the vertical fin in a retraction state.
3. The aircraft of claim 1, wherein: and when the vertical fin is in a retraction state, the vertical fin is attached to the skin of the aircraft.
4. The aircraft of claim 1, wherein: the portion of the vertical fin that is on the outer surface of the aircraft when the vertical fin is in the retracted state is adapted to the aerodynamic profile of the skin of the aircraft.
5. The aircraft of claim 1, wherein: the aircraft also comprises a mounting seat fixed on the aircraft, and the vertical fin is rotatably connected with the mounting seat; retraction and protraction of the tag is achieved by rotation of the tag about its mounting point on the mount.
6. The aircraft of claim 5, wherein: the rotation of the vertical fin around a point on the mounting seat is realized by an action device;
the mounting seat is a mounting lug, and the vertical fin is mounted on the mounting lug through a rotating shaft;
the action device comprises an action base, an actuator and an action lug; the actuating base is fixed on the aircraft; the actuator is a telescopic action device, the main body is connected with the actuating base through a rotating shaft, and the telescopic part is connected with the actuating lug piece through the rotating shaft; the actuating lug and the vertical tail are fixedly arranged.
7. The aircraft of claim 6, wherein: the mounting lugs are two or more groups and are connected with the vertical tails through rotating shafts.
8. The aircraft of claim 6 or 7, wherein: in any state, the mounting seat and the action device are arranged inside the skin of the aircraft.
9. The aircraft of claim 5, wherein: the vertical tails comprise a left vertical tail and a right vertical tail, and the retracting directions of the left vertical tail and the right vertical tail face to the central axis of the aircraft or are far away from the central axis of the aircraft.
10. The aircraft of claim 9, wherein: the extending limit of the vertical fin is that when the airplane sails parallel to the horizontal plane, the vertical fin is vertical to the horizontal plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023022318.XU CN214241213U (en) | 2020-12-14 | 2020-12-14 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023022318.XU CN214241213U (en) | 2020-12-14 | 2020-12-14 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214241213U true CN214241213U (en) | 2021-09-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202023022318.XU Active CN214241213U (en) | 2020-12-14 | 2020-12-14 | Aircraft |
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| CN (1) | CN214241213U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407245A (en) * | 2020-12-14 | 2021-02-26 | 中国科学院工程热物理研究所 | Aircraft |
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- 2020-12-14 CN CN202023022318.XU patent/CN214241213U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407245A (en) * | 2020-12-14 | 2021-02-26 | 中国科学院工程热物理研究所 | Aircraft |
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