CN111942572A - Side single vertical tail flying patrol device with vertical tail unfolding device - Google Patents
Side single vertical tail flying patrol device with vertical tail unfolding device Download PDFInfo
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- CN111942572A CN111942572A CN202010992087.0A CN202010992087A CN111942572A CN 111942572 A CN111942572 A CN 111942572A CN 202010992087 A CN202010992087 A CN 202010992087A CN 111942572 A CN111942572 A CN 111942572A
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- vertical tail
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- tail
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- 238000005096 rolling process Methods 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 3
- 238000009434 installation Methods 0.000 abstract description 2
- 230000003068 static effect Effects 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 241001155433 Centrarchus macropterus Species 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/10—Stabilising surfaces adjustable
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a side single vertical fin flying patrol device with a vertical fin unfolding device, wherein a vertical fin is fixedly connected with a vertical fin rotating shaft and a tension spring hook, an elastic baffle ring is sleeved on the vertical fin rotating shaft, and the tension spring hook can slide in a guide groove of a body side plate of a bomb; the second end of the tension spring hook is connected with the first end of the tension spring, the second end of the tension spring is fixed in the bullet body, and when the vertical tail is in a folded state, the tension spring is in a stretched state. According to the flight patrol device, a single foldable vertical fin arranged on the side is adopted, two vertical fins of the traditional flight patrol device are reduced to one, the requirement on the static stability of the course is ensured, and the number of foldable wing surfaces of the flight patrol device is reduced, so that the structural weight of a projectile body is reduced, and the number and the complexity of folding mechanisms are reduced; the vertical tail unfolding device adopts the tension spring to provide driving force, reduces the friction force in the vertical tail rotation process by additionally arranging the needle roller end face bearing, realizes the vertical tail rotation limitation by reserving the guide groove on the side wall of the bullet body, and has the advantages of simplicity, reliability, light weight and small installation occupation space.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a side-mounted single vertical tail flying patrol device with a vertical tail unfolding device.
Background
The flying patrol device is an unmanned flying platform, is usually thrown by platforms such as a transporter, a rocket projectile and a distributor or launched by a ground launching tube to take off, and is mainly used for detecting and striking time-sensitive targets. The aerodynamic airfoil needs to be foldable due to the need to be loaded in a launch platform or launch canister. In order to meet the requirement of folding loading, the conventional cruise flight device usually adopts a tandem wing type layout scheme of two pairs of front and rear main wing surfaces, and the control surface is usually located at the rear edge of the rear wing, such as a single-soldier cruise missile "spring knife" (switchblede) developed in the united states, a cruise missile "subwolf" (locast) developed in the united states, a cruise missile R-90 developed in russia, and the like. The folding wing surface number is large, the folding mechanism number is increased, the folding mechanism is complex, the reliability is reduced, and meanwhile, the structural weight is also increased, so that the folding flying patrol device needs to reduce the folding wing surface number and the control surface number as far as possible, and the unfolding device which is as simple and reliable as possible is adopted, so that the reliability of the whole machine is improved. Compared with the conventional flyer patrol device, the side single vertical tail flyer patrol device with the vertical tail unfolding device has fewer wing surfaces and a simple and reliable unfolding mechanism.
Disclosure of Invention
In order to solve the problems in the background art, the invention provides a side single vertical tail flight patrol device with a vertical tail unfolding device.
In order to achieve the purpose, the invention provides the following technical scheme:
a side-mounted single vertical tail flying patrol device with a vertical tail unfolding device comprises two front wings, two control surfaces, two rear wings, a missile body and a vertical tail, wherein the vertical tail is rotatably mounted on one side of the missile body; the elastic retainer ring is sleeved on the vertical tail rotating shaft and is positioned in the bullet body, and the second end of the tension spring hook penetrates through the guide groove of the lateral plate of the bullet body; the second end of the tension spring hook is connected with the first end of the tension spring, the second end of the tension spring is fixed in the bullet body, and when the vertical tail is in a folded state, the tension spring is in a stretched state.
Further, when the vertical fin is in the fully folded state, the tension spring is in a stretching state.
Further, when the vertical fin is in the fully opened state, the tension spring is in the non-stretching state.
Specifically, when the vertical tail is in a fully opened state, the distance between the tension spring hook and the second end of the tension spring is shortest; when the vertical fin is in a completely folded state, the distance between the tension spring hook and the second end of the tension spring is longest.
Specifically, a needle roller end face bearing is sleeved on the vertical tail rotating shaft and is positioned between the vertical tail and the bullet body side plate, and two rolling end faces of the needle roller end face bearing are respectively connected with one side face of the vertical tail and one side face of the bullet body side plate.
Specifically, the front wing and the rear wing are both rotatably connected with the missile body, and the control surface is arranged on the front wing.
Specifically, the two front wings, the two rear wings and the vertical tail do not protrude out of the maximum outline of the bullet body after being folded.
Compared with the prior art, the invention has the beneficial effects that:
1. the flying patrol device adopts a single foldable vertical fin arranged on the side, two vertical fins of the traditional flying patrol device are reduced to one, the requirement of course static stability is ensured, and the number of foldable wing surfaces of the flying patrol device is reduced, so that the structural weight of the projectile body is reduced, and the number and the complexity of the foldable mechanisms are reduced;
2. the size of the folded whole machine of each airfoil is not larger than the overall size of the missile body, the folding is compact, the space utilization rate is high, and a throwing cylinder or a launching cylinder is convenient to load and store;
3. the vertical tail unfolding device adopts the tension spring to provide driving force, reduces the friction force in the vertical tail rotation process by additionally arranging the needle roller end face bearing, realizes the vertical tail rotation limitation by reserving the guide groove on the side wall of the bullet body, and has the advantages of simplicity, reliability, light weight and small installation occupation space.
Drawings
FIG. 1 is a side view of a deployment axis of a cruise aircraft airfoil;
FIG. 2 is a side view of a folding axis of a flier airfoil;
FIG. 3 is a partial isometric view of the vertical tail deployment device;
FIG. 4 is a cross-sectional view of the vertical fin deployment device with the vertical fin deployed;
FIG. 5 is a side view of the trailing axle of the present application;
FIG. 6 is a schematic view of the structure of a tension spring in the present application;
FIG. 7 is a schematic view of a needle end bearing configuration of the present application;
FIG. 8 is a schematic view of a circlip structure of the present application;
FIG. 9 is a schematic diagram of a side plate structure of the projectile body according to the present application;
in the figure:
1-front wing, 2-control rudder face, 3-vertical tail, 4-rear wing, 5-missile body, 6-tension spring, 7-tension spring hook, 8-elastic retainer ring, 9-missile body side plate, 10-vertical tail rotating shaft and 11-needle roller end face bearing.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention provides the following technical scheme:
as shown in fig. 1-6, 8 and 9, the side single vertical tail 3 flying patrol device with the vertical tail 3 unfolding device comprises two front wings 1, two control surfaces 2, two rear wings 4 and a missile body 5, the flying patrol device comprises a vertical tail 3, wherein the vertical tail 3 is rotatably arranged on one side of a bullet body 5, the flying patrol device also comprises a vertical tail 3 unfolding device, the vertical tail 3 unfolding device comprises a bullet body side plate 9, a vertical tail rotating shaft 10, an elastic retainer ring 8, a tension spring 6 and a tension spring hook 7, the side surface of one end part of the vertical tail 3 is fixedly connected with the first end of the vertical tail rotating shaft 10 and the first end of the tension spring hook 7, the vertical tail 3 is vertical to the vertical tail rotating shaft 10, the bullet body side plate 9 is embedded and arranged on the bullet body 5, a through hole and an arc-shaped guide groove are arranged on the bullet body side plate 9, the vertical tail rotating shaft 10 is rotatably arranged in the through hole of the bullet body side plate 9, and the second end of the vertical; the elastic retainer ring 8 is sleeved on the vertical tail rotating shaft 10, the elastic retainer ring 8 is positioned in the bullet body 5, the tension spring hook 7 can slide in the guide groove of the bullet body side plate 9, and the second end of the tension spring hook 7 penetrates through the guide groove of the bullet body side plate 9; the second end of extension spring couple 7 is connected with the first end of extension spring 6, and the second end of extension spring 6 is fixed inside body of bullet 5, and when vertical fin 3 was in fold condition, extension spring 6 was in tensile state.
In the embodiment, the fly patrol device adopts a pair of differential ailerons positioned at the rear edge of the front wing 1 as a control surface 2, and the control moment generated on the control surface are in the same direction when the fly patrol device is controlled to raise or lower the head, so that the control efficiency is higher, and the fly patrol device is more beneficial to maneuver at the tail end attack stage;
in the embodiment, the vertical tail 3 unfolding device adopts the tension of a tension spring 6 as unfolding power;
in this embodiment, the guide groove that sets up on the body of bullet curb plate 9 can let the movement track of extension spring couple 7 match with the guide groove shape when the vertical fin 3 rotates to realize through the guide groove that vertical fin 3 rotates spacingly, ensure vertical fin 3 and expand the angle.
In this embodiment, the circlip 8 serves for vertical spacing of the tang 3.
In this embodiment, extension spring couple 7 slides in the guide way on bullet body curb plate 9 when vertical fin 3 is folding, and extension spring 6 is stretched simultaneously, and after 3 restraints of vertical fin were relieved, the pulling force of extension spring 6 drove vertical fin 3 and expandes through extension spring couple 7 on the vertical fin 3, and stop motion when extension spring couple 7 reachd the guide way extreme position on the bullet body curb plate 9, vertical fin 3 expandes to target in place.
In this embodiment, bullet body curb plate 9 links firmly with 5 skins of bullet body, reserves the guide way according to 3 folding in-process extension spring couple 7 movement tracks of vertical fin on the bullet body curb plate 9 to restrict vertical fin 3 through the guide way and continue to rotate, ensure that vertical fin 3 expandes the angle.
In this embodiment, the tension spring 6 is in tension when the tag 3 is in the fully folded state.
In this embodiment, the tension spring 6 is in a non-stretched state when the vertical fin 3 is in the fully opened state.
In this embodiment, when the vertical fin 3 is in the fully opened state, the distance between the tension spring hook 7 and the second end of the tension spring 6 is shortest; when the vertical tail 3 is in a completely folded state, the distance between the tension spring hook 7 and the second end of the tension spring 6 is longest.
In some embodiments, the vertical tail rotating shaft 10 and the tension spring hook 7 are integrally formed with the vertical tail 3 through hot pressing by a die.
As shown in fig. 4 and 7, a needle end bearing 11 is sleeved on the vertical fin rotating shaft 10 and located between the vertical fin 3 and the missile body side plate 9, and two rolling end surfaces of the needle end bearing 11 are respectively connected with one side surface of the vertical fin 3 and one side surface of the missile body side plate 9.
In the embodiment, the friction force between the vertical fin 3 and the bullet body side plate 9 can be reduced by adopting the needle roller end surface bearing 11;
as shown in fig. 1-2, the front wing 1 and the rear wing 4 are rotatably connected with the missile body 5, and the control surface 2 is arranged on the rear edge of the front wing 1.
In this embodiment, the front wing 1, the rear wing 4 and the vertical fin 3 are installed on the bullet body 5 in a staggered manner, so that the interference of the vertical fin 3 which is firstly unfolded to the unfolding of the front wing 1 and the rear wing 4 in the folding and unfolding process can be avoided. When folded, the front wing 1 rotates 90 degrees towards the back of the missile body 5, the rear wing 4 rotates 90 degrees towards the front of the missile body 5, the vertical fin 3 is folded forwards by 90 degrees and placed on the side of the missile body 5, and the folding is opposite when opened.
As shown in fig. 2, the two front wings 1, the two rear wings 4 and the vertical tail 3 do not protrude the maximum outer contour of the bullet body 5 after being folded.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. A side-mounted single vertical tail flying patrol device with a vertical tail unfolding device comprises two front wings, two control surfaces, two rear wings, a missile body and a vertical tail, wherein the vertical tail is rotatably arranged on one side of the missile body; the elastic retainer ring is sleeved on the vertical tail rotating shaft and is positioned in the bullet body, and the second end of the tension spring hook penetrates through the guide groove of the lateral plate of the bullet body; the second end of the tension spring hook is connected with the first end of the tension spring, the second end of the tension spring is fixed in the bullet body, and when the vertical tail is in a folded state, the tension spring is in a stretched state.
2. The side mounted single vertical tail flyer walker with vertical tail spreading device according to claim 1, wherein the tension spring is in tension when the vertical tail is in the fully folded state.
3. The side mounted single vertical tail flyer walker with vertical tail spreading device according to claim 1, wherein the tension spring is in a non-tension state when the vertical tail is in a fully open state.
4. The side single vertical tail flying patrol device with the vertical tail unfolding device according to claim 1, wherein when the vertical tail is in a fully opened state, the distance between the hook of the tension spring and the second end of the tension spring is shortest; when the vertical fin is in a completely folded state, the distance between the tension spring hook and the second end of the tension spring is longest.
5. The side single-vertical-tail flying patrol device with the vertical-tail unfolding device according to claim 1, wherein a needle end-face bearing is sleeved on the vertical-tail rotating shaft and is positioned between the vertical tail and the missile body side plate, and two rolling end faces of the needle end-face bearing are respectively connected with one side face of the vertical tail and one side face of the missile body side plate.
6. The side single vertical tail flying patrol device with the vertical tail unfolding device according to claim 1, wherein a front wing and a rear wing are both rotatably connected with the missile body, and a control surface is arranged on the front wing.
7. The side single vertical tail flying patrol device with the vertical tail unfolding device according to claim 1, wherein the two front wings, the two rear wings and the vertical tail do not protrude out of the maximum outer contour of the missile body after being folded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010992087.0A CN111942572A (en) | 2020-09-21 | 2020-09-21 | Side single vertical tail flying patrol device with vertical tail unfolding device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010992087.0A CN111942572A (en) | 2020-09-21 | 2020-09-21 | Side single vertical tail flying patrol device with vertical tail unfolding device |
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| CN111942572A true CN111942572A (en) | 2020-11-17 |
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| CN202010992087.0A Pending CN111942572A (en) | 2020-09-21 | 2020-09-21 | Side single vertical tail flying patrol device with vertical tail unfolding device |
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2020
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