CN205300398U - Can realize big power -driven target drone - Google Patents
Can realize big power -driven target drone Download PDFInfo
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- CN205300398U CN205300398U CN201620030092.2U CN201620030092U CN205300398U CN 205300398 U CN205300398 U CN 205300398U CN 201620030092 U CN201620030092 U CN 201620030092U CN 205300398 U CN205300398 U CN 205300398U
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- fuselage
- wing
- intake duct
- target drone
- horizontal tail
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Abstract
The utility model belongs to the technical field of unmanned vehicles, in particular to target drone. Its technical scheme is: a can realize big power -driven target drone, includes: fuselage (1), wing (2), vertical fin (3), horizontal tail (4), intake duct (5), characterized by: target drone aerodynamic layout adopts trapezoidal wing (2), and by the postposition type of the falling Y overall arrangement fin that vertical fin (3) and horizontal tail (4) are formed, intake duct (5) are divided into to streamlined fuselage (1) of circular section, ventral, the fuselage rear portion sets up the turbojet cabin. The utility model discloses special carry out the optimal design to high -speed (0.8M), big motor -driven (6g~8g) flight characteristics, dispose homemade ATD100 type turbojet, carry out pneumatics according to its lift performance, resistance performance, moment performance, engine performance and calculate, satisfy high -speed, big motor -driven requirement, have simultaneously the structure succinctly, effective weight reduction's advantage.
Description
Technical field
This utility model belongs to unmanned vehicle technical field, particularly to a kind of target drone.
Background technology
Target drone refers to a kind of dynamically physical object simulating device of the target that various air weapon system to attack. It is used for checking the performance characterisitic of whole armament systems, including weapon itself and mainly comprise subsystem, such as the combination property of guided missile, radar, optical tracker, launch control system etc. Therefore, require and from Armed Forces' training from Weapon System Development, all require that target drone is true to nature in real goal as much as possible in various performances. Target drone, except special equipment on some machine, all uses similar technology to unmanned vehicle.
Military power is all greatly developing variety classes, advanced in performance target, and existing nearly 30 national over one hundred companies develop 300 Multiple Types so far, and equipment uses total amount to reach several ten thousand framves. The particularly U.S., aerial target A wide selection of colours and designs, large number of, to simulate true to nature, it has also become aerial target quantity is maximum in the world, the state-of-the-art country of performance, representative model be that " Alectoris chukar ", " fire honeybee " are serial.
The domestic target drone development and production history of existing 50 years, including entity target drone, large high-speed target drone, small-sized low-altitude low-speed target drone, target missile etc., the aerial target of China formed vast sky series, target-5 second, destroy and-6 change, destroy-7 large-scale target drone series changing representative into, B-2 and B-7 is the small-sized target drone series of representative, supports domestic air-to-air armament system, the qualification test of low latitude armament systems and military training. But this type of target drone product can only simulate secondary operational aircraft target property, due to the design time early, the potentiality improving remodeling are also extremely limited. Aerodynamic arrangement's design is the emphasis of Aircraft Conceptual Design, directly influences the comprehensive serviceability of aircraft. Aerodynamic arrangement's design of existing target drone is difficulty with the high maneuver flight of 6g��8g, it is impossible to simulate all kinds of novel operational weapon preferably.
Summary of the invention
The purpose of this utility model is: provide a kind of new target drone aerodynamic arrangement to design, and to overcome the deficiencies in the prior art, coordinates domestic ATD100 type turbojet, it is achieved the target drone of high speed high maneuver flight.
The technical solution of the utility model is: a kind of target drone that can realize high maneuver, and it includes: fuselage, wing, vertical fin, horizontal tail, and S shape air intake duct;
Fuselage is divided into three sections along its length, and leading portion is inscribe bicircular arcs revolving body; Stage casing is cylindrical section; Back segment is the frustum section that cross section is gradually reduced;
S shape air intake duct is arranged on the hypogastric region of fuselage, for the turbojet engine nacelle supply arranged for fuselage afterbody; The Long Circle inlet lip of S shape air intake duct and fuselage boundary layer diverter separate, S shape air intake duct progresses into the flat segments of fuselage and its profile trousers and merges with fuselage, is additionally provided with rectification gondola at the rear portion of S shape air intake duct trousers and converges to the frustum section of fuselage gradually;
Wing is have 1 �� of established angle, 5 �� of leading edge sweeps, medium aspect ratio, the tapered wing that adopts the asymmetric midsetwing with camber high speed aerofoil profile to arrange, the trousers that its wing tip place is provided with and aerofoil profile is adaptive, and outside wing, trailing edge is provided with aileron;
Horizontal tail is have 30 �� of inverted diherdrals, medium aspect ratio, symmetrical airfoil, trailing edge with the trapezoidal horizontal tail of elevator;
Vertical fin is have 40 �� of leading edge sweeps, low aspect ratio, symmetrical airfoil, trapezoidal vertical fin with rudder;
Vertical fin and horizontal tail form rearmounted inverted Y-shaped layout empennage.
Beneficial effect: this utility model is specifically designed for (0.8M), high maneuver (6g��8g) flight characteristic at a high speed and is optimized design, configure domestic ATD100 type turbojet, Pneumatic Calculation is carried out according to its lift performance, resistance performance, moment properties, engine performance, meet high speed, high maneuver requirement, there is advantage simple for structure, that can effectively alleviate weight simultaneously.
Accompanying drawing explanation
Fig. 1 is outline drawing of the present utility model;
Fig. 2 is front view of the present utility model;
Fig. 3 is Fig. 2 A-A to sectional view;
Fig. 4 is Fig. 2 B-B to sectional view;
Fig. 5 is the top view of Fig. 2;
Fig. 6 is the left view of Fig. 2;
Fig. 7 is the inlet location shape view in this utility model;
Fig. 8 is the air intake duct view in this utility model;
Fig. 9 is Fig. 8 A-A to sectional view;
Figure 10 is Fig. 8 B-B to sectional view;
Figure 11 is Fig. 8 C-C to sectional view;
Figure 12 is Fig. 8 D-D to sectional view;
Figure 13 is the front view of fuselage in this utility model;
Figure 14 is Figure 13 A-A to sectional view;
Figure 15 is Figure 13 B-B to sectional view;
Figure 16 is Figure 13 C-C to sectional view;
Figure 17 is the front view of wing in this utility model;
Figure 18 is Figure 17 A-A to sectional view.
Wherein, 1-fuselage, 2-wing, 3-vertical fin, 4-horizontal tail, 5-shape air intake duct.
Detailed description of the invention
Develop simultaneously embodiment below in conjunction with accompanying drawing, this utility model is described in detail.
Referring to accompanying drawing, a kind of target drone that can realize high maneuver, it includes: fuselage 1, wing 2, vertical fin 3, horizontal tail 4, and S shape air intake duct 5;
Fuselage 1 is divided into three sections along its length, and leading portion is inscribe bicircular arcs revolving body; Stage casing is cylindrical section; Back segment is the frustum section that cross section is gradually reduced;
S shape air intake duct 5 is arranged on the hypogastric region of fuselage 1, for the turbojet engine nacelle supply arranged for fuselage 1 rear portion; The Long Circle inlet lip of S shape air intake duct 5 and fuselage 1 separate with boundary layer diverter, S shape air intake duct 5 progresses into the flat segments of fuselage 1 and its profile trousers and merges with fuselage 1, is additionally provided with rectification gondola at the rear portion of S shape air intake duct 5 trousers and converges to the frustum section of fuselage 1 gradually;
Wing 2 is have 1 �� of established angle, 5 �� of leading edge sweeps, medium aspect ratio, the tapered wing that adopts the asymmetric midsetwing with camber high speed aerofoil profile to arrange, the trousers that its wing tip place is provided with and aerofoil profile is adaptive, and outside wing 2, trailing edge is provided with aileron;
Horizontal tail 4 is have 30 �� of inverted diherdrals, medium aspect ratio, symmetrical airfoil, trailing edge with the trapezoidal horizontal tail of elevator;
Vertical fin 3 is have 40 �� of leading edge sweeps, low aspect ratio, symmetrical airfoil, trapezoidal vertical fin with rudder;
Vertical fin 3 and horizontal tail 4 form rearmounted inverted Y-shaped layout empennage.
Shown by flight test combining with theoretical analysis: when wing 2 adopts the relative chord length of maximum gauge to be the laminar flow airfoil of 8%; Horizontal tail 4 adopts the relative chord length of maximum gauge to be the symmetrical airfoil of 8%; Vertical fin 3 adopts the relative chord length of maximum gauge to be the symmetrical airfoil of 8%, and adopts the target drone that above-mentioned aerodynamic arrangement designs to have high maneuverability, and sustained maneuver overload reaches+6g, and flight speed is up to 0.8M.
Claims (2)
1. realizing a target drone for high maneuver, it includes: fuselage (1), wing (2), vertical fin (3), horizontal tail (4), and S shape air intake duct (5), it is characterized in that:
Described fuselage (1) is divided into three sections along its length, and leading portion is inscribe bicircular arcs revolving body; Stage casing is cylindrical section; Back segment is the frustum section that cross section is gradually reduced;
Described S shape air intake duct (5) is arranged on the hypogastric region of described fuselage (1), for the turbojet engine nacelle supply arranged for described fuselage (1) rear portion; The Long Circle inlet lip of described S shape air intake duct (5) and described fuselage (1) separate with boundary layer diverter, described S shape air intake duct (5) progresses into the flat segments of described fuselage (1) and its profile trousers and merges with described fuselage (1), is additionally provided with rectification gondola at the rear portion of described S shape air intake duct (5) trousers and converges to the frustum section of described fuselage (1) gradually;
Described wing (2) is have 1 �� of established angle, 5 �� of leading edge sweeps, medium aspect ratio, the tapered wing that adopts the asymmetric midsetwing with camber high speed aerofoil profile to arrange, its wing tip place is provided with the trousers adaptive with aerofoil profile, and described wing (2) outside trailing edge is provided with aileron;
Described horizontal tail (4) is have 30 �� of inverted diherdrals, medium aspect ratio, symmetrical airfoil, trailing edge with the trapezoidal horizontal tail of elevator;
Described vertical fin (3) is have 40 �� of leading edge sweeps, low aspect ratio, symmetrical airfoil, trapezoidal vertical fin with rudder;
Described vertical fin (3) and described horizontal tail (4) form rearmounted inverted Y-shaped layout empennage.
2. a kind of target drone that can realize high maneuver according to claim 1, is characterized in that: described wing (2) adopts the relative chord length of maximum gauge to be the laminar flow airfoil of 8%; Described horizontal tail (4) adopts the relative chord length of maximum gauge to be the symmetrical airfoil of 8%; Described vertical fin (3) adopts the relative chord length of maximum gauge to be the symmetrical airfoil of 8%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620030092.2U CN205300398U (en) | 2016-01-13 | 2016-01-13 | Can realize big power -driven target drone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620030092.2U CN205300398U (en) | 2016-01-13 | 2016-01-13 | Can realize big power -driven target drone |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205300398U true CN205300398U (en) | 2016-06-08 |
Family
ID=56475115
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620030092.2U Withdrawn - After Issue CN205300398U (en) | 2016-01-13 | 2016-01-13 | Can realize big power -driven target drone |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205300398U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105486177A (en) * | 2016-01-13 | 2016-04-13 | 北京金朋达航空科技有限公司 | Target drone capable of achieving great maneuver |
| EP3751227A4 (en) * | 2018-11-26 | 2021-11-10 | GFA Aviation Technology Beijing Co., Ltd. | Stealth large maneuvering target aircraft and control method for stealth large maneuvering target aircraft |
-
2016
- 2016-01-13 CN CN201620030092.2U patent/CN205300398U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105486177A (en) * | 2016-01-13 | 2016-04-13 | 北京金朋达航空科技有限公司 | Target drone capable of achieving great maneuver |
| CN105486177B (en) * | 2016-01-13 | 2017-03-01 | 北京金朋达航空科技有限公司 | A kind of target drone enabling high maneuver |
| EP3751227A4 (en) * | 2018-11-26 | 2021-11-10 | GFA Aviation Technology Beijing Co., Ltd. | Stealth large maneuvering target aircraft and control method for stealth large maneuvering target aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160608 Effective date of abandoning: 20171114 |
|
| AV01 | Patent right actively abandoned |