CN209588848U - A kind of high stealthy target drone of high speed high maneuver - Google Patents
A kind of high stealthy target drone of high speed high maneuver Download PDFInfo
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- CN209588848U CN209588848U CN201920165474.XU CN201920165474U CN209588848U CN 209588848 U CN209588848 U CN 209588848U CN 201920165474 U CN201920165474 U CN 201920165474U CN 209588848 U CN209588848 U CN 209588848U
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- fuselage
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- empennage
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Abstract
The utility model discloses a kind of high stealthy target drones of high speed high maneuver, comprising: fuselage, wing, engine, empennage and S curved intake port；The leading edge sweep of wing and the leading edge sweep of empennage are identical.The aileron leading edge of trailing edge is parallel with trailing edge；The elevator leading edge of empennage rear is parallel with empennage rear；The tangential direction of the end of S curved intake port is parallel with fuselage axis, and end outlet is connect with engine intake.The utility model realizes the flight of high subsonic speed using the lesser aerodynamic arrangement's design of resistance；High stealthy flight is realized using the methods of the wave crest number for reducing the target drone radar wave that radar receives when by radar illumination and the reflection sources for reducing radar wave；The offline mode for rolling inverted flight using half guarantees that the stable method of engine charge realizes high maneuver flight.Mach Number Never To Be Exceeded can reach 0.9, and in air intake duct flight downward, motor-driven overload can reach 6g+, and in air intake duct flight upward, RCS characteristic is better than 0.01m2。
Description
Technical field
The utility model belongs to unmanned plane field, is related to a kind of high stealthy target drone of high speed high maneuver.
Background technique
Target drone is mainly used for when military exercises or weapon-shooting are tested simulation enemy army's aircraft or attacks guided missile, is all kinds of
Type cannon or guided missile system provide imaginary target and shooting machine meeting, and the component that simultaneously can be used for military spacecraft system is surveyed
Examination.In order to improve army's military combat ability and further increase military technology strength, each military power, the world is all had developed
The target drone of various variety classes and performance, with being showing improvement or progress day by day for aeronautical technology, especially some six generation of military power, world machines
Gradually military service, new requirement is had also been proposed to target drone technical indicator, in addition to the high-altitude high speed performance of traditional target drone, high maneuver and
High stealthy index is also at the essential option of advanced target drone.The target drone product of the country mostly can only the equal two generation machines of simulated altitude high speed
Target property.It is domestic to there is no the target drone product for taking into account high maneuver (5g~7g) and Gao Yinshen (RCS ≯ 0.01m2) at present.
Summary of the invention
The purpose of this utility model is that in view of the deficiencies of the prior art, providing a kind of high stealthy target of high speed high maneuver
Machine.
The purpose of this utility model is achieved through the following technical solutions: a kind of high stealthy target drone of high speed high maneuver,
It include: fuselage, wing, engine, empennage and S curved intake port；The rear of each wing is provided with aileron, and the rear of empennage is set
It is equipped with elevator.The leading edge of aileron and the rear of wing are parallel；The leading edge of elevator and the rear of empennage are parallel；
Fuselage is divided into three parts: the forebody with revolution structure, the middle fuselage and rear body of cylindrical structure；It is described
Engine is mounted on rear body, the central axial direction of the power direction of engine along the fuselage.
Wing is tapered airfoil, and leading edge sweep is 30~40 °, and established angle 0, aspect ratio are 4~5, are located in fuselage
Portion, wing root and wingtip are all made of symmetrical laminar flow airfoil, and root relative thickness of airfoil is 12%~14%, and taper aerofoil profile is relatively thick
Degree is 8%~10%, and wing root portion combines together with fuselage；
Empennage is tapered airfoil, and leading edge sweep is identical as leading edge of a wing angle of sweep, and aspect ratio is 1~2, relative thickness of airfoil
It is 10~12%；
The tangential direction of the end of S curved intake port is parallel with fuselage axis, and end outlet is connect with engine intake.
Further, S curved intake port lip is crescent, has wedge to separate between lip and fuselage, S curved intake port fuselage
There is radome fairing between exterior portion and fuselage.
Further, engine is small sized turbine jet engine.
Further, the wingtip portion of wing has and the matched rectification bulge of wingtip aerofoil profile.
Further, empennage uses vee tail, and angle is 90 degree, and empennage is symmetrical about the longitudinally asymmetric face of fuselage.S is bent into
The same side of air flue and empennage installation fuselage.
The target drone realizes high maneuver in S curved intake port flight downward；In S curved intake port flight upward, realize high
It is stealthy.
The utility model has the beneficial effects that: the utility model is small-sized using the lesser aerodynamic arrangement's design outfit of resistance
The flight of turbojet realization high subsonic speed；Using the reduction target drone radar wave that radar receives when by radar illumination
Wave crest number and reduce the methods of the reflection sources of radar wave and realize high stealthy flight；The offline mode for rolling inverted flight using half,
Guarantee that the stable method of engine charge realizes high maneuver flight.
When being equipped with small sized turbine jet engine using the target drone of above-mentioned layout designs, Mach Number Never To Be Exceeded can reach 0.9, In
Motor-driven overload can reach 6g+ when air intake duct flight downward, and in air intake duct flight upward, RCS characteristic is better than 0.01m2。
Detailed description of the invention
Fig. 1 is target drone aerodynamic configuration figure；
Fig. 2 is target drone top view；
Fig. 3 is S curved intake port position；
Fig. 4 is S curved intake port main view；
Offline mode when Fig. 5 is high maneuver and climbs；
Fig. 6 is offline mode when taking off, land and simulate high Stealthy Target；
Fig. 7 is the schematic diagram using the target drone of X-type empennage；
Fig. 8 is the main view of target drone shown in Fig. 7.
Specific embodiment
The utility model is designed using highly swept wing tail and streamline fuselage, aircraft can be made in Mach
Resistance is smaller when number is between 0.6~0.9, and assembly small sized turbine jet engine can realize the high-speed flight of aircraft；
Identical by using wing, empennage leading edge sweep, aileron leading edge is parallel with trailing edge, elevator leading edge and tail
The wave crest number that radar receives when the parallel design of wing rear reduces radar illumination aircraft, and when doing high stealthy flight
Air intake duct flies upward, and fuselage has blocked radar to the visual field of air intake duct, reduces reflection of the air inlet to radar wave, thus real
High stealthy purpose is showed；
By using the offline mode of aircraft rolling 180 degree inverted flight, downward, air inlet stream incoming flow is equal for air intake duct at this time
It is even, be conducive to engine stabilizer work, the high maneuver of 5g~7g overload may be implemented using the target drone of above-mentioned layout designs.
Institute's utility model target drone takes off mode as rocket assist, and when taking off, S curved intake port 7 flies upward；It climbs to one
Level accelerates after determining height, reaches rolling 180 degree after certain speed, and S curved intake port 7 flies downward to be continued to climb, when simulation is big
S curved intake port 7 flies downward when maneuvering flight, and air intake duct is below fuselage at this time, and the air-flow at air inlet is relatively uniform, favorably
Engine stabilizer works when target drone does lasting high maneuver；The target drone rolling 180 degree S curved intake port 7 when simulating high Stealth
It flies upward, air intake duct is blocked in body upper by streamline fuselage at this time, reduces the scattering part of radar, to improve
Stealth Fighter；The target drone way of recycling is parachuting aerating capsule, and empennage 6 is upward upon recovery.
Below with reference to embodiment, the utility model is described in further detail.
Embodiment one
As shown in Figure 1, a kind of high stealthy target drone of high speed high maneuver, comprising: fuselage 1, wing 2, engine 4, empennage 6 with
And S curved intake port 7；The rear of each wing 2 is provided with aileron 3, and the rear of empennage 6 is provided with lifting/rudder 5.Aileron 3
Leading edge is parallel with the rear of wing 2；The leading edge of elevator 5 is parallel with the rear of empennage 6；
Fuselage 1 divides for three parts: the forebody with revolution structure, the middle fuselage and rear body of cylindrical structure；Institute
It states engine 4 and is mounted on rear body, the central axial direction of the power direction of engine 4 along the fuselage 1.
Wing 2 uses 30 degree of leading edge sweeps, and zero installation angle, the tapered airfoil that aspect ratio is 4 are located at 1 middle part of fuselage,
Wing root and wingtip are all made of symmetrical laminar flow airfoil, and root relative thickness of airfoil is 12%, and taper relative thickness of airfoil is 10%,
Wing root portion combines together with fuselage；
Empennage 6 uses vee tail, and leading edge sweep is identical as 2 leading edge sweep of wing, using the ladder of low aspect ratio 2
The shape wing, relative thickness of airfoil 10%；
The tangential direction of the end of S curved intake port 7 is parallel with fuselage axis, and end outlet is connect with engine intake.
Embodiment two
As shown in FIG. 7 and 8, the high stealthy target drone of a kind of high speed high maneuver, comprising: fuselage 1, wing 2, engine 4, empennage
6 and S curved intake port 7；The rear of each wing 2 is provided with aileron 3, and the rear of empennage 6 is provided with lifting/rudder 5.Aileron
3 leading edge is parallel with the rear of wing 2；The leading edge of elevator 5 is parallel with the rear of empennage 6；
Fuselage 1 divides for three parts: the forebody with revolution structure, the middle fuselage and rear body of cylindrical structure；Institute
It states engine 4 and is mounted on rear body, the central axial direction of the power direction of engine 4 along the fuselage 1.
Wing 2 uses 40 degree of leading edge sweeps, and zero installation angle, the tapered airfoil that aspect ratio is 5 are located at 1 middle part of fuselage,
Wing root and wingtip are all made of symmetrical laminar flow airfoil, and root relative thickness of airfoil is 14%, and taper relative thickness of airfoil is 12%,
Wing root portion combines together with fuselage；
Empennage 6 uses X-type empennage, and leading edge sweep is identical as 2 leading edge sweep of wing, using the ladder of low aspect ratio 2
The shape wing, relative thickness of airfoil 12%；
The tangential direction of the end of S curved intake port 7 is parallel with fuselage axis, and end outlet is connect with engine intake.
Small sized turbine jet engine is equipped with using the target drone of above-mentioned aerodynamic arrangement design, passes through wind tunnel test and engine
The data that test obtains can reach by the maximum flight Mach number of two target drone of simulation calculation embodiment one and embodiment
0.9, in S 7 flight downward of curved intake port, sustained maneuver overload is all satisfied 6g+, passes through the RCS of embodiment one and embodiment two spy
Property test, in S 7 flight upward of curved intake port, RCS characteristic is superior to 0.01m2。
Elevator 5 described in the utility model generally also can be used as rudder use.
As a preferred option, the utility model can use vee tail, and angle is 90 degree or X-type empennage, when using V
When type tail, the same side of S curved intake port 7 and the installation fuselage 1 of empennage 6 is conducive to air inlet and part tail when high stealthy flight
The wing is blocked by fuselage, reduces complete machine to the reflection sources of radar wave.
In the utility model, existing S curved intake port can be used.Lip is crescent, there is point between lip and fuselage
It splits and separates, the fuselage boundary-layer air-flow for reducing low energy enters air intake duct, has between the curved intake port fuselage outer side part S and fuselage
Radome fairing reduces resistance when flight to further increase the slickness of complete machine, and in the utility model, engine 4 can be small
Type turbojet is conducive to the advantage for remaining to overcome target drone resistance when flight under high subsonic speed.
In the utility model, as a preferred option, the wingtip portion of wing 2 have with the matched rectification bulge of wingtip aerofoil profile,
Advantageously reduce the vortex energy loss of wing tip.
Above-described embodiment is the explanation to the utility model, is not the restriction to the utility model, and any pair of sheet is practical new
Scheme after type simple transformation belongs to the protection scope of the utility model.
Claims (5)
1. a kind of high stealthy target drone of high speed high maneuver characterized by comprising fuselage (1), wing (2), engine (4), tail
The wing (6) and S curved intake port (7)；The rear of each wing (2) is provided with aileron (3), and the rear of empennage (6) is provided with lifting
Rudder (5)；The leading edge of aileron (3) is parallel with the rear of wing (2)；The leading edge of elevator (5) is parallel with the rear of empennage (6)；
Fuselage (1) is divided into three parts: the forebody with revolution structure, the middle fuselage and rear body of cylindrical structure；It is described
Engine (4) is mounted on rear body, the central axial direction of the power direction of engine (4) along the fuselage (1)；
Wing (2) is tapered airfoil, and leading edge sweep is 30 ~ 40 °, and established angle 0, aspect ratio are 4 ~ 5, are located in fuselage (1)
Portion, wing root and wingtip are all made of symmetrical laminar flow airfoil, and root relative thickness of airfoil is 12% ~ 14%, taper relative thickness of airfoil
It is 8% ~ 10%, wing root portion and fuselage one；
Empennage (6) is tapered airfoil, and leading edge sweep is identical as wing (2) leading edge sweep, and aspect ratio is 1 ~ 2, and aerofoil profile is relatively thick
Degree is 10 ~ 12%；
The tangential direction of the end of S curved intake port (7) is parallel with fuselage axis, and end outlet is connect with engine intake.
2. the high stealthy target drone of high speed high maneuver according to claim 1, which is characterized in that S curved intake port (7) lip is
Crescent has wedge to separate between lip and fuselage, has radome fairing between the curved intake port fuselage outer side part S and fuselage.
3. the high stealthy target drone of high speed high maneuver according to claim 1, which is characterized in that engine (4) is small-sized whirlpool
Take turns jet engine.
4. the high stealthy target drone of high speed high maneuver according to claim 1, which is characterized in that the wingtip portion of wing (2) has
With the matched rectification bulge of wingtip aerofoil profile.
5. the high stealthy target drone of high speed high maneuver according to claim 1, which is characterized in that empennage (6) uses V-type tail
The wing, angle are 90 degree, and empennage is symmetrical about the longitudinally asymmetric face of fuselage；S curved intake port (7) is same with empennage (6) installation fuselage (1)
Side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920165474.XU CN209588848U (en) | 2019-01-30 | 2019-01-30 | A kind of high stealthy target drone of high speed high maneuver |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920165474.XU CN209588848U (en) | 2019-01-30 | 2019-01-30 | A kind of high stealthy target drone of high speed high maneuver |
Publications (1)
| Publication Number | Publication Date |
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| CN209588848U true CN209588848U (en) | 2019-11-05 |
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ID=68381679
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|---|---|---|---|
| CN201920165474.XU Active CN209588848U (en) | 2019-01-30 | 2019-01-30 | A kind of high stealthy target drone of high speed high maneuver |
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| Country | Link |
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2019
- 2019-01-30 CN CN201920165474.XU patent/CN209588848U/en active Active
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