CN107228750B - Free flight model control surface deflection device - Google Patents
Free flight model control surface deflection device Download PDFInfo
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- CN107228750B CN107228750B CN201710334576.5A CN201710334576A CN107228750B CN 107228750 B CN107228750 B CN 107228750B CN 201710334576 A CN201710334576 A CN 201710334576A CN 107228750 B CN107228750 B CN 107228750B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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Abstract
The present invention relates to free flight model control surface deflection devices, including rudder face component, pivot block, compressed spring, pull pin and the inclined control block of rudder, two rudder faces in left and right are connected in the mounting hole of the same pivot block by the boss of respective rudderpost and rudderpost end, and it is screwed into pivot block circular hole using screw, fixed rudder face and pivot block, prevent rudder face from falling off, rudder face component and pivot block can be rotated around the axis of rudderpost；There is pivot block angle control plane on pivot block, pivot block has pivot block blind hole, and compressed spring is put into pivot block blind hole, and compressed spring one end withstands on pivot block blind via bottom, and the other end is fixed；There is the inclined control plane of rudder in the inclined control block of rudder, the control surface deflection angle of rudder face is adjusted in the upper-lower height for adjusting the inclined control plane of rudder, free flight model control surface deflection device of the present invention overcomes the problems such as wind tunnel free-flight model is small, mechanism design difficulty is big, solves control surface deflection triggering and angle control problem of the model during wind tunnel free-flight is without support.
Description
Technical field
The present invention relates to Machine Design and wind tunnel test more particularly to a kind of free flight model control surface deflection devices, belong to
Machine Design and Aerospace Engineering field.
Background technique
Rudder face is the main control plane of aircraft, and in order to obtain enough maneuverabilities, big multi-aircraft relies on control surface deflection
Various control torque is provided, but with the increase of flying speed, the inclined pneumatic efficiency of rudder can be decreased obviously, directly threat aircraft
Flight stability and mobility.
Existing a variety of hypersonic aircrafts still use rudder face to provide control moment.For hypersonic aircraft rudder face
Efficiency, existing main experimental research means be using the permanent technology such as static force measurement, though such technology can carry out it is higher
Mach number test, but control and movement Coupled Dynamic problem after control surface deflection are not considered.Wind-tunnel developed in recent years is virtual
Flight test technology solves drawbacks described above very well, and tradition wind tunnel test is extended to flowing, flight, control integration height.
But wind-tunnel virtual flight experimental technique existing capabilities are only capable of accomplishing subsonic speed.From the foregoing, it will be observed that the prior art is directed to supersonic speed and height
The Research Ability of the rudder face control effect problem of supersonic aircraft is limited, and it is superb when rudder face control effect exactly
It is easiest to go wrong.Therefore it is superb to study to be badly in need of a kind of experimental technique for combining control surface deflection with aircraft coupled motions
Velocity of sound vehicle rudder dynamic control effect problem, and development experiments technology needs matched experimental rig.
Summary of the invention
It is an object of the invention to overcome the above-mentioned deficiency of the prior art, a kind of free flight model control surface deflection dress is provided
It sets, which overcomes the problems such as wind tunnel free-flight model is small, mechanism design difficulty is big, solves model in wind-tunnel freedom
Fly without the control surface deflection triggering and angle control problem during support.
What above-mentioned purpose of the invention was mainly achieved by following technical solution:
Free flight model control surface deflection device, including rudder face component, pivot block, compressed spring, pull pin and rudder controls partially
Block, wherein rudder face component is two, is symmetrically mounted on pivot block by rudder face shaft, compressed spring is mounted on inside pivot block
Blind hole in, through-hole is opened up in rudder face control block, hole of pulling pin is opened up on pivot block, when rudder face component is in initial deflection angle,
It pulls pin in the hole of pulling pin of the through-hole insertion pivot block of rudder face control block, compressed spring is in compressive state；It pulls pin after extraction,
Pivot block drives rudder face component to rotate jointly around the axis of rudder face shaft under the action of compressed spring thrust, until pivot block
Angle control plane encounter the inclined control plane of rudder of the inclined control block of rudder.
In above-mentioned free flight model control surface deflection device, the rudder face component includes shaft and rudder face, one end of shaft
It is fixedly connected with rudder face, the other end of shaft forms boss, is fixedly connected by the boss with pivot block.
In above-mentioned free flight model control surface deflection device, the boss is by using two parallel planes to shaft
Cylindrical end carries out cutting formation, and described two parallel planes are parallel with the plane of shaft axis is crossed, and about the plane pair
Claim.
In above-mentioned free flight model control surface deflection device, the shaft mounting hole of perforation is opened up on the pivot block, and turn
Each on the upper and lower end face of shaft mounting hole symmetrically to open up two through-holes, the boss of the shaft is stretched from the both ends of shaft mounting hole respectively
Enter in mounting hole, and be screwed into the through-hole of pivot block by screw, realizes the fixation of rudder face component and pivot block.
It further include bottom plate in above-mentioned free flight model control surface deflection device, compressed spring one end is fixed on the bottom plate
On, the other end withstands on the blind via bottom opened up inside pivot block, and the inclined control block of rudder is fixedly mounted on bottom plate.
In above-mentioned free flight model control surface deflection device, installation is opened up on the shaft block body of the blind via bottom side
Hole forms angle control plane on the pivot block body surface of the other side, and shaft block body opens up hole of pulling pin.
In above-mentioned free flight model control surface deflection device, the inclined control block of rudder is the cavity body structure of open at one end, institute
The sidewall plane of cavity body structure is stated as the inclined control plane of rudder, ontology one end of the angled control plane of pivot block band is contained in the chamber
In body structure, when pivot block rotates, the angle control plane of pivot block and the rudder of the inclined control block of rudder control face contact partially.
In above-mentioned free flight model control surface deflection device, the bottom of the inclined control block cavity body structure of rudder opens up through-hole,
It pulls pin in the hole of pulling pin of through-hole insertion pivot block.
In above-mentioned free flight model control surface deflection device, the axis pulled pin crosses the mass center of free flight model；Using
Silk thread will pull pin to be connected with external emission device, and when on-test, free flight model is launched device and is emitted in flow field,
When silk thread reaches its limitation of length, pulls pin and be pulled out.
In above-mentioned free flight model control surface deflection device, rudder face is adjusted in the upper-lower height by adjusting the inclined control plane of rudder
The control surface deflection angle of component；By using a variety of control surface deflection speed of the compressed spring analog of different elastic force.
Compared with prior art, the present invention has the following advantages:
(1), innovative design of the present invention free flight model control surface deflection device, the device include rudder face component, pivot block,
Compressed spring is pulled pin and the inclined control block of rudder by the ingehious design to control surface deflection apparatus structure overcomes wind tunnel free-flight
The problems such as model is small, mechanism design difficulty is big solves control surface deflection triggering of model during wind tunnel free-flight is without support
And angle controls problem；
(2), the deflection angle of the controllable pivot block of angle of rudder reflection control plane and rudder face in the present invention, is controlled partially by adjusting rudder
The distance of face to axially bored line of pulling pin can achieve the purpose that adjusting rudder face drift angle, can realize simulation by using different elastic springs
Different angle of rudder reflection speed or the purpose of rudder inclined time.
(3), sleeve mechanism of the present invention is by control of pulling pin, and compressed spring will push pivot block and rudderpost one after extraction of pulling pin
Rotation is played, two rudder faces in left and right are connected by the same pivot block, it is ensured that the real time synchronization of two rudder faces rotation, to keep away
Exempt from the asynchronous caused aerodynamic interference of left and right rudder kick；
(4), present invention axially bored line of pulling pin crosses model mass center, can utmostly reduce movement of pulling pin to model free movement
It influences.
(5), spring still has part thrust after control surface deflection of the present invention, to prevent rudder face inclined next time in Aerodynamic force action.
Detailed description of the invention
Fig. 1 is rudder face position view in free flight model of the present invention；
Fig. 2 is control surface deflection apparatus structure schematic diagram of the present invention；
Fig. 3 is rudder face component structure diagram of the present invention；
Fig. 4 is pivot block structural schematic diagram of the present invention；
Fig. 5 is the inclined control block structural schematic diagram of rudder of the present invention；
Fig. 6 is structural scheme of mechanism before control surface deflection device of the present invention triggers；
Fig. 7 is structural scheme of mechanism after control surface deflection device of the present invention triggering.
Specific embodiment
The present invention is described in further detail in the following with reference to the drawings and specific embodiments:
It is as shown in Figure 1 rudder face position view in free flight model of the present invention, rudder face component 1 is located at free flight model two
The back segment of side aerofoil.It is illustrated in figure 2 control surface deflection apparatus structure schematic diagram of the present invention, control surface deflection device of the present invention includes rudder
Face component 1, pivot block 2, compressed spring 5, the inclined control block 3 of 4, rudder of pulling pin and bottom plate 6 (do not provide compressed spring 5 and bottom in Fig. 2
Plate 6).
It is illustrated in figure 3 rudder face component structure diagram of the present invention, rudder face component 1 is two, as seen from the figure rudder of the present invention
Face component 1 includes shaft 1-1 and rudder face 1-3, and one end of shaft 1-1 is fixedly connected with rudder face 1-3 or integrated molding, shaft 1-
1 other end forms boss 1-2, is fixedly connected by boss 1-2 with pivot block 2.
Boss 1-2 carries out cutting formation by using cylindrical end of two parallel planes to shaft 1-1, and two parallel
Plane and the plane of shaft 1-1 axis excessively are parallel and symmetrical about the plane, i.e., between two parallel planes and the plane
It is equidistant.Boss 1-2 is approximate rectangle boss formed by cutting, is opened up on the rectangle boss and pivot block 2
Shaft mounting hole 2-2 cooperation achieves a fixed connection.
It is illustrated in figure 4 pivot block structural schematic diagram of the present invention, blind hole 2-5, the side blind hole 2-5 are opened up inside pivot block 2
Shaft block body on open up the shaft mounting hole 2-2 of perforation, and each on the upper and lower end face of shaft mounting hole 2-2 symmetrically open up two
The boss 1-2 of a circular through hole 2-1, the shaft 1-1 of two rudder face components 1 protrude into peace from the both ends of shaft mounting hole 2-2 respectively
It fills in the 2-2 of hole, and is screwed into the through-hole 2-1 of pivot block by screw, realize the fixation of rudder face component 1 and pivot block 2.Mounting hole
2-2 be and the matched squarish hole of boss 1-2 shape.I.e. the two rudder face components 1 in left and right by respective rudderpost 1-1 and
The rectangle boss 1-2 of the end rudderpost 1-1 is connected in the square hole 2-2 of the same pivot block 2, and is screwed into pivot block using screw
In circular hole 2-1, fixed rudder face 1 and pivot block 2 prevent rudder face 1 from falling off, and rudder face component 1 and pivot block 2 can be around the axis of rudderpost 1-1
Line rotation.
Angle control plane 2-3 is formed on 2 body surface of pivot block of the other side blind hole 2-5, and is opened up on 2 ontology of pivot block
Pull pin hole 2-4, and the through-hole 3-2 that 4 pass through rudder face control block 3 that pulls pin is inserted into the hole 2-4 that pulls pin of pivot block 2.
5 one end of compressed spring is fixed on bottom plate 6, and the other end withstands on the bottom blind hole 2-5 opened up inside pivot block 2, and
The inclined control block 3 of rudder is fixedly mounted on bottom plate 6.As shown in Figure 6.
It is illustrated in figure 5 the inclined control block structural schematic diagram of rudder of the present invention, as seen from the figure inclined 3 internal notches of control block of rudder, shape
At the cavity body structure of open at one end, the sidewall plane of cavity body structure is as the inclined control plane 3-1 of rudder, and pivot block 2 is with angled control
Ontology one end of face 2-3 is contained in the cavity body structure, and when pivot block 2 rotates, the angle control plane 2-3 and rudder of pivot block 2 are inclined
The inclined control plane 3-1 contact of the rudder of control block 3.The rudder of rudder face component 1 is adjusted in upper-lower height by adjusting the inclined control plane 3-1 of rudder
Deflecting facet angle；By using a variety of control surface deflection speed of 5 analog of compressed spring of different elastic force.
The bottom of inclined 3 cavity body structure of control block of rudder opens up through-hole 3-2, pulls pin 4 across through-hole 3-2 insertion pivot block 2
It pulls pin in the 2-4 of hole, 4 axis of pulling pin crosses the mass center of free flight model.
The free flight model control surface deflection device course of work of the present invention is as follows:
It is illustrated in figure 6 structural scheme of mechanism before control surface deflection device of the present invention triggers, before on-test, will pull pin 4 passes through
In the hole 2-4 that pulls pin of the through-hole 3-2 insertion pivot block of rudder face control block, the rudder face component 1 of free flight model is in deflection at this time
Initial angle, while compressed spring 5 is in its larger compressive state, 4 axis of pulling pin cross model mass center, will pull pin 4 using silk thread
It is connected with external emission device.
It is illustrated in figure 7 structural scheme of mechanism after control surface deflection device of the present invention triggering, when on-test, free flight model quilt
Emitter is emitted in flow field, and when silk thread reaches its limitation of length, pulling pin 4 is pulled out, and due to pulling pin, 4 axis cross mass center,
The process of pulling pin can utmostly reduce the influence to model sport posture.Pull pin 4 be pulled out after, pivot block 2 is pushed away in compressed spring 5
Rudder face component 1 is driven to rotate jointly around the axis of shaft 1-1 under the action of power, until 2 angle control plane 2-3 of pivot block encounters
Until the inclined control plane 3-1 of rudder, the deflection angle of rudder face component 1 is the inclined final position of rudder at this time, and compressed spring 5 still has part at this time
Thrust can prevent rudder face inclined next time in Aerodynamic force action, control surface deflection off-test.
The present invention has the following main features and difficult point:
1) model need to carry out control surface deflection work in complete free state.The main feature of free flight model is exactly model
Without support, model sport is noiseless, but this also proposes compared with hang-up trigger mechanism design；
2) free flight model size is limited by the effective flow field regions of wind-tunnel and emission system performance, moulded dimension generally compared with
It is small.In present invention test, free flight model shape full-size ≈ 100mm × 80mm × 40mm, due to aircraft wing and head
Portion is relatively thin, and part cannot be utilized by ignoring, and can be used to install the space of actuation mechanism much smaller than above-mentioned size, modelling difficulty
Increase；
3) model actuation mechanism need to be placed on inside model.Wind tunnel free flight test is different from static force measurement test, the latter
Its actuation mechanism is mountable on the outside of model, and free flight model itself is small in size, and actuation mechanism be necessarily mounted at again it is narrow
Inside model, modelling difficulty is equally increased；
4) free flight model needs to have similar quality distribution with realistic model.These characteristics include model mass center
And inertia value, therefore in the requirement for carrying out that model quality parameter need to be taken into account while actuation mechanism design inside model, it increases
The difficulty of modelling；
5) the present invention claims model rudder faces can simulate a variety of control surface deflection speed and a variety of rudder face expanded angles, and rudder face
After deflection for guarantee angle of rudder reflection, mechanism need to have resist tunnel airstream ability to function, prevent rudder face return partially, modelling difficulty into
One step increases.
It is asked in view of the above-mentioned problems, the free flight model control surface deflection device very good solution of innovative design of the present invention is above-mentioned
Topic, sleeve mechanism is by control of pulling pin, and compressed spring will push pivot block after extraction of pulling pin and rudderpost rotates together, left and right two
Rudder face is connected by the same pivot block, it is ensured that the real time synchronization of two rudder faces rotation, to avoid left and right rudder kick not
Synchronize caused aerodynamic interference.Angle of rudder reflection control plane can control the deflection angle of pivot block and rudder face, be controlled partially by adjusting rudder
The distance of face to axially bored line of pulling pin can achieve the purpose that adjust rudder face drift angle.Simulation can be realized by using different elastic springs
Different angle of rudder reflection speed or the purpose of rudder inclined time.Axially bored line of pulling pin crosses model mass center, can utmostly reduce movement pair of pulling pin
The influence of model free movement.Spring still has part thrust after control surface deflection, to prevent rudder face inclined next time in Aerodynamic force action.
The above, optimal specific embodiment only of the invention, but scope of protection of the present invention is not limited thereto,
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art,
It should be covered by the protection scope of the present invention.
The content that description in the present invention is not described in detail belongs to the well-known technique of professional and technical personnel in the field.
Claims (8)
1. free flight model control surface deflection device, it is characterised in that: including rudder face component (1), pivot block (2), compressed spring
(5), it pulls pin (4) and the inclined control block of rudder (3), wherein rudder face component (1) is two, is symmetrically installed by rudder face shaft (1-1)
On pivot block (2), compressed spring (5) is mounted in the internal blind hole (2-5) of pivot block (2), and rudder face control block opens up on (3)
Through-hole (3-2) opens up hole of pulling pin (2-4) on pivot block (2), when rudder face component (1) is in initial deflection angle, pull pin (4) wear
It crosses in the hole of pulling pin (2-4) of through-hole (3-2) insertion pivot block (2) of rudder face control block (3), compressed spring (5) is in compression shape
State；It pulls pin after (4) extraction, pivot block (2) drives rudder face component (1) jointly around rudder under the action of compressed spring (5) thrust
The axis of face shaft (1-1) deflects, until the rudder that the angle control plane (2-3) of pivot block (2) encounters the inclined control block of rudder (3) is controlled partially
Face (3-1) processed；
It further include bottom plate (6), compressed spring (5) one end is fixed on the bottom plate (6), and it is internal that the other end withstands on pivot block (2)
The bottom blind hole (2-5) opened up, and the inclined control block of rudder (3) is fixedly mounted on bottom plate (6)；
The inclined control block of rudder (3) is the cavity body structure of open at one end, and the sidewall plane of the cavity body structure controls partially as rudder
Face (3-1), pivot block (2) are contained in the cavity body structure with ontology one end of angled control plane (2-3), pivot block (2)
When rotation, the angle control plane (2-3) of pivot block (2) is contacted with the inclined control plane of rudder (3-1) of the inclined control block of rudder (3).
2. free flight model control surface deflection device according to claim 1, it is characterised in that: rudder face component (1) packet
Shaft (1-1) and rudder face (1-3) are included, one end of shaft (1-1) is fixedly connected with rudder face (1-3), the other end shape of shaft (1-1)
At boss (1-2), it is fixedly connected by the boss (1-2) with pivot block (2).
3. free flight model control surface deflection device according to claim 2, it is characterised in that: the boss (1-2) passes through
Cutting formation, described two parallel planes and excessively shaft are carried out using cylindrical end of two parallel planes to shaft (1-1)
The plane of (1-1) axis is parallel, and symmetrical about the plane.
4. free flight model control surface deflection device according to claim 2 or 3, it is characterised in that: on the pivot block (2)
The shaft mounting hole (2-2) of perforation is opened up, and each on the upper and lower end face of shaft mounting hole (2-2) symmetrically opens up two through-hole (2-
1), the boss (1-2) of the shaft (1-1) protrudes into mounting hole (2-2) from the both ends of shaft mounting hole (2-2) respectively, and leads to
It crosses screw to be screwed into the through-hole (2-1) of pivot block, realizes the fixation of rudder face component (1) and pivot block (2).
5. free flight model control surface deflection device according to claim 1, it is characterised in that: blind hole (2-5) bottom
It is opened up mounting hole (2-2) on pivot block (2) ontology of side, forms angle control on pivot block (2) body surface of the other side
Face (2-3), and pivot block (2) ontology opens up hole of pulling pin (2-4).
6. free flight model control surface deflection device according to claim 1, it is characterised in that: the inclined control block of rudder (3)
The bottom of cavity body structure opens up through-hole (3-2), pull pin (4) across the through-hole (3-2) insertion pivot block (2) the hole (2- that pulls pin
4) in.
7. free flight model control surface deflection device described according to claim 1~one of 3, it is characterised in that: pull pin (4)
Axis cross the mass center of free flight model；It will be pulled pin (4) using silk thread and external emission device connects, when on-test,
Free flight model is launched device and is emitted in flow field, when silk thread reaches its limitation of length, pull pin (4) be pulled out.
8. free flight model control surface deflection device described according to claim 1~one of 3, it is characterised in that: by adjusting rudder
The control surface deflection angle of rudder face component (1) is adjusted in the upper-lower height of inclined control plane (3-1)；By using the compression of different elastic force
The a variety of control surface deflection speed of spring (5) analog.
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| CN201710334576.5A CN107228750B (en) | 2017-05-12 | 2017-05-12 | Free flight model control surface deflection device |
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| CN201710334576.5A CN107228750B (en) | 2017-05-12 | 2017-05-12 | Free flight model control surface deflection device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108318211A (en) * | 2018-01-21 | 2018-07-24 | 南京航空航天大学 | A kind of high-speed wind tunnel rotating model simultaneous test device |
| CN108583932A (en) * | 2018-01-21 | 2018-09-28 | 南京航空航天大学 | A kind of rudder face of adjustable deflection angle beats executive device partially |
| CN114261525B (en) * | 2021-12-30 | 2023-11-03 | 中国航天空气动力技术研究院 | Control surface deflection control and measurement system and method |
| CN114417578A (en) * | 2021-12-30 | 2022-04-29 | 中国航天空气动力技术研究院 | Deflection angle accurate positioning method and system of control surface automatic deflection mechanism |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH0972822A (en) * | 1995-09-07 | 1997-03-18 | Mitsubishi Heavy Ind Ltd | Wind tunnel testing apparatus |
| CN201126400Y (en) * | 2007-12-17 | 2008-10-01 | 中国航天空气动力技术研究院 | Novel aviation aerospace vehicle tunnel test model aerial rudder derivation angle fixture mechanism |
| CN101549754B (en) * | 2009-04-29 | 2012-05-23 | 北京航空航天大学 | A composite rotating fixed-wing aircraft and its design method |
| CN102305699A (en) * | 2011-05-19 | 2012-01-04 | 北京航空航天大学 | Wind tunnel experiment system for free flight model |
| CN104483089B (en) * | 2014-12-11 | 2017-03-15 | 中国航天空气动力技术研究院 | Full free flight shrapnel dispersion separation test system |
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