CN206648802U - A kind of pitching dynamic derivative experimental provision of tail vibration - Google Patents
A kind of pitching dynamic derivative experimental provision of tail vibration Download PDFInfo
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- CN206648802U CN206648802U CN201621418520.5U CN201621418520U CN206648802U CN 206648802 U CN206648802 U CN 206648802U CN 201621418520 U CN201621418520 U CN 201621418520U CN 206648802 U CN206648802 U CN 206648802U
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- decelerator
- gear frame
- balance
- derivative
- biasing post
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Abstract
A kind of pitching dynamic derivative experimental provision of tail vibration is the utility model is related to, motor is connected with decelerator, and decelerator is connected by ring flange with support；Decelerator front end connecting eccentric wheel, eccentric wheel are slided in the chute of gear frame, and gear frame is connected by arc-shaped slide rail, sliding block with support；Balance branch rod rear end is connected by Cone fit with gear frame；The both ends of spring angle balance connect with gear frame with support respectively.The utility model is a kind of tail vibration pitching dynamic derivative experimental provision, by designing special vibrating mechanism, gentle five COMPONENT BALANCE in spring angle day, the cross derivative that can measure the direct derivative of pitching and go off course direct derivative and induction of aircraft disclosure satisfy that wind tunnel experiment demand.
Description
Technical field
The present invention is a kind of pitching dynamic derivative experimental provision of tail vibration, and the pitching that can measure aircraft is directly led
Number and go off course direct derivative and the cross derivative of induction, belong to aviation aerodynamic force experimental technique field.
Background technology
Dynamic stability derivative abbreviation dynamic derivative, it is six Aerodynamic Coefficients of aircraft (three i.e. in three-dimensional cartesian coordinate system
Power and three moment coefficients) to aircraft attitude parameters time rate of change (p, q, r, α, β, dV/dt) derivative.Dynamic derivative is winged
Indispensable original aerodynamic parameter in row device guiding system, control system and dynamic quality analysis.Fly especially for space flight
Machine, airship, advanced feature military fighter aircraft, they will fly under High Angle of Attack, it will usually air-flow separation occur, whirlpool comes off
With rupture, longitudinal direction with transverse movement it is pneumatic sympathetic and sluggish phenomena such as, dynamic derivative then has bigger to aerodynamic characteristics of vehicle
Influence.
Tail vibration pitching dynamic derivative experimental provision can measure the direct derivative of pitching of aircraft, and driftage is directly led
Number and the cross derivative of induction.Existing pitching dynamic derivative experimental provision pole is motionless, and balance is done around aircraft center
Sinusoidal vibration, due to the aircraft of slender bodies, its inner space is narrow and small, and existing dynamic derivative device can not meet requirement of experiment.Should
Device realizes that pole, balance, aircraft surround the entirety sinusoidal vibration of aircraft center by designing special vibration switching mechanism,
Design the angular surveying that spring balance realizes aircraft simultaneously.
The content of the invention
The present invention is exactly to be directed to the deficiencies in the prior art, and is provided by using arc-shaped slide rail sliding block, five components
Its gentle spring balance can measure slender bodies aircraft and design provides a kind of pitching dynamic derivative balance device, can survey
The direct derivative of pitching and the direct derivative of driftage and the cross derivative of induction of aircraft are measured, disclosure satisfy that the demand of wind tunnel experiment.
The purpose of the technology of the present invention is achieved through the following technical solutions：
A kind of pitching dynamic derivative experimental provision of tail vibration is provided, the measurement apparatus includes motor (1), decelerator
(2), housing (3), spring (5), gear frame (6), hollow tapered sleeve (7), balance pole (8), five COMPONENT BALANCEs (9), sliding block (4),
Arc-shaped slide rail (10) and eccentric wheel (11)；
Motor (1), decelerator (2), gear frame (6), hollow tapered sleeve (7), sliding block (4) and arc-shaped slide rail (10) are arranged at
In housing (3), motor (1) couples with decelerator (2) power；Eccentric wheel (12) is connected on the output shaft of decelerator (2), and is led to
Cross bearings；Eccentric wheel (12) includes cylinder and biasing post, and described cylinder one end couples with the output shaft of decelerator (2),
Described biasing post is set on the periphery of the other end, and as cylinder rotates, described biasing post does ring motion；
Gear frame includes input frame, and the biasing post is inserted in the input frame, and the input frame A/F is more than
Eccentric wheel external diameter, the input frame open height are identical with biasing post external diameter；Described biasing post can be in the opening of input frame
In horizontally slip；Spring (5) is respectively equipped with the gear frame upper and lower ends, spring setting up and down forms spring angle day
It is flat；
Described gear frame is fixedly connected with a slide block, and described sliding block is slidably arranged between two arc-shaped slide rails；It is described
Sliding block be also fixedly connected with hollow tapered sleeve one end, the hollow tapered sleeve other end connection balance pole；The balance pole with
Five COMPONENT BALANCEs (9) are fixedly connected.
Five COMPONENT BALANCE topology layout forms are：Front and back position is laid out in three post beam forms, and center is laid out in cross
Beam form, foil gauge composition electric bridge is pasted on three post beams and rood beam, the input/output terminal of electric bridge is respectively and external controller
Relevant connection line end connects.
The operation principle of the present invention
The direct derivative of pitching of slender bodies aircraft is measured, the cross derivative of go off course direct derivative and induction is, it is necessary to design
A kind of tail vibrating mechanism, can make aircraft do the sinusoidal vibration of 1 degree of amplitude, and vibration is steady reliable.Measurement is needed to fly simultaneously
The aerodynamic loading of device, the vibration angle of aircraft.
Further, more specifically way is：The continuous rotary motion of the electronic eccentric shaft of motor reducer, lay on eccentric shaft deep
Ditch ball bearing, bearing are slided in the chute of gear frame, and gear frame is fixed on sliding block, by about on gear frame left and right directions
Beam, only there is the free degree in the vertical direction, gear frame can only be slided up and down with arc-shaped slide rail center.So eccentric wheel is continuous
Convert rotational motion moves up and down for chute, and then is converted into balance pole and does sinusoidal vibration around arc-shaped slide rail center.Pass through conjunction
The eccentric throw of reason design eccentric wheel, and choose the radius of turn of arc-shaped slide rail, it is possible to achieve five COMPONENT BALANCEs, aircraft are around arc
Sinusoidal vibration is done at slide rail center, and vibration angle is 1 degree.
Spring angle balance will realize the measurement FLIGHT VEHICLE VIBRATION angle under large deformation.Aircraft does 1 degree of sinusoidal vibration
When, the deformation of spring angle balance is about 12mm.Spring angle balance design can so meet Liang great into full of twists and turns beam form
Under deformation, meet with stresses and meet balance design requirement.Upper four foil gauges are pasted at balance beam center, form an electric bridge, first
The functional relation formula of angle amplitude and magnitude of voltage is obtained by loading.In test mould is obtained by measuring bridge voltage output
Type angle amplitude.
The COMPONENT BALANCE of pitching five is used for the aerodynamic loading of measurement model；Lift, pitching moment, side force, yawing, rolling
Torque.Five COMPONENT BALANCE front and back positions are laid out in three post beam forms, and center is laid out in rood beam form, can so realize day
Flat each first sensitivity matching, improves rolling moment member sensitivity.Five COMPONENT BALANCEs, one electric bridge of each member composition, realizes each vigour
The measurement of dynamic loading.
Advantage of the present invention
1, the present invention using tail vibration pitching dynamic stability derivatives device overall vibration topology layout, i.e., motor, decelerator, partially
Heart wheel, gear frame, arc-shaped slide rail sliding block, balance pole, five COMPONENT BALANCEs, spring angle day equality integrated connection form, accurately
The direct derivative of completion pitching, the cross derivative detection of go off course direct derivative and induction.
2, the present invention uses the full of twists and turns form of balance beam, and it is in special structure type to make spring angle balance.
3, for the present invention using rood beam topology layout among the post beam of both ends three, it is in special structure shape to make five COMPONENT BALANCEs
Formula.
4, design science of the present invention, reasonable, original, compact overall structure, small volume, low-power consumption, cost be cheap, can
Lean on, applicability and practicality are stronger, have preferable development prospect.
Brief description of the drawings
Fig. 1 is the lateral partial structurtes sectional view of the present invention；
Fig. 2 is the overall structure diagram of the present invention；
Fig. 3 is partial structural diagram；
Fig. 4 is another partial structural diagram；
Wherein：Motor (1), decelerator (2), housing (3), sliding block (4), spring (5), gear frame (6), hollow tapered sleeve (7),
Balance pole (8), five COMPONENT BALANCEs (9), arc-shaped slide rail (10), eccentric wheel (11).
Embodiment：
A kind of pitching dynamic derivative experimental provision of tail vibration is provided, the measurement apparatus includes motor (1), decelerator
(2), housing (3), spring (5), gear frame (6), hollow tapered sleeve (7), balance pole (8), five COMPONENT BALANCEs (9), sliding block (4),
Arc-shaped slide rail (10) and eccentric wheel (11)；
Motor (1), decelerator (2), gear frame (6), hollow tapered sleeve (7), sliding block (4) and arc-shaped slide rail (10) are arranged at
In housing (3), motor (1) couples with decelerator (2) power；Eccentric wheel (12) is connected on the output shaft of decelerator (2), and is led to
Cross bearings；Eccentric wheel (12) includes cylinder and biasing post, and described cylinder one end couples with the output shaft of decelerator (2),
Described biasing post is set on the periphery of the other end, and as cylinder rotates, described biasing post does ring motion；
Gear frame includes input frame, and the biasing post is inserted in the input frame, and the input frame A/F is more than
Eccentric wheel external diameter, the input frame open height are identical with biasing post external diameter；Described biasing post can be in the opening of input frame
In horizontally slip；Spring (5) is respectively equipped with the gear frame upper and lower ends, spring setting up and down forms spring angle day
It is flat；
Described gear frame is fixedly connected with a slide block, and described sliding block is slidably arranged between two arc-shaped slide rails；It is described
Sliding block be also fixedly connected with hollow tapered sleeve one end, the hollow tapered sleeve other end connection balance pole；The balance pole with
Five COMPONENT BALANCEs (9) are fixedly connected.
More particularly, arc-shaped slide rail (10) radius of turn is 600mm.
Further, spring angle balance (5) thickness is 1mm, high 42mm, long 9mm, and when extending 12mm, suffered stress is
100MPa。
Particularly, a diameter of 18mm of five COMPONENT BALANCEs.
Claims (1)
1. a kind of pitching dynamic derivative experimental provision of tail vibration, the measurement apparatus include motor (1), decelerator (2), housing
(3), spring (5), gear frame (6), hollow tapered sleeve (7), balance pole (8), five COMPONENT BALANCEs (9), sliding block (4), arc-shaped slide rail
And eccentric wheel (11) (10)；
Motor (1), decelerator (2), gear frame (6), hollow tapered sleeve (7), sliding block (4) and arc-shaped slide rail (10) are arranged at housing
(3) in, motor (1) couples with decelerator (2) power；Eccentric wheel (11) is connected on the output shaft of decelerator (2), and passes through axle
Hold support；Eccentric wheel (11) includes cylinder and biasing post, and described cylinder one end couples with the output shaft of decelerator (2), another
Described biasing post is set on the periphery at end, and as cylinder rotates, described biasing post does ring motion；
Gear frame includes input frame, and the biasing post is inserted in the input frame, and the input frame A/F is more than bias
External diameter is taken turns, the input frame open height is identical with biasing post external diameter；Described biasing post can be left in the opening of input frame
Right slip；Spring (5) is respectively equipped with the gear frame upper and lower ends, spring setting up and down forms spring angle balance；
Described gear frame is fixedly connected with a slide block, and described sliding block is slidably arranged between two arc-shaped slide rails；Described cunning
Block is also fixedly connected with hollow tapered sleeve one end, the hollow tapered sleeve other end connection balance pole；The balance pole with five points
Amount balance (9) is fixedly connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621418520.5U CN206648802U (en) | 2016-12-22 | 2016-12-22 | A kind of pitching dynamic derivative experimental provision of tail vibration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621418520.5U CN206648802U (en) | 2016-12-22 | 2016-12-22 | A kind of pitching dynamic derivative experimental provision of tail vibration |
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| Publication Number | Publication Date |
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| CN206648802U true CN206648802U (en) | 2017-11-17 |
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| CN201621418520.5U Active CN206648802U (en) | 2016-12-22 | 2016-12-22 | A kind of pitching dynamic derivative experimental provision of tail vibration |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110686855A (en) * | 2019-11-01 | 2020-01-14 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel translational vibration dynamic derivative test device |
| CN110726527A (en) * | 2019-11-08 | 2020-01-24 | 中国航空工业集团公司沈阳空气动力研究所 | Double-helix angle measuring balance for wind tunnel rolling vibration device |
| CN117890073A (en) * | 2024-03-15 | 2024-04-16 | 中国航空工业集团公司沈阳空气动力研究所 | Force balance and driving shaft integrated rolling rotation derivative test device |
-
2016
- 2016-12-22 CN CN201621418520.5U patent/CN206648802U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110686855A (en) * | 2019-11-01 | 2020-01-14 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel translational vibration dynamic derivative test device |
| CN110726527A (en) * | 2019-11-08 | 2020-01-24 | 中国航空工业集团公司沈阳空气动力研究所 | Double-helix angle measuring balance for wind tunnel rolling vibration device |
| CN110726527B (en) * | 2019-11-08 | 2021-07-13 | 中国航空工业集团公司沈阳空气动力研究所 | Double-helix angle measuring balance for wind tunnel rolling vibration device |
| CN117890073A (en) * | 2024-03-15 | 2024-04-16 | 中国航空工业集团公司沈阳空气动力研究所 | Force balance and driving shaft integrated rolling rotation derivative test device |
| CN117890073B (en) * | 2024-03-15 | 2024-05-14 | 中国航空工业集团公司沈阳空气动力研究所 | Force balance and driving shaft integrated rolling rotation derivative test device |
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