CN107933968A - A kind of three flywheel integrated configuration devices and its installation adjusting method - Google Patents
A kind of three flywheel integrated configuration devices and its installation adjusting method Download PDFInfo
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- CN107933968A CN107933968A CN201711122894.1A CN201711122894A CN107933968A CN 107933968 A CN107933968 A CN 107933968A CN 201711122894 A CN201711122894 A CN 201711122894A CN 107933968 A CN107933968 A CN 107933968A
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- flywheel
- main support
- support rod
- aircraft
- coordinate system
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
- B64G1/283—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect using reaction wheels
Abstract
The invention discloses a kind of three flywheel integrated configuration devices and its installation adjusting method.Three flywheel integrated configuration devices include：Arboraceous support, flywheel；Arboraceous support includes rack body；Longitudinal flywheel is installed on main support rod one end, and the main support rod other end is connected with aircraft；Main support rod is along aircraft body coordinate system Y direction, and the principal moments axis of longitudinal flywheel is along aircraft body coordinate system Y direction；Horizontal flywheel, tilting flywheel are separately mounted to each skewed horizontal load boom end, and the skewed horizontal load bar being connected with horizontal flywheel is vertical with main support rod, and along aircraft body coordinate system Z-direction, the principal moments axis of horizontal flywheel is along aircraft body coordinate system Z-direction；Each structure connecting rod is vertical with main support rod, end connection aircraft.The present invention solves spaces compact in aerospace craft cabin, and three flywheel groups layout is difficult, simultaneously because space opening character is bad in cabin, the problem of installation operation insufficient space, optical path accessibility is bad.
Description
Technical field
The present invention relates to a kind of three flywheel placement devices and its installation method, belong to aerospace craft structure total arrangement and set
Meter field.
Background technology
Change of flight posture or control external disturbance are, it is necessary to which flywheel carries out appearance during the in-orbit execution task of aerospace craft
State controls.The action principle of flywheel is to make angular momentum wheel acceleration or deceleration with torque motor, and the moment of reaction of generation is as control
Torque processed is used for change of flight device posture or confrontation disturbance torque.Aerospace craft flywheel group generally uses 4 flywheels, wherein
3 mutually orthogonal, opposite direction of another angle mount in 3 orthogonal flywheel synthesis angular-momentum vectors.
4 flywheel groups of most of spacecraft are all individually to arrange, distinguish support flying wheel by 4 stents so that flywheel branch
Frame quality weight, the space occupied are big.Since the arrangement space of conventional aerospace craft is more sufficient, arrangement space problem is not very
It is urgent.But it is more and more compacter with the structure of aerospace craft, inner space is less and less, the increase of below deck equipment pack completeness,
Especially re-entry space vehicle, can allow flywheel arrangement space very narrow and small, it is necessary to carry out the cloth of flywheel group in narrow space
Office, install and measure extremely difficult.
The content of the invention
Present invention solves the technical problem that it is：A kind of three flywheel integrated configurations are overcome the deficiencies of the prior art and provide
Device and its installation adjusting method, solve spaces compact in aerospace craft cabin, three flywheel groups layout is difficult, simultaneously because cabin
The problem of interior space opening character is bad, installation operation insufficient space, optical path accessibility is bad.By the way that three flywheels are integrated
Layout, using Arboraceous support scheme, while using switching prism, the benchmark prism of measurement is transferred out hemi-closure space, is realized
The optical path accessibility of theodolite.
The technical solution adopted in the present invention is：A kind of three flywheel integrated configuration devices, including：Arboraceous support, flywheel；
Flywheel includes horizontal flywheel, longitudinal flywheel, tilting flywheel；Arboraceous support includes rack body；The tree of being integrated of rack body
Shape stent, including main support rod, skewed horizontal load bar, structure connecting rod；Longitudinal flywheel is installed on main support rod one end, main support rod
The other end is connected with aircraft；Main support rod flies along aircraft body coordinate system Y direction, the principal moments axis edge of longitudinal flywheel
Device body coordinate system Y direction；Horizontal flywheel, tilting flywheel are separately mounted to each skewed horizontal load boom end, connect with horizontal flywheel
The skewed horizontal load bar connect is vertical with main support rod and along aircraft body coordinate system Z-direction, the principal moments axis edge of horizontal flywheel
Aircraft body coordinate system Z-direction；The X, Y, Z axis of the skewed horizontal load bar being connected with tilting flywheel and aircraft body coordinate system
Into specified angle；Each structure connecting rod is vertical with main support rod, end connection aircraft.
The Arboraceous support further includes stent and flywheel connecting interface；Horizontal flywheel, tilting flywheel and skewed horizontal load bar it
Between, it is connected between longitudinal flywheel and main support rod by stent with flywheel connecting interface；Stent and flywheel connecting interface be with
The disc structure of screw hole, is connected with horizontal flywheel, tilting flywheel, longitudinal flywheel respectively by screw；
The Arboraceous support further includes stent and aircraft connecting interface；Each structure connecting rod, main support rod pass through stent
It is connected with aircraft connecting interface with aircraft；Stent and aircraft connecting interface are the disc structure with screw hole, are passed through
Screw is fixed on board the aircraft.
The skewed horizontal load bar and the X, Y, Z axis of aircraft body coordinate system being connected with tilting flywheel are into 54.73 ° of folder
Angle.
The material of the Arboraceous support is T800 carbon fiber epoxy based composites.
The material of the connecting rod is aluminium alloy.
The material of the measuring prism is 9Cr18 stainless steels.
A kind of installation adjusting method of three flywheels integrated configuration device, includes the following steps：
Step 1: horizontal flywheel, tilting flywheel are separately mounted to each skewed horizontal load boom end of Arboraceous support；Will longitudinal direction
Flywheel is installed on main support rod one end of Arboraceous support；
Arboraceous support includes rack body；The tree-like stent of being integrated of rack body, including main support rod, skewed horizontal load
Bar, structure connecting rod；The skewed horizontal load bar being connected with horizontal flywheel is vertical with main support rod, the oblique branch being connected with tilting flywheel
Inclined angle between strut and main support rod；Each structure connecting rod is vertical with main support rod；
Step 2: installation measuring prism switching tooling；Measuring prism switching tooling includes connecting rod, measuring prism；Will be even
Extension bar one end is installed on the junction between horizontal flywheel and skewed horizontal load bar, and measuring prism is installed on the connecting rod other end；
Step 3: the main support rod other end is connected with aircraft, structure connecting rod is connected with aircraft so that：It is main
Supporting rod along aircraft body coordinate system Y direction, the principal moments axis of longitudinal flywheel along aircraft body coordinate system Y direction,
The skewed horizontal load bar being connected with horizontal flywheel flies along aircraft body coordinate system Z-direction, the principal moments axis edge of horizontal flywheel
Device body coordinate system Z-direction；
Step 4: aiming at measuring prism using laser tracker, the installation site of flywheel and Arboraceous support is measured,
Measure measuring prism normal direction and the angle theta of aircraft body coordinate system；Adjust aircraft and main support rod, each structure connecting rod
The tightness of attachment screw or by increasing gasket so that θ is less than setting value；
Step 5: remove prism switching tooling.
The present invention compared with prior art the advantages of be：
(1) since conventional flywheel group is split arrangement, the space occupied by 3 flywheels and stent is big, and the present invention will
Three flywheels spatially integrated arrangement, on Arboraceous support, cloth is more saved compared to the conventional placement scheme that separates
Between emptying, the arrangement of the three flywheel groups in aerospace craft small space is realized；
(2) flywheel-bracket used in conventional aerospace craft is aluminium alloy or titanium alloy, and three flywheels need three solely
Three single flywheel-brackets are reduced to Arboraceous support by vertical stent, the present invention, and use more lightweight, high intensity it is compound
Material, stent total quality are lighter；
(3) flywheel in conventional aerospace craft is separately installed, it is necessary to which three flywheels are carried out with separately installed, measurement
With adjustment, the time used is grown, and needs to enter in cabin and operate, and operating space is narrow and small, and the present invention will be installed on integration in flywheel
On stent, flywheel group is installed and measured out of my cabin, operating space out of my cabin is sufficient, realizes that stent is integrated with flywheel
Installation and measurement；
(4) conventional flywheel need to be arranged in more open space, it is necessary to which optical path is reachable, these limit flywheel
Position, increases the difficulty of aerospace craft layout, and the present invention sets measuring prism to transfer on flywheel integrated bracket
Frock interface, is reached measuring prism out of my cabin by switching tooling, simple in structure, quality is small, reliability is high, solves half envelope
Close optical path Reachability question under space.
Brief description of the drawings
Fig. 1 is flywheel integrated configuration and mount approach schematic diagram；
Fig. 2 is the switching tooling schematic diagram of measuring prism；
Fig. 3 is the definition of flywheel principal moments axis；
Fig. 4 is flywheel-bracket and flywheel body scheme of installation
Fig. 5 is measuring prism switching tooling and stent flywheel body connection diagram；
Fig. 6 is stent and measurement path schematic diagram of the flywheel group in aircraft cabin.
Embodiment
The present invention is further detailed below in conjunction with the accompanying drawings.
As shown in Fig. 3~Fig. 6, a kind of three flywheel integrated configuration devices, including：Arboraceous support 1, flywheel 3；Flywheel 3 wraps
Include horizontal flywheel 31, longitudinal flywheel 32, tilting flywheel 33；
Connect as shown in Figure 1, Arboraceous support 1 includes rack body 11, stent and flywheel connecting interface 12, stent and aircraft
Connection interface 13；
Rack body 11 is tree-like stent, including main support rod 111, skewed horizontal load bar 112, structure connecting rod 113；Longitudinal direction
Flywheel 32 is installed on 111 one end of main support rod, and 111 other end of main support rod is connected with aircraft；Main support rod 111 is along aircraft
Body coordinate system Y direction, the principal moments axis of longitudinal flywheel 32 is along aircraft body coordinate system Y direction；Horizontal flywheel 31, tiltedly
Put flywheel 33 and be separately mounted to each 112 end of skewed horizontal load bar, the skewed horizontal load bar 112 being connected with horizontal flywheel 31 and main support
Bar 111 is vertical and along aircraft body coordinate system Z-direction, and the principal moments axis of horizontal flywheel 31 is along aircraft body coordinate system Z
Direction of principal axis；The X, Y, Z axis of the skewed horizontal load bar 112 being connected with tilting flywheel 33 and aircraft body coordinate system is pressed from both sides into 54.73 °
Angle；Between horizontal flywheel 31, tilting flywheel 33 and skewed horizontal load bar 112, pass through between longitudinal flywheel 32 and main support rod 111
Stent is connected with flywheel connecting interface 12, and stent and flywheel connecting interface 12 are the disc structure with screw hole, pass through screw
Connection；Each structure connecting rod 113 is connected by stent with aircraft connecting interface 13 with aircraft, each structure connecting rod 113 with
Main support rod 111 is vertical；Main support rod 111 is connected by stent with aircraft connecting interface 13 with aircraft, stent and flight
Device connecting interface 13 is the disc structure with screw hole, is connected by screw；
1 material of Arboraceous support uses high-strength carbon fiber T800 epoxy resin-base composite materials, its static tension intensity is about
For 2500MPa, elasticity modulus about 150Gpa, by winding, assembling co-curing moulding process.111 length of stent main support rod is
400mm, 112 length of skewed horizontal load bar are 140mm, and skewed horizontal load bar 112 forms triangular support configurations, knot by auxiliary support bar
113 length of structure connecting rod is about 220m.Connecting rod 21 is made of aluminium alloy, measuring prism 22 by 9Cr18 materials stainless steel
Material is made, and six faces are reflective surface, and size is 30mm × 30mm × 30mm.
As shown in Fig. 2, measuring prism switching tooling 2 includes connecting rod 21, measuring prism 22；21 one end of connecting rod is installed on
On stent and flywheel connecting interface 12 between horizontal flywheel 31 and skewed horizontal load bar 112, the installation measurement of 21 other end of connecting rod
Prism 22, the normal direction in adjacent and orthogonal three faces of measuring prism 22 respectively the X with aircraft body coordinate system,
Y, Z axis is parallel.
A kind of installation adjusting method of three flywheels integrated configuration device, it is characterised in that include the following steps：
Step 1: horizontal flywheel 31, tilting flywheel 33 are separately mounted to each 112 end of skewed horizontal load bar of Arboraceous support 1
Portion；Longitudinal flywheel 32 is installed on to 111 one end of main support rod of Arboraceous support 1；
Arboraceous support 1 includes rack body 11；The tree-like stent of 11 being integrated of rack body, including main support rod 111,
Skewed horizontal load bar 112, structure connecting rod 113；It is vertical with main support rod 111 with the horizontal flywheel 31 skewed horizontal load bar 112 being connected,
Inclined angle between the skewed horizontal load bar 112 and main support rod 111 that are connected with tilting flywheel 33；Each structure connecting rod 113 with
Main support rod 111 is vertical；
Step 2: installation measuring prism switching tooling 2；Measuring prism switching tooling 2 includes connecting rod 21, measuring prism
22；21 one end of connecting rod is installed on the junction between horizontal flywheel 31 and skewed horizontal load bar 112, measuring prism 22 is installed
In 21 other end of connecting rod；
Step 3: 111 other end of main support rod is connected with aircraft, structure connecting rod 113 is connected with aircraft, is made
：Main support rod 111 is along aircraft body coordinate system Y direction, and the principal moments axis of longitudinal flywheel 32 is along aircraft body coordinate
It is Y direction, with the skewed horizontal load bar 112 that horizontal flywheel 31 is connected along aircraft body coordinate system Z-direction, horizontal flywheel 31
Principal moments axis along aircraft body coordinate system Z-direction；
Step 4: aiming at measuring prism 22 using laser tracker, the installation site of flywheel 3 and Arboraceous support 1 is carried out
Measurement, measurement 22 normal direction of measuring prism and the angle theta of aircraft body coordinate system；Adjust aircraft and main support rod 111, each knot
The tightness of the attachment screw of structure connecting rod 113 or by increasing gasket so that θ is less than setting value；
Step 5: remove prism switching tooling 2.
1, three 3 assembly of flywheel of Arboraceous support plays in aircraft can realize aircraft three-axis stabilization system
Zero momentum control mode.
Pass through four spiral shells between Arboraceous support 1 and flywheel interface 12 and horizontal flywheel 31, longitudinal flywheel 32, tilting flywheel 33
Nail connection, the screw-down torque of screw is set-point；Main support rod 111 be whole stent main support structure, the big portion of flywheel
Separate loading is born by main support rod；Skewed horizontal load bar 112 plays the role of assistant reinforcement supporting structure, and structure connecting rod 113 flies
The fractional load of wheel group is delivered in structure, is played a supportive role.
Measuring prism switching tooling 2 shifts the measuring basis of flywheel body, enabling installs essence to it out of my cabin
Degree is measured and demarcated.
What description of the invention was not described in detail partly belongs to general knowledge well known to those skilled in the art.
Claims (8)
- A kind of 1. three flywheel integrated configuration devices, it is characterised in that including：Arboraceous support (1), flywheel (3)；Flywheel (3) wraps Include horizontal flywheel (31), longitudinal flywheel (32), tilting flywheel (33)；Arboraceous support (1) includes rack body (11)；Rack body (11) the tree-like stent for being integrated, including main support rod (111), skewed horizontal load bar (112), structure connecting rod (113)；Longitudinal direction Flywheel (32) is installed on main support rod (111) one end, and main support rod (111) other end is connected with aircraft；Main support rod (111) Along aircraft body coordinate system Y direction, the principal moments axis of longitudinal flywheel (32) is along aircraft body coordinate system Y direction；It is horizontal Each skewed horizontal load bar (112) end is separately mounted to flywheel (31), tilting flywheel (33), is connected with horizontal flywheel (31) oblique It is vertical with main support rod (111) to supporting rod (112) and along aircraft body coordinate system Z-direction, the master of horizontal flywheel (31) Inertia axis is along aircraft body coordinate system Z-direction；The skewed horizontal load bar (112) being connected with tilting flywheel (33) and aircraft machine The X, Y, Z axis of body coordinate system is into specified angle；Each structure connecting rod (113) is vertical with main support rod (111), end connection Aircraft.
- A kind of 2. three flywheels integrated configuration device according to claim 1, it is characterised in that：The Arboraceous support (1) Further include stent and flywheel connecting interface (12)；Between horizontal flywheel (31), tilting flywheel (33) and skewed horizontal load bar (112), It is connected between longitudinal flywheel (32) and main support rod (111) by stent with flywheel connecting interface (12)；Stent is connected with flywheel Interface (12) is the disc structure with screw hole, is flown respectively with horizontal flywheel (31), tilting flywheel (33), longitudinal direction by screw Take turns (32) connection.
- A kind of 3. three flywheels integrated configuration device according to claim 1 or 2, it is characterised in that：The Arboraceous support (1) stent and aircraft connecting interface (13) are further included；Each structure connecting rod (113), main support rod (111) are by stent with flying Row device connecting interface (13) is connected with aircraft；Stent and aircraft connecting interface (13) are the disc structure with screw hole, It is fixed by screws on aircraft.
- A kind of 4. three flywheels integrated configuration device according to claim 3, it is characterised in that：With tilting flywheel (33) even The skewed horizontal load bar (112) and the X, Y, Z axis of aircraft body coordinate system connect is into 54.73 ° of angle.
- A kind of 5. three flywheels integrated configuration device according to claim 3, it is characterised in that：The Arboraceous support (1) Material be T800 carbon fiber epoxy based composites.
- A kind of 6. three flywheels integrated configuration device according to claim 5, it is characterised in that：The connecting rod (21) Material is aluminium alloy.
- 7. the three flywheel integrated configuration device of one kind according to claim 5 or 6, it is characterised in that：The measuring prism (22) material is 9Cr18 stainless steels.
- 8. a kind of installation adjusting method of three flywheels integrated configuration device, it is characterised in that include the following steps：Step 1: horizontal flywheel (31), tilting flywheel (33) are separately mounted to each skewed horizontal load bar of Arboraceous support (1) (112) end；Longitudinal flywheel (32) is installed on to main support rod (111) one end of Arboraceous support (1)；Arboraceous support (1) includes rack body (11)；The tree-like stent of rack body (11) being integrated, including main support rod (111), skewed horizontal load bar (112), structure connecting rod (113)；The skewed horizontal load bar (112) being connected with horizontal flywheel (31) and master Supporting rod (111) is vertically, inclined between the skewed horizontal load bar (112) and main support rod (111) that are connected with tilting flywheel (33) Angle；Each structure connecting rod (113) is vertical with main support rod (111)；Step 2: installation measuring prism switching tooling (2)；Measuring prism switching tooling (2) includes connecting rod (21), measuring prism (22)；Connecting rod (21) one end is installed on the junction between horizontal flywheel (31) and skewed horizontal load bar (112), rib will be measured Mirror (22) is installed on connecting rod (21) other end；Step 3: main support rod (111) other end is connected with aircraft, structure connecting rod (113) is connected with aircraft, is made ：Main support rod (111) is along aircraft body coordinate system Y direction, and the principal moments axis of longitudinal flywheel (32) is along aircraft body Coordinate system Y direction, the skewed horizontal load bar (112) being connected with horizontal flywheel (31) are horizontal along aircraft body coordinate system Z-direction To the principal moments axis of flywheel (31) along aircraft body coordinate system Z-direction；Step 4: aim at measuring prism (22) using laser tracker, to the installation site of flywheel (3) and Arboraceous support (1) into Row measurement, measurement measuring prism (22) normal direction and the angle theta of aircraft body coordinate system；Adjust aircraft and main support rod (111), the tightness of the attachment screw of each structure connecting rod (113) or by increasing gasket so that θ is less than setting value；Step 5: remove prism switching tooling (2).
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| CN201711122894.1A CN107933968B (en) | 2017-11-14 | 2017-11-14 | Three flywheel integrated configuration devices of one kind and its installation adjusting method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711122894.1A CN107933968B (en) | 2017-11-14 | 2017-11-14 | Three flywheel integrated configuration devices of one kind and its installation adjusting method |
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| CN107933968A true CN107933968A (en) | 2018-04-20 |
| CN107933968B CN107933968B (en) | 2019-06-18 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110884692A (en) * | 2019-11-10 | 2020-03-17 | 北京机械设备研究所 | Novel micro flywheel device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2057804A1 (en) * | 1990-12-21 | 1992-06-22 | Bernard Blancke | Attitude control system for stabilized three-axis satellite, including observation satellites |
| US5826829A (en) * | 1996-07-15 | 1998-10-27 | Space Systems/Loral Inc. | Spacecraft control system with a trihedral momentum bias wheel configuration |
| DE202006000022U1 (en) * | 2006-01-03 | 2006-03-09 | Astro- Und Feinwerktechnik Adlershof Gmbh | Reaction wheels arranging device for use on pico satellites, has gyroscopic wheels mounted on tetrahedron-shaped base body, where three wheels are provided for attitude stabilization in three degrees of freedom of rotation |
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| CN110884692A (en) * | 2019-11-10 | 2020-03-17 | 北京机械设备研究所 | Novel micro flywheel device |
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| CN107933968B (en) | 2019-06-18 |
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