CN110901944A - Helicopter engine installation design method - Google Patents
Helicopter engine installation design method Download PDFInfo
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- CN110901944A CN110901944A CN201911227775.1A CN201911227775A CN110901944A CN 110901944 A CN110901944 A CN 110901944A CN 201911227775 A CN201911227775 A CN 201911227775A CN 110901944 A CN110901944 A CN 110901944A
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- 238000009434 installation Methods 0.000 title claims abstract description 39
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000006243 chemical reaction Methods 0.000 claims description 23
- 239000003638 chemical reducing agent Substances 0.000 claims description 12
- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 230000003068 static effect Effects 0.000 claims description 3
- 239000013585 weight reducing agent Substances 0.000 abstract description 3
- 238000005457 optimization Methods 0.000 abstract description 2
- 238000004364 calculation method Methods 0.000 description 2
- 208000016261 weight loss Diseases 0.000 description 2
- 238000007796 conventional method Methods 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000013178 mathematical model Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
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Abstract
The invention belongs to the technical field of helicopter strength design, and discloses a helicopter engine installation design method, which comprises the following steps: s1, determining the installation load of the engine; s2, deploying a balance mode of the installation load of the engine; s3, according to the balance mode of the installation load of the engine, carrying out load distribution on the installation load of the engine; s4, designing an in-plane bracket for mounting the engine according to the load distribution; the quick design of the engine mounting structure can be realized, and the weight reduction optimization design of the mounting structure can be realized.
Description
Technical Field
The invention belongs to the technical field of helicopter strength design, and particularly relates to a helicopter engine installation design method.
Background
The engine is used as the only source of the power of the helicopter, and the installation device of the engine needs to have double requirements of high reliability and low weight cost. The traditional design method is usually non-forward development, the design process needs to be continuously iterated by design and calculation, the design workload is large, and the design period is long.
Disclosure of Invention
In view of the above problems in the background art, an object of the present invention is to provide a method for designing a helicopter engine installation, which can achieve a rapid design of an engine installation structure and a weight reduction optimization design of the engine installation structure.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme.
A helicopter engine mount design method, said method comprising:
s1, determining the installation load of the engine;
s2, deploying a balance mode of the installation load of the engine;
s3, according to the balance mode of the installation load of the engine, carrying out load distribution on the installation load of the engine;
and S4, designing an in-plane bracket for mounting the engine according to the load distribution.
The technical scheme of the invention has the characteristics and further improvements that:
(1) s1 specifically includes:
defining an engine mounting coordinate system OXYZ as a Cartesian coordinate system, wherein the X direction is the direction of an engine output shaft, and the Z direction is vertically upward;
thus, the mounting load of the engine is determined as: inertial loads F of the engine in three directions X, Y, Z resulting from the maneuvering of the aircraftx、Fy、Fz(ii) a Reaction torque M generated by engine output torquex(ii) a Gyroscopic moments M generated by coupling the pitching and yawing movements of an aircraft with the rapid rotation of the rotor of an enginey、Mz。
(2) A power output shaft sleeve is arranged between the engine and the main speed reducer, and the power output shaft sleeve and the main speed reducer are provided with a mounting point A;
s2 specifically includes:
inertial load F in X directionxThe inertia load F in the Y direction is balanced by the mounting point A of the power output shaft sleeve and the main speed reduceryBy Y-direction reversal of the carriage B in the YOZ plane perpendicular to the power take-off shaftActing force FByBalanced, Z-direction inertial loads FzZ-direction reaction force F of bracket B in YOZ plane perpendicular to power output shaftBzBalancing;
reaction torque MxLoad balancing through two mounting points of the bracket B in the YOZ plane; moment M of gyroyZ-direction reaction force F through mounting point AAzAnd Z-direction reaction force F of bracket BBzResulting in a moment balance, gyro moment MzY-direction reaction force F through mounting point aAyEquilibrium and Y-reaction force F of support BByThe resulting moment is balanced.
(3) S2 further includes: the following requirements are satisfied when the balance mode of the installation load of the engine is deployed:
the power output shaft of the engine and the input end of the main speed reducer are concentric shafts;
an axial clearance is provided between the in-plane bracket B and the engine or the in-plane bracket B can move axially to compensate the thermal expansion of the engine.
(4) S3 specifically includes:
establishing a load balance equation, and calculating the load F of the mounting point A in X, Y, Z three directionsAx、FAy、FAzLoad of bracket B in doughLoad of in-plane bracket BComponent F comprising two mounting pointsB1、FB2;
Establishing a load balance equation and a geometric equation, taking α and β as random variables, and solving FB1、FB2Wherein α, β are F, respectivelyB1、FB2Is inclined to the Z direction.
(5) S4 specifically includes:
the mounting point A is a spherical hinge which only transmits load;
two main force transmission path directions and component forces F of two mounting points of in-plane bracket BB1、FB2The load directions of the two are consistent;
taking the stress sigma of the in-plane bracket B as a variable according to the component force F of the two mounting pointsB1、FB2And the requirements of static strength, stability and fatigue life of the in-plane bracket B, and the section size of the in-plane bracket B is defined.
The design method for mounting the engine can shorten the design period, reduce the design cost and improve the design quality.
Drawings
FIG. 1 is a schematic view of a macro-stress analysis of an engine according to an embodiment of the present invention;
fig. 2 is a schematic view of a force analysis of an in-plane stent according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment of the invention provides a helicopter engine installation design method, which comprises the following steps:
s1, determining the installation load of the engine;
s2, deploying a balance mode of the installation load of the engine;
s3, according to the balance mode of the installation load of the engine, carrying out load distribution on the installation load of the engine;
and S4, designing an in-plane bracket for mounting the engine according to the load distribution.
The technical scheme of the invention has the characteristics and further improvements that:
further, S1 specifically includes:
defining an engine mounting coordinate system OXYZ as a Cartesian coordinate system, wherein the X direction is the direction of an engine output shaft, and the Z direction is vertically upward;
thus, the mounting load of the engine is determined as: inertial loads F of the engine in three directions X, Y, Z resulting from the maneuvering of the aircraftx、Fy、Fz(ii) a Reaction torque M generated by engine output torquex(ii) a Gyroscopic moments M generated by coupling the pitching and yawing movements of an aircraft with the rapid rotation of the rotor of an enginey、Mz。
A power output shaft sleeve is arranged between the engine and the main speed reducer, and the power output shaft sleeve and the main speed reducer are provided with a mounting point A;
s2 specifically includes:
as shown in fig. 1, the inertial load F in the X directionxThe inertia load F in the Y direction is balanced by the mounting point A of the power output shaft sleeve and the main speed reduceryBy Y-reaction F of the support B in the YOZ plane perpendicular to the power take-off shaftByBalanced, Z-direction inertial loads FzZ-direction reaction force F of bracket B in YOZ plane perpendicular to power output shaftBzBalancing;
reaction torque MxLoad balancing through two mounting points of the bracket B in the YOZ plane; moment M of gyroyZ-direction reaction force F through mounting point AAzAnd Z-direction reaction force F of bracket BBzResulting in a moment balance, gyro moment MzY-direction reaction force F through mounting point aAyEquilibrium and Y-reaction force F of support BByThe resulting moment is balanced.
S2 further includes: the following requirements are satisfied when the balance mode of the installation load of the engine is deployed:
the power output shaft of the engine and the input end of the main speed reducer are concentric shafts;
an axial clearance is provided between the in-plane bracket B and the engine or the in-plane bracket B can move axially to compensate the thermal expansion of the engine.
S3 specifically includes:
establishing a load balance equation, and calculating the load F of the mounting point A in X, Y, Z three directionsAx、FAy、FAzLoad of bracket B in doughLoad of in-plane bracket BComponent F comprising two mounting pointsB1、FB2;
Establishing a load balance equation and a geometric equation, taking α and β as random variables, and solving FB1、FB2Wherein α, β are F, respectivelyB1、FB2Is inclined to the Z direction.
S4 specifically includes:
the mounting point A is a spherical hinge which only transmits load;
as shown in FIG. 2, the two main force transmission path directions and the force components F of the two mounting points of the in-plane bracket BB1、FB2The load directions of the two are consistent;
taking the stress sigma of the in-plane bracket B as a variable according to the component force F of the two mounting pointsB1、FB2And the requirements of static strength, stability and fatigue life of the in-plane bracket B, and the section size of the in-plane bracket B is defined.
And finally, establishing a finite element model for engine installation through finite element simulation calculation, and checking whether the strength and the like of the installation structure meet the installation requirements.
The design method of the engine bracket, which is disclosed by the invention, is based on the optimal solution of the mathematical model, can realize the rapid design of the engine mounting structure, and can realize the weight-reduction optimal design of the mounting structure.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. A helicopter engine mount design method, said method comprising:
s1, determining the installation load of the engine;
s2, deploying a balance mode of the installation load of the engine;
s3, according to the balance mode of the installation load of the engine, carrying out load distribution on the installation load of the engine;
and S4, designing an in-plane bracket for mounting the engine according to the load distribution.
2. A helicopter engine installation design method according to claim 1, wherein S1 specifically comprises:
defining an engine mounting coordinate system OXYZ as a Cartesian coordinate system, wherein the X direction is the direction of an engine output shaft, and the Z direction is vertically upward;
thus, the mounting load of the engine is determined as: inertial loads F of the engine in three directions X, Y, Z resulting from the maneuvering of the aircraftx、Fy、Fz(ii) a Reaction torque M generated by engine output torquex(ii) a Gyroscopic moments M generated by coupling the pitching and yawing movements of an aircraft with the rapid rotation of the rotor of an enginey、Mz。
3. A helicopter engine installation design method according to claim 2, characterized by that, there is a power take-off shaft sleeve between the engine and the main reducer, the power take-off shaft sleeve and the main reducer have an installation point A;
s2 specifically includes:
inertial load F in X directionxThe inertia load F in the Y direction is balanced by the mounting point A of the power output shaft sleeve and the main speed reduceryBy Y-reaction F of the support B in the YOZ plane perpendicular to the power take-off shaftByBalanced, Z-direction inertial loads FzZ-direction reaction force F of bracket B in YOZ plane perpendicular to power output shaftBzAnd (4) balancing.
4. A helicopter engine installation design method according to claim 3, wherein S2 further specifically comprises:
reaction torque MxLoad balancing through two mounting points of the bracket B in the YOZ plane; moment M of gyroyZ-direction reaction force F through mounting point AAzAnd Z-direction reaction force F of bracket BBzResulting in a moment balance, gyro moment MzY-direction reaction force F through mounting point aAyEquilibrium and Y-reaction force F of support BByThe resulting moment is balanced.
5. A helicopter engine installation design method according to claim 4, characterized in that S2 further specifically comprises: the following requirements are satisfied when the balance mode of the installation load of the engine is deployed:
the power output shaft of the engine and the input end of the main speed reducer are concentric shafts;
an axial clearance is provided between the in-plane bracket B and the engine or the in-plane bracket B can move axially to compensate the thermal expansion of the engine.
6. A helicopter engine installation design method according to claim 4, characterized in that S3 specifically comprises:
7. A helicopter engine installation design method according to claim 6, characterized in that S3 further specifically comprises:
method for establishing load balanceEquation of course and geometry, using α, β as random variables to solve FB1、FB2Wherein α, β are F, respectivelyB1、FB2Is inclined to the Z direction.
8. A helicopter engine installation design method according to claim 7, wherein S4 specifically comprises:
the mounting point A is a spherical hinge which only transmits load;
two main force transmission path directions and component forces F of two mounting points of in-plane bracket BB1、FB2The load directions of the two are consistent;
taking the stress sigma of the in-plane bracket B as a variable according to the component force F of the two mounting pointsB1、FB2And the requirements of static strength, stability and fatigue life of the in-plane bracket B, and the section size of the in-plane bracket B is defined.
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112052531A (en) * | 2020-09-25 | 2020-12-08 | 中国直升机设计研究所 | Helicopter harpoon load calculation method |
CN112461525A (en) * | 2020-11-20 | 2021-03-09 | 中国直升机设计研究所 | Unmanned helicopter engine mounting bracket test device |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105270638A (en) * | 2015-11-17 | 2016-01-27 | 江西洪都航空工业集团有限责任公司 | Aeroengine mounting device |
CN107176303A (en) * | 2016-03-10 | 2017-09-19 | 通用电气公司 | The system and method for mounting aircraft engine |
CN107563039A (en) * | 2017-08-28 | 2018-01-09 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of intensity layout design method of aircraft engine installation system |
US20190009918A1 (en) * | 2015-09-04 | 2019-01-10 | Lord Corporation | Anti-torque aft-mounting systems, devices, and methods for turboprop/turboshaft engines |
CN109562841A (en) * | 2016-08-08 | 2019-04-02 | 洛德公司 | Installation system, device and method for aircraft engine |
-
2019
- 2019-12-04 CN CN201911227775.1A patent/CN110901944B/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20190009918A1 (en) * | 2015-09-04 | 2019-01-10 | Lord Corporation | Anti-torque aft-mounting systems, devices, and methods for turboprop/turboshaft engines |
CN105270638A (en) * | 2015-11-17 | 2016-01-27 | 江西洪都航空工业集团有限责任公司 | Aeroengine mounting device |
CN107176303A (en) * | 2016-03-10 | 2017-09-19 | 通用电气公司 | The system and method for mounting aircraft engine |
CN109562841A (en) * | 2016-08-08 | 2019-04-02 | 洛德公司 | Installation system, device and method for aircraft engine |
CN107563039A (en) * | 2017-08-28 | 2018-01-09 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of intensity layout design method of aircraft engine installation system |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112052531A (en) * | 2020-09-25 | 2020-12-08 | 中国直升机设计研究所 | Helicopter harpoon load calculation method |
CN112052531B (en) * | 2020-09-25 | 2022-12-30 | 中国直升机设计研究所 | Helicopter harpoon load calculation method |
CN112461525A (en) * | 2020-11-20 | 2021-03-09 | 中国直升机设计研究所 | Unmanned helicopter engine mounting bracket test device |
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