CN102788698B - Ground rotation testing device for solid rocket engine - Google Patents
Ground rotation testing device for solid rocket engine Download PDFInfo
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- CN102788698B CN102788698B CN201210286493.0A CN201210286493A CN102788698B CN 102788698 B CN102788698 B CN 102788698B CN 201210286493 A CN201210286493 A CN 201210286493A CN 102788698 B CN102788698 B CN 102788698B
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Abstract
The invention provides a ground rotation testing device for a solid rocket engine. The ground rotation testing device comprises a power device, transmission mechanisms, a supporting mechanism, a transition rack mechanism and an anti-torsion force measurement mechanism, wherein the transition rack mechanism comprises transition racks and an ignition current collector, the transmission mechanisms comprise driving wheels, driven wheels and transmission holding rings, and the supporting mechanism comprises a supporting platform and two supporting arch seats. With the adoption of the ground rotation testing device for the solid rocket engine, provided by the invention, through the power device and the transmission mechanisms, the solid rocket engine can rotate around the axis of the engine at a certain speed in an ignition working state, parameters, such as pressure, thrust force, rotating speed and temperature, can be measured during rotation, and the influence on the performance, structure and material of the engine caused by the rotating speed is determined.
Description
Technical field
The present invention relates to rocket engine ground test technical field, be specially a kind of solid propellant rocket ground rotation test device.
Background technology
After solid propellant rocket blasts off, himself rotation can cause motor body local temperature to heat up, if do not consider this phenomenon in ground design and process of the test, tends to cause engine Yin Wendu former thereby destroy, and causes abortive launch.Therefore in ground design and process of the test, need in the internal work characteristic under self rotation status, carry out certification test to engine.In open source literature, also there is no at present the technical scheme of correlation test equipment.
Summary of the invention
The technical matters solving
For realizing, engine is carried out to the object of certification test in the internal work characteristic under self rotation status, the present invention proposes a kind of solid propellant rocket ground rotation test device, for solid propellant rocket (hereinafter to be referred as engine) provides rotating torque and support.
Technical scheme
Device, according to different to the emphasis of motor body examination, has two kinds of basic structures.A kind of is that afterbody rises and revolves structure; Another kind is that head rises and revolves structure.
Technical scheme of the present invention is:
Described a kind of solid propellant rocket ground rotation test device, is characterized in that: comprise propulsion system, gear train, supporting mechanism, transition frame mechanism and the anti-force measuring machine of turning round;
The anti-cylinder of turning round in described place is for hollow structure, and one end is fixedly connected with load upper frame, and the anti-cylinder of turning round self can not be rotated; Prevent that turning round an other end is connected by thrust bearing and transition frame; Preventing that turning round an inside is fixed with dynamometry assembly, dynamometry assembly one end is fixed on anti-turning round on the inner wall of cylinder, and the dynamometry assembly other end is fixedly connected with the bearing seat of thrust bearing; The bearing seat of thrust bearing is turned round a secure fit with anti-, and bearing seat self can not be rotated;
Described transition frame mechanism comprises transition frame and igniting current-collector; Transition frame is hollow structure, and one end is connected by thrust bearing and the anti-cylinder of turning round, and the other end is coaxially fixedly connected with solid propellant rocket head, makes transition frame with solid propellant rocket synchronous rotary; In transition frame inside, be fixed with igniting current-collector, igniting current-collector housing is with transition frame by being fixedly connected with along transition frame connecting link radially, and the current-collector housing that makes to light a fire rotates in the lump with transition frame;
Described gear train comprises that driving wheel, engaged wheel and transmission embrace ring; The power output shaft of driving wheel and propulsion system is connected, and between driving wheel and engaged wheel, by driving-belt, is connected; Engaged wheel is loop configuration, and engaged wheel is embraced ring with transmission and is coaxially connected by transmission register pin, makes engaged wheel drive transmission to embrace ring and rotates; Transmission is embraced ring for loop configuration, and inner wall surface thereof and solid propellant rocket afterbody housing outer surface, by the key secure fit being uniformly distributed circumferentially, make transmission embrace the moving solid propellant rocket of endless belt and rotate;
Described supporting mechanism comprises support platform and two supporting arc seats; Supporting arc seat is fixed in support platform, supporting arc seat upper end is loop configuration, the loop configuration of a supporting arc seat upper end is enclosed within on one end that transition frame coordinates with solid propellant rocket head, and coordinate by radial ball bearing with transition frame, the loop configuration of another supporting arc seat upper end is enclosed within transmission, and to embrace ring upper, and embrace ring with transmission and coordinate by radial ball bearing.
Described a kind of solid propellant rocket ground rotation test device, is characterized in that: the bearing seat of thrust bearing, is turned round nail on a side wall surface and had holding screw anti-for clearance fit with the anti-cylinder of turning round, by bearing seat with anti-to turn round cylinder fixing.
Described a kind of solid propellant rocket ground rotation test device, is characterized in that: anti-turning round on a sidewall that coordinates one end with transition frame, overlap and have centering ring, centering is encircled and prevented turning round a clearance fit; In transition frame, there are annulus projection, the external diameter of annulus projection to equal anti-cylinder the coordinates one end end face external diameter with transition frame of turning round with anti-turning round on an end face coordinating.
Described a kind of solid propellant rocket ground rotation test device, is characterized in that: on the end face of the loop configuration of supporting arc seat upper end, have shoulder block, prevent that the mechanism rotating in process of the test from motion vertically occurring.
Described a kind of solid propellant rocket ground rotation test device, is characterized in that: comprise propulsion system, gear train, supporting mechanism, transition frame mechanism and the anti-force measuring machine of turning round;
The described anti-force measuring machine of turning round comprises load upper frame, anti-cylinder and the dynamometry assembly turned round; The anti-cylinder of turning round is for hollow structure, and one end is fixedly connected with load upper frame, and the anti-cylinder of turning round self can not be rotated; Prevent that turning round an other end is connected by thrust bearing and transition frame; Preventing that turning round an inside is fixed with dynamometry assembly, dynamometry assembly one end is fixed on anti-turning round on the inner wall of cylinder, and the dynamometry assembly other end is fixedly connected with the bearing seat of thrust bearing; The bearing seat of thrust bearing is turned round a secure fit with anti-, and bearing seat self can not be rotated;
Described transition frame mechanism comprises transition frame and igniting current-collector; Transition frame is hollow structure, and one end is connected by thrust bearing and the anti-cylinder of turning round, and the other end is coaxially fixedly connected with solid propellant rocket head, makes transition frame drive solid propellant rocket synchronous rotary; In transition frame inside, be fixed with igniting current-collector, igniting current-collector housing is with transition frame by being fixedly connected with along transition frame connecting link radially, and the current-collector housing that makes to light a fire rotates in the lump with transition frame; On one end lateral wall that transition frame coordinates with solid propellant rocket, have the driving groove of connection for transmission band;
Described gear train comprises driving wheel and driving-belt; The power output shaft of driving wheel and propulsion system is connected, and between driving wheel and transition frame, by driving-belt, is connected, and driving wheel drives transition frame to rotate by driving-belt;
Described supporting mechanism comprises support platform and two supporting arc seats; Supporting arc seat is fixed in support platform, supporting arc seat upper end is loop configuration, the loop configuration of a supporting arc seat upper end is enclosed within on one end that transition frame coordinates with solid propellant rocket head, and coordinate by radial ball bearing with transition frame, the loop configuration of another supporting arc seat upper end is enclosed within on solid propellant rocket afterbody housing, and coordinates by radial ball bearing with solid propellant rocket afterbody housing.
Described a kind of solid propellant rocket ground rotation test device, is characterized in that: the bearing seat of thrust bearing, is turned round nail on a side wall surface and had holding screw anti-for clearance fit with the anti-cylinder of turning round, by bearing seat with anti-to turn round cylinder fixing.
Described a kind of solid propellant rocket ground rotation test device, is characterized in that: anti-turning round on a sidewall that coordinates one end with transition frame, overlap and have centering ring, centering is encircled and prevented turning round a clearance fit; In transition frame, there are annulus projection, the external diameter of annulus projection to equal anti-cylinder the coordinates one end end face external diameter with transition frame of turning round with anti-turning round on an end face coordinating.
Described a kind of solid propellant rocket ground rotation test device, is characterized in that: on the end face of the loop configuration of supporting arc seat upper end, have shoulder block, prevent that the mechanism rotating in process of the test from motion vertically occurring.
Beneficial effect
The solid propellant rocket ground rotation test device that adopts the present invention to propose, by propulsion system and gear train, can realize solid propellant rocket under ignition operation state, with certain speed, around engine self axis, rotate, can gaging pressure in rotation, the parameter such as thrust, rotating speed, temperature, and the impact of definite rotating speed on engine performance, structure, material.
Accompanying drawing explanation
Fig. 1: afterbody of the present invention rises and revolves structural representation;
Fig. 2: head of the present invention rises and revolves structural representation;
Fig. 3: an anti-schematic diagram of turning round;
Fig. 4: an anti-structural scheme of mechanism of turning round;
Fig. 5: transition frame schematic diagram;
Fig. 6: the first gear train schematic diagram;
Wherein: 1, the anti-cylinder of turning round; 2, dynamometry assembly; 3, thrust bearing; 4, igniting current-collector; 5, First Transition frame; 6, radial ball bearing; 7, supporting arc seat; 8, support platform; 9, support; 10, the first gear train; 11, propulsion system; 12, the second gear train; 13, centering ring; 14, holding screw; 15, bearing seat; 16, engaged wheel; 17, transmission register pin; 18, ring is embraced in transmission; 19, V-type band; 20, driving wheel; 21, solid propellant rocket; 22, load upper frame; 23, the second transition frame.
Embodiment
Below in conjunction with specific embodiment, the present invention is described:
Embodiment 1:
With reference to accompanying drawing 1, the present embodiment adopts afterbody to play cyclone, and propulsion system are transmitted to engine afterbody by rotating torque, by engine afterbody, drives engine, transition frame, igniting current-collector and other rotation annex to be rotated.
With reference to accompanying drawing 1, the solid propellant rocket ground rotation test device in the present embodiment comprises propulsion system 11, the first gear train 10, supporting mechanism, transition frame mechanism and the anti-force measuring machine of turning round.
With reference to accompanying drawing 1, accompanying drawing 3 and accompanying drawing 4, the described anti-force measuring machine of turning round comprises load upper frame 22, anti-cylinder 1 and the dynamometry assembly 2 turned round.The anti-cylinder of turning round, for hollow structure, in the present embodiment, prevents that turning round one end is joint flange, and one end is step ring, between joint flange and step ring, by pillar, is welded to connect, and forms the anti-cylinder of turning round.Prevent that turning round joint flange one end is fixedly connected with load upper frame bolt, the anti-cylinder of turning round self can not be rotated.An anti-step ring one end of turning round is connected by thrust bearing 3 and First Transition frame 5, and thrust bearing can transmit the Thrust of Solid Rocket Motor that First Transition frame transmits, and does not transmit the rotating torque of First Transition frame simultaneously.Preventing that turning round an inside is fixed with dynamometry assembly 2, dynamometry assembly one end is bolted on anti-turning round on a joint flange, and the dynamometry assembly other end is bolted on the bearing seat 15 of thrust bearing.The bearing seat of thrust bearing is arranged on the anti-step ring inner side of turning round cylinder, the bearing seat of thrust bearing coordinates with step czermak space, on step ring-side wall nail have along step ring radially mark closely screw 14, make bearing seat and the step ring secure fit of thrust bearing, bearing seat and the anti-cylinder of turning round are fixed, bearing seat self can not be rotated, and then dynamometry assembly does not rotate yet.
Described transition frame mechanism comprises First Transition frame 5 and igniting current-collector 4.Transition frame is hollow structure, Main Function is for transmitting the thrust of solid propellant rocket, in the present embodiment, First Transition frame one end is joint flange, and the other end is engine head holder, between First Transition frame joint flange and engine head holder, by connecting rod, is welded and fixed.First Transition frame joint flange one end is connected by thrust bearing and the anti-cylinder of turning round, and on joint flange outer face, there is annulus projection, the external diameter of annulus projection equals the anti-small end external diameter of turning round a step ring, by being socketed centering ring 13 anti-turning round on a step ring small end sidewall and First Transition frame joint flange annulus projection sidewall, can realize that anti-to turn round cylinder coaxial with First Transition frame centering, wherein centering ring is turned round a step ring small end sidewall and First Transition frame joint flange annulus projection sidewall is clearance fit with anti-, can move vertically.The engine head holder of First Transition frame is coaxially fixedly connected with solid propellant rocket 21 heads, and also coaxial with First Transition frame joint flange, so also realizes First Transition frame with the synchronous coaxial rotating of solid propellant rocket.In First Transition frame inside, be fixed with igniting current-collector, igniting current-collector housing is with First Transition frame by being fixedly connected with along First Transition frame connecting link radially, and the current-collector housing that makes to light a fire rotates in the lump with transition frame.
With reference to accompanying drawing 6, described the first gear train comprise driving wheel 20, engaged wheel 16 and transmission embrace ring 18.The power output shaft of driving wheel and propulsion system is connected, and the present embodiment medium power device adopts stepless speed-regulating motor.Between driving wheel and engaged wheel, by V-type band 19, be connected, by the position of Level tune stepless speed-regulating motor, can realize the object of V-type band tensioning.Engaged wheel is loop configuration, and engaged wheel is embraced ring with transmission and is coaxially connected by transmission register pin 17, makes engaged wheel drive transmission to embrace ring and rotates.Transmission is embraced ring for loop configuration, and inner wall surface thereof and solid propellant rocket afterbody housing outer surface, by the key secure fit being uniformly distributed circumferentially, make transmission embrace the moving solid propellant rocket of endless belt and rotate.
Described supporting mechanism comprises support platform 8 and two supporting arc seats 7.Supporting arc seat is fixed in support platform, and supporting arc seat upper end is loop configuration, and the loop configuration of a supporting arc seat upper end is enclosed within on the lateral surface of First Transition frame engine head holder, and coordinates by radial ball bearing 6 with First Transition frame.The loop configuration of another supporting arc seat upper end is enclosed within transmission, and to embrace ring upper, and embrace ring with transmission and coordinate by radial ball bearing.On the end face of the loop configuration of supporting arc seat upper end, there is shoulder block, prevent the mechanism that rotates in process of the test, as motion vertically occurs for engine, First Transition frame etc., make rotation steadily.So, the moment of torsion that propulsion system produce just can steadily and without beating pass to engine, the tensile force that simultaneously V-type band can also be produced is embraced ring by transmission and is delivered on supporting arc seat through radial ball bearing, the moment of flexure of having avoided tensile force to produce engine.
Embodiment 2:
With reference to accompanying drawing 2, the present embodiment adopts head to play cyclone, and propulsion system are transmitted to the second transition frame by rotating torque, by the second transition frame, drives engine head, igniting current-collector and other rotation annex to be rotated.
With reference to accompanying drawing 2, the solid propellant rocket ground rotation test device in the present embodiment comprises propulsion system 11, the second gear train 12, supporting mechanism, transition frame mechanism and the anti-force measuring machine of turning round.
With reference to accompanying drawing 2, accompanying drawing 3 and accompanying drawing 4, the described anti-force measuring machine of turning round comprises load upper frame 22, anti-cylinder 1 and the dynamometry assembly 2 turned round.The anti-cylinder of turning round, for hollow structure, in the present embodiment, prevents that turning round one end is joint flange, and one end is step ring, between joint flange and step ring, by pillar, is welded to connect, and forms the anti-cylinder of turning round.Prevent that turning round joint flange one end is fixedly connected with load upper frame bolt, the anti-cylinder of turning round self can not be rotated.Prevent that turning round step ring one end is connected by thrust bearing 3 and the second transition frame 23, thrust bearing can transmit the Thrust of Solid Rocket Motor that the second transition frame transmits, and does not transmit the rotating torque of the second transition frame simultaneously.Preventing that turning round an inside is fixed with dynamometry assembly 2, dynamometry assembly one end is bolted on anti-turning round on a joint flange, and the dynamometry assembly other end is bolted on the bearing seat 15 of thrust bearing.The bearing seat of thrust bearing is arranged on the anti-step ring inner side of turning round cylinder, the bearing seat of thrust bearing coordinates with step czermak space, on step ring-side wall nail have along step ring radially mark closely screw 14, make bearing seat and the step ring secure fit of thrust bearing, bearing seat and the anti-cylinder of turning round are fixed, bearing seat self can not be rotated, and then dynamometry assembly does not rotate yet.
Described transition frame mechanism comprises the second transition frame 23 and igniting current-collector 4.Transition frame is hollow structure, Main Function is for transmitting the thrust of solid propellant rocket, in the present embodiment, second transition frame one end is joint flange, and the other end is engine head holder, between the second transition frame joint flange and engine head holder, by connecting rod, is welded and fixed.Second transition frame joint flange one end is connected by thrust bearing and the anti-cylinder of turning round, and on joint flange outer face, there is annulus projection, the external diameter of annulus projection equals the anti-small end external diameter of turning round a step ring, by being socketed centering ring 13 anti-turning round on a step ring small end sidewall and the second transition frame joint flange annulus projection sidewall, can realize that anti-to turn round cylinder coaxial with the second transition frame centering, wherein centering ring is turned round a step ring small end sidewall and the second transition frame joint flange annulus projection sidewall is clearance fit with anti-, can move vertically.The engine head holder of the second transition frame is coaxially fixedly connected with solid propellant rocket 21 heads, and also coaxial with the second transition frame joint flange, so also realizes the second transition frame and drives the synchronous coaxial rotating of solid propellant rocket.The driving groove that has connection for transmission band in the second transition frame engine head holder outside wall surface, coordinates for the V-type band with the second gear train.In the second transition frame inside, be fixed with igniting current-collector, igniting current-collector housing is with the second transition frame by being fixedly connected with along the second transition frame connecting link radially, and the current-collector housing that makes to light a fire rotates in the lump with the second transition frame.
Described the second gear train comprises driving wheel 20 and V-type band.The power output shaft of driving wheel and propulsion system is connected, and the present embodiment medium power device adopts stepless speed-regulating motor, by the position of Level tune stepless speed-regulating motor, can realize the object of V-type band tensioning.Between driving wheel and the second transition frame, by V-type band, be connected, driving wheel drives transition frame to rotate by driving-belt.
Described supporting mechanism comprises support platform 8 and two supporting arc seats 7.Supporting arc seat is fixed in support platform, and supporting arc seat upper end is loop configuration, and the loop configuration of a supporting arc seat upper end is enclosed within on the lateral surface of the second transition frame engine head holder, and coordinates by radial ball bearing with the second transition frame.The loop configuration of another supporting arc seat upper end is enclosed within on solid propellant rocket afterbody housing, and coordinates by radial ball bearing with solid propellant rocket afterbody housing.On the end face of the loop configuration of supporting arc seat upper end, there is shoulder block, prevent the mechanism that rotates in process of the test, as motion vertically occurs for engine, the second transition frame etc., make rotation steadily.So, the moment of torsion that propulsion system produce just can steadily and without beating pass to the second transition frame, by the second transition frame, drives engine rotation.
Claims (8)
1. a solid propellant rocket ground rotation test device, comprises propulsion system, gear train, supporting mechanism, transition frame mechanism; Described transition frame mechanism comprises transition frame, and transition frame is hollow structure;
It is characterized in that: described solid propellant rocket ground rotation test device also comprises the anti-force measuring machine of turning round; The described anti-force measuring machine of turning round comprises load upper frame, anti-cylinder and the dynamometry assembly turned round; The anti-cylinder of turning round is for hollow structure, and one end is fixedly connected with load upper frame, and the anti-cylinder of turning round self can not be rotated; Prevent that turning round an other end is connected by thrust bearing and transition frame; Preventing that turning round an inside is fixed with dynamometry assembly, dynamometry assembly one end is fixed on anti-turning round on the inner wall of cylinder, and the dynamometry assembly other end is fixedly connected with the bearing seat of thrust bearing; The bearing seat of thrust bearing is turned round a secure fit with anti-, and bearing seat self can not be rotated;
Described transition frame one end is connected by thrust bearing and the anti-cylinder of turning round, and the other end is coaxially fixedly connected with solid propellant rocket head, makes transition frame with solid propellant rocket synchronous rotary; In transition frame inside, be fixed with igniting current-collector, igniting current-collector housing is with transition frame by being fixedly connected with along transition frame connecting link radially, and the current-collector housing that makes to light a fire rotates in the lump with transition frame;
Described gear train comprises that driving wheel, engaged wheel and transmission embrace ring; The power output shaft of driving wheel and propulsion system is connected, and between driving wheel and engaged wheel, by driving-belt, is connected; Engaged wheel is loop configuration, and engaged wheel is embraced ring with transmission and is coaxially connected by transmission register pin, makes engaged wheel drive transmission to embrace ring and rotates; Transmission is embraced ring for loop configuration, and inner wall surface thereof and solid propellant rocket afterbody housing outer surface, by the key secure fit being uniformly distributed circumferentially, make transmission embrace the moving solid propellant rocket of endless belt and rotate;
Described supporting mechanism comprises support platform and two supporting arc seats; Supporting arc seat is fixed in support platform, supporting arc seat upper end is loop configuration, the loop configuration of a supporting arc seat upper end is enclosed within on one end that transition frame coordinates with solid propellant rocket head, and coordinate by radial ball bearing with transition frame, the loop configuration of another supporting arc seat upper end is enclosed within transmission, and to embrace ring upper, and embrace ring with transmission and coordinate by radial ball bearing.
2. a kind of solid propellant rocket ground rotation test device according to claim 1, is characterized in that: the bearing seat of thrust bearing, is turned round nail on a side wall surface and had holding screw anti-for clearance fit with the anti-cylinder of turning round, by bearing seat with anti-to turn round cylinder fixing.
3. according to a kind of solid propellant rocket ground rotation test device described in claim 1 or 2, it is characterized in that: anti-turning round on a sidewall that coordinates one end with transition frame, overlap and have centering ring, centering is encircled and prevented turning round a clearance fit; In transition frame, there are annulus projection, the external diameter of annulus projection to equal anti-cylinder the coordinates one end end face external diameter with transition frame of turning round with anti-turning round on an end face coordinating.
4. a kind of solid propellant rocket ground rotation test device according to claim 3, is characterized in that: on the end face of the loop configuration of supporting arc seat upper end, have shoulder block, prevent that the mechanism rotating in process of the test from motion vertically occurring.
5. a solid propellant rocket ground rotation test device, comprises propulsion system, gear train, supporting mechanism, transition frame mechanism; Described transition frame mechanism comprises transition frame, and transition frame is hollow structure;
It is characterized in that: described solid propellant rocket ground rotation test device also comprises the anti-force measuring machine of turning round; The described anti-force measuring machine of turning round comprises load upper frame, anti-cylinder and the dynamometry assembly turned round; The anti-cylinder of turning round is for hollow structure, and one end is fixedly connected with load upper frame, and the anti-cylinder of turning round self can not be rotated; Prevent that turning round an other end is connected by thrust bearing and transition frame; Preventing that turning round an inside is fixed with dynamometry assembly, dynamometry assembly one end is fixed on anti-turning round on the inner wall of cylinder, and the dynamometry assembly other end is fixedly connected with the bearing seat of thrust bearing; The bearing seat of thrust bearing is turned round a secure fit with anti-, and bearing seat self can not be rotated;
Described transition frame one end is connected by thrust bearing and the anti-cylinder of turning round, and the other end is coaxially fixedly connected with solid propellant rocket head, makes transition frame drive solid propellant rocket synchronous rotary; In transition frame inside, be fixed with igniting current-collector, igniting current-collector housing is with transition frame by being fixedly connected with along transition frame connecting link radially, and the current-collector housing that makes to light a fire rotates in the lump with transition frame; On one end lateral wall that transition frame coordinates with solid propellant rocket, have the driving groove of connection for transmission band;
Described gear train comprises driving wheel and driving-belt; The power output shaft of driving wheel and propulsion system is connected, and between driving wheel and transition frame, by driving-belt, is connected, and driving wheel drives transition frame to rotate by driving-belt;
Described supporting mechanism comprises support platform and two supporting arc seats; Supporting arc seat is fixed in support platform, supporting arc seat upper end is loop configuration, the loop configuration of a supporting arc seat upper end is enclosed within on one end that transition frame coordinates with solid propellant rocket head, and coordinate by radial ball bearing with transition frame, the loop configuration of another supporting arc seat upper end is enclosed within on solid propellant rocket afterbody housing, and coordinates by radial ball bearing with solid propellant rocket afterbody housing.
6. a kind of solid propellant rocket ground rotation test device according to claim 5, is characterized in that: the bearing seat of thrust bearing, is turned round nail on a side wall surface and had holding screw anti-for clearance fit with the anti-cylinder of turning round, by bearing seat with anti-to turn round cylinder fixing.
7. according to a kind of solid propellant rocket ground rotation test device described in claim 5 or 6, it is characterized in that: anti-turning round on a sidewall that coordinates one end with transition frame, overlap and have centering ring, centering is encircled and prevented turning round a clearance fit; In transition frame, there are annulus projection, the external diameter of annulus projection to equal anti-cylinder the coordinates one end end face external diameter with transition frame of turning round with anti-turning round on an end face coordinating.
8. a kind of solid propellant rocket ground rotation test device according to claim 7, is characterized in that: on the end face of the loop configuration of supporting arc seat upper end, have shoulder block, prevent that the mechanism rotating in process of the test from motion vertically occurring.
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| CN201210286493.0A CN102788698B (en) | 2012-08-13 | 2012-08-13 | Ground rotation testing device for solid rocket engine |
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| CN201210286493.0A CN102788698B (en) | 2012-08-13 | 2012-08-13 | Ground rotation testing device for solid rocket engine |
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| CN104019994B (en) * | 2014-04-24 | 2017-03-01 | 北京理工大学 | A kind of solid propellant rocket overload test device |
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| CN106546431B (en) * | 2015-09-17 | 2018-12-14 | 内蒙航天动力机械测试所 | Solid propellant rocket rotation test in-situ calibration system switching device |
| CN106546432B (en) * | 2015-09-22 | 2018-12-14 | 内蒙航天动力机械测试所 | A kind of solid propellant rocket ground rotation test calibrated in situ device |
| CN108362426B (en) * | 2018-01-22 | 2020-06-30 | 绍兴市秀臻新能源科技有限公司 | Aeroengine thrust detection equipment |
| CN109357881B (en) * | 2018-11-30 | 2020-06-12 | 西安航天动力测控技术研究所 | Thrust measuring device for special-shaped engine |
| CN109459242B (en) * | 2018-12-26 | 2020-04-03 | 北京理工大学 | High-speed self-rotating test bed measurement and control system of solid rocket engine |
| CN110411752B (en) * | 2019-08-07 | 2021-06-15 | 西安近代化学研究所 | Clamping device for high-speed rotation test of solid rocket engine |
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| 王增辉等.某火箭发动机高速旋转试车台旋转架一体化设计与分析.《电子机械工程》.2009,第25卷(第4期),第60-64页. |
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