CN102788698A - Ground rotation testing device for solid rocket engine - Google Patents
Ground rotation testing device for solid rocket engine Download PDFInfo
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- CN102788698A CN102788698A CN2012102864930A CN201210286493A CN102788698A CN 102788698 A CN102788698 A CN 102788698A CN 2012102864930 A CN2012102864930 A CN 2012102864930A CN 201210286493 A CN201210286493 A CN 201210286493A CN 102788698 A CN102788698 A CN 102788698A
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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 engines ground experimental technique field, be specially a kind of solid propellant rocket ground rotation test device.
Background technology
After solid propellant rocket blasted off, himself rotation can cause the motor body local temperature to heat up, if in ground design and process of the test, do not consider this phenomenon, tended to cause the former thereby destruction of engine Yin Wendu, caused abortive launch.Therefore in ground design and process of the test, need carry out certification test in the internal work characteristic under self rotation status to engine.The technical scheme that does not also have correlation test equipment at present in the open source literature.
Summary of the invention
The technical matters that solves
For realizing engine is carried out in the internal work characteristic under self rotation status the purpose of certification test; 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 has two kinds of basic structures according to different to the emphasis of motor body examination.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:
Said 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-tube of turning round in said place is hollow structure, and an end is fixedly connected with the load upper frame, and the anti-tube of turning round self can not be rotated; Prevent that turning round an other end is connected through thrust bearing and transition frame; Preventing that turning round an internal fixation has the dynamometry assembly, dynamometry assembly one end is fixed on anti-turning round on the inner wall of tube, 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;
Said transition frame mechanism comprises transition frame and igniting current-collector; Transition frame is a hollow structure, and an end is connected through thrust bearing and the anti-tube of turning round, and the other end is fixedly connected with the solid propellant rocket head is coaxial, and transition frame is rotated with solid propellant rocket synchronously; In the transition frame internal fixation igniting current-collector is arranged, igniting current-collector housing and transition frame make the current-collector housing of lighting a fire rotate in the lump with transition frame through being fixedly connected along transition frame connecting link radially;
Said gear train comprises that driving wheel, engaged wheel and transmission embrace ring; The PTO of driving wheel and propulsion system is connected, and is connected through driving-belt between driving wheel and the engaged wheel; Engaged wheel is a loop configuration, and engaged wheel is embraced ring with transmission and is connected through the transmission register pin is coaxial, makes engaged wheel drive transmission and embraces the ring rotation; Transmission is embraced ring and is loop configuration, and inner wall surface thereof and solid propellant rocket afterbody housing outer surface make transmission embrace the moving solid propellant rocket of endless belt and rotate through along circumferential equally distributed key secure fit;
Said supporting mechanism comprises support platform and two support arc seats; Supporting the arc seat is fixed on the support platform; Supporting arc seat upper end is loop configuration; Loop configuration that supports arc seat upper end is enclosed within on transition frame and the end that the solid propellant rocket head cooperates; And cooperate through radial ball bearing with transition frame, another loop configuration that supports arc seat upper end is enclosed within transmission and embraces on the ring, and embraces ring with transmission and cooperate through radial ball bearing.
Said a kind of solid propellant rocket ground rotation test device is characterized in that: the bearing seat of thrust bearing is clearance fit with the anti-tube of turning round, and turns round anti-that nail has holding screw on the side wall surface, with bearing seat with anti-to turn round tube fixing.
Said a kind of solid propellant rocket ground rotation test device is characterized in that: be with the centering ring on the sidewall that cooperates an end with transition frame anti-turning round, a centering ring and an anti-clearance fit of turning round; Have annulus protruding in transition frame with anti-turning round on the end face that cooperates, the protruding external diameter of annulus equals anti-tube cooperates an end with transition frame the end face external diameter of turning round.
Said a kind of solid propellant rocket ground rotation test device is characterized in that: on the end face of the loop configuration of support arc seat upper end shoulder block is arranged, prevent that the mechanism that rotates in the process of the test from motion vertically taking place.
Said 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 said anti-force measuring machine of turning round comprises load upper frame, anti-tube and the dynamometry assembly turned round; The anti-tube of turning round is hollow structure, and an end is fixedly connected with the load upper frame, and the anti-tube of turning round self can not be rotated; Prevent that turning round an other end is connected through thrust bearing and transition frame; Preventing that turning round an internal fixation has the dynamometry assembly, dynamometry assembly one end is fixed on anti-turning round on the inner wall of tube, 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;
Said transition frame mechanism comprises transition frame and igniting current-collector; Transition frame is a hollow structure, and an end is connected through thrust bearing and the anti-tube of turning round, and the other end is fixedly connected with the solid propellant rocket head is coaxial, makes transition frame drive solid propellant rocket and rotates synchronously; In the transition frame internal fixation igniting current-collector is arranged, igniting current-collector housing and transition frame make the current-collector housing of lighting a fire rotate in the lump with transition frame through being fixedly connected along transition frame connecting link radially; Have the driving groove that is connected driving-belt on the end lateral wall that transition frame and solid propellant rocket cooperate;
Said gear train comprises driving wheel and driving-belt; The PTO of driving wheel and propulsion system is connected, and is connected through driving-belt between driving wheel and the transition frame, and driving wheel drives transition frame through driving-belt and rotates;
Said supporting mechanism comprises support platform and two support arc seats; Supporting the arc seat is fixed on the support platform; Supporting arc seat upper end is loop configuration; Loop configuration that supports arc seat upper end is enclosed within on transition frame and the end that the solid propellant rocket head cooperates; And cooperate through radial ball bearing with transition frame, another loop configuration that supports arc seat upper end is enclosed within on the solid propellant rocket afterbody housing, and cooperates through radial ball bearing with solid propellant rocket afterbody housing.
Said a kind of solid propellant rocket ground rotation test device is characterized in that: the bearing seat of thrust bearing is clearance fit with the anti-tube of turning round, and turns round anti-that nail has holding screw on the side wall surface, with bearing seat with anti-to turn round tube fixing.
Said a kind of solid propellant rocket ground rotation test device is characterized in that: be with the centering ring on the sidewall that cooperates an end with transition frame anti-turning round, a centering ring and an anti-clearance fit of turning round; Have annulus protruding in transition frame with anti-turning round on the end face that cooperates, the protruding external diameter of annulus equals anti-tube cooperates an end with transition frame the end face external diameter of turning round.
Said a kind of solid propellant rocket ground rotation test device is characterized in that: on the end face of the loop configuration of support arc seat upper end shoulder block is arranged, prevent that the mechanism that rotates in the process of the test from motion vertically taking place.
Beneficial effect
The solid propellant rocket ground rotation test device that adopts the present invention to propose; Through propulsion system and gear train; Can realize that solid propellant rocket is under the ignition operation state; Rotate around engine self axis with certain speed, parameters such as energy measurement pressure, thrust, rotating speed, temperature in rotation, and definite rotating speed is to the influence of engine performance, structure, material.
Description of drawings
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-synoptic diagram of turning round;
Fig. 4: an anti-structural scheme of mechanism of turning round;
Fig. 5: transition frame synoptic diagram;
Fig. 6: the first gear train synoptic diagram;
Wherein: 1, the anti-tube of turning round; 2, dynamometry assembly; 3, thrust bearing; 4, igniting current-collector; 5, first transition frame; 6, radial ball bearing; 7, support the arc seat; 8, support platform; 9, support; 10, first gear train; 11, propulsion system; 12, 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, second transition frame.
Embodiment
Below in conjunction with specific embodiment the present invention is described:
Embodiment 1:
With reference to accompanying drawing 1, present embodiment adopts afterbody to play cyclone, and promptly propulsion system are transmitted to the engine afterbody with rotating torque, drives engine, transition frame, igniting current-collector and other rotation annex by the engine afterbody and is rotated.
With reference to accompanying drawing 1, the solid propellant rocket ground rotation test device in the present embodiment comprises propulsion system 11, 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 said anti-force measuring machine of turning round comprises load upper frame 22, anti-tube 1 and the dynamometry assembly 2 turned round.The anti-tube of turning round is hollow structure, and in the present embodiment, preventing turning round tube one end is joint flange, and an end is the step ring, is welded to connect through pillar between joint flange and the step ring, forms the anti-tube of turning round.Prevent that turning round a joint flange one end is connected with load upper frame bolt, the anti-tube of turning round self can not be rotated.Prevent that turning round step ring one end is connected through the thrust bearing 3 and first transition frame 5, thrust bearing can transmit the solid propellant rocket thrust that first transition frame transmits, and does not transmit the rotating torque of first transition frame simultaneously.Preventing that turning round an internal fixation has dynamometry assembly 2, dynamometry assembly one end is through being bolted to anti-turning round on the joint flange, and the dynamometry assembly other end is through on the bearing seat 15 that is bolted to thrust bearing.The bearing seat of thrust bearing is installed in the anti-step ring inboard of turning round tube; The bearing seat of thrust bearing cooperates with the step czermak space; On the step ring-side wall nail have along the step ring radially mark closely screw 14, make bearing seat and the step ring secure fit of thrust bearing, bearing seat and the anti-tube of turning round are fixed; Bearing seat self can not be rotated, and then the dynamometry assembly does not rotate yet.
Said transition frame mechanism comprises first transition frame 5 and igniting current-collector 4.Transition frame is a hollow structure; Mainly act as the thrust of transmitting solid propellant rocket; First transition frame, one end is a joint flange in the present embodiment, and the other end is the engine head holder, and is fixing through the connecting rod welding between the first transition frame joint flange and the engine head holder.The first transition frame joint flange, one end is connected through thrust bearing and the anti-tube of turning round; And on the joint flange outer face, there is annulus protruding; The protruding external diameter of annulus equals the anti-small end external diameter of turning round a step ring; Through preventing turning round socket centering ring 13 on a step ring small end sidewall and the protruding sidewall of the first transition frame joint flange annulus; Can realize that anti-to turn round tube coaxial with the first transition frame centering, wherein the centering ring is turned round a step ring small end sidewall and first transition frame joint flange annulus convexity sidewall is a clearance fit with anti-, can move vertically.The engine head holder of first transition frame and coaxial fixed connection of solid propellant rocket 21 heads, and also coaxial with the first transition frame joint flange, realize that so also first transition frame is with the synchronous coaxial rotation of solid propellant rocket.In the first transition frame internal fixation igniting current-collector is arranged, igniting current-collector housing is fixedly connected through edge first transition frame connecting link radially with first transition frame, and igniting current-collector housing is rotated with transition frame in the lump.
With reference to accompanying drawing 6, said first gear train comprise driving wheel 20, engaged wheel 16 and transmission embrace the ring 18.The PTO of driving wheel and propulsion system is connected, and present embodiment medium power device adopts stepless speed-regulating motor.Be connected through V-type band 19 between driving wheel and the engaged wheel,, can realize purpose the tensioning of V-type band through the position of horizontal adjustment stepless speed-regulating motor.Engaged wheel is a loop configuration, and engaged wheel is embraced ring through 17 coaxial connections of transmission register pin with transmission, makes engaged wheel drive transmission and embraces the ring rotation.Transmission is embraced ring and is loop configuration, and inner wall surface thereof and solid propellant rocket afterbody housing outer surface make transmission embrace the moving solid propellant rocket of endless belt and rotate through along circumferential equally distributed key secure fit.
Said supporting mechanism comprises support platform 8 and two support arc seats 7.Support the arc seat and be fixed on the support platform, supporting arc seat upper end is loop configuration, and a loop configuration that supports arc seat upper end is enclosed within on the lateral surface of the first transition frame engine head holder, and cooperates through radial ball bearing 6 with first transition frame.Another loop configuration that supports arc seat upper end is enclosed within transmission and embraces on the ring, and embraces ring with transmission and cooperate through radial ball bearing.Supporting on the end face of loop configuration of arc seat upper end has shoulder block, prevents the mechanism that rotates in the process of the test from like engine, first transition frame etc. motion vertically to take place, and makes rotation steadily.So; The moment of torsion that propulsion system produce just can be steadily and nothing pass to engine with beating; The tensile force that can also produce the V-type band simultaneously embrace ring through transmission and be delivered to through radial ball bearing and support on the arc seat, avoided tensile force to moment of flexure that engine produced.
Embodiment 2:
With reference to accompanying drawing 2, present embodiment adopts head to play cyclone, and promptly propulsion system are transmitted to second transition frame with rotating torque, drives engine head, igniting current-collector and other rotation annex by second transition frame and is rotated.
With reference to accompanying drawing 2, the solid propellant rocket ground rotation test device in the present embodiment comprises propulsion system 11, 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 said anti-force measuring machine of turning round comprises load upper frame 22, anti-tube 1 and the dynamometry assembly 2 turned round.The anti-tube of turning round is hollow structure, and in the present embodiment, preventing turning round tube one end is joint flange, and an end is the step ring, is welded to connect through pillar between joint flange and the step ring, forms the anti-tube of turning round.Prevent that turning round a joint flange one end is connected with load upper frame bolt, the anti-tube of turning round self can not be rotated.Prevent that turning round step ring one end is connected through the thrust bearing 3 and second transition frame 23, thrust bearing can transmit the solid propellant rocket thrust that second transition frame transmits, and does not transmit the rotating torque of second transition frame simultaneously.Preventing that turning round an internal fixation has dynamometry assembly 2, dynamometry assembly one end is through being bolted to anti-turning round on the joint flange, and the dynamometry assembly other end is through on the bearing seat 15 that is bolted to thrust bearing.The bearing seat of thrust bearing is installed in the anti-step ring inboard of turning round tube; The bearing seat of thrust bearing cooperates with the step czermak space; On the step ring-side wall nail have along the step ring radially mark closely screw 14, make bearing seat and the step ring secure fit of thrust bearing, bearing seat and the anti-tube of turning round are fixed; Bearing seat self can not be rotated, and then the dynamometry assembly does not rotate yet.
Said transition frame mechanism comprises second transition frame 23 and igniting current-collector 4.Transition frame is a hollow structure; Mainly act as the thrust of transmitting solid propellant rocket; Second transition frame, one end is a joint flange in the present embodiment, and the other end is the engine head holder, and is fixing through the connecting rod welding between the second transition frame joint flange and the engine head holder.The second transition frame joint flange, one end is connected through thrust bearing and the anti-tube of turning round; And on the joint flange outer face, there is annulus protruding; The protruding external diameter of annulus equals the anti-small end external diameter of turning round a step ring; Through preventing turning round socket centering ring 13 on a step ring small end sidewall and the protruding sidewall of the second transition frame joint flange annulus; Can realize that anti-to turn round tube coaxial with the second transition frame centering, wherein the centering ring is turned round a step ring small end sidewall and second transition frame joint flange annulus convexity sidewall is a clearance fit with anti-, can move vertically.The engine head holder of second transition frame and coaxial fixed connection of solid propellant rocket 21 heads, and also coaxial with the second transition frame joint flange, realize that so also second transition frame drives the synchronous coaxial rotation of solid propellant rocket.Have the driving groove that connects driving-belt on the second transition frame engine head holder outside wall surface, be used for cooperating with the V-type band of second gear train.In the second transition frame internal fixation igniting current-collector is arranged, igniting current-collector housing is fixedly connected through edge second transition frame connecting link radially with second transition frame, and igniting current-collector housing is rotated with second transition frame in the lump.
Said second gear train comprises driving wheel 20 and V-type band.The PTO of driving wheel and propulsion system is connected, and present embodiment medium power device adopts stepless speed-regulating motor, through the position of horizontal adjustment stepless speed-regulating motor, can realize the purpose with the tensioning of V-type band.Be connected through the V-type band between driving wheel and second transition frame, driving wheel drives transition frame through driving-belt and rotates.
Said supporting mechanism comprises support platform 8 and two support arc seats 7.Support the arc seat and be fixed on the support platform, supporting arc seat upper end is loop configuration, and a loop configuration that supports arc seat upper end is enclosed within on the lateral surface of the second transition frame engine head holder, and cooperates through radial ball bearing with second transition frame.Another loop configuration that supports arc seat upper end is enclosed within on the solid propellant rocket afterbody housing, and cooperates through radial ball bearing with solid propellant rocket afterbody housing.Supporting on the end face of loop configuration of arc seat upper end has shoulder block, prevents the mechanism that rotates in the process of the test from like engine, second transition frame etc. motion vertically to take place, and makes rotation steadily.So, the moment of torsion that propulsion system produce just can be steadily and nothing pass to second transition frame with beating, by second transition frame drive engine rotation.
Claims (8)
1. a 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 said anti-force measuring machine of turning round comprises load upper frame, anti-tube and the dynamometry assembly turned round; The anti-tube of turning round is hollow structure, and an end is fixedly connected with the load upper frame, and the anti-tube of turning round self can not be rotated; Prevent that turning round an other end is connected through thrust bearing and transition frame; Preventing that turning round an internal fixation has the dynamometry assembly, dynamometry assembly one end is fixed on anti-turning round on the inner wall of tube, 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;
Said transition frame mechanism comprises transition frame and igniting current-collector; Transition frame is a hollow structure, and an end is connected through thrust bearing and the anti-tube of turning round, and the other end is fixedly connected with the solid propellant rocket head is coaxial, and transition frame is rotated with solid propellant rocket synchronously; In the transition frame internal fixation igniting current-collector is arranged, igniting current-collector housing and transition frame make the current-collector housing of lighting a fire rotate in the lump with transition frame through being fixedly connected along transition frame connecting link radially;
Said gear train comprises that driving wheel, engaged wheel and transmission embrace ring; The PTO of driving wheel and propulsion system is connected, and is connected through driving-belt between driving wheel and the engaged wheel; Engaged wheel is a loop configuration, and engaged wheel is embraced ring with transmission and is connected through the transmission register pin is coaxial, makes engaged wheel drive transmission and embraces the ring rotation; Transmission is embraced ring and is loop configuration, and inner wall surface thereof and solid propellant rocket afterbody housing outer surface make transmission embrace the moving solid propellant rocket of endless belt and rotate through along circumferential equally distributed key secure fit;
Said supporting mechanism comprises support platform and two support arc seats; Supporting the arc seat is fixed on the support platform; Supporting arc seat upper end is loop configuration; Loop configuration that supports arc seat upper end is enclosed within on transition frame and the end that the solid propellant rocket head cooperates; And cooperate through radial ball bearing with transition frame, another loop configuration that supports arc seat upper end is enclosed within transmission and embraces on the ring, and embraces ring with transmission and cooperate through radial ball bearing.
2. according to the said a kind of solid propellant rocket of claim 1 ground rotation test device, it is characterized in that: the bearing seat of thrust bearing is clearance fit with the anti-tube of turning round, and turns round anti-that nail has holding screw on the side wall surface, with bearing seat with anti-to turn round tube fixing.
3. according to claim 1 or 2 said a kind of solid propellant rocket ground rotation test devices, it is characterized in that: be with the centering ring on the sidewall that cooperates an end with transition frame anti-turning round, a centering ring and an anti-clearance fit of turning round; Have annulus protruding in transition frame with anti-turning round on the end face that cooperates, the protruding external diameter of annulus equals anti-tube cooperates an end with transition frame the end face external diameter of turning round.
4. according to the said a kind of solid propellant rocket of claim 3 ground rotation test device, it is characterized in that: on the end face of the loop configuration of support arc seat upper end shoulder block is arranged, prevent that the mechanism that rotates in the process of the test from motion vertically taking place.
5. a 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 said anti-force measuring machine of turning round comprises load upper frame, anti-tube and the dynamometry assembly turned round; The anti-tube of turning round is hollow structure, and an end is fixedly connected with the load upper frame, and the anti-tube of turning round self can not be rotated; Prevent that turning round an other end is connected through thrust bearing and transition frame; Preventing that turning round an internal fixation has the dynamometry assembly, dynamometry assembly one end is fixed on anti-turning round on the inner wall of tube, 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;
Said transition frame mechanism comprises transition frame and igniting current-collector; Transition frame is a hollow structure, and an end is connected through thrust bearing and the anti-tube of turning round, and the other end is fixedly connected with the solid propellant rocket head is coaxial, makes transition frame drive solid propellant rocket and rotates synchronously; In the transition frame internal fixation igniting current-collector is arranged, igniting current-collector housing and transition frame make the current-collector housing of lighting a fire rotate in the lump with transition frame through being fixedly connected along transition frame connecting link radially; Have the driving groove that is connected driving-belt on the end lateral wall that transition frame and solid propellant rocket cooperate;
Said gear train comprises driving wheel and driving-belt; The PTO of driving wheel and propulsion system is connected, and is connected through driving-belt between driving wheel and the transition frame, and driving wheel drives transition frame through driving-belt and rotates;
Said supporting mechanism comprises support platform and two support arc seats; Supporting the arc seat is fixed on the support platform; Supporting arc seat upper end is loop configuration; Loop configuration that supports arc seat upper end is enclosed within on transition frame and the end that the solid propellant rocket head cooperates; And cooperate through radial ball bearing with transition frame, another loop configuration that supports arc seat upper end is enclosed within on the solid propellant rocket afterbody housing, and cooperates through radial ball bearing with solid propellant rocket afterbody housing.
6. according to the said a kind of solid propellant rocket of claim 5 ground rotation test device, it is characterized in that: the bearing seat of thrust bearing is clearance fit with the anti-tube of turning round, and turns round anti-that nail has holding screw on the side wall surface, with bearing seat with anti-to turn round tube fixing.
7. according to claim 5 or 6 said a kind of solid propellant rocket ground rotation test devices, it is characterized in that: be with the centering ring on the sidewall that cooperates an end with transition frame anti-turning round, a centering ring and an anti-clearance fit of turning round; Have annulus protruding in transition frame with anti-turning round on the end face that cooperates, the protruding external diameter of annulus equals anti-tube cooperates an end with transition frame the end face external diameter of turning round.
8. according to the said a kind of solid propellant rocket of claim 7 ground rotation test device, it is characterized in that: on the end face of the loop configuration of support arc seat upper end shoulder block is arranged, prevent that the mechanism that rotates in the process of the test from motion vertically taking place.
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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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| CN103018048A (en) * | 2012-12-03 | 2013-04-03 | 西安航天发动机厂 | Performance testing apparatus of two-way rocking mechanism |
| CN104019994A (en) * | 2014-04-24 | 2014-09-03 | 北京理工大学 | Overload testing device and method of solid rocket engine |
| CN104792540A (en) * | 2015-05-21 | 2015-07-22 | 中国工程物理研究院总体工程研究所 | Centrifugal overload test system of solid rocket engine |
| CN106546432A (en) * | 2015-09-22 | 2017-03-29 | 内蒙航天动力机械测试所 | A kind of solid propellant rocket ground rotation test calibrated in situ device |
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| CN110411752A (en) * | 2019-08-07 | 2019-11-05 | 西安近代化学研究所 | A kind of solid propellant rocket high speed rotation test clamping device |
| CN111766073A (en) * | 2020-07-09 | 2020-10-13 | 北京理工大学 | Solid rocket engine high-speed spin test holding device |
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