CN205785819U - A kind of test device for rocket engine ground firing - Google Patents

A kind of test device for rocket engine ground firing Download PDF

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Publication number
CN205785819U
CN205785819U CN201620478045.4U CN201620478045U CN205785819U CN 205785819 U CN205785819 U CN 205785819U CN 201620478045 U CN201620478045 U CN 201620478045U CN 205785819 U CN205785819 U CN 205785819U
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China
Prior art keywords
frame
pressure transducer
test device
oil cylinder
thrust
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CN201620478045.4U
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Chinese (zh)
Inventor
李锡文
魏佳
李宗元
曾广斌
杜松
詹小斌
黄兴
孙志斌
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Huazhong University of Science and Technology
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Huazhong University of Science and Technology
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Abstract

The utility model discloses the test device of a kind of ground firing for rocket engine, described test device includes stand assembly, working sensor, thrust frame, transition frame and anchor ear;Described anchor ear, transition frame, thrust frame and working sensor are from rear to the front top being set in turn in described stand assembly, and described transition frame, thrust frame and working sensor are positioned on the central shaft of described anchor ear.Described test device can also include the second pressure transducer pressing plate, the second pressure transducer, oil cylinder, adaptor and oil cylinder guide rod.Rocket engine is fixed by this utility model by anchor ear and transition frame, anchor ear and transition frame are replaceable, thus adapt to the firing test of the rocket engine of different model, widely applicable, operating pressure sensor can be carried out calibrated in situ simultaneously, thus improve measuring accuracy, effectively reduce the measurement error of test device.

Description

A kind of test device for rocket engine ground firing
Technical field
This utility model belongs to solid propellant rocket ground firing technical field, more particularly, to a kind of test device for rocket engine ground firing.
Background technology
Rocket engine ground firing has test rocket engine transient driving force, chamber pressure and the function of other important parameters, one of major way that ground firing improves as rocket engine Performance Testing and design, significant to the inspection of rocket engine product and the development of new model.Test tests the performance impact of system to the experimental performance parameter such as thrust and pressure, thus affect the precision of result of the test and the cycle of test.
In terms of test device, Aerospace Science and Industry Corporation's test devices using load pier and mounting platform separate type at present more, easily make the generation relative displacement of load pier and mounting platform when pick up calibration, affect the calibration of thrust pickup thrust, thus cause test-fired thrust measure precision low.In addition the test device of separate type is required for when each rocket engine ground firing carrying out mounting platform and load pier installing fixing, and needs to spend longer preparation before causing test;Meanwhile, current test device mostly is the customization of special specific model, needs different test devices for different models, thus improves testing cost.So needing badly in engines ground test run field, a kind of measuring accuracy is good, testing efficiency is high and the universal test system of system run all right.
Utility model content
For disadvantages described above or the Improvement requirement of prior art, this utility model provides a kind of test device for rocket engine ground firing, its object is to solve existing test device and fixes inconvenient, poor for applicability and that precision is low problem.
For achieving the above object, according to an aspect of the present utility model, it is provided that the test device of a kind of ground firing for rocket engine, including stand assembly, the first pressure transducer, thrust frame, transition frame and anchor ear;Described stand assembly is positioned at bottom, described anchor ear is arranged at the rear at described stand assembly top, its axis is parallel with the length direction of described stand assembly, described first pressure transducer is arranged at the front at described stand assembly top, described transition frame is arranged at the rear of described first pressure transducer, and the rear end of described transition frame connects the front end of thrust frame;Described anchor ear, transition frame, thrust frame and the first pressure transducer are coaxial;Described anchor ear, for fixing rocket engine from circumference, makes described rocket engine be positioned on the central shaft of described anchor ear, and described transition frame is for fixing rocket engine from axially, and described first pressure transducer is for measuring rocket engine thrust forward.
Preferably, described test device also includes the second pressure transducer pressing plate, the second pressure transducer (1), oil cylinder, adaptor and oil cylinder guide rod;Described second pressure transducer pressing plate, the second pressure transducer (1) and oil cylinder are sequentially connected with from front to back, described oil cylinder is arranged at the front of described first pressure transducer, the front end of described adaptor connects the rear end of described first pressure transducer, the rear end of described adaptor connects the front end of described thrust frame, and described second pressure transducer pressing plate, the second pressure transducer (1), oil cylinder, adaptor and oil cylinder guide rod are coaxial with described first pressure transducer;Described oil cylinder guide rod is arranged at the side of described oil cylinder, and the front end of described oil cylinder guide rod connects described second pressure transducer pressing plate, and the rear end of described oil cylinder guide rod connects described adaptor;Described oil cylinder is for sending thrust forward, described second pressure transducer is for measuring the thrust that described oil cylinder sends, described second pressure transducer pressing plate is for by described thrust reversing, described oil cylinder guide rod is for passing to adaptor by described reverse thrust, and described adaptor is for passing to the first pressure transducer by described reverse thrust.
As further preferably, described test device also includes that load pier, described load pier are arranged at the top of described stand assembly, and described load pier is used for supporting described oil cylinder, the side of described load pier is fixed with guide rod sleeve, and described leader casing jacket casing is located at the circumference of described oil cylinder guide rod;Described load pier is used for fixing described oil cylinder, and described guide rod sleeve is for fixing described oil cylinder guide rod from circumference.
Preferably, described stand assembly includes mounting platform, determines frame and moving frame;Described mounting platform is positioned at bottom, described determine frame and is fixed on the top of described mounting platform, and described moving frame is fixed on the described top determining frame by multiple support leaf springs, and described anchor ear is fixed on the top of described moving frame;Described support leaf spring is for reducing the described moving frame resistance of motion at fore-and-aft direction, and described mounting platform is for reducing the described relative displacement determining frame and ground.
As further preferably, described moving frame includes inverted T shape groove, described inverted T shape groove is arranged along the longitudinal direction, and the lower end of described anchor ear is provided with and the T-bolt of described inverted T shape groove fit, and described inverted T shape groove and T-bolt are for being relatively fixed described moving frame and described anchor ear.
As it is further preferred that described moving frame and described determine to be provided with between frame multiple first lifting support column;Described first lifting support column is for regulating the height of self, and when described test device is in off working state, its upper end supports moving frame, and when described test device is in running order, its upper end is away from moving frame, in order to avoid affecting the collection of experimental data.
Preferably, between described thrust frame and described stand assembly, the second lifting support column it is provided with;Described second lifting support column is for regulating the height of self, and when described test device is in off working state, the upper end of described second lifting support column supports thrust frame, when described test device is in running order, the upper end of described second lifting support column is away from thrust frame, in order to avoid affecting the collection of experimental data.
Preferably, described anchor ear includes being connected by fixing device between retainer ring and lower retainer ring, fixed ring and lower retainer ring, for being fixed between upper retainer ring and lower retainer ring by rocket engine.
Preferably, described transition frame is cylinder, for being replaced according to the volume of rocket engine, with the rocket engine of fixing different model.
In general, by the contemplated above technical scheme of this utility model compared with prior art, there is following beneficial effect:
1, rocket engine is fixed by this utility model by anchor ear and transition frame, according to different model rocket engine, replaceable different-diameter and length anchor ear and transition frame, thus adapts to the firing test of different model rocket engine;
2, use the devices such as the second pressure transducer pressing plate, the second pressure transducer, oil cylinder, adaptor that operating pressure sensor carries out calibrated in situ, thus improve measuring accuracy, effectively reduce the measurement error of test device;
3, moving frame and determine between frame use support leaf spring as connector, it is only the 0.075% of thrust in the resistance empirical tests of fore-and-aft direction, the effectively vibration during test of buffering rocket engine, and prevent the rigid shock because selecting roller of the prior art to produce as connector, thus improve measuring accuracy;
4, lifting support column is utilized to support thrust frame or moving frame when test device is in off working state, in order to avoid the loss that described device is produced by gravity, thus extend device lifetime.
Accompanying drawing explanation
Fig. 1 a-Fig. 1 d is respectively the integral plate spring running support of this utility model embodiment 1 rearview, side view, front view and top view when for maximum engine test run;
Fig. 2 is the integral plate spring running support of this utility model embodiment 1 side view when for minimum engine test run;
Fig. 3 is the hardware composition schematic diagram of this utility model embodiment 1;
Fig. 4 represents that this utility model embodiment 1 provides the software configuration schematic diagram of test system;
Fig. 5 represents that this utility model embodiment 1 provides the software function composition schematic diagram of test system;
In all of the figs, identical reference is used for representing identical element or structure, wherein:
1-the second pressure transducer, 2-oil cylinder, 3-load pier, 4-the first pressure transducer, 5-adaptor, 6-thrust frame, 7-lifts support column, 8-transition frame, 10-electromotor, 11-determines frame, 12-moving frame, 13-mounting platform, 14-anchor ear, 15-supports leaf spring, 16-the second pressure transducer pressing plate, 17-oil cylinder guide rod, 18-oil cylinder guide rod sleeve, the upper retainer ring of 19-, 20-T type bolt, retainer ring under 21-.
Detailed description of the invention
In order to make the purpose of this utility model, technical scheme and advantage clearer, below in conjunction with drawings and Examples, this utility model is further elaborated.Should be appreciated that specific embodiment described herein, only in order to explain this utility model, is not used to limit this utility model.As long as just can be mutually combined additionally, technical characteristic involved in each embodiment of this utility model disclosed below does not constitutes conflict each other.
This utility model provides a kind of test device for rocket engine ground firing, including stand assembly, the first pressure transducer 4, thrust frame 6, transition frame 8 and anchor ear 14;Described anchor ear 14, transition frame 8, thrust frame 6 and the first pressure transducer 4 are from rear to the front top being set in turn in described stand assembly, and described transition frame 8, thrust frame 6 and the first pressure transducer 4 are positioned on the central shaft of described anchor ear 14, and the central shaft of anchor ear 14 is that fore-and-aft direction is arranged;Wherein, described anchor ear 14 includes retainer ring 19 and lower retainer ring 21, is connected by fixing device such as bolt between fixed ring 19 with described lower retainer ring 21, for fixing rocket engine from circumference, makes rocket engine coaxial with anchor ear 14;Described transition frame 8 is cylinder, is fixed on the front of rocket engine when testing device work, for fixing rocket engine from axially;Described anchor ear 14 and described transition frame 8 all have multiple different size, can be replaced according to the model of rocket engine;The volume of rocket engine is the biggest, then the diameter of anchor ear 14 is the biggest, and the diameter of transition frame 8 is the biggest, and the length of transition frame 8 is the shortest;Described thrust frame 6 is for being used for measuring the thrust of rocket engine by the thrust of rocket engine to front transfer, described first pressure transducer 4.
Described stand assembly can include mounting platform, determine frame 11 and moving frame 12;Described determine frame 11 and be fixed on the top of described mounting platform, described moving frame 12 is fixed on the described top determining frame 11 by multiple support leaf springs 15, described mounting platform is for reducing the described relative displacement determining frame 11 and ground, described support leaf spring 15 is for reducing the described moving frame 12 resistance of motion at fore-and-aft direction, thus the rocket engine resistance of motion forward when decreasing test device work, improve measuring accuracy;Described moving frame 12 includes inverted T shape groove, and axially arranged for fore-and-aft direction along described moving frame 12 of described inverted T shape groove, the lower end of described anchor ear 14 is provided with and the T-bolt of described inverted T shape groove fit;When off working state, described T-bolt can be along inverted T shape groove slide anteroposterior, so that anchor ear adapts to the rocket engine of different model, time in working order, inverted T shape groove fixes with T-bolt, thus described moving frame 12 and described anchor ear 14 is relatively fixed;In described moving frame 12 and described determine between frame 11, it is additionally provided with multiple lifting support column 7, the bottom of described lifting support column 7 is positioned at determines on frame 11, top is connected without fixing with moving frame 12, described lifting support column 7 is used for regulating the height of self, and when described test device is in off working state, its apical support moving frame 12, to reduce the stress supporting leaf spring 15, the service life of extension fixture;When described test device is in running order, its top is away from moving frame 12, in order to avoid affecting the collection of experimental data;Between described thrust frame 6 and described stand assembly, it is again provided with lifting support column 7;When described test device is in off working state, the upper end of this lifting support column 7 supports thrust frame 6, and when described test device is in running order, the upper end of described lifting support column 7 is away from thrust frame 6, to reduce resistance forward, in order to avoid affecting the collection of experimental data.
Described test device can also include calibration assemblies, so that the first pressure transducer 4 is carried out calibrated in situ.Calibration assemblies can include load pier the 3, second pressure transducer pressing plate the 16, second pressure transducer 1, oil cylinder 2, adaptor 5 and oil cylinder guide rod 17;The bottom of load pier 3 is positioned on described stand assembly, is used for supporting described oil cylinder 2;Described second pressure transducer pressing plate the 16, second pressure transducer 1 and oil cylinder 2 are sequentially connected with from front to back, and it is coaxial with anchor ear 14 all equally, described oil cylinder 2 is arranged at the front end of described first pressure transducer 4, the front end of described adaptor 5 connects described first pressure transducer 4, and the rear end of described adaptor 5 connects described thrust frame 6;The side of described load pier 3 is provided with guide rod sleeve 18, and its internal sleeve is provided with oil cylinder guide rod 17, and the front end of described oil cylinder guide rod 17 connects described second pressure transducer pressing plate 16, and the rear end of described oil cylinder guide rod 17 connects described adaptor;Described oil cylinder 2 is for sending thrust forward, described second pressure transducer 1 is for measuring the thrust that described oil cylinder 2 sends, and this thrust is transferred to forward the second pressure transducer pressing plate 16, described second pressure transducer pressing plate 16 is for by described thrust reversing, and reverse thrust is passed to adaptor 5 by oil cylinder guide rod 17, described adaptor 5 is for passing to the first pressure transducer 4 by described reverse thrust, by comparing the first pressure transducer 4 and thrust measurement value of the second pressure transducer 1, thus reach to calibrate the purpose of the first pressure transducer 4.
Embodiment 1
Fig. 1 a-Fig. 1 d is respectively the test rearview of device, side view, front view and the top view of this utility model embodiment 1, and this test device has been fixed with the rocket engine of a diameter of 1000mm;Owing to the present embodiment is equipped with calibrating installation, can be directly to the first pressure sensor calibrating, greatly reducing extraneous factor affects the measurement error brought;Therefore, this test device mainly has two big functions, and one is to calibrate the first pressure transducer before ground firing, and two participate in the real-time measurement of the thrust of rocket engine when being ground firing.
Described test device includes stand assembly, calibration assemblies, the first pressure transducer 4, adaptor 5, thrust frame 6, transition frame 8 and anchor ear 14;Described anchor ear, transition frame 8, thrust frame 6, adaptor 5 and the first pressure transducer 4 are from rear to the front top being set in turn in described stand assembly, and described transition frame 8, thrust frame 6, first pressure transducer 4 and calibration assemblies are all positioned on the central shaft of described anchor ear 14, described anchor ear 14 is for fixing rocket engine 10 from circumference, described transition frame 8 is for fixing rocket engine 10 from axially, described thrust frame 6 is used for fixing described transition frame 8, described first pressure transducer 4 is for measuring rocket engine 10 thrust forward, described calibration assemblies is for calibrating described dynamometry module in place.Lifting support column 7 it is provided with below described adaptor 5 and described thrust frame 6;Wherein, the bottom being arranged at the lifting support column 7 below adaptor 5 is fixed on mounting platform 13, and the bottom being arranged at the lifting support column 7 below thrust frame 6 is fixed in moving frame 12;When described assay device is in off working state, the upper end of lifting support column 7 supports adaptor 5 and thrust frame 6, and when described test device is in running order, the upper end of lifting support column 7 is unsettled, in order to avoid affecting the measurement of thrust.
Wherein, described stand assembly includes mounting platform 13, load pier 3, determines frame 11, support leaf spring 15, moving frame 12 and lifting support column 9;Described mounting platform 13 is arranged at bottom, the front end at described mounting platform top is provided with load pier 3, for fixed calibration assembly, what the rear end at described mounting platform top was provided with rectangle determines frame 11, the described corner determining frame 11 top supports leaf spring 15 by 4 and is fixed with the moving frame 12 of rectangle, support leaf spring and moving frame 12 and determine the fixing of frame 11 and be connected by welding manner, supporting leaf spring is the double leaf spring of single active section, less in the fore-and-aft direction resistance of motion, after empirical tests selects this support leaf spring, resistance has been reduced to the 0.075% of rocket engine thrust;The left and right sides above described moving frame 12 offers two parallel inverted T shape grooves from front to back, is used for fixing anchor ear 14;The described corner determining frame 11 top is further fixed on 4 lifting support columns 9, described lifting support column 7 can regulate oneself height, for supporting moving frame 12 when described test device is in off working state, it is simultaneously used for when described test device is in running order, decline and make its top away from moving frame 12, in order to avoid the collection of impact test data.
Described transition frame 8 is multiple various sizes of cylinders, can be replaced according to the model of rocket engine, when testing device work, the front end of transition frame 8 and thrust frame 6 carry out Flange joint, rear end and rocket engine 10 carry out Flange joint, thus secure rocket engine in the axial direction;Described anchor ear 14 includes retainer ring 19 and lower retainer ring 21, as described in Fig. 1 c, anchor ear 14 is replaced also dependent on the model of rocket engine, to adjust the diameter of anchor ear 14, thus adapt to the rocket engine 10 of different model in the circumferential, the lower section of described lower retainer ring 19 is provided with two T-bolt, thus by the connection of T-bolt with the inverted T shape groove in moving frame, is fixed in moving frame 12 by anchor ear 14;This embodiment includes two anchor ears 14, and the relative distance of two anchor ears 14 can be adjusted according to the model of rocket engine 10, and rocket engine 10 is the longest, and the relative distance of anchor ear 14 can be the most remote so that fixing more firm.
Described calibration assemblies includes the second pressure transducer 1, oil cylinder the 2, second pressure transducer pressing plate 16, oil cylinder guide rod 17 and oil cylinder guide rod sleeve 18;Oil cylinder 2 is fixed on load pier 3, and is arranged at the front end of described first pressure transducer 4, and described second pressure transducer pressing plate the 16, second pressure transducer 1 and oil cylinder 2 are sequentially connected with from front to back;The both sides of described load pier 3 are respectively arranged with two guide rod sleeves 18, and its internal sleeve is provided with oil cylinder guide rod 17, and the front end of described two oil cylinder guide rods 17 connects the second pressure transducer pressing plate 16, rear end connection adapter piece 5;Described oil cylinder 2 is for sending thrust forward, described second pressure transducer 1 is for measuring the thrust that described oil cylinder sends, and pass to the second pressure transducer pressing plate 16, described second pressure transducer pressing plate 16 is for by this thrust reversing, described oil cylinder guide rod 17 for passing to adaptor 5 by the thrust that this is reverse, and passes to the first pressure transducer 4 further.By comparing the first pressure transducer 4 and thrust measurement value of the second pressure transducer 1, can reach the purpose of calibration the first pressure transducer 4.
The operation principle that this test device carries out rocket engine ground firing is as follows:
1, before ground firing, utilize calibration assemblies that this test device carries out calibrated in situ: described oil cylinder 2 forward end applies the thrust of step, the size of pressure is obtained after described second pressure transducer 1 pressurized, and this thrust is passed to the second pressure transducer pressing plate 16, second pressure transducer pressing plate 16 will be delivered to described oil cylinder guide rod 17 after this thrust reversing, oil cylinder guide rod 17 can horizontally slip in oil cylinder guide rod 18 sleeve;Under the effect of oil cylinder guide rod 17, adaptor 5 is by pulling force forward, make the first pressure transducer 4 also in pressured state, and described second pressure transducer 1 is equal with the first pressure transducer 4 pressure, thus complete the demarcation of the first pressure transducer 4, record the working curve of the first pressure transducer 4;
2, according to the model of rocket engine 10, suitable transition frame 8 and anchor ear 14 are selected;Rocket engine the biggest 10, then the diameter of transition frame 8 and anchor ear 14 is the biggest, and transition frame 8 is the shortest, and the distance of two anchor ears 14 is the most remote;In the present embodiment, the spacing between anchor ear 14 is that 200mm~1200mm can be adjusted according to the rocket engine 10 of a diameter of 100mm~1000mm;As Fig. 2 is this utility model embodiment the rocket engine 10 of minimum model is tested time schematic diagram;
3, being connected with thrust frame 6 by flange the front end of transition frame 8, rocket engine 10 is fixed on the rear of transition frame 8 by flange by rear;All of lifting support column 7 is turned down, under the supporting role supporting leaf spring 15, described moving frame 12 and rocket engine 10 mounted thereto are supported, rocket engine 10 is confined to the motion along the longitudinal direction of only one of which degree of freedom, when igniting, rocket engine 10 produces thrust forward, thrust is sequentially delivered to transition frame 8, thrust frame 6, adaptor 5 and the first pressure transducer 4, thus realizes the measurement of thrust.
Fig. 3 provides the hardware composition schematic diagram of test system for this utility model embodiment, including C3K-2400UPS power supply, DH17180D-2 power supply, display, sensor, amplifier, capture card and processor, first outfan of described C3K-2400UPS power supply connects the input of DH17180D-2 power supply, second outfan connects display, the first pressure transducer on described sensor connecting test device, sensor, amplifier, capture card, processor and display are sequentially connected with;Its major function has been the collection of the thrust signal of rocket engine on the first pressure transducer and has transmitted to computer.Rocket engine is while carrying out firing test, first pressure transducer 4 gathers the signals such as transient driving force (0~10mv) and enters test system, signal is amplified to 0~10v through the sensor of described test system, amplifier by signal, voltage is accepted, by the high speed acquisition (10 of capture card for capture card6Hz) to testing software.Described sensor uses Differential Input to computer, the most each sensor is sequentially connected with rosette amplifier by two heart yearns (other two cores are as standby), entering capture card, take two passages of capture card, Differential Input mode effectively reduces test error.On-the-spot ignition signal also gathers signal to test system and software thereof simultaneously as a road, is used for triggering the collection of test system, and the working asynchronously of running support and test system has been effectively ensured.Described ups power for maintaining the normal work of hardware when civil power power-off suddenly.
Fig. 4 provides the software configuration schematic diagram of test system for this utility model embodiment, and software system mainly includes program event control module, acquisition module, calibration module, processing module, initialization module and other module (such as display module, user's management etc.);Wherein, DBM is the basis of other modules, is responsible for test data and the management of system configuration parameter;Initialization module is that system performs each prefunctional preset parameter module, mainly the link of data base, the initialization at interface and function menu etc. is carried out Initialize installation etc.;Program event control module is responsible for and calls other submodules, makes corresponding control according to the various operations of user;Acquisition module, as the basis calibrated, process and show, utilizes capture card that sensing data is read computer;Calibration module calculates accordingly according to the data gathered, and draws working sensor straight line;Processing module mainly to the data collected according to corresponding computing formula, obtain the performance parameter of electromotor;Display module be responsible for the display supplementary module of data mainly include user manage, help, the miscellaneous function such as production report.
This software includes 7 big basic functions: the calibration of thrust pressure transducer, the collection of thrust pressure data, the calculating of thrust pressure intensity parameter curve plotting, thrust pressure data Filtering Processing, thrust pressure data performance parameter, thrust pressure test data point value export and thrust pressure intensity parameter data base administration.Signal enters software after Fig. 3 tests system acquisition, and the major function of software is that triggering collection card gathers, receives the data gathered and to Data Post, as shown in Figure 5.
Embodiment 2
The test device of embodiment 2 does not include calibration assemblies and adaptor 5;Additionally, in this test device, the first pressure transducer 1 is directly connected to thrust frame 6, and other structure is the most same as in Example 1, it is therefore desirable to test system hardware and software carry out ex situ demarcation to the first pressure transducer 4.Wherein, the method utilizing the ex situ carrying out the first pressure transducer 4 between demarcating to demarcate is as follows: the first pressure transducer 4 is placed between demarcation (and off-position) and calibrates, and the passage of its test system remains unchanged the same with the passage of calibrated in situ.Tester can select the first pressure transducer 4 carries out calibrated in situ or ex situ calibration according to practical situation.This automatic checkout system may also receive from the signal of ignition system, and described ignition system is by engine ignition simultaneously, and ignition signal also serves as a road and gathers signal to test system and software thereof, is used for triggering the collection of test system.
Those skilled in the art is easy to understand; the foregoing is only preferred embodiment of the present utility model; not in order to limit this utility model; all any amendment, equivalent and improvement etc. made within spirit of the present utility model and principle, within should be included in protection domain of the present utility model.

Claims (9)

1. the test device for the ground firing of rocket engine, it is characterised in that institute State test device include stand assembly, the first pressure transducer (4), thrust frame (6), transition frame (8) and Anchor ear (14);Described stand assembly is positioned at bottom, and described anchor ear (14) is arranged at described stand assembly top Rear, its axis is parallel with the length direction of described stand assembly, described first pressure transducer (4) Being arranged at the front at described stand assembly top, described transition frame is arranged at described first pressure transducer (4) Rear, the rear end of described transition frame (8) connects the front end of thrust frame (6);Described anchor ear (14), transition Frame (8), thrust frame (6) and the first pressure transducer (4) are coaxial.
Test device the most as claimed in claim 1, it is characterised in that described test device also includes Second pressure transducer pressing plate (16), the second pressure transducer (1), oil cylinder (2), adaptor (5) and oil Cylinder guide rod (17);Described second pressure transducer pressing plate (16), the second pressure transducer (1) and oil cylinder (2) Being sequentially connected with from front to back, described oil cylinder (2) is arranged at the front of described first pressure transducer (4), institute The front end stating adaptor (5) connects the rear end of described first pressure transducer (4), after described adaptor (5) End connects the front end of described thrust frame (6), and described second pressure transducer pressing plate (16), the second pressure pass Sensor (1), oil cylinder (2), adaptor (5) and oil cylinder guide rod (17) are same with described first pressure transducer (4) Axle;Described oil cylinder guide rod (17) is arranged at the side of described oil cylinder (2), the front end of described oil cylinder guide rod (17) Connecting described second pressure transducer pressing plate (16), the rear end of described oil cylinder guide rod (17) connects described switching Part (5).
Test device the most as claimed in claim 2, it is characterised in that described test device also includes Load pier (3), described load pier (3) is arranged at the top of described stand assembly, and described load pier (3) is used In supporting described oil cylinder (2), the side of described load pier (3) is fixed with guide rod sleeve (18), described guide rod Sleeve (18) is sheathed on the circumference of described oil cylinder guide rod (17).
Test device the most as claimed in claim 1, it is characterised in that described stand assembly includes peace Assembling platform (13), determine frame (11) and moving frame (12);Described mounting platform (13) is positioned at bottom, described determines frame (11) being fixed on the top of described mounting platform (13), described moving frame (12) is by multiple support leaf springs (15) Being fixed on the described top determining frame (11), described anchor ear (14) is fixed on the top of described moving frame (12).
Test device the most as claimed in claim 4, it is characterised in that described moving frame (12) is with described Determine between frame (11), to be provided with multiple first lifting support column (7).
Test device the most as claimed in claim 4, it is characterised in that described moving frame (12) includes down T-shaped groove, described inverted T shape groove is arranged along the longitudinal direction, the lower end of described anchor ear (14) be provided with The T-bolt of described inverted T shape groove fit.
Test device the most as claimed in claim 1, it is characterised in that described thrust frame (6) is with described The second lifting support column it is provided with between stand assembly.
Test device the most as claimed in claim 1, it is characterised in that described anchor ear (14) includes Pass through between retainer ring (19) and lower retainer ring (21), fixed ring (19) and lower retainer ring (21) Fixing device connects.
Test device the most as claimed in claim 1, it is characterised in that described transition frame (8) is cylinder Body.
CN201620478045.4U 2016-05-24 2016-05-24 A kind of test device for rocket engine ground firing Expired - Fee Related CN205785819U (en)

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CN109357881A (en) * 2018-11-30 2019-02-19 西安航天动力测控技术研究所 A kind of abnormity motor power measuring device
CN110220712A (en) * 2019-06-24 2019-09-10 西北工业大学 A kind of rocket engine propulsion test device
CN110553847A (en) * 2019-09-25 2019-12-10 泸州卓远液压有限公司 Buoyancy type thrust adapter
CN111795828A (en) * 2020-06-05 2020-10-20 湖北航天技术研究院总体设计所 Horizontal simulation launch test device and method
CN112012853A (en) * 2020-10-04 2020-12-01 西安航天动力测控技术研究所 Solid rocket engine of back skirt connection form thrust transmission device for ignition test
CN112161813A (en) * 2020-09-11 2021-01-01 北京灵动飞天动力科技有限公司 Mobile micro-friction solid rocket engine thrust measurement system and installation method thereof
CN112213062A (en) * 2020-09-29 2021-01-12 南京航空航天大学 Sudden-increase high-energy basic excitation test bed for laboratory and test method
CN112362318A (en) * 2020-09-18 2021-02-12 季华实验室 Jet detecting system, method, equipment and storage medium for ink jet printing head
CN112485012A (en) * 2020-11-13 2021-03-12 东北大学 Solid rocket engine experiment table and stress testing method
CN112710449A (en) * 2020-12-17 2021-04-27 北京苏试创博环境可靠性技术有限公司 Horizontal excitation test device, combination thereof and installation method of horizontal excitation test device
CN115042691A (en) * 2022-05-27 2022-09-13 火箭派(北京)航天科技有限公司 Integrated carrier rocket erecting and transferring trolley

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CN107238457A (en) * 2017-06-28 2017-10-10 北京航空航天大学 A kind of low thrust measurement apparatus
CN108106852B (en) * 2017-12-05 2019-10-22 西安航天动力测控技术研究所 A kind of flange sleeve test stand for rolling-control engine ground firing
CN108106852A (en) * 2017-12-05 2018-06-01 西安航天动力测控技术研究所 A kind of integral flange sleeve test stand for rolling-control engine ground firing
CN108414255A (en) * 2017-12-07 2018-08-17 上海航天精密机械研究所 A kind of push type firing mount separation simulation device
CN108362426A (en) * 2018-01-22 2018-08-03 赵国庆 A kind of aeroengine thrust detection 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
CN108225776A (en) * 2018-04-08 2018-06-29 中国空气动力研究与发展中心计算空气动力研究所 A kind of small-size turbojet engine vector spray testboard
CN108590889A (en) * 2018-05-09 2018-09-28 北京理工大学 A kind of larynx hydrant change propulsive solid propellant rocket ground test device
CN109029332A (en) * 2018-06-21 2018-12-18 湖北三江航天江河化工科技有限公司 A kind of ground experiment device for combined housing
CN108760326A (en) * 2018-07-24 2018-11-06 西安近代化学研究所 A kind of solid engines bump test clamp device
CN109339982B (en) * 2018-10-31 2024-02-13 沈阳航天新光集团有限公司 Rocket engine flexible limiting device
CN109339982A (en) * 2018-10-31 2019-02-15 沈阳航天新光集团有限公司 Rocket engine flexible limit device
CN109357881A (en) * 2018-11-30 2019-02-19 西安航天动力测控技术研究所 A kind of abnormity motor power measuring device
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
CN110220712A (en) * 2019-06-24 2019-09-10 西北工业大学 A kind of rocket engine propulsion test device
CN110220712B (en) * 2019-06-24 2020-08-07 西北工业大学 Rocket engine thrust testing arrangement
CN110553847A (en) * 2019-09-25 2019-12-10 泸州卓远液压有限公司 Buoyancy type thrust adapter
CN111795828B (en) * 2020-06-05 2022-06-03 湖北航天技术研究院总体设计所 Horizontal simulation launch test device and method
CN111795828A (en) * 2020-06-05 2020-10-20 湖北航天技术研究院总体设计所 Horizontal simulation launch test device and method
CN112161813A (en) * 2020-09-11 2021-01-01 北京灵动飞天动力科技有限公司 Mobile micro-friction solid rocket engine thrust measurement system and installation method thereof
CN112362318A (en) * 2020-09-18 2021-02-12 季华实验室 Jet detecting system, method, equipment and storage medium for ink jet printing head
CN112213062A (en) * 2020-09-29 2021-01-12 南京航空航天大学 Sudden-increase high-energy basic excitation test bed for laboratory and test method
CN112012853A (en) * 2020-10-04 2020-12-01 西安航天动力测控技术研究所 Solid rocket engine of back skirt connection form thrust transmission device for ignition test
CN112012853B (en) * 2020-10-04 2021-07-06 西安航天动力测控技术研究所 Solid rocket engine of back skirt connection form thrust transmission device for ignition test
CN112485012A (en) * 2020-11-13 2021-03-12 东北大学 Solid rocket engine experiment table and stress testing method
CN112710449A (en) * 2020-12-17 2021-04-27 北京苏试创博环境可靠性技术有限公司 Horizontal excitation test device, combination thereof and installation method of horizontal excitation test device
CN115042691A (en) * 2022-05-27 2022-09-13 火箭派(北京)航天科技有限公司 Integrated carrier rocket erecting and transferring trolley

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