CN103969019A - Drop test device with delivery and posture adjusting function - Google Patents
Drop test device with delivery and posture adjusting function Download PDFInfo
- Publication number
- CN103969019A CN103969019A CN201410222288.7A CN201410222288A CN103969019A CN 103969019 A CN103969019 A CN 103969019A CN 201410222288 A CN201410222288 A CN 201410222288A CN 103969019 A CN103969019 A CN 103969019A
- Authority
- CN
- China
- Prior art keywords
- spacecraft
- suspender
- lifting
- pose
- adjuster
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Load-Engaging Elements For Cranes (AREA)
Abstract
The invention discloses a drop test device with the delivery and posture adjusting function. The device comprises a delivery mechanism, an electrical delivery component, a turning-connecting lifting lug, a limiting rope, a lifting appliance and a posture adjusting mechanism, wherein the delivery mechanism is hung in a large lifting ring, the large lifting ring is hung in a crane lifting hook, the turning-connecting lifting lug is hung in a clamping hook below the delivery mechanism, the turning-connecting lifting lug is connected with a small lifting ring on the lifting appliance, the lifting appliance is connected with a lifting point of a spacecraft and is fastened through a bolt, one end of the limiting rope is connected with the large lifting ring, the other end of the limiting rope is connected with the small lifting ring on the lifting appliance, one end of the posture adjusting mechanism is connected with the spacecraft in a fastening mode, and the other end of the posture adjusting mechanism can be connected with a movable large-mass weight in a fastening mode. Compared with the prior art, delivery, lifting and posture adjusting functions of the spacecraft drop test device are achieved, the structure of all test devices is simplified, the aims of rapid separation of the test devices, and controllable delivery postures and interference removal are achieved, and the device is easy to operate, safe and reliable, and has the good use effect.
Description
Technical field
The invention belongs to spacecraft testing class frock technical field, specifically, relate to a kind of fall-down test device with input and posture adjustment function.
Background technology
In certain class spacecraft develops process, for testing its structural behaviour, conventionally need to carry out fall-down test.At present, conventionally there are two kinds of methods to realize fall-down test, one is to utilize falling test stand, product is placed on platform, then platform is risen to certain altitude, by the attitude of controlling platform, product is thrown in different angles and speed, still, this method is generally applicable to the product lightweight, volume is little.Another kind is to adopt special delivery device, and product is hung in the air, then throws in, and drops to ground in the mode of freely falling body.Generally speaking, the fall-down test of spacecraft adopts the mode of the movement of falling object, is first promoted to test height, and adjusts initial attitude, is then thrown in, and makes it do the movement of falling object, drops to test ground.Because the quality of spacecraft is heavier, size is larger, simultaneously higher to initial input attitude and rate request, current existing delivery device cannot meet load and posture adjustment requirement, therefore need to develop a kind of fall-down test device with input and posture adjustment function, to realize the spacecraft fall-down test of large load and high posture adjustment requirement.
Summary of the invention
The object of the present invention is to provide a kind of have throw in and the fall-down test device of posture adjustment function, be intended to solve spacecraft in fall-down test, throws in separate that response fast, input attitude are controlled, test unit is to the glitch-free technical barrier of spacecraft.
To achieve these goals, the present invention has adopted following technical scheme:
A kind of fall-down test device with input and posture adjustment function, comprise throwing mechanism, electric input assembly, switching hanger, limit rope, suspender, pose_adjuster, throwing mechanism top hangs in large suspension ring by shackle one, large suspension ring top hangs in the suspension hook of crane, switching hanger is hung in the grab of throwing mechanism below, grab before drop-test in closure state, the cable connector on the cable on throwing mechanism and electric input assembly; The below of switching hanger is connected with the little suspension ring on suspender by shackle two, suspender is connected with the suspension centre of spacecraft by adaptor, and by bolted, before lifting, the barycenter of suspender and spacecraft is at same axis, one end of limit rope is connected with the large suspension ring of throwing mechanism top by shackle three, the other end is connected with the little suspension ring on suspender by shackle four, pose_adjuster one end is connected fastening with spaceborne interface, the other end is connected fastening with removable large quality counterweight, in spacecraft hoisting process, pose_adjuster is in relaxed state.
Wherein, the cable on electric input assembly, according to release altitude configured length, is realized the release action of controlling grab on throwing mechanism on ground.
Wherein, limit rope is for controlling the falling head of suspender, when after throwing mechanism release, suspender and spacecraft are thrown in simultaneously, and in fall-down test, suspender cannot separate with spacecraft, by controlling the length of limit rope, control the dropping distance of suspender, avoid suspender and spacecraft to bump against;
Wherein, suspender adopts 2 lifting spacecrafts, is provided with regulating device on suspender, for adjusting the position of little suspension ring, ensures that the barycenter of itself and spacecraft of when lifting, on same axis, avoids bias to cause and rock;
Wherein, pose_adjuster is the pose_adjuster that two covers are identical, is connected respectively fasteningly with spacecraft, on spacecraft, is symmetrically distributed in spacecraft suspension centre interface both sides with the interface of pose_adjuster.
Compared with prior art, the present invention has realized the input of spacecraft fall-down test device, suspention and posture adjustment function, the functional requirement of fall-down test is rationally decomposed, thereby simplify the structure of each several part test unit, integrated by effective function, solve test unit and separated fast, thrown in controlled, the glitch-free technical barrier of attitude, this device is simple to operate, safe and reliable, obtain good result of use.
Brief description of the drawings
Fig. 1 is a kind of fall-down test device schematic diagram with input and posture adjustment function of the present invention;
Fig. 1-1st, the place of I shown in Fig. 1 partial enlarged view;
Wherein 1 is suspender; 2 is delivery device; 8 is switching hanger; 9 is shackle; 10 is large suspension ring; 11 is little suspension ring.
Fig. 2 is a kind of fall-down test device schematic diagram with input and posture adjustment function of the present invention;
Wherein 3 is limit rope; 4 is electric input assembly; 5 is pose_adjuster; 6 is removable large quality counterweight; 7 is spacecraft.
Fig. 3 is that a kind of fall-down test device with quick input and posture adjustment function of the present invention drops to view behind test site.
Embodiment
What below introduce is the embodiment as content of the present invention, below by embodiment, described content of the present invention is further illustrated.Certainly, describing following embodiment is only the content of example different aspect of the present invention, and should not be construed as the restriction scope of the invention.
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Fig. 1 is a kind of fall-down test device schematic diagram with input and posture adjustment function of the present invention.Fig. 1-1st, the partial enlarged view of the place of I shown in Fig. 1 structure.Fig. 2 is a kind of fall-down test device schematic diagram with input and posture adjustment function of the present invention.Wherein, a kind of fall-down test device with input and posture adjustment function of the present invention, comprises suspender 1, delivery device 2, limit rope 3, electric input assembly 4, pose_adjuster 5, removable large quality counterweight 6, switching hanger 8, upper and lower two shackles 9, large suspension ring 10, little suspension ring 11.Large suspension ring 10 are hung on the suspension hook of crane, delivery device 2 is arranged in the suspension ring of large suspension ring 10 by a shackle (shackle one) 9, the top of switching hanger 8 is hung in the grab of delivery device 2, and grab should be in closure state before drop-test; The below of switching hanger 8 is connected with the little suspension ring 11 of suspender 1 top by another shackle (shackle two) 9, and suspender 1 is connected fastening with spacecraft 7 by bolt, adjusts the barycenter of suspender 1 and spacecraft to same axis before lifting.One end of limit rope 3 is connected on large suspension ring 10 by shackle (shackle three) 9, and the other end is connected on little suspension ring 11 by shackle (shackle four) 9; Pose_adjuster 5 one end are connected fastening with spacecraft by bearing pin, the other end is bolted in removable large quality counterweight 6, and in spacecraft hoisting process, pose_adjuster 5 is in relaxed state.Cable connector on the cable of electric input assembly 4 and delivery device 2, now switch, in closed condition, switches on power, lift by crane delivery device 2 by crane, limit rope 3, suspender 1 and spacecraft 7 are to predetermined release altitude, mobile large quality counterweight 6 makes pose_adjuster 5 in tensioned state, by the micro-adjusting mechanism on pose_adjuster 5, adjust the attitude of spacecraft, make it reach initial input requirement, press the switch of electric input assembly 4, the grab of delivery device 2 is opened, switching hanger 8, suspender 1 and spacecraft 7 fall simultaneously, when whereabouts certain distance reaches after the length of limit rope, the limited rope of suspender 1 is held, be suspended in and can not continue in the air to decline, spacecraft 7 continues to decline and drops to test ground to state shown in Fig. 3.
In the process of lifting spacecraft, prevent that by operator's tractive pose_adjuster 5 rocking from appearring in spacecraft 7 on a large scale; When spacecraft 7 is lifted into after predetermined release altitude, pose_adjuster 5 is tightened, and the mobile large quality counterweight of locking 6 positions, then by the micromatic setting on pose_adjuster 5, adjust the attitude of spacecraft 7, until meet the initial Gesture of throwing in, locking micro-adjusting mechanism.
Although above the specific embodiment of the present invention is described in detail and is illustrated, but what should indicate is, we can make various changes and modifications above-mentioned embodiment, but these do not depart from the scope that spirit of the present invention and appended claim are recorded.
Claims (5)
1. one kind has the test unit of input and posture adjustment function, comprise throwing mechanism, electric input assembly, switching hanger, limit rope, suspender, pose_adjuster, throwing mechanism top hangs in large suspension ring by shackle one, large suspension ring top hangs in the suspension hook of crane, switching hanger is hung in the grab of throwing mechanism below, grab before drop-test in closure state, the cable connector on the cable on throwing mechanism and electric input assembly; The below of switching hanger is connected with the little suspension ring on suspender by shackle two, suspender is connected with the suspension centre of spacecraft by adaptor, and by bolted, before lifting, the barycenter of suspender and spacecraft is at same axis, one end of limit rope is connected with the large suspension ring of throwing mechanism top by shackle three, the other end is connected with the little suspension ring on suspender by shackle four, pose_adjuster one end is connected fastening with spaceborne interface, the other end is connected fastening with removable large quality counterweight, in spacecraft hoisting process, pose_adjuster is in relaxed state.
2. device as claimed in claim 1, wherein, the cable on electric input assembly, according to release altitude configured length, is realized the release action of controlling grab on throwing mechanism on ground.
3. device as claimed in claim 1, wherein, limit rope is for controlling the falling head of suspender, when after throwing mechanism release, suspender and spacecraft are thrown in simultaneously, and in fall-down test, suspender cannot separate with spacecraft, by controlling the length of limit rope, can control the dropping distance of suspender, avoid suspender and spacecraft to bump against.
4. the device as described in claim 1-3 any one, wherein, suspender adopts 2 lifting spacecrafts, is provided with regulating device on suspender, for adjusting the position of little suspension ring, ensures that the barycenter of itself and spacecraft of when lifting, on same axis, avoids bias to cause and rock.
5. the device as described in claim 1-3 any one, wherein, pose_adjuster is the pose_adjuster that two covers are identical, is connected respectively fasteningly with spacecraft, is symmetrically distributed in the both sides of spacecraft suspension centre interface on spacecraft with the interface of pose_adjuster.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410222288.7A CN103969019A (en) | 2014-05-23 | 2014-05-23 | Drop test device with delivery and posture adjusting function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410222288.7A CN103969019A (en) | 2014-05-23 | 2014-05-23 | Drop test device with delivery and posture adjusting function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103969019A true CN103969019A (en) | 2014-08-06 |
Family
ID=51238791
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410222288.7A Pending CN103969019A (en) | 2014-05-23 | 2014-05-23 | Drop test device with delivery and posture adjusting function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103969019A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108716977A (en) * | 2018-05-07 | 2018-10-30 | 中国飞机强度研究所 | A kind of flexibility pose adjustment position control device |
| CN109273106A (en) * | 2018-10-31 | 2019-01-25 | 上海核工程研究设计院有限公司 | A kind of device measuring nuclear fuel assembly screen work lattice cell stiffness characteristics |
| CN109383848A (en) * | 2018-11-15 | 2019-02-26 | 航天神舟飞行器有限公司 | A kind of fall-down test tooling can be used for small-sized fixed-wing unmanned plane |
| CN109612671A (en) * | 2018-12-07 | 2019-04-12 | 长春理工大学 | Large-scale fall arrest device device for adjusting posture and method |
| CN109848669A (en) * | 2019-01-21 | 2019-06-07 | 燕山大学 | Has the function of the soft or hard mixed connection tipping clamp device of Three Degree Of Freedom posture adjustment |
| CN112479034A (en) * | 2020-11-20 | 2021-03-12 | 中国直升机设计研究所 | Non-guide rail type throwing attitude control device and method |
| CN112649169A (en) * | 2019-10-10 | 2021-04-13 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Drop impact test platform system for measuring shock absorber buffering performance |
| CN117030292A (en) * | 2023-10-08 | 2023-11-10 | 广东粤港澳大湾区黄埔材料研究院 | Shock-falling testing device for aerocar |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102530726A (en) * | 2011-12-20 | 2012-07-04 | 北京卫星环境工程研究所 | Adjusting method for level adjustment of hanging tool for spacecraft |
| CN102879166A (en) * | 2012-09-21 | 2013-01-16 | 北京宇航系统工程研究所 | Impact test platform for point separation device and test method of test platform |
-
2014
- 2014-05-23 CN CN201410222288.7A patent/CN103969019A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102530726A (en) * | 2011-12-20 | 2012-07-04 | 北京卫星环境工程研究所 | Adjusting method for level adjustment of hanging tool for spacecraft |
| CN102879166A (en) * | 2012-09-21 | 2013-01-16 | 北京宇航系统工程研究所 | Impact test platform for point separation device and test method of test platform |
Non-Patent Citations (1)
| Title |
|---|
| 李晓欢等: "月球探测器着陆冲击试验的地面支持设备设计", 《航天器环境工程》, vol. 30, no. 2, 30 April 2013 (2013-04-30) * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108716977A (en) * | 2018-05-07 | 2018-10-30 | 中国飞机强度研究所 | A kind of flexibility pose adjustment position control device |
| CN109273106A (en) * | 2018-10-31 | 2019-01-25 | 上海核工程研究设计院有限公司 | A kind of device measuring nuclear fuel assembly screen work lattice cell stiffness characteristics |
| CN109383848A (en) * | 2018-11-15 | 2019-02-26 | 航天神舟飞行器有限公司 | A kind of fall-down test tooling can be used for small-sized fixed-wing unmanned plane |
| CN109612671A (en) * | 2018-12-07 | 2019-04-12 | 长春理工大学 | Large-scale fall arrest device device for adjusting posture and method |
| CN109848669A (en) * | 2019-01-21 | 2019-06-07 | 燕山大学 | Has the function of the soft or hard mixed connection tipping clamp device of Three Degree Of Freedom posture adjustment |
| CN112649169A (en) * | 2019-10-10 | 2021-04-13 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Drop impact test platform system for measuring shock absorber buffering performance |
| CN112479034A (en) * | 2020-11-20 | 2021-03-12 | 中国直升机设计研究所 | Non-guide rail type throwing attitude control device and method |
| CN117030292A (en) * | 2023-10-08 | 2023-11-10 | 广东粤港澳大湾区黄埔材料研究院 | Shock-falling testing device for aerocar |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103969019A (en) | Drop test device with delivery and posture adjusting function | |
| CN104034596B (en) | A kind of lever crouches pull-type concrete creep and elasticity modulus test device | |
| CN103274288B (en) | Suspending and releasing system used for impact test of lander | |
| CN107891986A (en) | Crawl structure, aircraft, system and its application method of aircraft | |
| CN203855299U (en) | Lifting appliance suitable for one-hook slinging | |
| CN113281355A (en) | X-ray detection device and method for overhead line hardware | |
| CN103158887B (en) | Fixed wing aircraft open-water-area ditching test apparatus | |
| CN103212171A (en) | Intelligent traction type throwing device of forest fire fighting bomb | |
| CN202116184U (en) | Multipoint self-balancing lifting appliance of cable crane | |
| CN103043533A (en) | Crane and control method thereof | |
| CN104236838B (en) | A kind of moment automatic releasing device | |
| CN205275004U (en) | Automatic balanced type hanging beam | |
| CN107972871A (en) | A kind of unmanned plane undercarriage and unmanned plane for launching crawl object | |
| CN109353953A (en) | A kind of electronic intelligence hook assembly of fixed pulley | |
| CN205419515U (en) | C type hook of many lewis holes | |
| CN202717540U (en) | Button box device used for controlling electric chain block | |
| CN109353518A (en) | A method of the intelligence based on unmanned plane, which is launched, collects fixed pulley | |
| CN105217036A (en) | Traction air-drop parachuting unit | |
| CN113428815B (en) | Manned space operation stable platform | |
| CN207658068U (en) | Crawl structure, aircraft and the system of aircraft | |
| CN104386592B (en) | A kind of special lorry-mounted crane of railway | |
| CN203699589U (en) | Machine-room-less elevator rescue device | |
| CN203753405U (en) | Simple drop device for load drop of model airplane | |
| CN203903768U (en) | Adjustable loading and unloading lifting bracket for waste heat boiler module | |
| CN207631476U (en) | A kind of unmanned plane undercarriage and unmanned plane for launching crawl object |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140806 |