GB2096287A - Launch vehicle constraining - Google Patents
Launch vehicle constraining Download PDFInfo
- Publication number
- GB2096287A GB2096287A GB8209824A GB8209824A GB2096287A GB 2096287 A GB2096287 A GB 2096287A GB 8209824 A GB8209824 A GB 8209824A GB 8209824 A GB8209824 A GB 8209824A GB 2096287 A GB2096287 A GB 2096287A
- Authority
- GB
- United Kingdom
- Prior art keywords
- jaw member
- adjusting
- jaw
- vehicle
- constraining
- 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.)
- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/052—Means for securing the rocket in the launching apparatus
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Vehicle Cleaning, Maintenance, Repair, Refitting, And Outriggers (AREA)
Abstract
Constraining apparatus for holding a vertically launched rocket vehicle in an upright position includes upper and lower jaws 9, 5 which grip a lug 10 on the vehicle, and are vertically adjustable with respect to a rocking member 7 and a temporarily fixed member 1, respectively, by shims, such that a desired clamping force is obtained irrespective of variations in lug position due to build tolerances. The members 1, 7 and their associated jaws are urged together by a geometric lock 11. The force exerted by the lock is determined by replacing it with a jack and load measuring device, extending the jack until the desired force is measured, and re-inserting the lock with adjustment of the jaws 5, 9 as necessary. <IMAGE>
Description
SPECIFICATION
Launch vehicle constraining means
This invention relates to constraining means for holding vertically launched flight vehicles, for example those rocket vehicles used to carry spacecraft on the first part of a mission, in an upright position both during preparation and also during initial running of the engines until sufficient thrust has been achieved to effect successful liftoff.
According to one aspect of the present invention, such constraining means include a temporarily fixed structural member, a fixed but adjustable lower jaw member carried by the structural member, adjusting means for adjusting the height of the jaw member with reference to the structural member, a movable but adjustable upper jaw member carried by a rocking member itself pivotally mounted on the structural member, adjusting means for adjusting the height of the upper jaw member with reference to the rocking member, the jaw members being arranged to clamp a region of the vehicle, and urging means coupled between the rocking member and the structural member to temporarily urge the upper jaw member toward the clamping position.
Preferably, the urging means includes a
geometric lock arrangement which in a rigid
locked condition is sized to provide a
predetermined loading in the rocking member and
hence a predetermined clamping force on the
clamped region of the vehicle, and which in an
unlocked position releases the predetermined
loading and allows the upper jaw member to be
urged away from the lower jaw member.
By this arrangement the setting up of the
constraining means to provide the predetermined
clamping force is facilitated. It is found that, due tq
build tolerances, that region of the vehicle to be
clamped may vary in its exact location along the
length of the vehicle, so that to accurately mount
the vehicle in its upright position at a desired
height the lower jaw member must be adjusted vertically; naturally this affects the distance
between the jaw members and hence the
predetermined clamping load exerted. The upper jaw member must accordingly be vertically
adjusted. By the presently described arrangement,
any adjustment of the height of the lower jaw
member to suit a particular vehicle can be effected by shims, and any corresponding adjustment of the upper jaw member can be similarly effected.
Conveniently and simply, such shim adjustment is effected by merely taking a shim from an adjusting position on one jaw and placing it in an adjusting position on the other.
According to a further aspect of the invention, a method ot adjusting such constraining means includes the not necessarily sequential steps of:
temporarily fixing the structural member, positioning a dummy region of the vehicle at a desired height by adjusting the lower jaw member with reference to the structural member,
replacing the urging means with jack means and load measuring means,
clamping said dummy region between the lower and upper jaw members by extending the jack means until a desired clamping load is measured and the distance between the rocking member and the structural member is greater than that dictated by the urging means when in its rigid locked condition,
reducing said distance to that dictated by the locked urging means by effecting adjustment of the upper and lower jaw members whilst maintaining the desired clamping load,
replacing the jack means and load measuring means with the urging means, and, with said dummy region removed, adjusting the upper and lower jaws identically to suit when the actual height of an actual region of the vehicle to be clamped is known.
Preferably, where the jaw member adjustment is by means of shims, said identical adjustment of the upper and lower jaws is by moving a shim or shims from one jaw to the other.
One embodiment of the invention is now described by way of example with reference to the accompanying drawings in which: Figure 1 is a side elevation of one of four constraining units which in use are equally spaced around a vertical axis with which the longitudinal axis of the vehicle is aligned.
Figure 2 illustrates an enlarged view of the region of box II of Figure 1, and
Figure 3 illustrates a similar view to that of
Figure 2 but with the apparatus installed to facilitate setting up.
Referring to Figure 1, a constraining unit includes a structural member 1 which for the purposes of the present description is fixed in the support position shown, but can be swung about a horizontal pivot axis 2 by means of a jack 3 away to the right as drawn to clear the vehicle, not shown. A geometric lock arrangement 4 rigidly holds the constraining unit in the support position.
Referring now to Figure 2 additionally to Figure 1, the structural member 1 carries a lower jaw 5 which is adjustable in height with respect to the member 1 by the insertion or removal of shims 6 at a region A between the jaw and the member 1.
The member 1 also carries a rocking member 7, which pivots about an axis 8 parallel to the axis 2.
One end of the rocking member 7 carries an upper jaw 9 which is adjustable with respect to the rocking member by the removal or insertion of shims 6 at a region B between the upper jaw and the rocking member. A shim associated with one jaw can be removed and inserted for association with the other. The jaws 5 and 9 are such to clamp between them a lug 10 being part of the vehicle.
There is one lug for each constraining unit. As before discussed, each lug 10 may deviate from a nominal position, that is to say its position may vary along the length of the vehicle, due to build tolerances. It follows that the position of the lug 10 varies with reference to its associated constraining unit, hence the lower jaw 5 is adjustable in height at A by means of shims 6 to
allow for this. As also described the upper jaw 9 is
similarly adjustable at B to maintain a desired
predetermined clamping load on the lug 1 0.
The structural member 1 also carries urging
means in the form of a geometric lock 11 which
comprises a first member 1 2 pivoted to that end
of the rocking member 7 remote from the upper jaw 9 and to a second member 13 which itself is
pivoted directly to the structural member.
The geometric lock members 12 and 1 3 are
chosen to be of such a length that when aligned with one another in a locked, rigid condition as
drawn, their combined length is such to urge the
rocking member 7 so that the jaws exert a desired
clamping force on the lug 10, assuming correct
setting up. The member 12 is designed to be
compressible but at a certain limit of compression
to act as a rigid strut; it acts as a rigid strut in the
rigid locked condition.
A jack 14 is provided to break the geometric
lock at a certain stage in the lift-off sequence by
tending to draw the member 1 3 in a clockwise
direction as drawn about its pivot on the structural
member 1. In this circumstance, the clamping force of the jaws decays since the preload (i.e.
distortion) in the rocking member 7 is removed but a residual clamping force is provided by a spring assembly 1 5 included in and tending to extend the geometric lock member 12.
In use the constraining unit is first set up to provide the predetermined clamping force for a nominal position of the lug 10. When the actual position of the lug 10 on a particular vehicle is known, then the shims 6, if necessary, are moved between the regions A and B to allow for any deviation of the lug from a nominal position without altering the predetermined clamping force.
The initial setting up for a nominal lug position is described as follows with reference to figure 3.
A dummy lug 10 is located in the nominal vertical position by means of the lower jaw 5 adjusted for height by the insertion or removal of shims 6 at A.
The first member 12 of the geometric lock is replaced by a load cell 16 and a hydraulic jack 17 lying in tandem. With the dummy lug 10 in the nominal position, the jack 1 7 is extended to clamp the lug 10 between the upper and lower jaws 5 and 9 respectively until the desired clamping load is indicated by the load cell 1 6 readout. The dimension X is then measured, the arrangement being that the measured dimension X is always greater than the length of a standard first member
12. The dimension X is then reduced, by placing shims 6 at B, to the exact length of the standard first member 12 whilst maintaining the desired clamping load. The load cell 1 6 and the hydraulic jack 1 7 are removed and replaced by the first member 12. As before stated, any deviation of a position of the lug 10 from the nominal position in an actual vehicle to be launched is accommodated by moving shims 6 of identical thickness between the regions A and B. The predetermined clamping load is unaffected.
Claims (7)
1. Constraining means for holding vertically launched flight vehicles in an upright position, including a temporarily fixed structural member, a fixed but adjustable lower jaw member carried by the structural member, adjusting means for adjusting the height of the jaw member with reference to the structural member, a movable but adjustable upper jaw member carried by a rocking member itself pivotally mounted on the structural member, adjusting means for adjusting the height of the upper jaw member with reference to the rocking member, the jaw members being arranged to clamp a region owt the vehicle, and urging means coupled between the rocking member and the structural member to temporarily urge the upper jaw member toward the clamping position.
2. Constraining means, according to Claim 1, wherein the urging means includes a geometric lock arrangement which in a rigid locked condition is sized to provide a predetermined loading in the rocking member and hence a predetermined clamping force on the clamped region of the vehicle, and which in an unlocked position releases the predetermined loading and allows the upper jaw member to be urged away from the lower jaw member.
3. Constraining means, according to Claim 1 or
Claim 2, wherein the adjusting means for the lower jaw member and the upper jaw member are such to allow identical adjustment of each jaw member.
4. Constraining means, according to Claim 3, wherein the adjusting means include at least one shim which can be moved from one jaw member to the other jaw member,
5. A method of adjusting the constraining means of Claim 2 including the not necessarily sequential steps of- temporarily fixing the structural member,
positioning a dummy region of the vehicle at a desired height by adjusting the lower jaw member with reference to the structural member,
replacing the urging means with jack means and load measuring means,
clamping said dummy region between the lower and upper jaw members by extending the jack means until a desired clamping load is measured and the distance between the rocking member and the structural member is greater than that dictated by the urging means when in its rigid locked condition,
reducing said distance to that dictated by the locked urging means by effecting adjustment of the upper and lower jaw members whilst maintaining the desired clamping load,
replacing the jack means and load measuring means with the urging means, and, with said dummy region removed,
adjusting the upper and lower jaws identically to suit when the actual height of an actual region of the vehicle to be clamped is known.
6. A method of adjustment, according to Claim 5, where the jaw member adjustment is by means of shims, wherein said identical adjustment of the upper and lower jaws is by moving a shim or shims from one jaw to the other.
7. Constraining means for holding vertically launched flight vehicles in an upright position substantially as described with reference to
Figures 1 and 2 of the accompanying drawings.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB8209824A GB2096287A (en) | 1981-04-04 | 1982-04-02 | Launch vehicle constraining |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB8110633 | 1981-04-04 | ||
GB8209824A GB2096287A (en) | 1981-04-04 | 1982-04-02 | Launch vehicle constraining |
Publications (1)
Publication Number | Publication Date |
---|---|
GB2096287A true GB2096287A (en) | 1982-10-13 |
Family
ID=26279035
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB8209824A Withdrawn GB2096287A (en) | 1981-04-04 | 1982-04-02 | Launch vehicle constraining |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB2096287A (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101419037B (en) * | 2008-12-11 | 2010-09-22 | 北京航天发射技术研究所 | Air spring slow-releasing mechanism |
WO2010113171A1 (en) * | 2009-03-30 | 2010-10-07 | Director General, Defence Research & Development Organisation | A mobile missile launch system and method thereof |
CN111256534A (en) * | 2020-03-05 | 2020-06-09 | 北京中科宇航技术有限公司 | Rocket transport device and launching device |
CN113739634A (en) * | 2021-08-11 | 2021-12-03 | 浙江蓝箭航天空间科技有限公司 | Drag slow release device and launching pad of carrier rocket |
CN115507699A (en) * | 2022-08-15 | 2022-12-23 | 蓝箭航天空间科技股份有限公司 | Automatic reverse type drag release device |
-
1982
- 1982-04-02 GB GB8209824A patent/GB2096287A/en not_active Withdrawn
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101419037B (en) * | 2008-12-11 | 2010-09-22 | 北京航天发射技术研究所 | Air spring slow-releasing mechanism |
WO2010113171A1 (en) * | 2009-03-30 | 2010-10-07 | Director General, Defence Research & Development Organisation | A mobile missile launch system and method thereof |
AU2010231536B2 (en) * | 2009-03-30 | 2013-07-18 | Director General, Defence Research & Development Organisation | A mobile missile launch system and method thereof |
RU2493529C2 (en) * | 2009-03-30 | 2013-09-20 | Директор Дженерал, Дифенс Рисёч Энд Девелопмент Организейшен | Mobile rocket launcher and method of rocket launcher |
US8800418B2 (en) | 2009-03-30 | 2014-08-12 | Director General, Defence Research & Development Organisation | Mobile missile launch system and method thereof |
CN111256534A (en) * | 2020-03-05 | 2020-06-09 | 北京中科宇航技术有限公司 | Rocket transport device and launching device |
CN111256534B (en) * | 2020-03-05 | 2022-02-01 | 北京中科宇航技术有限公司 | Rocket transport device and launching device |
CN113739634A (en) * | 2021-08-11 | 2021-12-03 | 浙江蓝箭航天空间科技有限公司 | Drag slow release device and launching pad of carrier rocket |
CN115507699A (en) * | 2022-08-15 | 2022-12-23 | 蓝箭航天空间科技股份有限公司 | Automatic reverse type drag release device |
CN115507699B (en) * | 2022-08-15 | 2024-06-11 | 蓝箭航天空间科技股份有限公司 | Automatic reversing type drag release device |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2825477A (en) | Engine work stand and method of using the same | |
US10538191B2 (en) | Removal/installation apparatus for boat capture system | |
EP0117976B1 (en) | Method for automatically attaching sub-assembly to main assembly and system therefor using industrial robots | |
GB2096287A (en) | Launch vehicle constraining | |
ATE79810T1 (en) | TOW VEHICLE FOR AIRCRAFT DEFINED LASHING FORCES. | |
EP0672585A1 (en) | Rigging of aircraft wing flaps | |
JP2002048963A (en) | Lens system, especially, projection lens system for semiconductor lithography | |
JP2001512049A (en) | A device for cracking the connecting rod and the large end of the connecting rod | |
GB2459878A (en) | Clamping system | |
US4114839A (en) | Aerial photography camera mount assembly | |
ES8308053A1 (en) | Airborne missile launcher | |
US4402380A (en) | Apparatus and method for supporting a transmission | |
CN114509271A (en) | Engine thrust measuring rack and thrust measuring method | |
US5411617A (en) | Method for use in fabricating and/or testing a thin mirror | |
US5065688A (en) | Flexible weapon handling support system | |
JPH061097A (en) | Cylindrical supporting part for use on optical plotter | |
US4958794A (en) | Dual purpose alignment bracket for use with laser or optical scope | |
US2352221A (en) | Photographic stand | |
CN210849283U (en) | Automatic clamp for engine cylinder cover | |
JP2002518254A (en) | Apparatus and method for properly unloading or receiving cargo from aircraft | |
US20240025561A1 (en) | System for handling a side shell of an aircraft with a view to assembling a fuselage barrel of the aircraft and method for assembling a fuselage barrel of an aircraft | |
US3618797A (en) | Load transfer device and method | |
US4214692A (en) | Butt-welding apparatus for assembling and laying pipe strings in deep water | |
RU1841307C (en) | A device for orientation and installation of large-sized parts in a satellite fixture | |
US2826974A (en) | Adjustable mount for sight unit and camera |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |